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ROSINA Users Manual

1. X j 7 SS Persons ES zi pusuns 06 Pi SK f al SX Deg PISOS Ei S 906 Jn J9UU J940 N N Mamas 38 BET XS gusce 4 Dy wm Bd M a 04 9pm 03 90 Configuration Figure 2 3 The dimensional view of DFMS in Operating eo i e eo T s D 5 tv So a o o 08 X 5i mm E 4 O o tc T 1 we o room F E da as e D 5 x o 4 o Lop u o0 on 8 o0 k c 9oon00 rj Gun JD dii E vi o x zz o Oo oO co AUN an dar Seq Ty Fig 2 4 Mechanical Interface Control drawing of DFMS in Operating Configuration UoB Drawing M155 1004 Rosetta ROSINA Reference RO ROS Man 1009 Issue D3 Rev 0 Date 01 11 06 Section 3 Page 6 2 1 2 1 3 Reflectron Time of Flight Spectrometer Figure 2 5 Three dimensional
2. Emergency modes TBD 4 2 4 1 Power Consumption of RTOF The power consumption of RTOF is composed of six main components namely of the standby power low voltage converters and main controller of the analyser part of the filament of the data acquisition system s used of the ion source heater and of the cover motor It does vary neither with triple or single reflection nor with using one or two channels The following table shows the four contributions pL Power W Reference RO ROS Man 1007 Rosetta 3 P Issue Rev ROSINA Date 01 11 06 Section 4 Page 12 Standby mode LVPS MC Analyzer Part Flament ETE wer ETELT low power or ETS L B ETS 7 Both 11 lon source heater Cover motor Not run in parallel to analyser part filament or cover motor The power used in each mode can therefore be calculated A normal measurement mode in power savings mode needs 20 W with ETS in normal operation 23 W with ETS L and ETS 27 W the ion source heater needs 22 W Reference RO ROS Man 1007 Rosetta 3 P Issue Rev Date 01 11 06 ROSINA Section 4 Page 13 4 2 5 COPS Operational modes COPS has two principal modes one is the monitoring mode the other one the scientific mode In the monitoring mode the nude gauge is used alone in the science mode both gauges are used For redundancy reasons it is also possible to do the monitoring mode with t
3. 4 6 Data Operations Handbook ascnncc imnic ucainisimnninnainiaimnicsnnmnkainiens 1 6 1 Telecommand Function Definitions soesoossessoesocssessossocssessoseocssessossooesesssssoossosso 1 6 2 Telemetry Packet Definitions ceres ee ee eee eerte ee sete sesso sesto sese sena 1 62 1 DPU S C HotsekeeptngPackelts ucro nat toe tend tere ceaa brace seva Easy EUS 1 6 2 2 Mechanic TI 1 6 2 3 Science Packet Definitions s oratinascnnsd sien sededdaopiasaatvedennactieddeeedndealadnodiactadncoeataailes 2 6 2 4 Science Housekeeping Definitions eere treten anre t nant aab cdd 3 6 3 Event Packet Definitions csisssicsscesscosccssesssccssnsseosesescessossesossascsescoussensassceesedenenssocsees 11 6 3 1 Pa ket Typ s and EID mM ainan eisenii aaaea ipiis 11 6 3 2 Normal Event Packet Definitions Sub Type 1 esses 11 6 3 3 Anomalous Event Packet Definitions Sub Type 2 esses 16 6 3 4 Ground Action Event Packet Definitions Sub Type 3 sss 18 6 3 5 On board Action Event Packet Definitions Sub Type 4 18 6 4 Context File Definition eee e eee eese eee eee e eee eee ee eee aee eee eee eee aee eee eee eese ae 19 Reference RO ROS Man 1009 Rosetta r p Issue Rev ROSINA Date 01 11 06 Section 1 Page 4 Change Record Issue Date
4. Position Bytes Bits Name Data 000 1 DFMS Science Header 0x84 001 1 Type Identifier 002 2 Packet Count 004 2s HK Science Data DFMS Science HK data only in 4092 first packet Reference RO ROS Man 1007 Rosetta r La Issue Rev Rosina Date 01 11 06 Section 10 Page 3 6 2 3 2 RTOF Science Packet Position Bytes Bits Name Data 000 1 RTOF Science Header 0x88 001 1 Type Identifier 002 2 Packet Count 004 2 HK Science Data RTOF Science HK data only in first 4092 packet 6 2 3 3 COPS Science Packet Position Bytes Bits Name Data 000 1 COPS Science Header 0x8C 001 1 Type Identifier 002 2 Packet Count 004 gu Science Data 4092 6 2 4 Science Housekeeping Definitions A set of science related HK data is transmitted in addition to normal housekeeping data at the beginning of each Science Data Set A description of these data can be found in the general HK description document annex D4 6 2 4 1 DFMS Science HK Data Length 8 words Position Bytes Bits Name Data 000 1 DFMS Science HK Header OxC4 001 1 Spare 002 2 Voltage flags 1 15 14 MG 0 Off 1 Ok 2 Low 3 High 13 12 ISB 0 Off 1 Ok 2 Low 3 High 11 10 ISP 0 Off 1 Ok 2 Low 3 High 9 8 IRP1 0 Off 1 Ok 2 Low 3 High 7 6 IRP2 0 Off 1
5. Contact Area 20cm2 ors nin BOTTOM VIEW zn xl IN Figure 2 10 Mechanical Interface Control drawing of COPS UoB Drawing M158 1001 Reference RO ROS Man 1009 Rosetta Issue 3 Rev 0 Date 01 11 06 ROSINA Section 3 Page 12 2 1 2 1 5 Data Processing Unit DPU Figure 2 11 Three dimensional view of the e eo r Oo zx S T eo ooo isiw ERE 1 0 om sans oe S3 0G OISAHd s Oo WNISOH VLISSOH a 0 tv Add 31 gt tc A ledIUeYOaW oO E i i 8 e EDIT LT LU Hipi 080S SSRIAAO SGUN SEGuGLS USZUBJAPI Sues P5 T9 ipe a E Er eger Ko T quied woelq jewuay snid fc co O c 2 pl SUM SINIWLYJYL 3O JuNS L e 8 MY S AONE TWIMLWW TWEALONYLS a B 8 c n Sood fad x FL 9525 Lit me fa ot Eo WOO 0 890898 YILYSNI 4O SLNAWOW hoy e c 900 T3 oir n wwo og Z uugg A uugQ x 7 SSYW JO 3H1N32 1003 338 WU T T EXE 86 n
6. ac L 0 x8 DSPA RTOF I F Tor uF 8 gt TSC21020 Driver HW FPGA RTOF Data Cmd amp HK S C Interface FPGA Status EEPROM LU Switch NDM Data Cmd amp HK 4 EM NDM I F FPGA NDM I F Driver HW Address Decoder Error Detection HW 5V 1 I DPUHardCore A 1 5Ve DSP B TSC21020 Reference RO ROS Man 1009 Rosetta r Issue Rev ROSINA Date 01 11 06 Section 3 Page 1 2 Experiment Configuration 2 1 Physical 2 1 1 Mechanisms Concept The 3 sensors are equipped with the following mechanisms DFMS 1 entrance aperture cover mechanism e 2 gas valves for in flight calibration RTOF 1 entrance aperture cover mechanism e 2 gas valves for in flight calibration The mechanisms for DFMS and RTOF are identical Each entrance aperture cover mechanisms consist of e An elliptically deformed pyrocord from Dassault that initially cuts the hermetically sealed cover open e A brushless DC motor from Minimotor that opens and closes the aperture cover in space e A pyrotechnically actuated fail safe mechanism that opens the aperture cover in case of motor or gear failure Each gas valve consists of a sapphire ball clamped in a stainless steel tube Expanding the tube with a heater opens the valve Ro setta Reference
7. 6 ETS Ram Test Active 0 Off 1 On 5 ETS Ram Test Status 0 Off 1 On 4 ETS Ram Test Data Dec value 3 0 Spare 004 2 ETS L Lower Read Address Hex value 006 2 ETS L Upper Read Address Hex value 008 2 Status Bits 2 15 1 Spare 3 12 ETSL Lower Range 0 Off 1 On 11 ETSL Upper Range 0 Off 1 On 10 FEC Fil2 Gas 0 Off 1 On 9 FEC Fil 1 Gas 0 Off 1 On 8 FEC Fil 2 lon 0 Off 1 On 7 FEC Fil 1 lon 0 Off 1 On 6 FEC I Status 0 lon 1 Gas 5 FEC EH lon 0 Off 1 On 4 FEC EH Gas 0 Off 1 On 3 ETS L LRA Bit 16 Hex value 2 ETS L URA Bit 16 Hex value 1 ETS Lower Range 0 Off 1 On 0 ETS Upper Range 0 Off 1 On 010 2 MC FEC ION FIHEAT I value 0 2651 mA 012 2 MC FEC GAS FIHEAT value 0 2013 mA 014 2 MC FEC ION REP V ZA V value 0 0371 0 0894 016 2 MC FEC ION REP V ZB V value 0 037 0 1574 018 2 MC FEC GAS REP V A V value 0 0371 0 271 020 2 MC FEC GAS REP V 4B V value 0 0372 0 2382 022 2 MC FEC ION FIL V V value 0 0327 176 02 024 2 MC FEC GAS FIL V V value 0 0313 168 53 026 2 MC FEC GAS FIL I value 0 0852 0 6257 uA 028 2 MC FEC ION ENT V V value 0 0133 54 068 030 2 MC FEC ION ENT1 I value 0 0851 0 133 uA 032 2 MC FEC GAS TRAP V V value 0 0149 0 0486 034 2 MC FEC HVVG V U value 5 1e 3 0 0256 V 036 2 MC FEC HEAT VG V U value 5 1e 3 0 0257 V 038 2 MC FEC TEMP T value 0 060 273 C 04
8. Ok 2 Low 3 High 5 4 ERP 0 Off 1 Ok 2 Low 3 High 3 2 FIL 1 Bias 0 Off 1 Ok 2 Low 3 High 1 0 FIL 2 Bias 0 Off 1 Ok 2 Low 3 High 004 2 Voltage flags 2 15 14 FIL 1 Emi 0 Off 1 Ok 2 Low 3 High 13 12 FIL 1 Cur 0 Off 1 Ok 2 Low 3 High 11 10 FIL 2 Emi 0 Off 1 Ok 2 Low 3 High 9 8 FIL 2 Cur 0 Off 1 Ok 2 Low 3 High 7 6 SEL 0 Off 1 Ok 2 Low 3 High Reference RO ROS Man 1007 Rosetta Issue D3 Rev 0 i Date 01 11 06 Rosina Section 10 Page 4 5 4 SLR 0 Off 1 Ok 2 Low 3 High 3 2 SES 0 Off 1 Ok 2 Low 3 High 1 0 SEB 0 Off 1 Ok 2 Low 3 High 006 2 Voltage flags 3 15 14 TLL 0 Off 1 Ok 2 Low 3 High 13 12 TLR 0 Off 1 Ok 2 Low 3 High 11 10 VACC Dac 0 Off 1 Ok 2 Low 3 High 9 8 ESS1 Dac 0 Off 1 Ok 2 Low 3 High 7 6 ESS2 Dac 0 Off 1 Ok 2 Low 3 High 5 4 RQ Dac 0 Off 1 Ok 2 Low 3 High 3 2 ESAC Dac 0 Off 1 Ok 2 Low 3 High 1 0 ESAO Dac 0 Off 1 Ok 2 Low 3 High 008 2 Voltage flags 4 15 14 ESAI Dac 0 Off 1 Ok 2 Low 3 High 13 12 MP Dac 0 Off 1 Ok 2 Low 3 High 11 10 HP Dac 0 Off 1 Ok 2 Low 3 High 9 8 Z1Q Dac 0 Off 1 Ok 2 Low 3 High 7
9. 006 NRNAG30D 1 Symbol Hex value 007 1 Value Hex value 008 NRNAG30E 4 Correct Data high Hex value 012 2 Correct Data low Hex value 014 NRNAG3OF 4 Read Data high Hex value 018 2 Read Data low Hex value 6 3 2 3 DM Test Report EID 44003 Length 10 words Pos RSDB Byte Bit Name Data 000 NRNAG304 2 EID 44003 002 NRNAG30C 2 Spare 0 004 1 Unit 208 005 1 Type Hex value 006 NRNAG30D 1 Symbol Hex value 007 1 Value Hex value 008 NRNAG30E 4 Correct Data high Hex value 012 2 Correct Data low Hex value 014 NRNAG3OF 4 Read Data high Hex value 018 2 Read Data low Hex value 6 3 2 4 EEPROM Test Report EID 44004 Length 10 words Pos RSDB Byte Bit Name Data 000 NRNAG304 2 EID 44004 002 NRNAG316 2 Spare 0 004 1 Unit 208 005 3 Address Hex value 008 NRNAG30E 4 Correct Data high Hex value 012 2 Correct Data low Hex value 014 NRNAG3OF 4 Read Data high Hex value 018 2 Read Data low Hex value Rosetta Rosina Issue Date Section Reference RO ROS Man 1007 MEC Rev 0 01 11 06 10 Page 14 6 3 2 5 Operation Mode Change Report EID 44005 Length 12 words Pos RSDB Byte Bit Name Data 000 NRNAG304 2 EID 44005 002 NRNAG305 1 Unit 208 003 1 Spare 0 004 NRNAG31B 2 DPU Mode Hex value 006 NRNAG3AO 2 DPU Status Hex value 008 NRNAG31C 2 DFMS Mode Hex v
10. 3 ETS VCC On 0 Off 1 On 2 ETS VCC Off 0 Off 1 On 1 ETS VSH VE On 0 Off 1 On 0 ETS VSH VE Off 0 Off 1 2 On 054 2 MC Power State 8 15 GCU 1 On 0 Off 1 On 14 GCU 1 Off 0 Off 1 On 13 GCU 2 On 0 Off 1 On 12 GCU 2 Off 0 Off 1 On 11 GCU 1 Valve On 0 Off 1 On 10 GCU 1 Valve Off 0 Off 1 On 9 GCU 2 Valve On 0 Off 1 On 8 GCU 2 Valve Off 0 Off 1 On Reference RO ROS Man 1007 Rosetta Issue 3 Rev 0 Date 01 11 06 Rosina Section 10 Page 7 7 FEC VCC On 0 Off 1 On 6 FEC VCC Off 0 Off 1 On 5 FEC VDD On 0 Off 1 On 4 FEC VDD Off 0 Off 1 On 3 FEC Heater VG On 0 Off 1 On 2 FEC Heater VG Off 0 Off 1 On 1 FEC HV VG On 0 Off 1 On 0 FEC HV VG Off 0 Off 1 On 056 2 MC ETSL TEMP V value 366e 6 058 2 MC ETS TEMP CLK V value 366e 6 060 2 MC ETS TEMP DIG V value 366e 6 062 2 PSDC ELB I V value 0 0062 064 2 PSDC ELA I V value 0 0062 066 2 PSDC GH I V value 0 0062 068 2 PSDC BP I V value 0 0062 070 2 PSDC GR G V value 0 00619 072 2 PSDC BP G V value 0 0062 074 2 HV1 SL G V value 1 0271 110 5 076 2 HV1 A2 G V value 0 506 42 568 078 2 HV1 A1 G V value 0 2561 48 511 080 2 HV1_SL_ V value 1 0122 44 499 08
11. 44007 Length 10 words Pos RSDB Byte Bit Name Data 000 NRNAG304 2 EID 44007 002 NRNAG322 1 Unit 196 DFMS 200 RTOF 204 COPS 208 DPU 003 1 Flags Hex value 004 NRNAG3A5 2 Progress No Hex value 006 NRNAG38A6 2 Progress Code Hex value 008 NRNAG3A7 4 Progress Position Hex value Address 012 NRNAG38A8 2 Command counter Counter 0 65535 014 NRNAG32E 2 Unit Mode Hex value 016 NRNAG3A4 2 Unit Status Hex value 018 NRNAG330 2 Spare 0 6 3 2 8 Table Setting Report EID 44008 Length 28 words Pos RSDB Byte Bit Name Description 000 NRNAG304 2 EID 44008 002 NRNAG3A9 1 Unit 196 DFMS 200 RTOF 204 COPS 208 DPU 003 1 Type type of table 004 NRNAG3AA 2 Table No pointer to table 006 NRNAG3AB 2 Entry No pointer to parameter entry 008 NRNAG3AC 2 Function Shift function no shift parameter 010 NRNAG3AD 2 Mask and mask 012 NRNAG3AE 4 Default or mask 016 NRNAG3AF 4 Parameter Value 1 multiplier floating point 020 NRNAG3BO 4 Parameter Value 2 offset floating point 024 NRNAG3B1 2 Monitoring monitoring function no 026 NRNAG3B2 2 Wait wait time for monitoring in ms 028 NRNAG3B3 4 Parameter Value 3 step width floating point 032 NRNAG3B4 4 Parameter Value 4 limit floating point 036 NRNAG3B5 4 Parameter Value 5 sleep time in ms 040 NRNAG3B6 4 HK Cmd 1 sensor cmd for hk
12. length 170 bytes Pos Byte Bit Name Data 000 2 Header 002 2 Spare 004 2 Number 006 6 Time 012 2 DPU Cmd counter Counter 0 65535 014 2 DPU Cmd Error counter Counter 0 65535 016 2 Latch Up Counter Counter 0 65535 018 1 PM Error Count 1 Counter 0 255 019 1 PM Error Count 2 Counter 0 255 020 1 DM Error Count 1 Counter 0 255 021 1 DM Error Count 2 Counter 0 255 022 1 EEPROM Error Count 1 Counter 0 255 023 1 EEPROM Error Count 2 Counter 0 255 024 2 DPU S W mode Mode No 026 2 DPU S W status Hex value 028 2 DPU Last Mode 030 2 DPU Abort Status 032 2 Spare 1 034 2 Spare 2 036 2 DFMS Cmd counter Counter 0 65535 038 2 DFMS Cmd Error cnt Counter 0 65535 040 2 DFMS Science counter Counter 0 65535 042 2 DFMS Science Error counter Counter 0 65535 044 2 DFMS S W mode Mode No 046 2 DFMS S W status Hex value 048 2 DFMS Motor Pos 1 050 2 DFMS Motor Pos 2 052 2 DFMS GCU 1 On Time 054 2 DFMS GCU 2 On Time 056 2 DFMS Filament Status Rosetta Rosina Reference RO ROS Man 1007 Issue MEC Rev Date 01 11 06 Section 10 Page 0 20 058 2 DFMS Heater Status 060 2 DFMS Last Mode 062 2 DFMS Abort Status 064 2 DFMS Last Scan Mode 066 2 DFMS Last Seque
13. 0011 0 467 174 2 MC ETSL MVCA V value 7e 4 6 1e 3 176 2 MC ETSL PVDD V value 3 1e 3 1 26e 2 178 2 MC ETSL MVDD V value 2 8e 3 6 8e 3 180 2 MC HEAT ION VG V value 0 0051 0 036 182 2 MC_HEAT_GAS _VG V value 0 0052 0 0362 184 2 MC ETS 33V V value 366e 6 186 2 MC ETS PVCA V value 366e 6 188 2 MC ETS MVCA V value 366e 6 190 2 MC ETS VE V value 0 0014 0 001 V 192 2 MC ETS PVDD V value 0 0031 0 0093 V 194 2 MC ETS MVDD V value 0 0032 0 1103 V 196 2 MC ETS VSH V value 0 0096 0 0747 V 198 2 MC ETSL PVCA V value 1 1e 3 0 467 200 2 PSU 5 Val V value 0 001488 202 2 PSU 5 Val V value 0 001428 204 2 PSU 415 Val V value 0 00458 206 2 PSU 15 Val V value 0 004415 208 2 PSU 424 Val V value 0 006954 210 2 PSU 48 Val V value 0 0014792 212 2 PSU 45 Add Val V value 0 0014798 214 2 PSU 40 Val V value 0 0174 0 4234 216 2 PSU 70 Val V value 0 0107 4 173 Reference RO ROS Man 1007 Rosetta Issue MEC Rev 0 Date 01 11 06 Rosina Section 10 Page 10 218 2 PSU 45 Cur value 0 4383 30 mA 220 2 PSU 5 Cur value 0 1508 28 016 mA 222 2 PSU 415 Cur value 0 1133 16 502 mA 224 2 PSU 15 Cur value 0 0553 24 715 mA 226 2 PSU 424 Cur value 0 1285 33 042 mA 228 2 PSU 40 70
14. 01 11 06 Section 3 Page 54 This section is maintained as a separate procedure Annex C RO ROS MAN 1023 ROSINA Contingency Recovery Procedure Reference RO ROS Man 1007 Rosetta 3 Issue Rev 0 ROSINA Date 01 11 06 Section 4 Page 1 4 Mode Descriptions 4 1 Mode Transition Table Instrument mode transition table 1G 1L Off Memory test tandby 11 AL RTO D2 DPU DPU S5 COPS 5M C PS OS Ari Standby Instrument tandby Monitoring booting D5 DPU l IN software patchina 5 COP Allowed mode transitions with DPU in transition mode 4 Switching between modes or both modes simultaneously are allowed D3 E1 E2 E4 E5 emergency modes transition into these modes possible from all modes gt Only simultaneously if DFMS off RTOF full Rosetta ROSINA Reference RO ROS Man 1007 Issue 3 Rev 0 Date 01 11 06 Section 4 Page 2 The detailed mode transition tables for DFMS and RTOF can be found in Annex D1 D2 4 2 Detailed Mode Description 4 2 1 Each sensor operation is independent from the others except that COPS is required to be on whenever DFMS and or RTOF are switched on Simultaneous operation of the full RTOF and DFMS is not foreseen power Transition into emergency modes possible from all respective instrument modes Transitions during ground tests as during measurement modes Each sensor has a large number of individual submodes which are described i
15. 06 Section 3 Page 17 MEP Mech Ctrl Sensor L Sine 65KHz L Structure GND L Signal GND Rosina Power Block Diagram Power GND Uni Rosetta ROSINA Fig 2 16 DFMS Power Switching Block Diagram DFMS Interface Data Sheet Po Le Maximum Input Current 46 0 28V 1 64A Switch on Inrush lt 1A usec Input Voltage 25V 32V Inrush current after 8msec 1A usec 8msec gt 0 8A Bus Isolation Noise Emission Suseptibility EMC Requirements and Suseptibility Requirements are kept by the provision of Common Mode Noise and Conducted Noise Filtering Reference RO ROS Man 1009 Rosetta Issue 3 Rev 0 ROSINA Date 01 11 06 Section 3 Page 18 Signal alt deat rietatik liin Ground i DC DC Converter i 1 Primary Secondary Isolation i Sync 524kHz H Ed v ei Sane Seen CENT ARE E V DC DC Structure 1 15V noc Er ponc DC DC 28V E gt Main 45V Pwr On B I 28V Red B p Main Relay FET Switch V amp Soft Start Circuit 5V 28V Main Ret 28V Red Ret V C 50n S C Structure nd Fig 2 17 RTOF Power Switching Block Diagram RTOF nterface Data Sheet 1 1 O LLL LLL Maximum Input Current 44 6 28V 1 6A Switch on Inrush lt 1A usec Input Voltag
16. 1 Error 5 EEPROM self test 0 Ok 1 Error 4 SRAM 1 self test 0 Ok 1 Error 3 SRAM 2 self test 0 Ok 1 Error 2 Stat EEPROM self test 0 Ok 1 Error 1 0 Sensor I F self test 0 Ok 1 DFMS Error 2 RTOF Error 3 COPS Error 013 DPU Status 7 DPU power save 0 Off 1 On 6 LU detect 0 Off 1 On 5 Boot Err PM 0 Off 1 On 4 Boot Err DM 0 Off 1 On 3 0 Spare 014 NRNAG309 DPU power status 15 Spare 14 Status SRAM 2 0 Off 1 On 13 Status SRAM 1 0 Off 1 On 12 Status Stat EEPROM 0 Off 1 On 11 Status I F COPS 0 Off 1 On 10 Status I F RTOF 0 Off 1 On 9 Status I F DFMS 0 Off 1 On 8 Status EEPROM 0 Off 1 On 7 Sensitivity DSP 0 Low 1 High 6 Sensitivity SRAM 2 0 Low 1 High 5 Sensitivity SRAM 1 0 Low 1 High 4 Sensitivity Stat EEPROM 0 Low 1 High 3 Sensitivity I F COPS 0 Low 1 High 2 _ Sensitivity I F RTOF 0 Low 1 High 1 Sensitivity I F DFMS 0 Low 1 High 0 Sensitivity EEPROM 0 Low 1 High 016 NRNAG30A DPU S W status Hex value Reference RO ROS Man 1007 Rosetta Issue D3 Rev 0 Date 01 11 06 Rosina Section 10 Page 13 6 3 2 2 PM Test Report EID 44002 Length 10 words Pos RSDB Byte Bit Name Data 000 NRNAG304 2 EID 44002 002 NRNAG30C 2 Spare 0 004 1 Unit 208 005 1 Type Hex value
17. 1 Change X Responsible October 2000 Initial Issue Altwegg Issue 1 December Adapted to FM Altwegg 2000 1 rev 2 July 2001 DPU commands and Altwegg housekeeping as separate documents in the annex A and B mil 2 rev 0 February 2002 RTOF WCS replacement by ETS Altwegg L DPU commands and housekeeping flight operations planet flyby s and cruise phase AN rev 1 March 2002 Added DPU event packets and Altwegg reference to CRP Issue 2 rev2 July 2002 Changes according to EFOR include operations manual temp in limits New organisation with annexes A F 2002 mode manuals Update of annexes B C deletion of ground test procedures consolidation after launch List of reference documents RD1 RO EST RS 3013 Issue1 RevO EID B D1 D2 D3 D4 F1 F2 F3 F5 G1 G2 G3 Reference RO ROS Man 1009 Rosetta Issue 3 Rev 1 ROSINA Date 01 11 06 Section 1 Page 5 List of Annexes Deleted after launch RO ROS MAN 1015 4 2a RO ROS MAN 1023 1 1 RO ROS MAN 1010 3 4 RO ROS MAN 1011 5 0 RO ROS MAN 1019 1 3 Hk monitoring xls ROS TUB MA 08 1 0 ROS TUB SP 04 2 4 ROS TUB SP 02 3 0 ROS TUB MA 07 1 8 ROS TUB SP 05 2 3 ROS TUB MA 05 2 3 ROS TUB ID 07 2 1 ROS TUB MA 03 3 1 RO ROS Man 1007 1 1 Ground test Procedures 13 05 04 Flight operations procedures 21 03 2006 ROSINA Contingency Recovery Procedure Instrument Modes 19 12 2005 DFMS Instrument Operatio
18. 13 words Pos RSDB Byte Bit Name Data 000 NRNAG304 2 EID 44101 002 NRNAG305 1 Unit 208 003 1 Spare 0 004 NRNAG338 1 PM Error Count 1 Symbol Counter 005 1 PM Error Count 2 Symbols Counter 006 NRNAG339 2 PM Error status Hex value 008 NRNAG383A 4 PM Error address Hex value 012 NRNAG33B 1 DM Error Count 1 Symbol Counter 013 1 DM Error Count 2 Symbols Counter 014 NRNAG33C 2 DM Error status Hex value 016 NRNAG33D 4 DM Error address Hex value Reference RO ROS Man 1007 Rosetta Issue 3 Rev 0 i Date 01 11 06 Rosina Section 10 Page 17 020 NRNAG3BB 1 EEPROM Error Count 1 Counter 0 255 OxFF for Boot 021 1 EEPROM Error Count 2 Counter 0 255 OxFF for Boot 022 NRNAG31B 2 DPU Mode Boot CRC Cnt Hex value 024 NRNAGSAO 2 DPU Status Hex value 6 3 3 3 DPU General Error Report EID 44102 Length 11 words Pos RSDB Byte Bit Name Data 000 NRNAG304 2 EID 44102 002 NRNAG305 1 Unit 196 DFMS 200 RTOF 204 COPS 208 DPU 003 1 Spare 0 004 NRNAG307 4 Error Code Hex value 008 NRNAG308 4 Error Position Address Hex value 012 NRNAG3A8 2 Cmd HK counter Counter 0 65535 014 NRNAG345 1 DPU Processor load 1 100 Percent 015 1 Used memory PM 1 100 Percent 016 NRNAG346 1 Used memory DM 1 100 Percent 017 1 Spare 0 018 NRN
19. 34 8 kg 49 W N A itis not foreseen to operate DFMS RTOF and COPS in their maximum power modes simultaneously 2 4 2 Data Rates DMS Resource Requirements 2 4 2 1 SSMM Utilisation The tables below summarise the requirements for the expected use of the on board mass memory by ROSINA for the different mission phases SSMM Utilisation Mission Phase Commissioning Instrument ROSINA Data Type Description Volume Operational Usage MByte Non Science Housekeeping 2 25 bit s Telemetry Science 4 50 bit s Telemetry Context 1 kByte S W patches 0 5 Other SSMM Utilisation Mission Phase Asteroid Fly by 1 Instrument ROSINA Data Type Description Volume Operational Usage MByte Non Science Housekeeping 2 25 bit s Telemetry Reference RO ROS Man 1009 Rosetta Issue 3 Rev 0 ROSINA Date 01 11 06 Section 3 Page 42 Science 4 50 bit s Telemetry Context 1 kByte S W patches 0 5 Other TBD SSMM Utilisation Mission Phase Asteroid Fly by 2 Instrument ROSINA Data Type Description Volume Operational Usage MByte Non Science Housekeeping 2 25 bit s Telemetry Science 8 100 bit s Telemetry Context 1 kByte S W patches 0 5 Only for contingency upload of SW Other TBD SSMM Utilisation Mission Phase Comet approach Instrument RO
20. 6 Z2Q Dac 0 Off 1 Ok 2 Low 3 High 5 4 CEM REP Dac 0 Off 1 Ok 2 Low 3 High 3 2 CEM HV Dac 0 Off 1 Ok 2 Low 3 High 1 0 CEM THR Dac 0 Off 1 Ok 2 Low 3 High 010 2 Voltage flags 5 15 14 CEM Cur 0 Off 1 Ok 2 Low 3 High 13 12 MCP Front 0 Off 1 Ok 2 Low 3 High 11 10 MCP Back1 0 Off 1 Ok 2 Low 3 High 9 8 MCP Back2 0 Off 1 Ok 2 Low 3 High 7 6 FDP REP Ena 0 Off 1 Ok 2 Low 3 High 5 4 Spare 0 Off 1 Ok 2 Low 3 High 3 2 Spare 0 Off 1 Ok 2 Low 3 High 1 0 Spare 0 Off 1 Ok 2 Low 3 High 012 2 MAG Temp C value 1 2048e 2 26 6 014 2 Spare 6 2 4 2 RTOF Science HK Data Length 123 words Position Bytes Bits Name Data 000 1 RTOF Science HK Header 0xC8 001 1 Spare 002 2 Status Bits 1 15 PSU 9kV 0 Off 1 On 14 PSU 70V 0 Off 1 On 13 PSU lon MCP 0 Off 1 On 12 PSU Gas MCP 0 Off 1 On 11 PSU HM Power 0 Off 1 On Reference RO ROS Man 1007 Rosetta Issue 3 0 Rev Date 01 11 06 Rosina Section 10 Page 5 10 PSU Pulser 0 Off 1 On 9 ETSL Ram Test Active 0 Off 1 On 8 ETSL Ram Test Status 0 Off 1 On 7 ETSL Ram Test Data Dec value
21. 8 ETSL DTS Status 0 Off 1 On 7 6 ETSL Input Status 0 lon 1 Calibrator 2 Gas 3 Gas 5 ETSL Cal Power Status 0 Off 1 On 4 ETSL ADC HIRM Status 0 Off 1 On 3 ETSL RAM Threshold 0 Low 1 High 2 ETSL FIFO Threshold 0 Low 1 High 1 ETSL Latchup Enabled 1 Off 0 On O ETSL Latchup Detected 0 Off 1 On 126 1 ETSL Status 2 7 _ ETSL ADC Power Status 0 Off 1 On 6 ETSL ADC Threshold 0 High 1 Low 5 4 ETSL ML Mode 0 Adapt 1 ML31 2 ML63 3 ML255 3 0 Spare 1 ETSL Threshold Level 0 5 5mV 1 8mV 2 12mV 3 16 7mV 4 20mV 5 23 4mV 6 26 6mV 7 33 4mV 128 2 ETSL Extraction Delay t Value 26 5ns 158 5 130 2 ETSL ToF t Value 26 5ns 26 5 132 2 ETSL Cal Start Delay t Value 26 5ns 26 5 141 134 2 ETSL Cal Pulse Height V value 2 266 mV 3 3659 mV 136 2 ETSL Cal Pulse Width t value 1 44 ns 112 47 ns 138 2 ETS Status 1 15 ETS lon Pulser Status 0 Off 1 On 14 ETS Gas Pulser Status 0 Off 1 On 13 ETS Synchronization Status 0 Int 1 Ext 12 ETS Calib Trigger Status 0 Off 1 On 11 ETS Data Readout Status 0 Off 1 On 10 ETS Acquisition Status 0 Off 1 On 9 ETS DTS Status Cancel 0 Event 1 Extraction 8 ETS DTS Status 0 Off 1 On 7 6 ETS Input Status 0 lon 1 Calibrator 2 Gas 3 Gas 5 ETS Cal Power Status 0 Off 1 On 4 ETS ADC HIRM Status 0 Off 1 On 3 ETS RAM Threshold 0 Low 1 Hi
22. FOV s are determined by a set of electrodes upstream of the ionization region In Figure 1 2 only those for the wide FOV are shown Suitable potentials applied to these electrodes prevent the entry of low energy ions into the DFMS in the gas mode Cometary ions with higher energies gt 60 eV cannot pass through the analyzer and it is not necessary to prevent their entry into the ion source In the ion mode the potentials on these electrodes are changed to attract the cometary ions even in case of positive charging of the S C and to focus them into the gas ionization region of the source A coarse meshed grid on a negative potential surrounding the ion source area to a distance of 15 cm is used to augment the ion attraction The instrument degassing could lead to serious interference while measuring the cometary gases To keep the interference as low as possible the whole ion source region is built to UHV standards and degassed before launch and also during flight Since the narrow analyzer entrance slit has a very low vacuum conductance only connection between the source and analyzer regions outgassing from internal sensor parts is efficiently suppressed Reference RO ROS Man 1009 Rosetta Issue 3 Rev 1 ROSINA Date 01 11 06 Section 1 Page 14 The cometary gases entering the source are ionized with an electron beam parallel to the slit direction A weak magnetic field m OPTICAL 0 02T is used to guide the e
23. Man 1009 Rosetta r e Issue Rev ROSINA Date 01 11 06 Section 3 Page 40 2 3 1 5 Data Delivery Concept Application Process IDs Table 2 8 1 4 1 shows the required Application Process IDs and summarises the housekeeping event and science data packets Process Id Packet Packet Usage Category Type 80 12 TC Command packets to ROSINA 80 1 TM Command acknowledge packet 80 4 TM Housekeeping packet type 1 and 2 80 7 TM Event reporting packet 80 9 TM Memory Dump packet 80 11 TM Context file transfer packet 80 12 TM Science data packet Table 2 8 1 4 1 Application Process IDs 2 3 1 6 Timing Requirements The ROSINA DPU will use an internal S W timer which is triggered by an internal crystal oscillator 50ppm to maintain the S C time reference The ROSINA internal time needs to be synchronised to the S C time This shall be done 11 seconds after switch on of the instrument plus in intervals of not more than 30 minutes to maintain a maximum time difference of less than 100ms 2 4 Budgets Rosetta ROSINA 2 4 4 Mass and Power Reference RO ROS Man 1009 Issue 3 Rev 0 Date 01 11 06 Section 3 Page 41 Below are typical power numbers for the operation of ROSINA For a detailed power budget for the different scientific modes see 4 2 Mass Mean Power Max Power DFMS 16 2 kg 19W 28W RTOF 14 7 kg 24 W 27 W COPS 1 6 kg 3W 7W DPU 2 3 kg 3W 7W Total
24. N A All Standby during turn on turn off off DPU phases sequences High On off off Both closed off off S Cor N A All Safe mode during thruster Pressure off DPU phases firing and high pressure alert mode lon Source On off off Both open on off DPU gt 1 h All Regular cleaning of ion source cleaning off phases by heating 1 week TBC 1L Low Noise On On On ETS open off off DPU 10s All Background measurement of Power phases detectors every few minutes Background On On On ETS Partiall off off DPU 5 min All Background measurement of y open phases sensor by blocking off cometary material lt 1 day Reference RO ROS Man 1007 Rosetta Issue Rev 0 ROSINA Date 01 11 06 Section Page 10 Measureme On On On ETS open off off DPU 100s All Normal mass spectrum mass nt mass phases 1 500 amu e spectru m In flight On On On ETS open off on DPU 30 min All In flight calibration with gas calibration phases calibration unit 1 week 1G Gas Noise On On On ETS open off off DPU N A All Background measurement of phases detectors every few minutes Background On On On ETS Partiall off off DPU 5 min All Background measurement of y open phases sensor by blocking off cometary material 1 day Measure On On On ETS open off off DPU 100s All Normal mass spectrum mass ment mass phases 1 500 amu e spectru m In flight On On On ET
25. Octet Pressure minute 1 Octet Gradient OxFF if not available Events COPS Pressure Event Packet EID 44300 1 Octet Pressure Alert 1 Octet Gradient Reference RO ROS Man 1007 Rosetta Issue 3 Rev 0 Rosina Date 01 11 06 Section 6 Page 4 5 2 Flight Control procedures This document is maintained as a self standing document Annex B RO ROS MAN 1015 Rosetta Rosina 6 Data Operations Handbook 6 1 See Annex F1 6 2 Telemetry Packet Definitions Telecommand Function Definitions 6 2 1 DPU S C HousekeepingPackets See Annex F2 6 2 2 Science Data Sets Each Science Data Set consists of one or several Science Packets defined in 3 All values are in TM words 16 bits Reference RO ROS Man 1007 Issue 3 Date 01 11 06 Section 10 Rev 0 Page 4 6 2 2 4 DFMS Type Type Name Length Packet Usage Description No Ident Count D1 0x81 MCP Dual Raw 2062 2 Test Calibration 8 HK 2050 LEDA A B D3 0x83 MCP Raw 1034 1 Low High Zoom 8 HK 1024 LEDA D5 0x85 MCP Full Raw Low 20662 11 Full spectrum low 20 8 1024 D6 0x86 MCP Full Raw High 103302 51 Full spectrum high 100 8 1024 D7 0x87 MCP 12bit 394 1 12bit data compr 8 HK 384 LEDA D8 0x88 MCP 12bit Low High 106 1 4 comb pixel 12bitor 8 HK 96 LEDA center 128pix 12bit D20 0x20 MCP Compressed Max Max Full or single X
26. RO ROS Man 1009 Issue D3 Rev 0 ROSINA Date 01 11 06 Section 3 Page 2 2 1 2 Mechanical Interface 2 1 2 1 Mechanical Interface Control Drawings 2 1 2 1 1 Double Focusing Mass Spectrometer DFMS Yu M 1 25 2 1 2 1 2 Figure 2 1 Three dimensional view of DFMS in Launch Configuration Rosetta ROSINA Reference RO ROS Man 1009 Issue D3 Rev 0 Date 01 11 06 Section 3 Page 3 Fig 2 2 2 1 1 2 Mechanical Interface Control Drawing of DFMS in Launch Configuration UoB Drawing M155 1001 0 4 Ber zm ES vool ssiw Rev Page se vadoug 1eon do ouueut 01 11 06 w E xs e co w a oer ws E m us Ej xx amen 2x o o em mney venoaue upsa J m n EEN S uedoJd eA JO PIB Reference RO ROS Man 1009 Issue Date Section Een AGN i O 9 L0 4 d 5 s v EP ope He PISIUSUNS 06 Dawe PARA Rosetta ROSINA v9 18 N T O C PL z 1 F z o o ES i SPISINO JAOD M i H Ti
27. TBD TB DPU N A All phases Emergency handling for all the D Instruments TBD DPU DPU Memory Test On Off Off S C N A Ground test Test sequence during ground Ground test Test Instruments Test On Off On Off DPU N A Ground test Test sequence during ground On test DPU On On Off On DPU N A All phases Transitions of all the Transition Off Instruments Mode 4 2 3 DFMS Rosetta ROSINA Reference RO ROS Man 1007 Issue Date Section 3 Rev 01 11 06 4 Page 0 5 DFMS has several parameters in order to measure mass spectra of ions or neutrals between two given mass numbers with a high or low mass resolution with adjustable electron emission current and energy It has three different detector systems with different detector modes in order to accommodate the different density regimes of the mission The main unit operational modes are given below Full control of all sensor modes is within the DPU Data compression is achieved by integration over several spectra depending on data rate A more complete list can be found in annex D1 Mode Sub 28V HV Filam Cover lon GCU Activ Typical Used in Description mode ent source ated time phase Frequence of heater by activation S2 Cover Off Off Off Pyro Off Off S C N A Commissioni Breaking of vacuum seal Standby initial firing ng in LEO opening Safe On off off open off off S C N A All phases Standb
28. UGH EE r 5usnoH sojuo oeg 7 PA X0 3004 6urunoy lt PAES N AREN D Y Y uonoes b xeyeJ6i5 JEJEH JeAe 4 1 IPUJ YL Rk RBS E wJ0J3eld 2 6 03 WY pequnou 4214 xog sojuo n2erg a 264 tue LI E Rosetta ROSINA d N pu uorysedsay UOT yor Gupus A o Ni o f 6ujsnon 89100 40813 su V i Z ni a f Yee T ze in i i E i sen He 21 i sm zw i siz c P sue ve i o um p p em is d ape Y 73e S Jo ij j eunlo pea ese NY ne j m gt 3S BETO 26 D aunoa penesau c Fig 2 8 Mechanical Interface Drawing of RTOF in Operating Configuration UoB Drawing M156 1003 Reference RO ROS Man 1009 Rosetta Issue 3 Rev 0 Date 01 11 06 ROSINA Section 3 Page 10 2 1 2 1 4 Comet Pressure Sensor Fig 2 9 3 dimensional view of the COPS sensor Rosetta Reference RO ROS Man 1009 Issue 3 Rev 0 Date 01 11 06 ROSINA Section 3 Page 11 Purging Systen rot show ISOMETRIC VIEW 12 ISOMETRIC VIEW 2 12 5
29. a range is shown in Table 2 4 3 1 Experiment Unit Operating W DFMS Sensor 3 8 Electronics 15 1 RTOF Sensor 3 2 Electronics 19 0 COPS 2 1 7 0 about 3 W dissipated in gauge filaments and coupled to space Table 2 4 3 2 Heat Exchange Reference RO ROS Man 1009 Rosetta Issue 3 Rev ROSINA Date 01 11 06 Section 3 Page RTOF Sensor COPS Sensor DPU Table 2 3 3 5 Temperature Monitoring S C Provided Thermistors 55 to 90 C 55 to 90 C N A Temperature Sensors Electronics housing Detector Sensor head Electronics N A 2 4 3 3 2 Experiment Provided Temperature Sensors Experiment Unit DFMS Sensor RTOF Sensor COPS Sensor Table 2 3 3 6 Experiment provided Temperature Sensors Temperature Range 55 to 150 C 55 to 150 C 80 to 500 C 55 to 150 C 80 to 500 C N A N A N A N A 55 to 150 C 55 to 150 C N A Location DFMS Magnet DFMS Detector lon Source Heater RTOF Detectors lon Source Heaters ETS Board ETS L Board Gas pulser lon pulser Gauge G1 Electronics Board 2 N A Experiment Provided Temperature Sensors 0 45 Reference RO ROS Man 1009 Rosetta r Issue Rev ROSINA Date 01 11 06 Section 3 Page 46 3 Experiment Operations 3 1 ROSINA FM Operations Manual 3 1 1 Operating principles ROSINA consists of three sensors and a common DPU All sensors are operated indepen
30. any rate desired Sensors on the cover provide the motor controller with the open and close limits In addition the motor has hall sensors which the motor controller uses to count the number of motor revolutions The position of the cover as a function of the number of revolutions is calibrated prior to launch so that the cover can be placed in any arbitrary position between the open and closed limits The ion source contains two filaments for redundancy which are powered by the ion source controller The ion source controller regulates the current to the filaments and also receives housekeeping information on the source filament current and temperature in the vicinity of the filament see fig 1 6 for a block diagram The current limits for the ion source are set prior to electronics integration Otherwise he filaments can be commanded to any current level within these limits by the ion source controller In addition to the low voltage high current power supply for electron emission there are 10 other power supplies for the ion source Starting at the entrance to the ion source there is one ion source voltage commandable from 0 to 300 V with 12 bits accuracy This voltage repels ions coming from the comet so that when it is on and the emission source is on neutrals from the comet can be analysed without interference from cometary ions or from ions of other origin Following the ion suppression two power supplies provide vol
31. conceptual S W architecture in Fig 2 8 1 1 2 shows the basic S W tasks of all levels level number in brackets and its dependencies followed by a short description of each basic task DFMS Control 2 COPS Control 2 DPU H W Control 2 C Execution H Tables 4 Command S C Interpreter Command amp Service Execution 2 i and Data Processing 5 E Data ii Spectra w D E Data Telemetry i Service Acquisition Integration 2 Monitoring 4 H K 3 3S Collection 3S C In flight Calibration 4 C Virtuoso Real Time Operating System 1 Hardware Driver amp Boot Loader 1 Fig 2 8 1 1 2 Conceptual S W Architecture Command Service Decoding and error handling of commands from the S C Command interpreter amp execution Interpretation and execution C of low level commands or interpretation and transfer to higher level tasks of high level commands Sequencing of sensors and data processing Commands will be analysed for priority and queued into dedicated command execution chains Autonomous sequencing of different measurement cycles in cooperation with data acquisition Execution of the commands C will be possible immediately or related to the measurement cycle DFMS control Commands for the sensor electronics section of DFMS will be forwarded and the execution will be checked RTOF control Same as DFMS control COPS control Same as DFMS control R
32. day 2 2 6 3 Timing Ref to sec 2 8 ROSINA has no particular requirements on the timing wrt UTC 2 2 6 4 Monitoring Ref to sec 2 8 Rosetta ROSINA Issue 3 Date 01 11 06 Section 3 2 2 6 5 Electrical Interface Circuits Reference RO ROS Man 1009 Rev 0 Page 29 The OBDH interface will be according to EID A chapter 2 7 using the driver and receiver circuits in figure 2 7 3 1 to 2 7 3 4 No cross coupling between redundant drivers and redundant processing units is foreseen inside the DPU The SBDL interface receiver circuit in figure 2 7 3 1 is used for the signals TC Sampling TC Data TC TM Clock TM Sampling and Timer Sync Pulse main and redundant DRIVER S C 5V 9 DPU or equivalent v Signal GND n Chassis GND N 56 1 4 Ss HS 26C31RH fe SIGNAL TRUE m ii T il SIGNAL COMP li Fig 2 22 SBDL Interface Receiver Circuit RECEIVER 1 4 HS 26C32RH l or equivalent Signal GND V Chassis GND Reference RO ROS Man 1009 Rosetta Issue 3 Rev 0 Date 01 11 06 ROSINA Section 3 Page 30 The SBDL interface driver circuit in figure 2 23 is used for the signal TM Data main and redundant RECEIVER S C DRIVER DPU 1 4 HS 26C31RH HS 26C32RH or equivalent ii or equivalent v Signal GND mm Signal GNO Y Chassis GND Chassis GND Fig 2 23 SBDL Interface Driver Circuit Reference R
33. free drift path This time focusing property of the ion mirror for a given drift path length is often referred to as isochronous operation since the flight time does not depend on the energy of the ions The energy range of isochronous operation is 10 of the nominal energy for this design Therefore ions with a specific energy distribution and the same m q ratio will reach the detector plane simultaneously The reflectron generates an image of the first time focus after the ion source to a time focus at the exit path with reversed velocity vectors for the ions The step from a discrete two stage reflectron to a grid free reflectron is made by simply omitting the grids The omission of grids makes the mechanical design of the reflectron easier and avoids transmission losses due to the limited ion optical transparency of the grid which is significantly lower than the geometrical transparency However the homogeneous electrical field configuration with parallel Reference RO ROS Man 1009 Rosetta r a Issue Rev Date 01 11 06 ROSINA Section 1 Page 31 equipotential lines changes into curved equipotential lines by superposition of the different potentials applied to form the retarding and repelling electrical field The curved potential contour lines geometrically influence the passing ion trajectories Therefore a grid free reflectron also has geometrical focusing or defocusing properties Due to the positive voltages in the reflectron
34. gt Ex sow ty g d i 82 gp x 5 B i g f TE gee 25 y S A HIT nh 55 Illustrative sketch only for internal temperature limits ref to Table 2 2 5 1 o oN ed o Sy AF 0 0 E d d T So 2 989 04 2 G o C Ss ehG z E a un w2ed ma vub xadg danpwradwiey a2bviars e g Jejow JIP 13407 2040n D P ie 93Jnog UO osd 93409 pe bbb PMS EUJr JSG 2 d pons jeuJeui Jeuui D CEPS c O9t O e p vs o 6 PA 9 t DoS i JOJN pJeH JE amp UOAO o LoF SS 5 mi t a D 04 DF ut rLan aunyyradma4 busporado J0199190 dH oz popa uea JUGS uoi ANIL NIJO NON aqn 44017 uoi ee ee anal ONIY B3Qdo DOCTA O A0 2 00 93 J 0p 22 32d wo 2 vos ow t 22ej2Q sanjan oahd 12402 UOS 551J0g D918J591ul o x zz o Oo oO co 5USnoH S5100 12913 DO ot 2 0y Oht Ot 2 09 JO 1 2wi2 2 PIU DMO wr Illustrative sketch only for internal temperature limits ref to Table 2 2 5 1 Reference RO ROS Man 1009 Rosetta r L5 Issue Rev ROSINA Date 01 11 06 Section 3 Page 27 2 2 6 OBDH INTERFACE REQUIREMENTS 2 2 6 1 Channel Allocation Interface Signal Type or Function E Redundant Telecommand Memory Load Commands Channels High Power ON OFF 2 2 Commands Telemetry 16 Bit Serial Digital Channel 1 1 Channels Fast Serial Interface Monitor Channels Spacecraft Powered 3 2 Thermistors a ll ll n Table 2 7 1 Experiment OBDH Interface Channels Fu
35. internal time response for single ion events of less than one nano second have to be used A narrow time width not only improves the mass resolution but also increases the peak amplitude and therefore improves the signal to noise ratio The geometry in the ROSINA RTOF limits the diameter of the ion beam to 12 mm For mass saving reasons the active area of the detector is therefore only 18 mm Micro channel plates of imaging quality have been selected for registering the ions micro sphere plates turned out to be not stable enough over the projected lifetime of the RTOF sensor The critical issue for the detector is the anode design which has to ensure a 50 Q impedance coupling of the electron pulse released from the channel plate into a standard transmission line with minimal signal reflections and distortions Wurz et al 1994 Wurz et al 1996 The detector output is capacitively decoupled from the anode and thus allows the detector unit to float electrically The transition line yields directly into a SMA output connector to connect the signal line The signal is routed through semi rigid cable impedance Z 50 Q and extra high frequency tri axial vacuum feed through rated 4 GHz to the data acquisition system to minimize the noise pickup The measured pulse width for a single ion event of this detector including the signal routing is about 500 ps The detector contains an integrated voltage divider to provide the various voltages needed to suppl
36. oe pns Gupunouo Lc HUET LUI 43 Li LII LITE de e amp er 4 4 or LU B i o eps ioa Rosetta ROSINA 966 paruadin USpunpsu P kr 3uepunpey HOO I0 d P d 4 UH HOBO oor i 590 RUBS 0 NEE SOLU PBS Lor D 3oig Jeog gor Se p p Sidi RUBS SO S33 Jarod vo Mechanical Interface Control Drawing of the DPU UoB Drawing M157 1000 DPU Figure 2 12 Reference RO ROS Man 1009 Rosetta r Issue Rev ROSINA Date 01 11 06 Section 3 Page 14 2 2 Electrical 2 2 1 General Each 28 V MAIN BUS supply comprises 2 supply wires and 2 return wires for each main and redundant I F respectively see Table 2 1 Number of Number of LCL Class Main Lines Redundant Required Lines Required 28 V MAIN BUS E Switched and Current limited 109W 4 0A trip off limit 28V NON OPS HEATER POWER for DFMS B Switched and Current limited 22 W 0 8 A trip off limit Converter Synchronisation Signal po foo 2 2 2 Power Distribution and Redundancy Scheme Each major subassembly has it s own power converter controlled by the DPU The DPU has redundant power converters Fig 2 13 Both 28 V lines are routed to both DPU converters and via the intra instrument harness to all three sensors In each of the sensors units each
37. of Explosives 70mg 40mg AW1 30mg RDX Dimensions diameter 14 mm length 35 7 mm Table 2 5 3 Pyrotechnic Device Interface Characteristics Cover Separation Function Reference RO ROS Man 1009 Rosetta r T Issue Rev ROSINA Date 01 11 06 Section 3 Page 23 Pyrotechnic Initiator for the Cover Bellow Actuator PEU Load Interface Specification and Mechanical Characteristics Pyro Type MARK20 MOD 0 Manufacturer Quantic Industries Procurement Specification PN 1379 AS 781 Electrical Characteristics Bridge Resistance 1 0 0 15 Ohm All Fire Condition 4A 20msec Current and Pulse Duration No Fire Current Current and Pulse Duration 1A 5min Insulation Resistance between filaments gt 100 MOhm 500 V DC before and EED case before Firing short circuit expected after firing 25000V 500pF 5KOhm Electrostatic Discharge Strength inc Conditions 54 C 74 C Operating and Non Op Temperature Range 54 C 54 C Storage Temperature Range Mechanical Characteristics Mass lt 5g Maximum mass of Explosives 61 mg Black powder Dimensions diameter 7 7mm x 25 5mm The electrical parameters for the Initiator are being adjusted by an additional passive matching network Comprehensive Qualification and Functional Tests under audit will be performed Table 2 5 4 Pyrotechnic Device Interface of the Cover Bellow Actuator Reference RO ROS Man 1009 Rosetta Is
38. package which is represented in figure 1 8 10000 Accumulated ADC codes 1000 219 229 239 249 259 269 279 289 299 309 Anode nr Fig 1 9 LEDA response Ro setta Reference RO ROS Man 1009 Issue 3 Rev 1 ROSINA Date 01 11 06 Section 1 Page 24 High Resolution Mass Spectrum 10000 ROSINA DFMS EOM Zoom factor 6 4 zoom optics January 10 2000 1000 Count rate s 100 10 24800 25000 25200 25400 25600 25800 26000 26200 26400 Jacq wide s qdzn umant Aga Lp Detector y position um Fig 1 10 High Resolution mass spectrum with the DFMS EQM The Remote Detector Package RDP with 4 boards located just behind the collector and the Faraday cup They include the most sensitive circuits which need to be as close as possible to the LEDA and Faraday cup and the associated interface circuits with the FDP The Floating Detector Package FDP with 3 boards mounted insulated on the DFMS base plate and which provide digital interfacing with the RDP boards processing of the analog signals from the LEDA and FC and MCP floating HV and FDP power supply voltages This pack floats at the detector acceleration potential somewhat above VACCEL of the ASP Like the ASP it is electrically isolated from the base plate by high voltage standoffs and thermal dissipation is accomplished in the same way as the ASP di
39. power supplies The high accuracy is required because the ESA voltages are used to select specific ion energies and focus specific masses on the Channel electron multiplier in the detector section In the original design critical elements in the DFMS electronics like the ESA power supplies were to be temperature controlled to very high accuracy The resource requirements for this control proved to be prohibitive and a compromise control scheme was developed The ESA voltage is temperature compensated using a pre programmed lookup table in the ESA controller The lookup table is pre programmed during EAS voltage calibration to compensate the temperature changes in the voltage and keep the ESA voltage stable during the measurement cycle with stability approaching 4 parts per million 18 bit Following the ESA the ion trajectory is again corrected in several optical low voltage optical elements controlled by one 0 to 110 V and three 0 50 V power supplies prior to entering the permanent magnet The magnet is a static element in the ion path but the temperature is monitored by the DFMS electronics Upon exiting the magnet the ion trajectory is again corrected with a low voltage 0 to 110 V prior to entering the zoom optics When the optical elements in this section are not active the DFMS is in low mass resolution mode and the mass dispersed ion beam impinges on the detector selected by the optical steering When the four optical elements powe
40. stay in an open position The secondary structure is made from aluminum partly as honeycomb structure It houses the different electronics pack The electronics which is on high voltage is insulated from the spacecraft ground by BeO standoffs in order to guarantee at the same time a good electrical insulation as well as a good thermal conductivity The primary structure is mounted on spring blades made from carbon fiber material on top of the secondary structure This allows compensation for the different thermal Reference RO ROS Man 1009 Rosetta r a Issue Rev ROSINA Date 01 11 06 Section 1 Page 19 l C o l l l l l i 0 to 110V l l l l l l l Temperature sensor MTH MTL Temperature sensor for permanent sector DTL DTH magnet for LEDA VACCL OV or RE 100to 6500v T sp peme l suppressor position 14bit HME 0 or 70V EME sensitive Analyzer detector laic mass Potential igh mass 0 to 3000V Rosetta Rosina DFMS block diagram with principal d 10bit Analyzer and Detectors power supplies ground PHYSIKALISCHES INSTITUT UNIVERSITY OF BERN Fig 1 6 DFMS Electronics Block Diagram expansion coefficients The in flight calibration system contains two gas containers each containing about 10 cm of a noble gas mixture at 1 bar pressure It is identical to the one used in RTOF For a detailed description see 1 2 4 Fig 1 5 shows the ele
41. the TOF system The small duty cycle resulting from pulsing ions out of a continuous beam is one of the major drawbacks of the orthogonal extraction ion source The final energy of the extracted ions on the drift sections is again 3 5 keV The energy is achieved using a two stage acceleration region allowing for second order focusing at the first time focus plane The ion source consists of a rotational symmetric ion extraction and acceleration section and the off axis ionisation assembly mounted perpendicularly to the former see Figure 1 12 The extraction and acceleration section of the orthogonal extraction ion source are the same as in the storage ion source The filament and trap assemblies are planar symmetric in the plane of the drawing Cometary ions are pulled into the entrance system of the off axis ionisation assembly by an external attraction grid and their energy is adjusted to be about 10 eV by suitable acceleration or deceleration The entrance section also has a filament assembly to create ions from in flowing gas by electron impact ionisation The ions are accelerated to form a continuous ion beam orthogonal to the principal ion optical axis of the TOF system The following skimmer arrangement minimizes the velocity components in and against the direction of the principal ion optical axis of the TOF system Therefore the turn around time which is the limiting factor for the mass resolution of the system is largely reduced resulting in a
42. the ideal surface All the ion optical elements are co aligned with an accuracy of a few um All along the ion trajectories the surfaces are gold plated or gold sputtered in order to get uniform electrical fields The primary structure is electrically and thermally isolated from the secondary structure The main part is at high voltage of up to 6 kV during operation whereas the ROSINA DFMS entrance part with the ion source is at a few volts relative to the Fig 1 5 DFMS Electrical Qualification model spacecraft A ceramic ring guarantees the electrical insulation between the two parts In order to maintain the detectors within the given temperature limits of 20 to 30 C the MLI surrounding the detector part contains a non operational heater as well as a radiator The primary structure will be baked out and then sealed by a cover to minimize contamination It will be evacuated through a pump off valve The vacuum keeping requirements ask for a pressure of 10 mbar after 1 week without pumping The cover will only be opened in space by a pyrotechnical device After the initial opening it can be reclosed and will be tight with respect to the molecular flow conditions in space It is intended to close the cover during thruster firing and in case of high dust activity near the comet in order to keep the sensor clean In case of a failure of the cover motor a pyrotechnical device can disengage the gear of the cover and the cover will then
43. 0 2 MC GEX TEMP V value 366e 6 042 2 MC HM PW V value 0 0037 0 4095 044 2 MC HM DEL V value 0 0037 0 2594 046 2 MC HM TEMP V value 366e 6 048 2 MC Power State 2 Rosetta Reference genie o Issue Rev Date 01 11 06 Rosina Section 10 Page 6 15 ETSL VDD On 0 Off 1 2 On 14 ETSL VDD Off 0 Off 1 On 13 ETSL VCC On 0 Off 1 On 12 ETSL VCC Off 0 Off 1 On 11 Heater Gas On 0 Off 1 On 10 Heater Gas Off 0 Off 1 On 9 Heater lon On 0 Off 1 On Heater lon Off 0 Off 1 On 7 Motor Hall Enable 0 Off 1 On 6 Motor Hall Disable 0 Off 1 On 5 Motor Direction Open 0 Off 1 On 4 Motor Direction Close 0 Off 1 On 3 Motor Power On 0 Off 1 On 2 Motor Power Off 0 Off 1 On 1 Motor High Torque On 0 Off 1 On 0 Motor High Torque Off 0 Off 1 On 050 2 MC Pulser State 15 Gas Pulser On 0 Off 1 On 14 Gas Pulser Off 0 Off 1 On 13 HM Pulser On 0 Off 1 On 12 HM Pulser Off 0 Off 1 On 11 lon Pulser On 0 Off 1 On 10 lon Pulser Off 0 Off 1 On 9 0 Spare 052 2 MC Power State 6 15 1 Spare 0 9 Disable ETS LU 0 Off 1 On 8 Enable ETS LU 0 Off 1 On 7 ETS VCA On 0 Off 1 On 6 ETS VCA Off 0 Off 1 On 5 ETS VDD On 0 Off 1 On 4 ETS VDD Off 0 Off 1 On
44. 2 High mass dispersion can be achieved by using a electrostatic zoom lens system At the high mass resolutions the detector and focal plane coincide only at one mass number High resolution can thus only be obtained for the mass multiplets at one mass number and the mass lines from neighboring mass numbers will show less mass resolution To obtain a full high resolution mass spectrum from 12 to 100 amu q it is thus necessary to record a mass spectrum at each integer mass number The analyzer can also be operated in a low resolution mode which allows the simultaneous recording of several mass lines on the position sensitive detector with a resolution of m Am of several hundred Neighboring integer mass numbers are well separated at this mass resolution In this mode the zoom system is used to rotate the alpha focal plane into the plane of the position sensitive detector lon detectors The instrument has three independent ion detectors see Figure 1 2 Design considerations for detectors Within a mass range which is controlled by the setting of the ion optics ions exiting from the DFMS are focused on a focal plane and therefore provide an instantaneous one dimensional image of the mass spectrum of the comet ionised or neutral gas The detector package which has been designed specifically for the DFMS has to meet to a number of requirements which may be briefly summarized as follows Inthe central part of the ion beam exiting the spectrometer the
45. 2 2 HV1_A2 V value 0 5089 35 088 084 2 HV1 A1 I V value 0 2566 20 022 086 2 HV2 PG V value 0 1258 2 7606 088 2 HV2 PI V value 0 1261 5 0041 090 2 HV1 D V value 0 5088 31 123 092 2 HV2 HM3 V value 0 1294 1 2232 094 2 HV1 H1 V value 0 1268 3 0101 096 2 HV1_R2 V value 0 2765 2175 6 098 2 HV1_RL V value 0 5594 4371 5 100 2 HV1_HM1 V value 0 2777 2156 2 102 2 HV2_HM2 V value 0 0393 308 38 104 2 HV1_HML V value 0 5207 4123 106 2 HV2 M_I V value 0 7818 14 283 108 2 HV2 M G V value 0 7695 47 787 110 2 PSDC E2 V value 0 0062 112 2 PSDC Temp BP I TBD 114 2 PSDC Temp BP G T value 1 831e 2 50 C 116 2 PSU Temp MCP I TBD 118 2 PSU Temp MCP G TBD 120 2 PSU Temp HV1 T value 0 0089 9 C 122 2 PSU Temp LVPS T value 0 0089 9 C 124 2 ETSL Status 1 15 ETSL lon Pulser Status 0 Off 1 On 14 ETSL Gas Pulser Status 0 Off 1 On Reference RO ROS Man 1007 Rosetta Issue 3 0 Rev Date 01 11 06 Rosina Section 10 Page 8 13 ETSL Sync Status 0 Int 1 Ext 12 ETSL Calib Trigger Status 0 Off 1 On 11 ETSL Data Readout Status 0 Off 1 On 10 ETSL Acquisition Status 0 Off 1 On 9 ETSL DTS Status Cancel 0 Event 1 Extraction
46. 31 1k S4 RTOF DFMS Standby on stby stby Micro 36 5 25 E4 RTOF DFMS Emergency on on on Micro 36 5 500 G4 RTOF DFMS Ground test on stby stby stby 32 5 46k 4 RTOF Single DFMS on on on Full 52 2k S5 COPS Standby on off off stby 8 25 E5 COPS Emergency on off off on 8 500 G5 COPS Ground test on off off stby 8 500 5M COPS monitoring on off off Nude Micro 9 25 5 COPS Full on off off Full 11 25 Table 3 1 shows the major operation mode definitions for the instrument the state of the different units the mode command parameter the average power consumption and Rosetta Reference RO ROS Man 1007 Issue 3 Rev 0 ROSINA Date 01 11 06 Section 4 Page 4 4 2 2 DPU Modes DPU Modes Mode Sub mode 28V Experiment HV Activ Typic Usedin Desription ated al phase Frequency of by time activation DPU Initial booting On Off Off S C 10s Ground test Ground test Mode Booting DPU Patching On Off Off S C N A All phases Software download DPU Normal On Off Off S C or N A All phases All the Instruments are Standby DPU switched Off excepted the DPU DPU Pressure Monitoring On COPS On DPU 10s All phases Monitoring of pressure and gas Instrument parameters Instruments Mode On COPS On Off Off DPU N A All phases All the sensor modes DFMS On Off On RTOF On Off DPU Pressure Alert On Off Off DPU N A All phases All the sensors are switched Emergency Off Emergency On
47. 8 HK Y LEDA 26426 13 depends on compr factor D40 0x40 CEM Full Raw High Max Max Full or single spectrum X 8 HK 4 Y CEM 32834 17 D42 Ox42 FAR Full Raw High Max Max 5 Full or single spectrum X 8 HK 2 Y FAR Reference RO ROS Man 1007 Rosetta r Issue Rev i Date 01 11 06 Rosina Section 10 Page 2 8810 6 2 2 2 RTOF Type Type Name Length Packet Usage Description No Ident Count R20 0x14 ETS Full Raw Max Max Test Calibration 123 HK X 5 3 ETS 393740 193 R21 0x15 ETSL Full Raw Max Max Test Calibration 123 HK X 5 3 ETSL 393740 193 R22 0x16 ETS Select Raw 16354 8 300 mass 18 points 123 HK 16215 ETS R23 0x17 ETSL Select Raw 16354 8 300 mass 18 points 123 HK 16215 ETSL R24 0x18 ETS Compressed Max Max Full spectrum 123 HK X ETS 98304 48 depends on compr factor R25 0x19 ETSL Compressed Max Max Full spectrum 123 HK X ETSL 98304 48 depends on compr factor R26 Ox1A ETS HIRM Max Max Test Calibration 123 HK 3 4 X 5 3 295340 145 ETS 6 2 2 3 COPS Type Type Name Length Packet Usage Description No Ident Count C1 0x10 Full Pressure 72 1 Background Alert 10 HK 30 2 Pres 60s 6 2 3 Science Packet Definitions 6 2 3 1 DFMS Science Packet
48. AG31B 2 DPU Mode Hex value 020 NRNAG3AO 2 DPU Status Hex value 6 3 3 4 Sensor I F Error Report EID 44103 Length 14 words Pos RSDB Byte Bit Name Data 000 NRNAG304 2 EID 44103 002 NRNAG322 1 Unit 196 DFMS 200 RTOF 204 COPS 003 1 Flags Hex value 004 NRNAG34A 2 Sensor HK amp power status 15 COPS HK Status 0 Off 1 On 14 RTOF HK Status 0 Off 1 On 13 DFMS HK Status 0 Off 1 On 12 9 Spare 8 COPS Transc Enable 0 Diabled 1 Enabled 7 COPS Main Power 0 Off 1 On 6 COPS Red Power 0 Off 1 On 5 RTOF Transc Enable 0 Diabled 1 Enabled 4 RTOF Main Power 0 Off 1 On 3 RTOF Red Power 0 Off 1 On 2 DFMS Transc Enable 0 Diabled 1 Enabled 1 DFMS Main Power 0 Off 1 On 0 DFMS Red Power 0 Off 1 On 006 NRNAG34B 2 Sensor HK counter Counter 0 65535 008 NRNAG34C 2 Sensor Cmd counter Counter 0 65535 010 NRNAG34D 2 Sensor Cmd Error counter Counter 0 65535 Reference RO ROS Man 1007 Rosetta Issue 3 Rev 0 i Date 01 11 06 Rosina Section 10 Page 18 012 NRNAG34E 2 Sensor Cmd Error position Hex value 014 NRNAG34F 2 Sensor Science counter Counter 0 65535 016 NRNAG350 2 Sensor Science Error cnt Counter 0 65535 018 NRNAG351 2 Se
49. Cur value 0 0174 0 4234 mA 230 2 PSU 5 Add Cur value 0 0571 3 4918 mA 232 2 PSU 48 Cur value 0 0254 5 663 mA 234 4 ETSL NOE 31 2 Spare 5 24 1 NOE High value Dec value 7 16 9 Spare 8 1 NOE Low value Dec value 0 NOE Status 0 Continuous 1 NOE 238 2 ETS NOE High 15 9 Spare 8 1 NOE High value Dec value 240 2 ETS NOE Low 15 9 Spare 8 1 NOELow value Dec value 0 NOE Status 0 Continuous 1 NOE 242 2 Spare 1 244 2 Spare 2 6 2 4 3 COPS Science HK Data Length 10 words Position Bytes Bits Name Data 000 1 COPS Science HK Header OxCC 001 3 Spare 004 4 Pressure NG Pressure in mbar floating point 008 4 Pressure RG Pressure in mbar floating point 012 4 Calib factor Offset NG Floating point value 016 4 Calib factor Offset RG Floating point value 018 2 Active Filament Microtips 15 8 Microtips Array MT 8 1 0 On 1 Off 7 6 DPU MT lon Range 0 Low 1 Medium 2 High 5 DPU MT Emission Range 0 Low 1 High 4 Filament 0 Left 1 Right 3 2 DPU Fil lon Range 0 Low 1 Medium 2 High 1 DPU Fil Emission Range 0 Low 1 High 0 DPU Function 0 NG 1 RG Reference RO ROS Man 1007 Rosetta Issue MEC Rev 0 i Date 01 11 06 Rosina Section 10 Page 11 6 3 Event Packet Definitions 6 3 1 Packet Types and
50. EIDs Sub EID RSDB Packet Description Type Size words 1 44001 YRNG3001 9 Power On self test report 1 44002 YRNG3002 10 Program memory test report 1 44003 YRNG3003 10 Data memory test report 1 44004 YRNG3004 10 EEPROM test report ground test only 1 44005 YRNG3005 12 Operation mode change report 1 44006 YRNG3006 17 Sensor switch on report 1 44007 YRNG3010 10 Progress report 1 44008 YRNG3011 28 Table Setting report 2 44100 YRNG3007 7 DPU latch up report 2 44101 YRNG3008 13 DPU memory error report 2 44102 YRNG3009 11 DPU general error report 2 44103 YRNG300A 14 Sensor I F error report 2 44104 YRNG300B 11 Sensor error report 3 4 44300 YRNG300C 3 COPS Pressure Alert 4 44301 YRNG300D 2 Switch Off Ready Alert 6 3 2 Normal Event Packet Definitions Sub Type 1 6 3 2 1 POST Report EID 44001 Length 9 words Pos RSDB Byte Bit Name Data 000 NRNAG304 2 EID 44001 002 NRNAG305 1 Unit 208 003 1 Spare 0 004 NRNAG307 4 Error Code Hex value 008 NRNAG308 4 Error Position Address Hex value Boot Err Cnt PM DM 012 NRNAG306 1 DPU Self test status Reference RO ROS Man 1007 Rosetta Issue D3 Rev 0 Date 01 11 06 Rosina Section 10 Page 12 7 Processor self test 0 Ok 1 Error 6 PM self test 0 Ok
51. ERFACE REQUIREMENTS General Interface Description Rosina has two different Electro Explosive Devices on the cover opening mechanism on each of the sensor units DFMS and RTOF The Pyrotechnical Separation System breaks the vacuum sealing between the cover and the instrument and will be activated shortly after launch Upon separation the cover can be moved freely open and close by the commandable cover mechanism drive on the hinge The Cover Pyro Detonator has two redundant ignition blocks and therefore needs a redundant wiring scheme The Cover Bellow Actuator is a fail safe provision for the cover mechanism which only will be activated in case of a cover mechanism failure whereby the cover is released into a final open position Because this actuator acts as a backup there is only one non redundant actuator used Number of Number of Main Lines Redundant Required Lines Open DFMS Vacuum Seal Entrance Aperture DFMS Cover fail save actuator Open RTOF Vacuum Seal RTOF Cover fail save actuator Table 2 5 1 PEU Firing Lines Requirements Function Initiator Principle Power supplied by if applicable No alternate N N A Initiators used Table 2 5 2 Alternate Initiators Function and Supply Reference RO ROS Man 1009 Rosetta Issue 3 Rev 0 Date 01 11 06 ROSINA Section 3 Page 21 2 2 4 2 Pyrotechnic Firing Line PYR Interface The following drawings show the Pyrotechnical Interfaces of the S C to th
52. Gas oe io d Range amu Component Highest time resolution for full spectrum 120s i d TEE 7 RF 1 h gt 300 bsoo o 1 1x10 A mbar corresponds to 0 2 counts s if TET is 1 cm Emission current of the ion source at 10 uA can be increased up to a factor of 5 or decreased Counts per second for cometary ion density of 1 cm Ratio of highest to lowest peak in one measurement cycle Total measurement range High resolution mode Narrow field of view entrance COPS gt a on ee oOo C rn L 1 1 2 Scientific Closure Table 3 shows the data products from the ROSINA investigation and the corresponding scientific objectives that will be addressed using these data products In addition to the specific science objectives of ROSINA listed in the table the data products will provide key information for additional science objectives of other Reference RO ROS Man 1009 Rosetta r a Issue Rev ROSINA Date 01 11 06 Section 1 Page 11 Rosetta orbiter and lander instruments Collaboration between the ROSINA investigation and other orbiter and lander investigations will greatly enhance the scientific results in several key areas including dust gas interaction gas plasma interaction causes of cometary activity and compositional differences within the nucleus Table 1 3 ROSINA sensors data products and science objectives Sensor Data Product Science Objective High Resolution an
53. K and MC 8 Gas Calibration Unit GCU Contains two full redundant units for the in flight calibration with a gas of defined composition 9 lon Gas and Hard Mirror Pulser The lon and Gas pulsers perform the extraction with a negative pulse with a fast falling edge and a medium fast rising edge The amplitude is programmable The Hard Mirror Pulser deflects charged particles before they hit the detector with a positive pulse from a positive Hard Mirror potential Pulse width delay from trigger and pulse amplitude are programmable 10 Filament Emission Controller FEC The FEC regulates the emission current of the Gas and the lon Source filament It also contains the selection of the redundant filament sets in case of failure Equivalent Time Sampling System ETS The ETS is one of two data acquisition systems in the RTOF sensor to digitize analog signals It is a multiple ADC high speed data acquisition unit that is especially designed for fast and non periodic pulses recorded by the Micro Channel Plate MCP detectors 16 high speed 8bit low power ADC s are fired with a 2ns delay Fig 1 120 RTOF electrical after an input signal exceeds a 3 bit programmable trigger level 10 100mV The delay between the occurring waveform and the ADC start is less than 3 ns to minimize the trigger jitter The sample and hold gate time is 1 ns The signal source can be selected by DPU command out of the 2 inputs one for the ion and one for the neutral
54. O ROS Man 1009 Rosetta Issue 3 Rev 0 ROSINA Date 01 11 06 Section 3 Page 31 The high power ON OFF command interface receiver circuit in figure 2 24 is used for the signals High Power Set and High Power Reset main and redundant OBDH USER DPU HIGH POWER ON OFF SIG TSP TSP HIGH POWER ON OFF RTN 7 Signal GND i j ional igna Signal GND g Chassis GND Chassis GND Fig 2 24 High Power ON OFF Command Receiver Circuit Reference RO ROS Man 1009 Rosetta Issue 3 Rev 0 Date 01 11 06 ROSINA Section 3 Page 32 The conditioned analogue thermistor interface circuit in figure 2 25 is used for the signals Thermistor 1 Thermistor 2 and Thermistor 3 main and redundant OBDH S C Signal Receiver V Ky R1 To V T LJ R2 f i USER DPU COND ANALOG e TP wal L COND ANALOG RTN Signal GND M Structure GND Fig 2 25 Conditioned Analogue Interface Circuit Reference RO ROS Man 1009 Rosetta r L9 Issue Rev ROSINA Date 01 11 06 Section 3 Page 33 2 3 Software 2 3 1 2 3 1 1 Software Concept and Functional Requirements Software Overview The DPU S W is based on a real time multitasking kernel ROSINA uses the Virtuoso SP Eonic Systems that provides 1 preemptive event driven scheduling 2 dynamically prioritised tasks 3 synchronisation and communication facilities semaphores mailboxes qu
55. Origin of material Molecular abundances Heavy organic molecules Origin of material processing of material prior to incorporation in comets Reduced vs oxidized molecules Chemical and physical conditions during molecule formation origin of material Reference RO ROS Man 1009 Rosetta r Issue Rev ROSINA Date 01 11 06 Section 1 Page OT Series of molecules e g CnHm Origin of material processing of material prior to incorporation in comets Os Os Origin of terrestrial oxygen Radicals Physical and chemical conditions during comet formation processing of comets Ph ysical and chemical processes Extended Sources Composition of dust in the coma Molecular abundances as function of heliospheric distance Nucleus composition and processing of nucleus Molecular abundance differences in jets Homogeneity of nucleus composition spatial and temporal differences Abundance differences between Oort cloud comets and Kuiper belt comets Physical and chemical conditions in the different comet forming regions chemistry in the solar nebula and sub nebulae 1 1 1 Scientific Goals As part of the core payload of the Rosetta mission the Rosetta Orbiter Spectrometer for lon and Neutral Analysis ROSINA will answer outstanding questions concerning the main objectives of the mission The primary measurement objective of the spectrometer is To determine the elemental isotopic and molecular composition of the atmospheres an
56. Reference RO ROS Man 1009 Rosetta Issue Rev 1 ROSINA Date 01 11 06 Section 1 Page 1 ROSINA Users Manual Issue 3 1 Authorised for the Principal Investigator Hans Balsiger ROSINA Principal Investigator Approved by P Ferri ESOC Reference RO ROS Man 1009 Rosetta r a Issue Rev ROSINA Date 01 11 06 Section 1 Page 2 Table of Content 1 General Description Rosetta Orbiter Spectrometer for Ion and Neutral Analysis IOSINA 6 1 4 Scientific DO CUIV ES eB 6 1 1 1 Scientific Goals NNI 7 1 1 2 Scientific C IDRBEB sisone rr Due i E a EEE 10 1 2 Experiment Over View ssscsssesssecssoossocccossccocssoocsooossooscosscoossssoessoossosesoosesssssseessse 12 1 2 1 DEMS 12 12 4 RTOP MOMENTE NERONE NOM RUN HUNE 26 1 2 3 COPS p E E E E ene ence ese arene eres 42 1 2 4 DPU T E E E 45 2 o ges XE 07 7 NEC 1 2 1 Physical Merc 1 2 1 1 Mech amisms CONCEP P biases 1 2 1 2 Mecha mical MIE ACS 211i crccaateaetsanncssacasconsnadtensszuateiateanresteueenisaunterebaaeoreranbinwess p 2 2 HNC CUPICA e 14 2 2 1 E e I E 14 PAPA Power Distribution and Redundancy Scheme esses 14 2 2 3 Experiment Power Requirements seeseesseees
57. S open off on DPU 30 min All In flight calibration with gas calibration phases calibration unit 1 week 1l lon Noise On On Off ETS L open off off DPU N A All Background measurement of phases detectors every few minutes Background On On Off ETS L Partiall off off DPU 5 min All Background measurement of y open phases sensor by blocking off cometary material 1 day Measureme On On Off ETS L open off off DPU 100s All Normal mass spectrum ions nt mass phases mass 1 500 amu e spectru m 1 RTOF Noise On On on ETS open off off DPU N A All Background measurement of full and phases detectors every few minutes Reference RO ROS Man 1007 Rosetta Issue 3 Rev 0 ROSINA Date 01 11 06 Section 4 Page 11 ETS L Background On On on ETS Partiall off off DPU 5 min All Background measurement of and y open phases sensor by blocking off ETS_L cometary material lt 1 day Measureme On On on ETS open off off DPU 100s All Normal mass spectrum ions nt and mass phases and gas mass 1 500 amu e ETS L spectru m G1 Normal On off Off ETS closed off off DPU N A Groun Test sequence during ground Ground and dtest test if no vacuum pump is test ETS L attached Special test On On On ETS closed off off DPU 2h Specia Test sequence during ground and test if vacuum pump is ETS L ground attached test
58. SINA Data Type Description Volume Operational Usage MByte Non Science Housekeeping 2 25 bit s Telemetry Science 100 1300 bit s Telemetry Context 1 kByte S W patches 0 5 Other SSMM Utilisation Mission Phase Nucleus mapp Instrument ROSINA Data Type Description Volume Operational Usage MByte Non Science Housekeeping 2 25 bit s Telemetry Science 100 1300 bit s Telemetry Context 1 kByte S W patches 0 5 Other TBD Reference RO ROS Man 1009 Rosetta r Issue Rev ROSINA Date 01 11 06 Section 3 Page 43 SSMM Utilisation Mission Phase Comet escort Instrument ROSINA Data Type Description Volume Operational Usage MByte Non Science Housekeeping 2 25 bit s Telemetry Science Telemetry 200 2600 bit s Context 1 kByte S W patches 0 5 Other 2 4 3 Rosetta Reference RO ROS Man 1009 Issue 3 Rev 0 ROSINA Date 01 11 06 Section 3 Page 44 Thermal Budget 2 4 3 1 Heater Power Requirements Experiment Unit Power W DFMS Sensor 2 4 3 2 RTOF Sensor COPS Sensor DPU Table 2 4 3 1 Heater Power Requirements The non ops heaters are switched on automatically by the S C if the temperature drops below the specified lower non ops value at the temperature reference point see 2 2 5 Heat Exchange Budget The heat exchange given as
59. Section 4 Page 8 The power used in each mode can therefore be calculated A normal measurement mode including noise mode or calibration mode needs 19 W a background mode with cover 21 W the ion source heater needs 26 W 4 2 4 RTOF Rosetta ROSINA Reference RO ROS Man 1007 Issue Date Section 3 01 11 06 14 Rev Page 0 9 RTOF has several parameters in order to measure mass spectra of ions or neutrals between two given mass numbers with a high or low mass resolution with adjustable electron emission current and energy It has two channels one optimized for neutrals Storage Source SS one optimized for ions Ortho Source OS with two different data acquisition system Both channels however can also be used vice versa The main operational modes are given below Full control of all sensor modes is within the DPU Data compression is achieved by integration over several spectra and 2D wavelet compression depending on data rate A more complete list can be found in annex D2 Mode Sub mode 28 HV Filam ETS Cover lon GC Activa Typical Used Description Frequence of V ent ETS_ source U ted by time in activation Gas L heater phase S1 Cover initial Off Off Off Both Pyro Off Off S C N A Commi Breaking of vacuum seal Standby opening off firing ssionin gin LEO Safe mode On off off Both open off off S C or
60. a new value for the central mass requires about 0 5 s This includes the time necessary to optimize the detector gain A full high resolution mass spectrum from 12 to 100 amu q can thus be recorded in 79x1 5 120 s A complete low resolution spectrum from 12 to 100 amu q can be acquired in 12x1 5 18 s Telemetry limitations even after data compression may not allow the transmission of all these data Several 1 s spectra with the same settings will then be recorded either in sequence or cyclical Reference RO ROS Man 1009 Rosetta r a Issue Rev Date 01 11 06 ROSINA Section 1 Page 26 and transferred each one to the DPU After statistical analysis spectra recorded with identical settings will be added compressed and transmitted as full mass spectra This procedure optimizes the scientific data return from the instrument 1 2 2 RTOF The reflectron time of flight RTOF spectrometer was designed to complement the DFMS by extending the mass range and increasing the sensitivity of the full instrument package TOF instruments have the inherent advantage that the entire mass spectra are recorded at once without the need of scanning the masses through slits With a storage ion source a source that stores the continuously produced ions until their extraction into the TOF section with high transmission in the TOF section and with a sensitive detector it is possible to record a very large fraction gt 60 of all ions produced in the ion
61. al spread of the ion packets at the location of the detector Unlike other types of spectrometers TOF spectrometers have no limit to the mass range In practice the mass range is limited by the size of Reference RO ROS Man 1009 Rosetta M a Issue Rev ROSINA Date 01 11 06 Section 1 Page 27 the signal accumulation memory The ROSINA RTOF sensor includes two almost independent mass spectrometers in one common structure The spectrometers share the principal ion optical components the reflectron and the hard mirror The ion sources the detectors and the data acquisition systems are separate The electron impact storage ion source is dedicated to analysing neutral particles and the orthogonal extraction ion source is assigned to analyse cometary ions This configuration guarantees high reliability by almost complete redundancy 1 2 2 1 lon Optics The RTOF sensor consists of five main components the ion sources the ion optics the reflector the hard mirror and the detectors Two different channels are used in this spectrometer one in which cometary gas is ionized and stored in an ion source and one that pulses the incoming cometary ions directly onto the TOF path The two ion sources are mechanically very similar with one source optimized for gas measurements and one source optimized for ion measurements Electron impact storage ion source Fig 1 13 Schematic of the RTOF electron impact storage source To a
62. alue 010 NRNAG3A1 2 DFMS Status Hex value 012 NRNAG31D 2 RTOF Mode Hex value 014 NRNAG3A2 2 RTOF Status Hex value 016 NRNAG31E 2 COPS Mode Hex value 018 NRNAG3AS3 2 COPS Status Hex value 020 NRNAG31F 2 Mode Change ID Hex value 022 NRNAG320 1 Active SID Hex value 023 1 Spare 0 6 3 2 6 Sensor Switch On Report EID 44006 Length 17 words Pos RSDB Byte Bit Name Data 000 NRNAG304 2 EID 44006 002 NRNAG322 1 Unit 196 DFMS 200 RTOF 204 COPS 003 1 Flags Hex value 004 NRNAG323 2 Power State 1 Hex value 006 NRNAG324 2 Power State 2 Hex value 008 NRNAG325 2 Power State 3 Hex value 010 NRNAG326 2 Voltage Value 1 V value X 012 NRNAG327 2 Voltage Value 2 V value X 014 NRNAG328 2 Voltage Value 3 V value X 016 NRNAG329 2 Current Value 1 A value X 018 NRNAG32A 2 Current Value 2 A value X 020 NRNAG32B 2 Current Value 3 A value X 022 NRNAG32C 2 Temperature Value 1 C value X Y 024 NRNAG32D 2 Temperature Value 2 C value X Y 026 NRNAG32E 2 Unit Mode Hex value 028 NRNAG3A4 2 Unit Status Hex value 030 NRNAG32F 2 Mode Change ID Hex value 032 NRNAG330 2 Spare 0 Reference RO ROS Man 1007 Rosetta Issue MEC Rev 0 Date 01 11 06 Rosina Section 10 Page 15 6 3 2 7 Progress Report EID
63. ated on the current trapped by the anode Taking into account the range of the electrometer and the X ray limitation the expected pressure range is 10 10 mbar The preliminary results from the laboratory prototype indicate a sensitivity of 3 mbar for nitrogen 1 2 3 2 The ram gauge A spherical cavity 60 mm diameter with a 6 mm aperture facing the comet stands on a hollow boom A screen prevents the gas from directly impinging in the boom where the density is measured Fig 25 The configuration allows the gas to be isotropised and thermalised to the wall temperature before it reaches the ionisation area The conductance of the top aperture is 3 4 s 1 for the water at 200K giving an equilibrium time Bermann 1985 of less than 200 ms for the system The real response time of the instrument is driven by the electrometer see below The Reference RO ROS Man 1009 Rosetta Issue 3 Rev 1 ROSINA Date 01 11 06 Section 1 Page 43 density is measured by an extractor type gauge Redhead 1966 which measures lower pressures no X ray limit than a typical Bayard Alpert gauge and shows better reproducibility Indeed the collector is hidden by a shield from the X rays generated by electrons hitting the anode grid The created ions are collected by a 3 element lens like configuration of anode shield reflector The gauge is also based on the extractor geometry and has been modified to accommodate a new source of electrons called micro t
64. ated reflectron or helix reflectron The voltages and thus the electrical fields are defined by a voltage drop over a resistor in the form of a helix applied to the inner surface of a ceramic tube with an inner diameter of 78 mm see Fig 1 13a The potential drop is constant along the helix and complements exactly the helix pitch Therefore the integrated reflectron shows no electrical fringe field zone in close proximity to the cylindrical boundary given by the mechanical structure An ideal electrical field for the grid free reflectron is generated in the entire inner volume of the structure The total resistance over the helix is designed to be about 10 Q The resistance has to be high to keep the power consumption of the HV supply low but also it has to be low enough that absorbed charges won t change the potential distribution in a noticeable way The minimum resistance is determined from the maximum ion current of about 1 nA extracted from the ion source and the required adjustment accuracy for the reflector voltages of about 1 V The resistor helix is painted in a specially developed procedure at the inner surface of a ceramic tube and afterward is subjected to a sintering process Manufacturing and processing of the integrated reflectron was performed at GVE EMPA in Z rich Switzerland The helix consists of two segments where the length of the retarding segment is half the length of the repelling segment but the voltage drop over the reta
65. channel The signal bandwidth is about 800MHz to record with minimal signal distortion Both inputs are terminated to 50Q and are AC coupled The inputs are protected to 1 5 V The system must be enabled by the DPU command to start acquisition The data acquisition sequence then is started with the internal generated start signal going to the ion or to the neutral extraction pulser There is the option to run the unit in a half synchronized way with an external trigger Instead of starting the system periodically by the internally generated extraction clock the circuitry waits for the external trigger from ETS L to get started A jitter of approx 32ns relative to the external trigger might occur to get the ETS internal state machine synchronized For testing and stimulating the electronics a stimulator is available that generates an analog signal 1 s 255 ns width Amplitude and width are programmable with 8bit The stimulated signal TOF after an extraction is programmable with 13 bit 32 ns resolution An 8 bit conversion takes 2 5 clock cycles at 50 MHz The ADC units are designed for asynchronous operation to save power Each unit contains an S amp H circuit and the ADC as well as the control logic The dead time between two trigger events Reference RO ROS Man 1009 Rosetta Issue 3 Rev 1 ROSINA Date 01 11 06 Section 1 Page 39 generated from an incoming waveform is 7 Clock cycles 224 ns For the case that a time gap free
66. chieve high sensitivity it is necessary to produce ions continuously to store the formed ions for a certain time and to extract them at regular intervals into the TOF analyzer This is done by the electron impact storage ion source which is shown in Reference RO ROS Man 1009 Rosetta M za Issue Rev ROSINA Date 01 11 06 Section 1 Page 28 the schematic illustration of Figure 1 13 The ion source has a rotational symmetry with the exception of the filament repeller assemblies The section plane shown in fig 1 13 is representative for the three dimensional model The ion source contains a double filament assembly for redundancy reasons Only one filament is active at a time and it emits electrons which are accelerated to energies of up to 70eV The electron beam can be guided through the extraction zone using the two repeller electrodes rep A and rep B The inactive filament repeller assembly located on the opposite side of the extraction zone is used as an electron trap to monitor the electron emission A constant number of passing electrons ensure a constant ion production The continuous electron beam ionises gas atoms in the region between the back plane and the extraction grid The ions are kept in the potential depression generated by the space charge of the electron beam For a nominal repetition rate of 10 kHz the continuously created ions have to be stored for 100 us the applied extraction pulse lasts for 1 us The appl
67. cted main share of variables and constants in SRAM SSCDSD and configuration parameters in additional EEPROM error code protected by S W Reference RO ROS Man 1009 Rosetta r Issue Rev ROSINA Date 01 11 06 Section 3 Page 37 EEPROM 128k8 Non volatile Parameters PROM 8K8 MO Volatile mA du Ro ADI COMO CERA Deo do ae oe di Bootstrap Kernel At Bootstrap Kernel At EEPROM 256k48 Boot Loader Power U Operating System System Boot Telemetry Handling Instrument Control Operating System Telecommand Handling Variables Instrument Control J Kernel Program i Program Variables i Refresh Patch 2 3 1 2 Telemetry Telecommand Fig 2 8 1 1 3 Memory Configuration Autonomy Concept Due to the long signal turn around times of ROSETTA and the non availability of a downlink in certain circumstances ROSINA will be capable of autonomous operations in various circumstances One example is the asteroid flyby where we are aware that it might be possible to have no up or downlink available The concept of autonomous experiment monitoring consists of three steps as shown in figure 2 8 1 2 1 e Subsystem individual control Commands for the electronics of the subsystem will be forwarded and the execution will be checked e H K collection and monitoring Monitors the housekeeping information of the subsystems on a regular basis Takes pre programme
68. ctrical qualification model of DFMS 1 2 1 4 Electronics The ROSINA DFMS electronics described here controls provides power and controls the cover mechanism ion source and gas calibration unit all elements of the ion optics and the detectors All control is provided through an interface with the ROSINA DPU The ROSINA DPU does actual commanding and acquiring housekeeping and science data so that the DFMS electronics is not required to store data or commands An overall block diagram is given in fig 1 6 A cover that once the vacuum seal is broken after launch can be open and closed and placed in intermediate positions protects the ion source This capability is required to protect the instrument from contamination for example from very high pressures near the comet and it provides a shutter which can be partially closed blocking the cometary ion and neutral influx This second purpose will allow in flight calibration using the calibration unit and also allow determination of the rest gas inside the spectrometer during the comet encounter The cover motor and the ion source are on spacecraft ground potential The motor is controlled by a pre programmed actel chip which provides the capability to ramp Reference RO ROS Man 1009 Rosetta Issue 3 Rev 1 Date 01 11 06 ROSINA Section 1 Page 20 up the cover motor current at any rate desired maintain a constant current input to the motor and ramp down the cover motor current at
69. d High Origins of Comets Sensitivity Mass Spectra Origins of organic material in comets Heliocentric temporal dependence Onset of cometary activity composition changes in the coma Cometocentric dependence Coma chemistry gas dust interaction Causes of cometary activity Detailed mapping of active and Composition of the Nucleus quiescent regions compositional differences within the nucleus COPS Neutral Pressures Velocities Coma gas dust dynamics Temperatures A complete understanding of the dust gas interaction will require collaboration between ROSINA and the dust investigation The comet produces approximately equal concentrations of gas and dust and there is a strong indication that this combination is responsible for extended sources such as CO in comet Halley Extended observations of the comet by both ROSINA and the dust experiments will be exploited in a search for other extended gas sources and a complete characterization of the known extended sources and their origin within the dusty atmosphere Similarly an understanding of the gas plasma interaction will require collaboration between ROSINA and the plasma experiment Basic quantities such as the gas production rate of the comet obtained from ROSINA will be important elements in the understanding of the plasma observations Likewise the plasma flow velocity the electron temperature and the magnetic field will be important quantities for determining and checking t
70. d automatic reactions to avoid potential sensor damage e Command Telemetry Global long term monitoring and failure reactions as ground operations A list of all HK which are monitored by the DPU of their ranges and of the actions taken if these ranges are exceeded is given in annex D4 HK monitoring The measurement sequences of ROSINA are very flexible and can be adapted to the various mission phases to the available bit rate and power and to very different scientific goals Both mass spectrometers have a large number of possible modes which however differ very little in the power consumption A measurement sequence consists of different modes in sequence background inflight calibration optimisation scientific measurements which will be commanded by the DPU in a preset way As especially the optimisation routine can Reference RO ROS Man 1009 Rosetta Issue Rev 0 ROSINA Date 01 11 06 A Section 3 Page 38 vary in time function of temperature gradient etc the time when mode changes occur cannot be precisely predicted A measurement sequence can last from a few minutes up to days and can be repeated indefinitely For a detailed explanation of instrument modes see annexes D1 D3 Command Interpreter Sensors Control x o 2 e o Put 4 xe e I Collection Telemetry amp Service DPU H W Monitoring Control Fig 2 8 1 2 1 Experiment Monitoring 2 3 1 3 Software Maintena
71. d ionospheres of comets as well as the temperature and bulk velocity of the gas and the homogenous and inhomogeneous reactions of gas and ions in the dusty cometary atmosphere and ionosphere In determining the composition of the atmospheres and ionospheres of comets the following prime scientific objectives also defined by the Rosetta Science Definition Team will be achieved Determination of the global molecular elemental and isotopic composition and the physical chemical and morphological character of the cometary nucleus Determination of the processes by which the dusty cometary atmosphere and ionosphere are formed and to characterize their dynamics as a function of time heliocentric and cometocentric position Investigation of the origin of comets the relationship between cometary and interstellar material and the implications for the origin of the solar system Investigation of possible asteroid outgassing and establish what relationships exist between comets and asteroids To accomplish these very demanding objectives ROSINA must have unprecedented capabilities including Reference RO ROS Man 1009 Rosetta Issue 3 Rev 1 ROSINA Date 01 11 06 Section 1 Page 8 1 Very wide mass range from 1 amu Hydrogen to gt 300 amu organic molecules 2 Very high mass resolution ability to resolve CO from Nz and C from CH 3 Very wide dynamic range and high sensitivity to accommodate very large difference
72. d to split the collector of the imaging detector into two halves along the focal plane axis and thus to use an ASIC circuit with two separate and redundant collectors and electronics thus ensuring a total redundancy of this critical part of the instrument Description of the detector package The detector package is shown in figure 1 3 which represents a section along the plane of symmetry The development of this package was the result of a joint effort by teams from BIRA IASB CETP IMEC for the ASIC electronics realization and LMATC for part of the electronics The broken red line indicates the location of the theoretical focal plane of the spectrometer The main imaging detector is located in the center of the detector package as indicated by the position of the MCP We anticipate using a stack of 2 Chevron MCP s with a rectangular form adapted to the geometry of the focal plane a pore size of either 6 or 12u and a total gain at saturation of about 10 In order to keep the maximum resolution the MCP front face should have been located exactly coincident with the focal plane However the energy of the ions impinging on the front face of the MCP must be larger than about 0 5 keV in order to allow for a large enough MCP detection efficiency A maximum of efficiency for ion species that are expected in the comet atmosphere is reached at about 3 keV For this reason the front face of the MCP is polarized at a negative voltage of 3 kV when the float
73. dently from the others The DPU controls all the housekeeping values and issues commands to the sensors autonomously or by TC It collects the science data does on board data evaluation and compression and sends the HK and the science data to the S C The software is divided into several levels In the top level predefined sequences can be commanded by TC They are based on predefined instrument modes which are executed in sequence in order to achieve a given scientific goal The modes themselves consist of predefined parameter settings and sub functions There are a few restrictions to the operation of ROSINA COPS has to be monitoring the ambient pressure whenever RTOF or DFMS are turned on The pressure has to be below 10 mbar in order to operate RTOF or DFMS COPS will switch automatically off whenever the pressure rises above 10 mbar On ground RTOF and DFMS can only be operated whenever a vacuum pump is connected to the sensor and the pressure is below 10 COPS can only be operated in a vacuum chamber with a pressure below 10 mbar Reference RO ROS Man 1009 Rosetta r Issue Rev ROSINA Date 01 11 06 Section 3 Page 47 3 1 2 General The ROSINA FM instrument is a delicate instrument requiring great precautions with respect to handling cleanliness and operation Whereas the DPU is a normal electronics box containing neither high voltages nor pyros and can therefore be handled by standard rules all three sens
74. detector must provide an image of the focal plane with a resolution corresponding to the highest mass resolving capability of the spectrometer This corresponds to an equivalent pixel size of 25u along the direction of the focal plane over a length of about 1 25 cm The overall dynamical range of the detector has to comply with the anticipated extremely large variations of ion fluxes at the exit of the spectrometer These arise predominantly from the variations of nucleus outgassing as a function of comet activity from the large differences in density between major constituents such as water and minor constituents or isotopes and also from the varying sensitivity of the instrument as a function of its mode of operation ion and neutral mode low or high mass resolution etc The necessary overall dynamical range has been estimated to about 10 orders of magnitude The instantaneous dynamical range has to cope with the temporal variations of the cometary gas during a single measurement and with the differences in ion fluxes impinging at various locations on the detector front face for the whole range of masses simultaneously measured Owing to the expected quite slow temporal variations of the cometary atmosphere in the vicinity of the orbiter and to the fast measuring rate allowed by the detector which can be made as fast as 100 measurements per second the second constraint is more important From the anticipated chemical and isotopic compositi
75. e 25V 32V Inrush current after 8msec 1A usec 8msec gt 0 8A Bus Isolation 28V amp 28V Ret SignalGround gt 1MOhm gt 5nF Switch on off Z35V Zenerdiode as freewheeling Noise Emission Suseptibility EMC Requirements and Suseptibility Requirements are kept by the provision of Common Mode Noise and Conducted Noise Filtering Rosetta Reference RO ROS Man 1009 Issue 3 Rev 0 Date 01 11 06 ROSINA Section 3 Page 19 DC DC Converter l Primary Secondary Signal Ground Sync 65 5kHz j i Sync Free 40kHz for i P lt 1 5Watt i Power Ground Structure Ground Saw Pwr On 28V Mai Db Pwr On_ 28V Red Main Relay FET amp Soft Start Circuit 28V Main_Re 28V Red Ret C 50n S C tructure Gni Fig 2 18 COPS Power Switching Block Diagram COPS Interface Data Sheet fe Maximum Input Current 7W 28V 0 25A Switch on Inrush lt 1A usec Input Voltage 25V 32V Inrush current after 8msec 1A usec 8msec gt 0 8A Bus Isolation 28V amp 28V Ret SignalGround gt 1MOhm gt 5nF Noise Emission Suseptibility EMC Requirements and Suseptibility Requirements will be kept by the provision of Common Mode Noise and Conducted Noise Filtering 28V 0 22A 112 Ohm 2 2 4 2 2 4 1 Reference RO ROS Man 1009 Rosetta r Issue Rev ROSINA Date 01 11 06 Section 3 Page 20 PYROTECHNIC INT
76. e a breakdown of the program execution which is monitored by a watchdog circuit Single event latch up SEL induced overcurrents will be detected by current monitoring 9 current monitors protect each of both DPU branches If an overcurrent occurs the DPU branch will be de energized by a fast us current breaker 1 2 4 2 DPU Software Design The DPU S W is based on the real time multitasking operating system Virtuoso Eonic Systems that provides 1 preemptive event driven scheduling 2 dynamically prioritized tasks 3 synchronization and communication facilities semaphores mailboxes queues timers 4 dynamic memory management and 5 handling of multilevel device interrupts All S W tasks are grouped in a layer model with 6 layers 5 Scientific Software 4 Operation Control command execution emergency mode In flight calibration etc 3S Service Functions command interpreter housekeeping collection data compression etc 3 Element Functions detector on off data acquisition handling etc 2 Subelement Functions direct control of subelements and 1 Low Level S W H W driver I O control 1 2 4 3 Electrical Ground Support Equipment EGSE S C Data amp C id A 512k x SRAM DFMS Data DEMS I F DFMS I F Cmd amp HK Driver HW FPGA les 230k x8 EEPROM gt
77. e hard mirror 1 2 2 4 Electronics The entire electronics of the RTOF instrument consists of the following 10 functional blocks 1 Main Controller MC The MC handles the commands coming from the DPU and the Data and Housekeeping going to the DPU It contains the following blocks Motor Driver for the cover Housekeeping unit Power switching unit Filament emission Gas calibration unit Hard mirror pulser ETS latch up disable Reference RO ROS Man 1009 Rosetta 3 4 Issue Rev ROSINA Date 01 11 06 Section 1 Page 37 Fig 1 20 RTOF electrical qualification model Differential serial interface to the DPU Gateway switches for ETS ETS Light Digital Board 2 Equivalent Time Sampler ETS Data acquisition system for fast and non repetitive signal pulses 3 Equivalent Time Sampler Light ETS L Data acquisition system for fast non repetitive single ion pulses 4 High Voltage Board 1 HV 1 Supply for Extraction Hard Mirror Acceleration Lens Reflector and drift voltages 5 High Voltage Board 2 HV 2 Supply for extraction grid detectors and hard mirror pulser voltages 6 Low Voltage Power Supply LVPS Supply for analog 5V dig 5V 8V analog 15V 24V 35V 55V Reference RO ROS Man 1009 Rosetta r Issue Rev ROSINA Date 01 11 06 Section 1 Page 38 7 Digital Board for power supplies Back plane entrance lens and entrance supplies controller for the supplies H
78. e integrated reflectron whereas the ceramic tube of the integrated reflectron is part of the entire RTOF vacuum enclosure The sensor head mounted at the opposite end of the drift tube will carry the storage ion source and the orthogonal acceleration ion source with the respective detector as well as the commonly used hard mirror The ion sources and the detectors will be fixed on the sensor head according to the experimentally determined tilt angles with respect to the ion optical axis of the system The whole primary structure can be baked out to 150 C and the ion sources to 300 C The sensor will be launched under vacuum conditions and the cover only opened in space to minimize contamination Reference RO ROS Man 1009 Rosetta 3 4 Issue Rev ROSINA Date 01 11 06 Section 1 Page 36 Gas Calibration Unit Electron impect lon Source Extraction Pulser lon Attraction Grid lon Flight Tube Support Bracket with HY Insatio ns Cover Opening Mecharisn View without Orthogonal Extraction lon Source Electron Impact Storage len Source High Voltage Protection Fol Orthogonal Source Protection Srield Storage Source Protection Shield LaL RTOF has an identical in flight calibration system as the DFMS sensor see above except that in this case each ion sources has its own gas line The secondary structure is made from aluminum and houses eight electronics board and the three pulsers two for the ion sources one for th
79. e turn around time in the extraction region The turn around time is the time necessary to reverse the direction of an ion with its initial velocity typical 0 1 eV directed against the extraction direction of the ions by the extraction field in the source Orthogonal extraction ion source The concept of the orthogonal extraction ion source was initially introduced for cluster ion measurements to provide an improvement to the limited resolution of conventional TOF instruments of the Wiley McLaren type 1955 The orthogonal extraction ion source allows for easy coupling of a TOF MS with a wide range of external continuous or pulsed ion sources In the case of the RTOF sensor the orthogonal extraction ion source is dedicated to the measurement of the ionised component of the cometary atmosphere The orthogonal extraction ion source uses off axis created ions ions either coming from an external ion source the comet in our case or using ions formed by electron impact ionisation in an off axis electron impact ionisation assembly The orthogonal extraction ion source is shown in the schematic illustration of Figure 1 15 These ions propagate orthogonally to the principal ion optical axis of the TOF system with an initial energy of about 10 eV When passing through the extraction region of the orthogonal extraction ion source part of these ions are extracted by a fast voltage pulse on the extraction grid and are further accelerated onto the drift path of
80. e two sensor units DFMS and RTOF Cover Detonator 1llliCover Detonator 2 Cover Fail Safe Actuato DFMS DFMS DFMS 22 DBMA 25P P22 DBMA 25S Safety Connector Structure Fig 2 19 Pyrotechnical I F of the S C to the DFMS sensor Cover Detonator 1i Cover Detonator 2 Cover Fail Safe Actuato RToF RToF RToF J32 DBMA 25P P32 DBMA 25S Safety Connector Structure Fig 2 20 Pyrotechnical I F of the S C to the RTOF sensor Reference RO ROS Man 1009 Rosetta r Issue Rev ROSINA Date 01 11 06 Section 3 Page 22 The characterisitics of the Pyrotechnic Initiators are compiled in the following tables Pyrotechnic Initiator for the Cover Separation System PEU Load Interface Specification and Mechanical Characteristics Pyro Type 1 DPWH 30 Detonator Manufacturer Dassault Procurement Specification FICHE E1 02 Electrical Characteristics Bridge Resistance 1 05 0 15 Ohm All Fire Condition 4 A gt 10ms 20msec Current and Pulse Duration No Fire Current 1A 5 min Current and Pulse Duration Insulation Resistance between filaments and EED case before and after Firing gt 100 MOhm Electrostatic Discharge Strength 25 000 V 500 pF 5 KOhm inc Conditions Operating and Non Op Temperature Range 90 C 100 C Storage Temperature Range 10 C 30 C Mechanical Characteristics Mass 14g Maximum mass
81. ed across a high voltage interface to the low voltage power supply in the MEP pack Detector electronics The required very large dynamical range led us to consider for the imaging detector Rosetta Reference RO ROS Man 1009 Issue 3 Rev 1 ROSINA Date 01 11 06 Section 1 Page 23 CEM slit CEM repeller Anode Ch It Floating Detector Pack refere ene GEM Analog current measurement i Faraday cup Digital counter T4 MCP Front 0 to 3 kV DFMS reference level DFS at acceleration 7 reference leve CEM Front 7 voltage voltage FC repeller acceleration 0 to 6 5 kV voltage a sist p o 6 Spacecraft reference level Spacecraft reference level DFMS detector block diagram for MCP CEM and Faraday cup digital word stored in a spectrum accumulation memory The instrument DPU through an opto coupler link ultimately reads out this memory As a consequence of the accelerating voltage applied to the front face of the MCP and of the variable HV polarization between the front and the back faces of the MCP which controls its gain the LEDA is at a floating detector package potential FDP S i FRE ect to the DFMS reference level In order to HN ae d acsi ics RN he Faraday cup and difficulties associated with Tod tronics installed in the detector package the at the same floating voltage as the LEDA All or
82. eference RO ROS Man 1009 Rosetta r Issue Rev ROSINA Date 01 11 06 Section 3 Page 36 e DPU H W control Latchup handling memory error handling memory scrubbing watchdog handling clock frequency management e Data acquisition Fetching of scientific data from all three sensors e Spectra integration Preprocessing and evaluation of scientific data e Data compression Processing of scientific data from all three sensors e Data formatting Combines science HK and synchronisation information to experimental data blocks according to the available telemetry capacity e Telemetry service Provision of the experimental data blocks to the S C e Housekeeping collection H Collection and pre formatting of housekeeping data from all sub units e H K Monitoring All H K information from the sub units can be monitored on a regular basis Pre programmed automatic reactions can be taken to avoid potential sensor damage e In flight calibration Automatic calibration of the sensors and acquisition systems during flight The S W is located in distinct memory areas Fig 2 8 1 1 3 A boot strap kernel providing a boot loader and the basic telemetry telecommand handling for S W update in PROM complete program code and additional patch code in EEPROM error code protected coding decoding and correction by S W executable copy of EEPROM code in fast SRAM Single Symbol Correction Double Symbol Detection SSCDSD prote
83. er firing should be finished by the time the covers are opened for the first time appr 70 days after launch Before cover opening the ambient pressure as recorded by COPS MICROTIPS OR FILAMENT has to be below 10 mbar After cover opening enough time has to elapse days to allow an outgassing of the sensors before power is turned on To accelerate outgassing of the DFMS ion source the ion source heater will be used All three sensors should be checked out separately For this operation near real time commanding and science data are needed Deatails are given in the flight operations procedure annex B 3 2 3 Instrument check out and inflight calibration A detailed check out of the entire instrument will be made during the initial turn on in the cometary neighborhood similar to the first commissioning An inflight calibration program will be activated every 1 2 weeks Both mass spectrometers are equipped with gas tanks containing a gas mixture He CO2 and Kr for RTOF Ne CO and Xe for DFMS A defined pressure inside the ion sources is built up with a regulated gas valve The instrument response is then measured The program will encompass internal calibration of the different ion detectors of the DFMS and RTOF and ion source and analysis operation modes as well as an absolute calibration of the overall sensitivity using the calibrated gas release system This mode will run automatically from the DPU upon command from ground or upon inter
84. esererssrsererressesrresressrteresrenserseesres 16 2 2 4 PYROTECHNIC INTERFACE REQUIREMENTS eene 20 2 2 92 Thermal Inst ESOS on eet s dcin ee iaaa e Aaa muss Rad aSa aS 24 2 2 6 OBDH INTERFACE REQUIREMENTS 5c epn sede deve neue dese ve Ce yeu Rue 27 PA SOMWATE e N 33 2 3 1 Software Concept and Functional Requirements eese 33 2 4 nr c 41 2 4 1 IVEASS aid PODES cata SorsdassdSsansasasedeatnendandaGatsdnetl o uM ossa cedet R adds bbs qaa MEER 41 242 Data Rates DMS Resource Requirements eene 41 2 4 3 Therm l B d asa be sens cen 44 3 Experiment Operations 46 3 1 ROSINA FM Operations Manual esesoesosoesescscsossoscesescscsocsosossesescsocscscesssese 46 3 1 1 Operating eli T 46 3 1 2 G nerale CROP ere nee REN NOCT E A rr 47 3 1 3 Safety asp cts HV M 47 3 1 4 Cleanliness Purging PUEIDIDE sorore rattet re hot Sohle sani tocca erii br aan ia dd 48 3 1 5 M tna AW eT nie a E RE EE EEE REER 49 3 1 6 arra enee a a a E a E 49 3 2 Operations PUA cescccscsceaiciuciedscacscoussicecdsonaescaesstecscancquccvasedsecascencasetecdaqatsnsseabeonaveasess 50 3 2 1 Gro nd Test Plat uude b ERR id ar id dae edad a R REER 50 3 2 2 Commissioning Phase near Earth LEO esee 50 3 2 3 Instrument check out and inflight calib
85. etely That could mean that the extraction rate is smaller than programmed For this reason there are two 24 bit counters implemented to count the initial extraction rate and the actual rate Another counter is for the external trigger source These data are transferred to the DPU between the header block and the accumulated data Equivalent Time Sampler Light This board has the same feature as the ETS except that there are no ADC s It therefore works as a time to digital converter TDC system As long as there are no Rosetta ROSINA 8 a o a intensity 1 o counts 0 99 1 00 1 01 1 02 2 00 2 01 2 02 mass amu intensity counts N 8 3 01 3 02 3 03 3 99 4 00 4 01 mass amu mass amu Fig 1 22 Mass spectrum for a mixture of helium and hydrogen Q 1996 UoB Scherer dynamic range opjidrange_G eps Reference RO ROS Man 1009 Issue 3 Rev 1 Date 01 11 06 Section 1 Page 40 multiple simultaneous ion impacts on the detector this is sufficient For the orthogonal source where the intensity is much less than for the storage source this is sufficient Gas Calibration Unit GCU The GCU Gas Calibration Unit is designed as a sub component of the RTOF Instrument It will be used as a stimulating device by the injection of a gas mixture noble gases into the Gas Source and lon Source if selected By source stimulating with noble gasses with well known masses TOF para
86. etween the single and triple reflection mode is done with the reflector lens by a change of the lens voltage The single reflection mode requires a typical reflectron lens voltage of about 2200 V below the drift potential whereas the triple reflection mode operates with a reflector lens voltage of 4650 V below the drift potential There is no mechanical tilt element to be operated in flight nor are there electrical deflection plates which could redirect the ion beam between the single and triple reflection mode The gas and ion channel must always operate in the same mode because of the commonly used reflectron structure and the differing voltage set for the single and triple reflection mode Gas mode The gas mode is assigned to the electron impact storage ion source and analyzes initially neutral particles During the storage period up to 10 ions will be accumulated in the ion source and released by an extraction pulse firing into the TOF analyzer section The data acquisition system has to be able to record the detector signal proportional to the number of incoming ions The data acquisition system has to be able to record the detector signal proportional to the number of incoming ions In flight the gas mode signal is processed with the Equivalent Time Sampling ETS which is described below lon mode The ion mode is performed with the orthogonal extraction ion source dedicated to analyze cometary ions Moreover the orthogonal extracti
87. eues timers dynamic memory management and 5 handling of multilevel device interrupts Fast interrupt routines Low Level S W serve as the front line to the H W the data processing is done by dedicated S W tasks The S W tasks including the operating system will be represented by 6 levels from bottom level 1 to top level 5 Figure 2 8 1 1 1 shows the structure of the lowest two levels 0 and 1 and the structure of the application S W located in level 2 and up Level 4 Command Execution Emergency Handling In flight Calibration H K Collection Command Level 3S Interpreter Data Compression Level 3 Element Functions Data Acquisition and Handling Sensor S C and Level 2 Subelement Functions DPU H W Service MICRO Kernel 1 0 Ctrl Level 1 Virtuoso NANOKernel T O functions Low Level S W Level 0 DSP H W Dedicated H W Hardware description Fig 2 8 1 1 1 DPU Software Levels e Level 5 Scientific Software Reference RO ROS Man 1009 Rosetta r Issue Rev ROSINA Date 01 11 06 Section 3 Page 34 This level defines algorithms for automatic measurement by using the operation modes of each of the three experiments e g search for organics deuterium search Level 4 Operation Control Level 4 provides procedures for each operation mode of the three ROSINA units DFMS RTOF COPS These procedures implement the operation modes as defined by the scientists Procedures for In f
88. gh 2 ETS FIFO Threshold 0 Low 1 High 1 ETS Latchup Enabled 1 Off 0 On 0 ETS Latchup Detected 0 Off 1 On 140 ETS Status 2 Reference RO ROS Man 1007 Rosetta Issue 3 0 d Rev Date 01 11 06 Rosina Section 10 Page 9 7 ETS ADC Power Status 0 Off 1 On 6 ETS ADC Threshold 0 High 1 Low 5 4 ETS ML Mode 0 Adapt 1 ML31 2 ML63 3 ML255 3 0 Spare ETS Threshold Level 0 5 5mV 12 8mV 2 12mV 3 16 7mV 4 20mV 5 23 4mV 6 26 6mV 7 33 4mV 142 2 ETS Extraction Delay t Value 26 5ns 158 5 144 2 ETS ToF t Value 26 5ns 26 5 146 2 ETS Cal Start Delay t Value 26 5ns 26 5 141 148 2 ETS Cal Pulse Height V value 2 314 mV 4 928 mV 150 2 ETS Cal Pulse Width t value 1 2615 ns 51 728 ns 152 2 MC FEC PVCC V U value 1e 3 0 0156 V 154 2 MC FEC MVCC V U value 7e 4 0 008 V 156 2 MC FEC PVDD V U value 3 1e 3 0 0497 V 158 2 MC FEC MVDD V U value 2 8e 3 0 1508 V 160 2 MC GEX PVCC V value 0 001 0 0058 162 2 MC GEX VD V value 0 0083 0 0417 V 164 2 MC IEX PVCC V value 0 001 0 0058 166 2 MC IEX VD V value 0 0083 0 0417 V 168 2 MC HM PVCA V value 0 001 0 0038 170 2 MC HM VD V value 0 0083 0 0478 172 2 MC ETSL PVCC V value 0
89. h gilded tracks in eight interlaced groups of Rosetta Reference RO ROS Man 1009 Issue 3 Rev 1 Date 01 11 06 ROSINA Section 1 Page 44 vertical lines This arrangement gives eight independent emitters that can be addressed separately either sequentially or jointly Each group can deliver 1 mA at 70 V extraction voltage Fig 27 For very low pressures several groups emit together For higher pressures a pulsed mode or scanning mode is adopted Possible redundancy is obvious and an improved resistive layer should emphasise this advantage An advantage of this emitter is that no heat is generated unlike a filament This is important because the gas temperature is not modified Such an emitter is of particular interest for space applications because of its low power consumption 1 2 3 4 Mechanical Structure Electronics Fig 1 26 COPS EQM Reference RO ROS Man 1009 Rosetta r P Issue Rev ROSINA Date 01 11 06 Section 1 Page 45 The nude and ram gauges are each mounted at the end of a boom Fig 28 to avoid direct gas reflections from the payload platform or the nearest instruments For mechanical stiffness and accommodation for launch the booms are limited to lengths of 25 cm In order to preserve cleanliness the gauges will be continuously purged with nitrogen until launch The three electronic boards are housed in a 165x140x75 mm box that also supports the booms The instrument mass is 1 5 kg The d
90. he location of the contact surface near the comet when it is close to the sun Low energy ion flow inside the contact surface is significantly affected by the presence of this barrier and its location will be important in interpreting the ROSINA ion observations A complete understanding of the causes of cometary activity and compositional differences within the nucleus will require collaboration between ROSINA and Reference RO ROS Man 1009 Rosetta r Issue Rev Date 01 11 06 ROSINA Section 1 Page 12 several orbiter and lander investigations One important aspect to be investigated is the composition of volatiles measured by ROSINA and the composition of non volatiles surface components measured by the lander A cross check of the relative composition of these two cometary components is required to completely account for cometary composition and to understand how or if the cometary coma differs from the evacuated material in the mantle This combination of orbiter and lander composition measurements will be key in resolving the question of the ultimate fate of comets in the solar system Causes of cometary activity and compositional differences within the nucleus will also be investigated through a collaboration between ROSINA and other orbiter investigations One important collaboration will be the coordinated mapping of cometary active regions with ROSINA the camera investigations and the dust investigation Possible compos
91. he ram gauge in case of a nude gauge failure Full control of all sensor modes is within the DPU A more complete list can be found in annex D3 Mode Sub mode 28V Filament Microtip Activated Typical Used in Description Frequence S by time phase of activation G5 Standby Safe mode On Off off DPU N A All phases 5M Monitoring low On off on DPU 10s All phases Monitoring of pressure Microtips power 5 Filament Monitoring On On off DPU 10s All phases Monitoring of pressure 5 Full Measurement On On on DPU 10s All phases Measurement of gas parameters T v p 4 2 5 1 Power Consumption The power consumption of COPS is composed of two main components namely of the standby power low voltage converters and main controller and of the filament The power used by the microtips can be neglected The following table shows the two contributions Reference RO ROS Man 1007 Rosetta Issue 3 Rev 0 Date 01 11 06 ROSINA Section 4 Page 14 __ Power W Standby mode LVPS 4 5 MC e Notrun in parallel to analyzer part filament or cover motor The power used in each mode can therefore be calculated A normal measurement mode with microtips needs 4 5 W with the filament 6 5 W Reference RO ROS Man 1007 Rosetta r Issue Rev Rosina Date 01 11 06 Section 6 Page 1 5 Operational procedures 5 1 On board control procedures 5 1 1 On Board Co
92. heater and calibration MEP C mechanism control controls cover and also contains the CEM detector high voltage MEP D CEM processing electronics for the CEM data MEP E Acceleration bias supply providing the 6500 V floating potential for the ion optics MEP F Filament bias supply providing the ion source filament potential MEP G lon source controller controlling the potentials in the ion source that accelerate and focus the ions MEP H Transfer optics high voltage bias for the transfer optics MEP K Transfer optics pre regulator for the transfer optics high voltage power supplies MEP M Motherboard which connects MEP A through K Residing below the baseplate MEP N Low voltage power supply which interfaces with the spacecraft power provided through the DPU The Acceleration Supply Pack consists of 5 electronics boards This pack floats at the VACCEL potential and the pack is electrically isolated from the base plate by high voltage standoffs Thermal dissipation is accomplished through these standoffs as well as radiatively from the sides and ends of the pack ASP A Low high voltage generating voltage for the FDP package which floats at a potential above the ASP package ASP B Digital Control for the ASP package including the ESA ASP C ESA high voltage providing the 18 bit ESA voltagesASP D Medium high voltage providing voltages for the optical elements after the ESA including the zoom optics ASP E Interface and power for the ASP pack connect
93. herefore reduction of the scientific data is a basic task It is performed in two levels 1 H W based integration within the sensor electronics and 2 subsequent S W processing as i spectrum windowing ii averaging resulting in degraded mass and or time resolution iii loss less compression modified Rice PSI14 and task specific lossy compression All S W processing is done in the DPU by a 32 bit digital signal processor DSP TSC21020F with a large amount of fast SRAM memory 3 Mbytes program 8 Mbytes data memory Fig 1 19 shows an overall block diagram of the DPU All DPU functions are duplicated and organized into two independent cold redundant branches except 1 the three sensor interfaces and 2 the hard core for selection of the active branch Cross strapping is applied between each sensor interface and each DPU branch and between each DPU power converter and each DPU branch The program and data memory is H W protected against singe event upsets SEUs and permanent device failures For adaptation to 8 bit wide memory devices a Single 8 bit Symbol Error Correction Double 8 bit Symbol Error Detection 48 72 Reed Solomon Code is used Periodic scrubbing of the memories acts against Rosetta Reference RO ROS Man 1009 Issue 3 Rev 1 Date 01 11 06 ROSINA Section 1 Page 46 accumulation of non correctable double symbol errors Remaining SEU induced undetected errors gt 2 symbol memory errors can produc
94. higher mass resolution of the ion channel Reference RO ROS Man 1009 Rosetta M g Issue Rev Date 01 11 06 ROSINA Section 1 Page 30 Fig 1 16 Integrated reflectron than the gas channel Reflectron The reflectron represents a key ion optical element of the RTOF sensor necessary to achieve the desired scientific performance Basically the reflectron is an ion optical mirror at the end of a field free drift path to redirect an incoming ion beam by an appropriate choice of repelling electrostatic fields Thus the field free drift path is used twice and therefore the flight path is doubled maintaining the overall geometrical dimensions of the sensor The technical design requirements made it necessary to come up with a completely novel reflectron design shown in a schematic representation in Fig 1 16 Due to the initial energy distribution of the ions and the resulting negative time of flight dispersion the temporal width of an ion packet will increase after the first time focus with increasing distance when moving along the field free drift path In the ion mirror ions with a higher energy penetrate deeper into the repelling field before returning than do lower energetic ions Consequently the faster ions have a longer time of flight through the reflectron than slower ones By careful selection of the electric fields this effect allows to compensate over a wide energy range the negative time of flight dispersion on the field
95. ied extraction voltage is about 350 V This corresponds to an electrical field strength of Es Fig 1 14 Schematic of the RTOF orthogonal extraction source 175 V mm in the ionisation region the distance between the back plane and the extraction grid of 2 mm length as shown in Figure 1 13 The final energy of the extracted ions is obtained after passing two acceleration electrodes An additional electrostatic lens located after the acceleration electrodes is used to form a parallel ion beam of diameter 5 mm at the source exit For the nominal total ion energy of 3 5 keV this extraction voltage results in a maximal energy dispersion of 10 for the Reference RO ROS Man 1009 Rosetta r Issue Rev ROSINA Date 01 11 06 Section 1 Page 29 ions However the time of flight dispersion for an energy dispersion of that magnitude is kept minimal by the use of a second order time focusing TOF system The mass resolution of the RTOF sensor is mainly determined by temporal spread of the ion bunches at the first time focus thus given by the performance of the ion sources The extracted ions are compressed to ion packets of several nanoseconds duration at the time focus plane located approximately 5 cm after the ion source By a suitable choice of the acceleration potentials second order focusing at the first time focus plane is achieved The temporal spread of the ion packet at the first time focus plane is then mostly governed by th
96. igital board controls the link with ROSINA s controlling DPU The second board contains high voltage supply and control for the ram gauge plus two electrometers to measure the ion current of each gauge Each electrometer has three ranges 10 1 100M_ with 1 uF integration capacitor switched by the D U The measured value is 12 bit digitised and the total range is 0 1 pA 1 pA The third board is dedicated to the power supplies for the nude gauge The total nominal consumption is 7 Watt 28 V primary with 2400 mW for the nude gauge and 720 mW for the ram gauge the difference lying in the ram gauge s newer technology The ram gauge boom points toward the comet while the nude gauge boom is parallel to the solar panels Half of COPS will never be exposed to the Sun so half of each boom is sandblasted and the other half is gold plated To avoid strong thermal gradient in the ram gauge it would degrade the measurement half of its boom is sandblasted and the other half is gold plated The electronics box is protected by multi layer insulation 1 2 4 DPU 1 2 4 1 DPU Hardware Design Principal drivers of the DPU design are a optimum use of the allocated telemetry rate b single failure tolerance for all functions serving more than one sensor and c design not dependant on availability of radiation hardened parts The primary data rate of all three detectors exceeds the maximum S C telemetry rate 20 kbps by more than three orders of magnitude T
97. in a vacuum below 10 mbar 7 lon source heaters must not be activated during ground operation except during SPT s see point 1 8 RDP heater DFMS should not be activated except during SPT s see point 1 9 All commands related to the gas calibration units RTOF and DFMS must not be activated except during SPT s 3 1 4 Cleanliness Purging Pumping Extreme care has to be taken with the cleanliness Both mass spectrometers have high voltage isolation parts made out of ceramics Dust or high humidity could lead to HV discharges thus damaging the sensor permanently COPS has to be purged permanently according to the purging procedure RO ROS MAN 1001 In case this purging has to be disrupted shipping of S C etc Cops should not be turned on before the purging has been resumed for at least 24 h The biweekly pump off of RTOF and DFMS should be done by S C personnel according to the pump off procedure RO ROS MAN 1017 Reference RO ROS Man 1009 Rosetta r Issue Rev ROSINA Date 01 11 06 Section 3 Page 49 Before vibration of the S C and before launch the additional commercial valves and the support structures for these valves have to be removed and the flight valves of DFMS and RTOF have to be closed This should be done only under the supervision of UoB personnel 3 1 5 Thermal H W When DFMS is delivered the upper part of the thermal H W is already installed This part should not be removed except by UoB
98. ing variable voltage of the spectrometer which accelerates the ions exiting from the ionizing source is set lower than approximately 0 5 kV when focusing ions with masses larger than 12 amu In order to prevent large perturbations of the ion trajectories which would totally deteriorate the focusing properties of the spectrometer the MCP must be approximately perpendicular to the average ion trajectories and positioned as shown in figure 1 3 Extensive numerical modeling has shown that with such a geometry the global resolution of the instrument is adequate and reaches the specified value Reference RO ROS Man 1009 Rosetta M p Issue Rev ROSINA Date 01 11 06 Section 1 Page 17 Detector Assembly j f Faraday Cup FC lon Source RDP Electronics Sun Shield W ii Tw 1 SS Beta Deflector SS Position Sensitive Detector MCP LEDA Transfer Optics Channeltron CEM Pyro Cord Analyzer Entrance Slits Entrance Slit Switch Electrostatic Analyzer ESA ee S Zoom Quadrupole 2 Zoom Quadrupole 1 Energy Slit Hexapole Zoom Optics NN Sector Magnet MLI Insulation S S MEP Electronics F H Frane ff Motherboard LVPS Board ASP Electronics Electronics FDP Electronics Fig 1 4 3 d engineering model of DFMS The CEM is located at the upper left part of the de
99. ion The optimization process has to be performed autonomously on board the spacecraft by the ROSINA DPU due to a limited command and data transfer rate during the mission in particular during the early phases The gas calibration system releases a defined quantity of a calibration gas a mixture of CO He and Kr from a reservoir being part of the sensor into an ion source For each ion source there is a gas calibration system Detailed mode descriptions can be found in Annex D1 1 2 2 3 Mechanical Structure Similar to the DFMS sensor the RTOF sensor see Fig 1 15 consists of a primary structure containing all ion optical elements within an ultra high vacuum enclosure a cover opening mechanism a secondary structure which houses the electronics The secondary structure also serves as support for the primary structure and an in flight calibration system The primary structure of RTOF is made from titanium and ceramics The sensor head which is electrically at structure ground is isolated electrically from the tube which is at drift potential by a ceramic ring A reclosable cover identical to that of DFMS will protect the sensor head with both ion sources The mechanical structure of the field free drift path works simultaneously as the ultra high vacuum enclosure of the RTOF sensor The potential applied to the drift tube defines the ion energy The rotational symmetric axis of the integrated reflectron will be aligned with the axis of th
100. ips see below The reflector is a hemisphere of 8 mm radius with an apex aperture through which is mounted the collector 0 15 mm diameter 3 mm long The anode 16 mm diameter 19 mm height is at 180 V the shield with an aperture of 3 4 mm diameter at its centre is at 0 V The anode 16 mm diameter 19 mm height is at 180 V The sensitivity of the laboratory prototype is 5 0 mbar for nitrogen and 5 8 mbar for argon between 10 mbar and 10 mbar The gauge should be able to measure down to 10 mbar Tests in the Casymir showed the capability to measure gas speed Micro tip field emitter devices replaced the usual filament 1 2 3 3 The microtips The micro tips of the Spindt type Meyer 1966 Constancias 1998 were introduced into this type of set up by Baptist et al 1996 The micro tips have a resistive layer Levine 1996 to increase emission stability and serve as ballast in case of arc generation This type of micro emitter is the only one in volume production for flat panel displays The manufacturers claim a 20 000 h lifetime much longer than for Fig 1 25 Schematic of the Ham gauge silicon tips and others Tests are evaluating their resistance to the cometary environment The influence of O2 and H2 has already been studied Temple 1999 The emitter is made of more than 1 800 000 tips arrayed in 32x32 pixels representing an emitting area of 14x14 mm Fig 26 The 1024 pixels were grouped by bonding onto a ceramic wit
101. itional differences of the active regions will be measured directly with the narrow field of view part of the ROSINA DFMS In coordination with camera and dust observations these regions will be localized and identified Possible compositional differences of each of these regions will be investigated periodically during the mission to determine if gas from these regions change with increasing cometary activity 1 2 Experiment Overview 1 2 1 DFMS 1 2 1 1 Design Goals The double focusing mass spectrometer is a state of the art high resolution Matauch Herzog mass spectrometer resolution m Am 3000 at 196 peak height with a high dynamic range and a good sensitivity It is based on well proven design concepts which were optimized for mass resolution and dynamic range using modern methods for calculating ion optical properties The main design goals are given in table 1 2 The DFMS has two basic operation modes a gas mode for analyzing cometary gases and an ion mode for measuring cometary ions Switching between the gas and ion modes requires changing only a few potentials in the ion source and suppression of the electron emission that is used to ionize the gas All other operations are identical for the two modes 1 2 1 2 lon Optics lon source The design of the ion source is based on the electron bombardment source used in modern laboratory rare gas mass spectrometers This source combines high sensitivity 10 A mbar with good linearity
102. lectrons arse Two filaments are provided to give redundancy The electron energy can be varied between about 10 and 90 eV At higher electron energies the ionization cross section is maximal and hence the instrument sensitivity optimal At low electron energies the cross section is considerably smaller but there is much less fragmentation of the more complex molecules This can be used to facilitate DETECTOR ii the identification of unknown species The ion source can be operated with electron currents of 2 uA 20 pA or 200 MCP FAR m In Dt i LES pa cH LA E uA to provide three sensitivity levels peee m which differ by a factor of 10 A gas Fig 1 3 Section of the detector package in the pipette delivering calibrated amounts of a plane of symmetry with the associated RDP noble gas mixture into the ionization electronics boards FC E araday rx region will be used for in flight tests and Channeltron For mass scanning it is necessary to vary the energy of the ions To minimize the resulting mass and sensitivity discrimination the ion source is operated at a fixed acceleration potential of 3 kV After the first focus line width typical 150 um a transfer lens is used to accelerate decelerate and focus the ions onto the entrance slit of the analyzer section There are two entrance slits a narrow slit 14 um and a wide slit 200 uum The ion beam can be guided through the narrow slit in the high resolution m
103. lent to the cometary gas flux From the two measurements the expansion velocity can be derived 1 2 3 1 The nude gauge Free electrons emitted from a 17 mm filament at 30 V are accelerated towards a cylindrical anode grid 20 mm diameter 40 mm height at 150 V Inside the anode the thin molybdenum wire 0 15 mm diameter 38 mm long collector is mounted and connected to an electrometer The electrons follow an orbital motion around the collector ionising the gas along their path The measured ion current is directly proportional to the density The density is measured by an extractor type gauge Redhead 1966 which measures lower pressures no X ray limit than a typical Bayard Alpert gauge and shows better reproducibility Indeed the ion collector is hidden by a shield from the X rays generated by electrons hitting the anode grid The created ions are collected thanks to a 3 element electrostatic lens like system anode shield Reflector The anode 20 mm diameter 32 mm height is at 180 V Such configuration prevents also solar UV to reach the collector The gauge is decoupled from the surrounding plasma by an external grid maintained at 12 V spacecraft potential Two filaments will be available for redundancy addressable by a switch Presently made of 3 ReW as flown on Giotto Krankowsky et al 1981 investigations are continuing to improve the filament lifetime in the water rich cometary environment Each filament can emit up to 1 mA regul
104. light calibration and housekeeping monitoring of the sensors are included Level 3S Service Functions The Service Functions level is one of two level 3 sublevels and it implements functions providing software services e g housekeeping collection command interpreter data compression Level 3 Element Functions This level contains basic data acquisition and handling procedures Data acquisition operates all three units DFMS RTOF and COPS in parallel Data formatting processes both H K and science data for the S C telemetry interface Level 2 Sub element Functions Level 2 interfaces to both the RTOS and the low level driver software It consists of service functions to the serial devices of DFMS RTOF and COPS On the spacecraft side telemetry and telecommand interfaces served All software interfaces above this level are hardware independent Level 1 Low Level S W This level interfaces the H W of the DPU with the next higher S W level Level 1 is shared by the RTOS Virtuoso and driver software The RTOS interacts with processor devices The drivers serve dedicated hardware The boot loader program can load program data from the internal EEPROM or from the spacecraft via the telecommand interface Level 0 Hardware Level 0 consists of hardware descriptions like address port and data definitions Sensors The Reference RO ROS Man 1009 Rosetta Issue 3 Rev 0 Date 01 11 06 ROSINA Section 3 Page 35
105. mal high resolution mode mass spectrum of one mass number per measurement Low res On On On open off off DPU N A Special S C mode Normal low resolution mode mass spectrum of eight mass numbers per measurement G2 Ground Normal off Off closed off off DPU N A Ground test Test sequence during ground test if no vacuum Reference RO ROS Man 1007 Rosetta 3 P Issue Rev ROSINA Date 01 11 06 Section 4 Page r4 test pump is attached Special On On On closed off off DPU 2h test Special ground test Test sequence during ground test if vacuum pump is attached Emergency modes TBD 4 2 3 1 Power Consumption The power consumption of DFMS is composed of five main components namely of the standby power low voltage converters and main controller of the analyzer part of the filament of the ion source heater and of the cover motor The power consumption of DFMS is more or less independent of the detector used It does vary neither with low or high resolution nor with the zoom optics The following table shows the five contributions os Power W Ee me PS mode LVPS Analyzer Pat 1 Flamen 2 e Notrun in parallel to analyzer part filament or cover motor Reference RO ROS Man 1007 Rosetta Issue 3 Rev 0 ROSINA Date 01 11 06
106. mbar I s and 10 mbar s The necessary gas beam depends very strong of the injection position of the very end of the additional gas tube which connects the GCU outputs with the sources and the preferred parts intensity to be analyzed Preliminary tests have shown sufficient control range of the mini pirani circuitry to allow source stimulation The GCU can be separately powered by 5V DC and 6V for valve resistor in both gas pipes The output pressure of the individual gas pipes can be controlled in a closed loop circuitry A set value has to be used as control value earned by pre calibration and a converted pressure value is detected via housekeeping by the DPU The DPU software should be able to make comparison between Set value and measured value which leads to the ON OFF command for valve heating The command is send to the Main Controller MC which is able to switch the selected valve resistor ON or OFF About 4 actions per s for the DPU should be enough to get stable gas flow into the Sources Reference RO ROS Man 1009 Rosetta r P Issue Rev ROSINA Date 01 11 06 Section 1 Page 42 1 2 3 COPS The COPS Comet Pressure Sensor consists of two sensors based on the Bayard Alpert ionisation gauge principle The first gauge called the nude gauge will measure the total pressure more exactly the density of the cometary gas The second gauge called the ram gauge will measure the ram pressure equiva
107. meter can be calibrated with regard to mass resolution For the two source stimulation purpose two similar gas pipe structures are designed intensity 10 counts at 19 96 19 98 20 00 20 02 mass amu Fig 1 23 Argon mass peak in a noble gas mixture intensity 10 counts 30 25 15 10 96 UeB Scherer pasmi epy argon G eps 39 92 39 94 39 96 39 98 40 00 mass amu which are individual remote controllable Both gas pipes are hosted in a common housing and carried on one electronic board The two pipes consist out of tank high pressure gauge valve low pressure gauge mini pirani and a capillary tube with a Reference RO ROS Man 1009 Rosetta r a Issue Rev Date 01 11 06 ROSINA Section 1 Page 41 10 ES N 5 1048 8 f i ag 9 On 4 l i b E o 4 blank amplitude B 3 l i E 0V 22 Jo e 80V TE ev a 100V uoi v 200V ux W E s 10 S 10 20 24 28 32 36 40 mass u Fig 1 24 Signal strength for masses 18 to 40 amu e for a noble gas mixture normalized to the signal without blank pulse at the hard mirror standard CAJON vacuum connection at the very end of the unit All sub components have to be fabricated very clean to avoid any gas contamination Leakage rate for all components and mounted pipe with close valve is defined as 10 mbar I s The controllable pressure range of the low pressure gauge can be defined between 10
108. most pristine bodies in the solar system They were created 4 6 billion years ago far away from the sun and have stayed for most of the time of their existence far outside of Pluto They are small enough to have experienced almost no internal heating They therefore present a reservoir of well preserved material from the time of the creation of the solar system They can present clues to the origin of the solar system material and to the processes which led from the solar nebula to the formation of planets Some of the material present in comets can even be traced back to the dark molecular cloud from which our solar system emerged e g Irvine 1999 In contrast to meteorites the other primitive material available for investigations comets have maintained the volatile part of the solar nebula Several interesting questions on the history of the solar system materials can therefore only be answered by studying comets and in particular by studying the composition of the volatile material which is the main goal of the ROSINA instrument Below is a list of measurements still to be made and the associated topics that can benefit from it The list is certainly incomplete and will evolve with time Elemental abundances Nitrogen abundance Physical and chemical conditions during comet formation Noble gases Processing of comets Isotopic abundances D H in heavy organic molecules Origin of material Other isotopes in different molecules C O etc
109. n Modes 24 01 2002 RTOF Instrument Operation Modes 19 12 2001 COPS Instrument Operation Modes 19 12 2005 HK Monitoring 19 04 2002 ROSINA FS SW operations Manual Operations Handbook 19 04 2002 S C DPU Command Packets 19 04 2002 DPU S C Housekeeping Packets 29 07 2002 S C DPU Command description 04 07 2001 DPU S C Event Packets 05 09 2001 ROSINA Mode Change Commands EGSE 04 04 2002 Configuration Status 04 04 2002 User Manual 16 08 2000 EGSE Startup Manual Ro setta Reference RO ROS Man 1009 Issue 3 Rev 1 ROSINA Date 01 11 06 Section 1 Page 6 1 General Description Rosetta Orbiter Spectrometer for lon and Neutral Analysis ROSINA The Rosetta Orbiter Spectrometer for lon and Neutral Analysis ROSINA will answer outstanding questions concerning the main objectives of the Rosetta mission To accomplish the very demanding objectives ROSINA will have unprecedented capabilities including very wide mass range from 1 amu to gt 300 amu very high mass resolution ability to resolve CO from Nz and C from CH very wide dynamic range and high sensitivity the ability to determine cometary gas velocities and temperature The necessities for these capabilities stems from the requirements to monitor the comet during the whole mission through all different phases of activities Two sensors are needed to accomplish the science objectives 1 1 Scientific Objectives Comets are believed to be the
110. n the annexes D1 D3 The science operation consists of a sequence of individual submodes e g Calibration mode followed by background mode followed by gas mode followed by ion mode etc for DFMS and in parallel permanent gas mode in high sensitivity for RTOF Such a sequence can last between a few minutes up to 24 h or more and can be repeated indefinitely Instrument modes The allowed ROSINA instrument mode configurations are specified in the following tabel No Experiment Mode DPU DFMS RTOF COPS Power W Data Rate bits s 0 Instrument off Off off off off 0 0 D1 DPU Booting on off off off 6 0 D2 DPU Standby on off off off 4 5 25 D3 DPU Emergency on off off off 4 5 500 D4 DPU Ground Test on off off off 6 500 D5 DPU S W patch on off off off 6 500 S1 RTOF Standby on off stby Micro 20 5 25 E1 RTOF Emergency on off on Micro 20 5 500 Reference RO ROS Man 1007 Rosetta Issue 3 Rev ROSINA Date 01 11 06 Section 4 Page G1 RTOF ground test on off stby off 25 30k 1L RTOF Low Power on off on Micro 29 1k 1G RTOF Gas on off on Micro 32 1k 1I RTOF ion on off on Micro 29 500 1 HTOF Full Gas and lon on off on Micro 42 1 5k S2 DFMS Standby on stby off Micro 25 25 E2 DFMS Emergency on on off Micro 25 500 G2 DFMS Ground Test on stby off off 25 18k 2 DFMS Normal on on off Micro 28 1k 3 DFMS Narrow on on off Full nude
111. nal command sequence stored in the DPU Reference RO ROS Man 1009 Rosetta r L3 Issue Rev ROSINA Date 01 11 06 Section 3 Page 51 3 2 4 Flight Operations plans Mission Phase Following are the special requirements for the different mission phases 3 2 4 1 Cruise Phase hibernation No checkout maintenance operation is needed for ROSINA during cruise phases hibernation Before going into hibernation the covers of RTOF and DFMS should be closed 3 2 4 2 Check out No passive checkout is foreseen During active checkout the cover mechanisms have to be exercised and the background of the S C will be monitored 3 2 4 3 Planet fly by s ROSINA should be turned on during the Mars flyby to measure the martian exosphere The measurement modes will be similar to the asteroid flyby slf feasible the planet fly by s should be used to heat up the spacecraft experiment platform turn it towards the sun to outgas is so as not to let the dirt get sticky No operation is planned for the earth fly by s 3 2 4 4 Asteroid Fly By s A few days 55 TBC prior to the asteroid fly by s the COPS MICROTIPS OR FILAMENT the RTOF and the DFMS have to be commissioned The filaments of all three sensors need a slow and careful conditioning before the actual fly by based on the same procedures as the initial switch on and the instrument has to perform a thorough measurement of the background outgassing of the spacecraft The data
112. nce 068 2 Sequence Position 1 070 2 Sequence Position 2 072 4 Sequence Parameter 1 076 4 Sequence Parameter 2 080 4 Sequence Parameter 3 084 4 Sequence Parameter 4 088 2 DFMS Spare 1 090 2 DFMS Spare 2 092 2 RTOF Cmd counter Counter 0 65535 094 2 RTOF Cmd Error cnt Counter 0 65535 096 2 RTOF Science counter Counter 0 65535 098 2 RTOF Science Error counter Counter 0 65535 100 2 RTOF S W mode Mode No 102 2 RTOF S W status Hex value 104 2 RTOF Motor Pos 1 106 2 RTOF Motor Pos 2 108 2 RTOF GCU 1 On Time 110 2 RTOF GCU 2 On Time 112 2 RTOF Filament Status 114 2 RTOF Heater Status 116 2 RTOF Last Mode 118 2 RTOF Abort Status 120 2 RTOF Last Scan Mode 122 2 RTOF Last Sequence 124 2 Sequence Position 1 126 2 Sequence Position 2 128 4 Sequence Parameter 1 132 4 Sequence Parameter 2 136 4 Sequence Parameter 3 140 4 Sequence Parameter 4 144 2 RTOF Spare 1 146 2 RTOF Spare 2 148 2 COPS Cmd counter Counter 0 65535 150 2 COPS Cmd Error counter Counter 0 65535 152 2 COPS HK Error counter Counter 0 65535 154 2 COPS S W mode Mode No 156 2 COPS S W status Hex value 158 2 COPS Filament Status 160 2 COPS Microtips Status 162 2 COPS Monitoring Status 2 164 COPS Last Mode Reference RO ROS Man 1007 Rosetta Issue 3 Rev 0 Rosina Date 01 11 06 Section 10 Page 21 166 2 COPS Abort Status 168 2 COPS Spare
113. nce Approach It will be possible to load particular memory areas from ground via telecommand packets as described in EID A chapter 2 8 3 It will be possible to dump any memory area to ground via telemetry packets as described in EID A chapter 2 8 3 Reference RO ROS Man 1009 Rosetta Issue 3 Rev 0 ROSINA Date 01 11 06 Section 3 Page 39 2 3 1 4 DPU S C Memory Management Services 2 3 1 4 1 1 Memory Types and IDs ID Word Address Range Description Width bits 120 48 0x00000000 Ox0O005FFFF Program Memory 121 48 0x00060000 0x0007FFFF Sensor Function Memory 122 48 0x00C00000 OxOOCIFFFF EEPROM 1 123 48 0x00C20000 OxOOC3FFFF EEPROM 2 124 32 0x00000000 OxOO0DFFFF Data 1 Memory 125 32 0x00400000 OxOO4FFFFF Data 2 Memory 126 32 0x000E0000 OxOO0FFFFF Table Memory 127 32 0x00000000 0x0007FFFF Start Address 2 3 1 4 2 2 Allowed Memory Types and Addresses for Bench and SIS Tests ID Word Address Range Description Width bits 120 48 Not allowed 121 48 0x0007D000 0x0007EFFF Program Memory test 122 48 0x00C00000 OxOOCIFFFF Only for S W Update 123 48 0x00C20000 OxOOC3FFFF Only for S W Update 124 32 Not allowed 125 32 0x004FE000 OxOO4FFFFF Data 2 Memory test 126 32 0x000FEO000 OxOOOFFFFF Data 1 Memory test 127 32 Not allowed Reference RO ROS
114. nctions Functional Description of OBDH Channels High Power ON OFF Commands Two channels are needed for switching between the main and redundant DPU branches Spacecraft Powered Thermistors One thermistor for each DFMS RTOF both redundant and COPS non redundant is needed to monitor the temperature when the instrument is off Other Channels Standard function according to EID A Reference RO ROS Man 1009 Rosetta r L3 Issue Rev ROSINA Date 01 11 06 Section 3 Page 28 2 2 6 2 Bit Rate Requirements The data collection rate of the ROSINA instrument is continuous and occurs at a bit rate of gt 1 Mbps which is far too high to be transmitted It is therefore foreseen to reduce the data stream in the instrument The reduction is performed on two levels 1 H W based integration within accumulation memories of 32k 64 k channels 2 S W processing as i spectrum windowing ii averaging resulting in degraded mass and or time resolution iii lossless compression modified Rice PS 14 and in case of low telemetry rates task specific lossy compression The level 1 H W is part of the sensor electronics Depending on the scientific task continuous monitoring characterisation of outbursts and jets etc and the available rate and time for data transmission the bit rate of the DPU to the spacecraft can be adjusted between 200 bps and 4000 bps continuous data flow between 17 Mbit and 350 Mbit per
115. nity of the nucleus it may also be necessary to operate the instrument for extended periods of time while it is not pointed at the nucleus Angular scans using the narrow FOV of the DFMS will be required for studying individual gas sources on the nucleus Interferences Operation of the ACS thrusters interferes with the operation of the instrument and could even cause permanent damage It is therefore mandatory that the instrument is put in a safe mode before the thrusters are operated The instrument can only be turned on again 10 minutes after the thrusters are turned off Several hours may be necessary after instrument turn off to reach stable background conditions As an additional safety measure the COPS MICROTIPS OR FILAMENT will be used as a monitor of ambient conditions and will signal the mass spectrometer to turn off if ambient pressure should increase above a preset limit 10 mbar for instance due to a cometary outburst during the near comet phases of the mission or episodic S C outgassing If the pressure exceeds 10 mbar the COPS MICROTIPS OR FILAMENT will also be turned off 3 2 6 Operational constraints There are no pointing constraints nor constraints to other instrument operations for ROSINA RTOF in full mode both channels active should not be operated in parallel to DFMS for thermal reasons Rosetta ROSINA 3 3 Failure detection and recovery strategy Reference RO ROS Man 1009 Issue 3 Rev 0 Date
116. nsor Science Error pos Hex value 020 NRNAG31B 2 DPU Mode Hex value 022 NRNAG3AO0 2 DPU Status Hex value 024 NRNAG32bE 2 Sensor Mode Hex value 026 NRNAG3A4 2 Sensor Status Hex value 6 3 3 5 Sensor Error Report EID 44104 Length 11 words Pos RSDB Byte Bit Name Data 000 NRNAG304 2 EID 44104 002 NRNAG322 1 Unit 196 DFMS 200 RTOF 204 COPS 003 1 Flags Hex value 004 NRNAG3BC 2 Error No Hex value 006 NRNAG356 2 Table ID Hex value 008 NRNAG357 2 Limit ID Hex value 010 NRNAG358 2 Value No Hex value 012 NRNAG359 2 Expected Value Hex value 014 NRNAG35A 2 Read Value Hex value 016 NRNAG32E 2 Sensor Mode Hex value 018 NRNAG3A4 2 Sensor Status Hex value 020 NRNAG330 2 Spare 0 6 3 4 Ground Action Event Packet Definitions Sub Type 3 N A 6 3 5 On board Action Event Packet Definitions Sub Type 4 6 3 5 1 COPS Pressure Alert EID 44300 Length 3 words Pos RSDB Byte Bit Name Data 000 NRNAG304 2 EID 44300 002 NRNAG305 1 Unit 204 003 1 Spare 0 004 NRNAG35F 1 COPS Pressure mmmmeeee mbar 005 1 COPS Pressure Gradient mmmmeeee mbar s Reference RO ROS Man 1007 Rosetta r P Issue Rev Rosina Date 01 11 06 Section 10 Page 19 6 3 5 2 Switch Off Ready Alert EID 44301 Length 2 word Pos RSDB Byte Bit Name Data 000 NRNAG304 2 EID 44301 002 NRNAG305 1 Unit 208 003 1 Spare 0 6 4 Context File Definition Context File
117. ntrol Procedures The table below gives an overview of the use of on board control procedures OBCPs ON BOARD CONTROL PROCEDURES SUMMARY Instrument ROSINA OBCP Name Function PL OBCP 5 RN 1 Switch On PL OBCP 5 RN 2 Switch Off PL OBCP 5 RN 3 Emergency S W reload 5 1 2 On Board Monitoring Requirements The table below gives an overview of the use of on board monitoring No parameters have to be monitored because the DPU monitors all HK s DMS MONITORING Instrument ROSINA Monitored Entity Monitoring Requirements Action on Error Parameters Events Operation mode Wait for ROSINA ready to switch off Switch Off change report Event 8 TBD Reference RO ROS Man 1007 Rosetta Issue 3 Rev 0 Rosina Date 01 11 06 Section 6 Page 2 Reference RO ROS Man 1007 Rosetta r Issue Rev i Date 01 11 06 Rosina Section 6 Page 3 5 1 3 Information Distribution Requirements The tables below give an overview of the information required and offered by the instrument INFORMATION REQUIRED Instrument ROSINA Entity Requirements Remarks Parameters Giada Dust Flux every 1 min 2 Octets OxEE if not available Events Event 1 Event 8 INFORMATION OFFERED Instrument ROSINA Entity Availability Remarks Parameters COPS Pressure Every HK Frame SID 32 nom once a 1
118. ode or through the wide slit in the low resolution mode by electrostatic deflection The axis of the transfer lens is tilted by 6 relative to the ion source axis This shields the narrow entrance slit of the analyzer from cometary dust particles The final ion energy is established in the transfer section of the ion source To pass through the analyzer with its fixed magnetic field the ion energy must be changed from 6 keV at mass 12 amu to 720 eV at 100 amu Thus the 3 keV ions from the source are either accelerated or decelerated in this section and at the same time focused on the entrance slit of the analyzer The mass analyser The following key requirements for the Rosetta DFMS which had to be considered in the selection of the analyzer geometry were Mass resolution m Am 3000 for mass range 12 to 100 amu q at the 1 96 peak level Good energy focusing properties to allow AE E of up to 196 important if lower ion energies are used High mass dispersion to allow the use of a position sensitive focal plane detector A large free viewing angle preferably 2x for the ion source acceptance Reference RO ROS Man 1009 Rosetta r P Issue Rev ROSINA Date 01 11 06 Section 1 Page 15 A small overall size with a radius of curvature in the magnet not more than 10 cm The resulting optimal field geometry is a combination of a 90 toroidal electrostatic analyzer ESA with a 60 sector magnet for momentum analyses see Figure 1
119. on ion source also has the redundant ability to ionize incoming neutral particles with a filament assembly using electron impact ionization Both channels could therefore be used for gas or ions In flight an light version of the ETS ETS L data acquisition system counts the incoming ion events extracted from the orthogonal extraction ion source which is described below Blank mode The blank mode gives the opportunity to suppress selected mass lines in order to prevent an overload of the detector in case of very intensive mass lines e g water ions This mode is available only together with the triple reflection mode since the blank pulse operation is performed with the hard mirror and requires synchronization of the extraction pulse firing with the hard mirror blank pulse Calibration mode A calibration mode has been foreseen to self optimize the RTOF sensor To achieve optimal performance of the RTOF sensor the electrical parameters i e voltages on the ion optical elements etc have to be fine tuned carefully In flight the RTOF sensor will operate with a preset adjustment of the electrical parameters In addition Reference RO ROS Man 1009 Rosetta r a Issue Rev Date 01 11 06 ROSINA Section 1 Page 35 to achieve optimal performance an automatic optimization algorithm will be used for fine tuning during flight involving either the calibration system for the initial optimization or using cometary gas for routine optimizat
120. on of the cometary gas an instantaneous dynamical range of 4 10 was taken as the design objective Reference RO ROS Man 1009 Rosetta Issue 3 Rev 1 ROSINA Date 01 11 06 Section 1 Page 16 The detector package has to warrant the necessary accuracy of the measurements up to the end of a long lived mission of more than 10 years Owing to the anticipated gain variations of MCP s or Channeltrons it is thus necessary for the detector package to provide an absolute calibration by measuring directly the ion fluxes in the focal plane that correspond to the most abundant species such as H20 or the water group ions This led to include a Faraday cup in parallel to the main imaging MCP based detector and to have modes wherein the water peak can be moved alternately from the imaging detector to the Faraday cup Finally reliability considerations that are of paramount importance for this long and certainly innovative mission have led to two last specifications First it was decided to equip the detector package with a second detector allowing measurements of the mass spectrum with a resolution and a dynamical range identical to those provided by a single pixel of the imaging detector This was achieved by using a Channeltron CEM with a slit in front of the entrance to insure the necessary resolution The second specification is related to the imaging detector itself the large height of the mass focal lines in the focal plane has allowe
121. ors have to be handled with exceptional care DFMS and RTOF are built to ultrahigh vacuum standards and are closed off by a cover However they need to be pumped app every two weeks to maintain a vacuum below 10 mbar COPS needs permanent purging with nitrogen The two mass spectrometers use high voltages up to 9 kV Dust or humidity on the isolating ceramic parts may cause permanent damage to the sensors All three sensors contain delicate structures which can easily be broken off like for example the grids of the COPS nude gauge or the attraction grids of RTOF and DFMS The isolating cermamic parts of DFMS and RTOF are vulnerable to any mechanical force This is especially true for the reflectron of RTOF can be broken off the feedthroughs possible leaking and the isolating ceramic rings close to the covers Due to the fact that the pressure inside the sensors is not known except during active pumping no voltages should be applied to the inner parts of the sensors during normal system tests The HV safety plugs have to be connected at all times Additionally to the high voltages there are a number of other activities which cannot be performed on ground or only during active pumping of the sensors see chapter 2 The filaments and microtips of COPS will suffer permanent damage if turned on in ambient pressure That means that very great care has to be taken not to switch on any voltages affecting the gauges of COPS Only the 28V can be swi
122. ot reach the detector Due to the short image length of the hard mirror the longitudinal separation of iso mass ion packets in the hard mirror itself is small compared to the hard mirror length and allows for moderate blank pulse amplitudes to exclude individual mass lines The pulse slope requirements are less stringent compared to the extraction pulse The hard mirror structure for the flight model is based on a ceramic tube body with an inner diameter of 36 mm Three conductive silver ring electrodes are applied on the inner surface of the ceramic body with a sophisticated shaped back plane defining the repelling potential surface The passing ion trajectories in the immediate vicinity of the hard mirror demand an appropriate shielding of the electrical fields inside the hard mirror towards the field free drift section by minimizing the field penetration For this reason the hard mirror contains a conductive coating on the outer surface connected to drift potential and an extended entrance ring electrode with the same potential as the drift section Detector Detecting single ion events as well as ion bunches with up to 10 ions arriving within nano seconds time requires a detector with high detection efficiency Furthermore the detector has to have the ability to linearly amplify the incoming particles over a wide dynamic range In order to minimize the time spread of the ion bunches registered on the detector sufficiently fast detectors with an
123. over a very wide gas pressure range from several 10 mbar to below 10 mbar small energy dispersion and low background The source has two viewing directions with different field of views FOV The one Rosetta ROSINA HEXAPOLE FOR ROTATION OF FOCAL PLANE Reference RO ROS Man 1009 Issue 3 Rev 1 Date 01 11 06 Section 1 Page 13 FARADAY B DETECTOR POSITION SENSITIVE MCP DETECTOR CEM DETECTOR QUADRUPOLES FOR ZOOM SYSTEM ENERGY MATSUDA EP ROTATED QUADRUPOLE FOR OPTICS CORRECTION TRANSFER LENS CALIBRATION J FRINGING FIELD SHUNTS ELECTROSTATIC ANALYZER ALPHA SLIT ENTRANCE SLIT SWITCH HIGH LOW RESOLUTION ENTRANCE SLITS ET DEFLECTOR SOURCE EXIT SLIT NARROW ANGLE FOV Fig 1 2 DFMS ion optical principle 7 A d amp A V A ONIZATION BOX FILAMENT MAGNET lon Optics of Double Focusing MS Rosetta ROSINA DFMS PHYSIKALISCHES INSTITUT UNIVERSITAET BERN Fischer parallel to the source axis has a wide FOV of 20 the one orthogonal to it a narrow FOV of 2 For most of the measurements t he wide FOV will be used allowing cometary gas with wide angular spread in the flow direction to enter the ionization region The narrow FOV will be used for determining the exact flow direction of the cometary gases The axis of the wide FOV will normally be directed towards the nucleus and hence be parallel to the axis of t he cameras The
124. personnel as this operation is very delicate The lower part of the thermal H W can only be finally installed when the pump off valve support has been removed see chapter 4 To install this lower part of the thermal H W consult the manual RO ROS MAN 1012 RTOF will be delivered with a HV protection foil and with part of the thermal H W already installed These items should not be removed except by UoB personnel To mount the remaining part of the thermal H W consult the manual RO ROS MAN 1013 COPS will be delivered without the thermal H W installed To install the thermal blankets follow the manual RO ROS MAN 1014 3 1 6 Operations All operations have to follow the agreed test procedures ROSINA should neither be switched on without the ROSINA EGSE connected to the central checkout equipment nor without a representative of the ROSINA team present Deviations from this can be agreed with the ROSINA team on a case by case basis Separate operation manuals for the EGSE and the S W exist ROS TUB MA 03 1 1 and ROS TUB MA 05 Reference RO ROS Man 1009 Rosetta r e Issue Rev ROSINA Date 01 11 06 Section 3 Page 50 3 2 Operations Plan 3 2 1 Ground Test Plan deleted March06 3 2 2 Commissioning Phase near Earth LEO The covers of RTOF and DFMS should only be opened after the spacecraft has had sufficient time to outgas Also the main orbit and attitude correction maneuvers of the spacecraft which use a lot of thrust
125. r Gur e69310A UGH en 3661 d oue ajg jj6 PSuould ue 30511 uou eaten 440 dund Be i a g ze RE uori3e304d AH or Capui 7036 sejgeo Jo BUNIOA pe Jesea CHI 3003630 PUJOL 8 0 THI 3915930 PUUL Josusg DW Ys zum Mechanical Interface Control Drawing of RTOF in Launch Configuration UoB Drawing M156 1002 Reference RO ROS Man 1009 Rosetta Issue 3 Rev 0 ROSINA Date 01 11 06 Section 3 Page 8 Figure 2 7 Three dimensional view of RTOF in Operating 0 9 o e e M c 0 c 2 D zm zum e E HIRET 1 o o eo tc T 1 T O fc c O c Quo 199 2O 44u00 7838 soqo Jo TWIS xoi eufis Jeee Jake 4 1 jeuaeur UoRDeIOld N eun o panies CAL i4609 Jo U01987044 TEUJSUL oO GAL 08ueg JO U0 5010 44 1eUJeU ee ee NR e Saj TUAE n i c c o Oo A i o99072 E DH O 22 gat ff E i i e N on co E c 900 ze n su i 9D 0 pee j sey eu JO SJUSUOH n i ww 2705 Z wu ZI wu gu B uoe 2 5 i i SSE Jo Jeque fe oil Oy rl seew Josue j Eee A HEH pms upunoug 38jsusar e38Q ndi ie 4 i i Set GUL anog Od af P Sun sang en S d lt lt ELIT T cw di Bui GOP NOT
126. r savings mode where only the channel which is adapted to low densities will be operated which should allow an early turn on Where this switch on occurs will be determined by available spacecraft power and telemetry DFMS and COPS should be turned on as soon as feasible from the power point of view During commissioning the DFMS and RTOF ion sources will be degassed by the ion source heaters for several days Careful conditioning of the filaments and use of the inflight calibration system have to be included in the commissioning phases Regarding telemetry cometary gas densities will be low at large heliocentric distances requiring very long integration periods and monitoring of spacecraft outgassing Thus telemetry requirements may be significantly lower than later when the gas densities are larger Mapping Phase During the mapping phase of the mission the instrument will be used to survey the nucleus surface To search for active areas on the nucleus surface where volatiles are at or near the surface and to search for suitable landing places for the SSP a survey of the gas density around the nucleus at an altitude of about one nuclear radius is required The intensive study of the gas density composition and dynamics must be continued during the entire mapping and close survey phase to achieve the science goals It will also require use of the narrow FOV of the DFMS which must be directed towards the nucleus Escort to Perihelion Af
127. rate however can be small during this period During the actual fly by the RTOF should be fully operating at the highest possible data rate to gather mass spectra with high spatial resolution If power and available bit rate permit the DFMS will be used to complement RTOF by looking at specific molecules in a low mass resolution mode The sensors will be operated throughout the asteroid flyby s in the same measurement modes gas channel RTOF low resolution DFMS That means no commanding will be necessary 3 2 4 5 Comet Approach After reaching the neighborhood of the comet it is mandatory that the instrument is switched on as soon as possible to study outgassing and 3 2 4 6 3 2 4 7 Reference RO ROS Man 1009 Rosetta r Issue Rev Date 01 11 06 ROSINA Section 3 Page 52 cometary activity at large heliocentric distances At these distances the expected cometary gas densities are low and S C outgassing and instrument background must be reduced to the lowest possible level This requires exposure of the experiment platform to sunlight for several days to accelerate degassing of adsorbed gases This degassing process should be monitored by COPS MICROTIPS OR FILAMENT The covers of the two sensors should be opened when S C outgassing has been sufficiently reduced as determined by the COPS MICROTIPS OR FILAMENT The first sensor to be switched on will be the RTOF because it has a larger sensitivity than the DFMS RTOF has a powe
128. ration esses 50 Reference RO ROS Man 1009 Rosetta r P Issue Rev ROSINA Date 01 11 06 Section 1 Page 3 3 2 4 Flight Operations plans Mission Phase eene 51 3 2 5 WMS TS RNC 8 iissa ans na a UC TR TERNI TS EMEN TION DE 53 3 2 6 Operational contes til nece ese iH Ru O d iesu ben aaeinncannateeeenans 53 3 3 Failure detection and recovery strategy aeree eee etienne tena en nnn 54 4 Mode DOSCFIB IOHS oues on OU QUI N RCRUM ain GAMO EMI RUE BLU QAI RU eis 1 4 1 Mode Transition Table eniti tno rer ri He tni atio iEn rere SE IER IUE IEE 1 4 2 Detailed Mode DescrIplBl aoo dedkeeioscikkcan eeu EFEAR a CHE FRRKE CUN GERG FORE 2a e RE FAR RE E CRREC K UNE SaH 2 4 2 1 Instrument foe inu dic dietro eE o ca lia op ra IUD euo Re kd rada 2 4 2 2 DPU Mod s e P 9 4 4 2 3 DEMS n 5 4 2 4 RTOP a onocnod pH atu E qu SP E E Na SNR 9 4 2 5 COPS Operational modes socii dad tuse ipii nS adetentwehetevub Emu Posi eines 13 5 Op rational procedures liceret nae rente EYXEREE UA REO QUO EPEQ SERUUM EE TE PA E ieaS ESVE ORT 1 5 1 On board control procedures icc o roi etae In rh nth et nonno tih rk oH eR ROS ree 1 5 1 1 On Board Control Procedures iiie asa Sorel ere Rpe ecd dcus debdedps CE d o as RUM A 1 5 1 2 On Board Monitoring Requirements eese 1 3 1 3 Information Distribution Requirements essere 3 5 2 Flight Control procedures e
129. rding segment is two times the value for the repelling segment according to the second order focus conditions The voltage drop over the reflectron is controlled at three points Furthermore the ceramic structure of the integrated reflectron acts simultaneously as the ultra high vacuum enclosure for the RTOF sensor and is an integral part of the overall mechanical sensor structure The ratio of the ion optically usable inner Reference RO ROS Man 1009 Rosetta r P Issue Rev Date 01 11 06 ROSINA Section 1 Page 32 diameter 78 mm and the mechanical outer diameter 80 mm is minimized This results in a 50 weight saving compared to the classical ring stack reflectron which requires an additional vacuum housing and high voltage feed throughs A photograph of the realized integrated reflectron is reproduced in Fig 1 13b Hard mirror The hard mirror represents an additional reflecting element in the RTOF system Hohl et al 1999 and is shown schematically in Fig 1 14 The hard mirror increases the flight path in the RTOF system by almost a factor of two by introducing an additional reflection while maintaining the initial time spread generated in the ion source This also increases the mass resolution by almost a factor of two The hard mirror consists of cylindrical tubes with a sophisticated formed back plane Restricted by the narrow space between ion source and detector see fig 1 10 the hard mirror has to fit geometricall
130. read 044 NRNAG3B7 4 HK Cmd 2 sensor cmd for hk read 048 NRNAG3B8 4 HK Cmd 3 sensor cmd for hk read 052 NRNAG3B9 4 HK Cmd 4 sensor cmd for hk read Reference RO ROS Man 1007 Rosetta Issue MEC Rev 0 Date 01 11 06 Rosina Section 10 Page 16 6 3 3 Anomalous Event Packet Definitions Sub Type 2 6 3 3 1 DPU Latch up Report EID 44100 Length 7 words Pos RSDB Byte Bit Name Data 000 NRNAG304 2 EID 44100 002 NRNAG305 1 Unit 208 003 1 Spare 0 004 NRNAG333 2 Latch up position Hex value 006 NRNAG3BA 2 Latch up counter Counter 008 NRNAG309 2 DPU power status 15 Spare 14 Status SRAM 2 0 Off 1 On 13 Status SRAM 1 0 Off 1 On 12 Status Stat EEPROM 0 Off 1 On 11 Status I F COPS 0 Off 1 On 10 Status I F RTOF 0 Off 1 On 9 Status I F DFMS 0 Off 1 On Status EEPROM 0 Off 1 On Sensitivity DSP 0 Low 1 High Sensitivity SRAM 2 0 Low 1 High Sensitivity SRAM 1 0 Low 1 High amp O01 O NIO Sensitivity Stat Eeprom 0 Low 1 High 3 Sensitivity I F COPS 0 Low 1 High 2 Sensitivity I F RTOF 0 Low 1 High 1 Sensitivity I F DFMS 0 Low 1 High O Sensitivity EEPROM 0 Low 1 High 010 NRNAG31B 2 DPU Mode Hex value 012 NRNAG3AO 2 DPU Status Hex value 6 3 3 2 DPU Memory Error Report EID 44101 Length
131. red by two 0 to 500 V 14 bit and two 0 to 2000 V 14 bit supplies are active the DFMS is in high mass resolution mode and the ion beam that impinges on the chosen detector is considerably more dispersed in the transverse mass direction Through a high voltage transformer interface the DFMS electronics also provides Reference RO ROS Man 1009 Rosetta r i Issue Rev ROSINA Date 01 11 06 Section 1 Page 22 power to the CEM detector and repeller grid the repeller grid for the faraday cup detector and the front and back high voltages for the MCP The MCP voltages are programmable to 10 bit accuracy to allow for safe HV detector turn on and potential decrease in the MCP gain during the long encounter with the comet The entire electronics package is housed below the DFMS optics see Figure 1 3 Three packages are attached to the DFMS base plate These packages consist of the Main Electronics Pack the Acceleration Supply Pack and the Floating Detector Pack A fourth package discussed with the sensor is called the Remote Detector Pack The Main Electronics Pack consists of 8 electronics boards a motherboard connecting these eight and a low voltage power supply board These boards are all at the local spacecraft ground and are attached directly to the base plate for thermal dissipalion directly through the feet of the base plate attached to the spacecraft MEP A data and command handler interface with the DPU MEP B ion source
132. s in ion and neutral gas concentrations and large changes in the ion and gas flux as the comet changes activity between aphelion and perihelion 4 The ability to determine the outflowing cometary gas flow velocities The necessity for the unusual high capabilities of this experiment stems from the fact that it is one of the key instruments which is able to give meaningful data during the whole mission and thus by monitoring and characterizing the different phases of comet activity from apogee through perigee will lead to a full understanding of cometary behavior Correlated studies with optical observations with for example the dust instruments the magnetometer and the surface science package further augment the scientific return of the ROSINA instrument A RTOF Giotto IMS Mass Resolution e Operating pressure range 10 100 1000 10 100 1000 Mass RTOF A gt a Jow resolution DFMS high resolution DFMS c ih c a E lt x gt a o c o o 10 100 1000 Mass Fig 1 1 Comparison of the operating ranges of DFMS and RTOF Reference RO ROS Man 1009 Rosetta r P Issue Rev ROSINA Date 01 11 06 Section 1 Page 9 INSTRUMENT REQUIREMENTS Table 1 lists the science objectives and the instrument requirements necessary to achieve them The necessary performance of ROSINA is summarized in table 2 and the comparison of operating ranges of the two mass analy
133. sampling is required the system can be set into the Time Delayed Sampling Mode where the acquisition start delay value is not fixed but increased automatically by 32ns after each extraction Four 512x18bitx2 FiFo s are used for fast data storage 4 sets of ADC data are stored in each FiFo The Time of Flight TOF measurement is the base for the address generation at which the data are stored in the accumulation RAM The address is stored in a 512X18bit FiFo The Start Delay Time and the Time Of Flight can be programmed with 17 bit each that refers to 131 073us That means a total time of 262 144us can be covered After the programmed times are elapsed the accumulation of the data is initiated 8 bit data are accumulated to a 24 bit wide word as well as the number of events for each channel So altogether 48 bits belong to a single time of flight address These data are transferred to the DPU after a valid readout command has been received Data acquisition has the highest priority Readout will be performed after the data accumulation is finished and settings 100 v Q amp G Es i S i 3 2 10 3 o 1 2 5 S 1 g 3 e E 100 200 300 400 500 mass amu Fig 1 21 Mass spectrum of the calibration compound heptacosafluorotributylamine become valid after the accumulation is finished For high event frequency the extraction will be kept disabled as long as the accumulation is not yet finished compl
134. source These factors contribute to the overwhelming sensitivity of TOF instruments Another reason to use TOF instruments in space science is their simple mechanical design their performance depends on fast electronics rather than on mechanical tolerances and easy operation An RTOF type instrument was successfully flown on the GIOTTO mission to measure atoms and molecules ejected from a surface during impact of fast cometary dust particles Fig 1 12 shows the principle of the realized RTOF sensor A time of flight spectrometer operates by simultaneous extraction of all ions from the ionisation region into a drift space such that ions are time focused at the first time focus plane TF at the beginning of the drift section The temporal spread of such an ion packet is compressed from about 800 ns at the exit of the ionisation region to about 3 ns for grid free reflectron TTT ee a HHA detector ion source length 1 m Fig 1 12 lon optical principle of RTOF mass 28 amu e at the first time focus plane These very short ion bunches are then imaged onto the detector by the isochronous drift section Because different m q bunches drift with different velocities the length of the drift section determines the temporal separation of the bunches If properly matched to the drift section the reflectron establishes the isochronity of the ion optical system The mass resolution is determined by the total drift time and the tempor
135. ssipation FDP A Analog processing for the high resolution detector and the faraday cup detector FDP B Digital control for the detector FDP C Interface and power for the FDP package connected across a high voltage interface to the low voltage power supply in the MEP pack Reference RO ROS Man 1009 Rosetta M p Issue Rev Date 01 11 06 ROSINA Section 1 Page 25 Measurement sequences The instrument has a large number of operational parameters which could be individually adjusted to fit any specific measurement requirements However a certain number of predetermined modes and measurement sequences will be 100000 DFMS EOM Feb 18 2000 10000 Accumulated ADC code MCP LEDA Anode Number Fig 1 11 Low resolution mass spectrum m 27 28 29 amu implemented and we expect that most measurements will be made using these From time to time it will be necessary to retune all voltages to optimize the instrument performance and to compensate for mechanical thermal etc drifts which could occur during launch or in space We expect that the basic retuning can be done autonomously but some manual adjustments might still be necessary requiring extensive ground command sessions For any given instrument setting we will use a basic integration time of approximately 1 s The accumulated spectra will be transferred to the DPU for further data processing The adjustment of the instrument to a new setting for instance
136. sue Rev 0 ROSINA Date 01 11 06 Section 3 Page 24 2 2 5 Thermal Interfaces There are several drivers which determine the thermal requirement of ROSINA 1 The operating temperature of the detectors of all three sensors has to be between 30 C and 30 C 2 The ion sources of the two mass analysers DFMS and RTOF should be warmer or at least not colder than the other experiments on the platform or the platform itself contamination 3 No temperature gradient in the sensors and stable temperatures for several measurement cycles several minutes Experiment Operating Nonoperating Switch on Unit Subsystem Temperature Temperature Temperature max max max DFMS Sensor 50 C DFMS Detector 40 C Cover separation 30 C pyrocord Cover fail safe 74 C mechanism DFMS 30 C 50 C 50 C 50 C Electronics RTOF Sensor 50 C RTOF Detector 40 C Cover separation 30 C pyrocord Cover fail safe 74 C mechanism Electronics COPS Sensor 60 C 30 C 50 C Electronics Table 2 2 5 1 ROSINA temperature requirements The critical areas of DFMS and RTOF driving the thermal design are defined in the two drawings below Rosetta Reference RO ROS Man 1009 Issue Rev ROSINA Dao 01 11 06 Page i Q aay dd g gg PR Alo uI g g E T g 8 ae TERES x ar ajgsETUT d Es 8 T Q T RS Ae 79 ic 9 E A Mi gt AM X RN Y T 4 E ees LL A ae Vena 5j E HT a HT
137. tages which keep ions created in the ion source from escaping back through the entrance aperture Two power supplies provide the ionisation box with potentials which accelerate the electrons from the filament across the aperture field of view The IRP2 Ion Filament 1 on repeller ERP Trap Emission Regulator Emission 2 20 200 pA ELE 5 to 100V Source exit ERP 10 to 140V slit Trap 20 or 100V 0 to 3000V 12bit Rosetta Rosina DFMS block diagram with principal Ion Source and Transfer Optics power supplies PEYSIKALISCHES INSTITUT UNIVERSITY OF BERN INSTITUT UNIVERSITY OF ERN Fig 1 7 lon source and transfer optics o diagram TLR Transfer lens right 0 to 2000V 16bit TLL Transfer lens left 0 to 2000V 16bit ISB 0 to 200V 8bit Ton Source Potential Ton source heater d 0 24V 10W Temperature sensor PT 1000 SG Shielding Grid around ion source and transfer optics Meshed Grid 0 to 50V 8bit Reference RO ROS Man 1009 Rosetta r a Issue Rev ROSINA Date 01 11 06 Section 1 Page 21 newly created ions are extracted from the ionisation region accelerated to high voltage and passed through the transfer optics section using high voltages from 5 more power supplies Two of these power supplies in the transfer optics section require 0 to 2000 V with 16 bit accuracy The accuracy of all power supplies in the ion source and ion optics is determined by
138. tched on during S C tests in ambient pressure 3 1 3 Safety aspects HV For the safety aspects regarding high voltage pyrotechnics and pressurized items consult the safety and hazard analysis document ROS DOC 4001 For the on ground operation of ROSINA the following activities may cause permanent damage to the sensors Reference RO ROS Man 1009 Rosetta Issue 3 Rev 0 ROSINA Date 01 11 06 Section 3 Page 48 e Cover operation Voltages applied to the ion optical parts inside the two mass spectrometers Operation of the gas calibration unit Operation of the heaters inside the vacuum part of the sensors Operation of the filaments Operation of the microtips Therefore the following guidelines have to be followed at all times 1 HV plugs have to be installed at all times except during SPT s where DFMS and RTOF are actively pumped and the pressure inside the sensors is known to be less than 107 mbar 2 HV plugs have to remain installed during system tests including TV tests 3 All commands related to the covers must not be activated This is especially true for the pyro commands but also for all other commands cover open close etc 4 All commands related to filaments must not be activated DFMS RTOF except during SPT s see point 1 5 All commands related to filaments or microtips for COPS must not be activated except in a vacuum below 10 mbar 6 No voltages for the COPS ram gauge may be set except
139. tector package A 20 p wide slit positioned 1 cm in front of it and coincident with the location of the end of the focal plane provides the required resolution At the same time it prevents the high voltage on the CEM entrance to leak and affect ion trajectories in the drift space before the focal plane The CEM may be operated both in a counting and an analogue mode The Faraday cup FC can be seen on the right end of the figure with a 0 35 mm slit in front of the cup and coincident with the right end of the focal plane It provides the needed medium resolution measurements current on the water peak with a current range from 10 to 10 A 1 2 1 3 Mechanical Structure Fig 1 4 shows a three dimensional picture of the DFMS sensor The main components are the primary structure which contains the ion optics the secondary structure that houses the electronics the cover opening mechanism and the in flight Reference RO ROS Man 1009 Rosetta M Ld Issue Rev Date 01 11 06 ROSINA Section 1 Page 18 calibration system The primary structure is made from Conte s titanium and ceramics in order to be compatible with the ultrahigh vacuum requirements It can be baked out up to 120 C or up to 250 C for the ion source The banana shaped tube contains all ion optical elements The mechanical requirements with respect to tolerances are very high The toroidal surfaces of the electrostatic analyzer have to be within 2 um of
140. ter the SSP has been deployed and during the escort to perihelion phase the gas production rate will increase The increased production will allow accurate measurements at large cometocentric distances In this phase the RTOF will serve as survey instrument measuring a very large mass range whereas the DFMS will concentrate on individual masses to get a full mass resolution for critical mass peaks e g mass 28 amu To study the release of gas from grains extended sources and to get insight into the complex coma chemistry and the interaction 3 2 5 Reference RO ROS Man 1009 Rosetta Issue 3 Rev 0 ROSINA Date 01 11 06 Section 3 Page 53 between gas and dust several radial excursions from about one nuclear radius to at least 1000 km with extended stays at large distances may be required These excursions must be interspersed with detailed investigation of the sunward near nucleus hemisphere of the coma The observations of the outgassing behavior of active areas during terminator crossings and in the shadow will be a diagnostic tool for the morphology of the nuclear surface regions in these areas These observations require stays above the dawn and dusk terminator regions and occasional observations of the nightside of the coma To measure minor constituents of the gas and to get isotope ratios for a large number of species it is essential to have very long integration periods Depending on the actual gas flow field in the vici
141. the 28V line and the Redundant line have its own electronic switch which is controlled by the DPU Additionally to the switch there is a current limiter circuit After that at the inputs of the non redundant power converter boards the redundant power lines are electrically OR ed i e duplication protects against broken wires connections only Reference RO ROS Man 1009 Rosetta Issue MEC Rev 0 ROSINA Date l oo P Section Page Sensors Sensor Electronics DPU DFMS Electronics Data amp Cmd Data amp Cmd A Main DPU Power On Off TSC21020 Timer Sync Pulse A RTOF Electronics Data amp Cmd Hard Core Switch Closure On Off Cmds Power On Off Data amp Cmd B Red DPU COPS TSC21020 Electronics Data amp Cmd iE Timer Sync Pulse B Power On Off T 8 DEN Lm Co UN din ps S C Powered Thermistors TE Thermigtors se Fig 2 13 Power and Harness Distribution Reference RO ROS Man 1009 Rosetta Issue 3 Rev 0 Date 01 11 06 ROSINA Section 3 Page 16 2 2 3 Experiment Power Requirements Ref to Sec 4 for a description of ROSINA modes and for the respective power requirements Fig 2 14 General Sensor Primary Power Switch RESET Main o SET Main RESET Red SET Red 28V Main 28V Red Return path and freewheeling diodes not shown Fig 215 DPU Power Switching Block Diagram Reference RO ROS Man 1009 Rosetta r e Issue Rev ROSINA Date 01 11
142. the mass resolution requirements of the DFMS Following the transfer optics section ions pass through a wide range of ion optical elements which ultimately focus a mass dispersed ion beam onto several possible detectors including a high resolution position sensitive detector Since the ion source resides on spacecraft ground the ion optics must float at high voltage acceleration potential This floating acceleration potential is provided by a 14 bit full scale 0 to 6500 V power supply Also since the optical elements float at this high potential they are electrically isolated from the power supplies and instrument controllers that reside on ground Communication to and from these isolated power supplies is provided by a serial interface across several fiber optics channels The design for the fibre optics was derived from the successful design used in the Toroidal Imaging Mass Angle Spectrograph TIMAS Shelley et al 1995 Power is supplied across a high voltage transformer In the original DFMS design a mechanical slit was to be used to select high or low resolution mass spectra During DFMS prototype testing this mechanical system was replaced with an electrical slit system powered by two 1000 V 12 bit power supplies directly behind the transfer optics Following a corrective lens element accomplished by a set of plates at low voltage 0 to 50 V the ions enter the electrostatic analyser This analyser is powered by two 10 to 550 V 18 bit
143. upto 1 96 Sensitivity gt 10 mass 300 amu A Torr Determine isotopic Separate CH and C Mass resolution gt 3000 at 1 composition of Measure HDO DCN and peak height relative volatiles other deuterated neutrals accuracy 1 96 absolute and ions accuracy 10 96 Study the Measure the composition Mass range 1 300 amu development of the water and minor dynamic range 10 cometary activity constituents between 3 5 AU gas production rate 10 s and perihelion 10 s Study the coma chemistry and test existing models Study the gas dynamics and the interaction with the dust Characterization of the nucleus Characterization of asteroids Measure ions and molecules in the mass range 1 300 amu and their velocity and temperature Measurement of the bulk velocity and temperature of the gas Characterization of outbursts and jets of limited angular extent Detect asteroid exosphere or determine Mass range for ions and neutrals 1 2300 amu dynamic range 10 sensitivity 10 A mbar Reference RO ROS Man 1009 Rosetta Issue 3 Rev 1 ROSINA Date 01 11 06 Section 1 Page 10 Bulk velocity corresponding to E 0 02 eV 10 95 temperature 0 01 eV t 2096 2 Narrow field of view time resolution 21 minute Extreme sensitivity for H2O CO and CO upper limit Table 1 2 ROSINA Performance Mass Mass Resolution Sensitivity Dynamic Pressure Range m Am at 1
144. view of RTOF in Launch Configuration Note The pump off valve will be removed respectively pinched off before launch Rev Reference RO ROS Man 1009 Issue Q N O tc N 0 D tv n oO e T TS T Q c ems 2 D o Go Aw ROSINA Fig 2 6 aooi ss w ISO V LL350H JOSU6G 01H 649 uaung yaou uoog 9 299 weedy 30e3u0 XAJ HPWBJ H Joc 4 1 PUJ UL BL 48109 JO uorgaerog PuuayL AL Josueg jo uoroegoug PWJ UL Sedd PUL 26 000 71 BO Z200 I 26 29000 t a5 eur60 71 UO 196 t 26y 890I0 t PO 04 P8908545 PIJU JO SiUGUON ww gz A wg Eeeh JO Jenue D ci SseH Joeuec tee00 og unpe nty no waren 158 4190014 Te5jueuoed um pig Z uoj1e 2 5 Pa SONNY Buisnoy sououioe 7 A5 99 Say 1561005 xeye 6i5 Jelue3e 4eAe7 4 1 Jeuueu wuJoj3elg 2 5 OF pequnou YY xog sojuo 12er l BUBTOH SOIR 3004 GuruNoW D u y uonoes Or uipue 038 S8109 J6j eun o peaesaa 918 S81G25 JOJ BUNTON pe jesea TH avs 20 E zu su a ew o 3 Pui U0r3933y UOL was bupuncus jsuis eyed dd E x JJ BUT Jand oJ d dr m aur Jerod e
145. with respect to the drift path the entrance part acts like the first half of a positive electrostatic lens A grid free reflectron always shows lens effects for ions travelling out of the line of the ion optical axis An ion beam will diverge in the entrance of a reflectron as it does in the entrance of a positive Einzel lens To reduce the positive lens effect of the reflectron itself a negative lens the reflectron lens is used at the reflectron entrance The reflectron lens offers the opportunity to optimise the time focussing with the reflector potentials and independently to optimise the geometrical focusing with the potential on the reflector lens The adjustment of the reflector lens voltage allows also manipulation of the inclination angle of the returning ion trajectories with regard to the ion optical axis of the system Therefore generally a grid free reflectron with an integrated electrostatic lens at the entrance no longer shows the characteristic of a homogeneous ion mirror that the angle of incidence is equal to the angle of emergence The practical application of this feature is demonstrated for the different operation modes of the RTOF sensor The electric fields for a reflectron are usually established by a set of rings connected to a resistive voltage divider We designed a novel approach for generating the retarding and repelling electrical fields where the voltage divider is an integral part of the reflectron which we called integr
146. y during turn on mode or turn off sequences DPU High On off off closed off off S C N A All phases Safe mode during Pressure or thruster firing and high mode DPU pressure alert lon On off off open on off DPU 1h All phases Regular cleaning of ion Source source by heating 1 cleaning week TBC 2 Noise On On On open off off DPU 10s All phases Background Normal measurement of detectors every few minutes Rosetta ROSINA Reference RO ROS Man 1007 Issue Date Section 3 Rev 01 11 06 14 Page 0 6 Backgro und Partiall y open off off DPU 5 min All phases Background measurement of sensor by blocking off cometary material lt 1 day High res On On On open off off DPU 10s mass All phases Normal high resolution mode mass spectrum of one mass number per measurement Low res open off off DPU 10s 8 masses All phases Normal low resolution mode mass spectrum of eight mass numbers per measurement Intercali bration open off off DPU 10 min All phases Intercalibration of all three detectors LEDA CEM Faraday 1 day In flight calibratio n open off on DPU 30 min All phases In flight calibration with gas calibration unit 1 week Narrow angle High res open off off DPU N A Special S C mode Nor
147. y in the TOF system without substantially Fig 1 17 Hard mirror increasing the distance between ion source and detector to keep the angle between the incoming ion trajectory and the outgoing trajectory in the reflectron as small as possible The reflecting region is short compared to the grid free reflectron and thus performs a hard reflection which means the penetration depths of ions of different energies are almost the same The time focus of the hard mirror is chosen to be close to its exit plane since the hard mirror has limited time focusing capabilities due to its small size Similar to the previously described grid free reflectron the hard mirror contains a negative electrostatic lens at the entrance to shape the ion trajectories spatially Subsequently the cylindrical electrodes following the hard mirror lens in conjunction with the back plane allow the adjustment of the retarding and repelling electrical fields The hard mirror offers the unique opportunity to suppress selected mass lines by applying a pulsed defocusing voltage to the back plane electrode see Fig 1 14 The electrical field configuration during the applied blank pulse results in a strong geometrical defocusing of ions travelling not along the rotational axis Thus these Reference RO ROS Man 1009 Rosetta Issue 3 Rev 1 ROSINA Date 01 11 06 Section 1 Page 33 ions will be lost by scattering inside the drift tube structure and will n
148. y the two MCP stages in the detector The voltage divider is built on a ceramic substrate with ultra high vacuum components to ensure short electrical connections for fast replenishing of the extracted charge of the MCPs Wurz et al 1996 The detector can be operated in analog mode or in pulse counting mode 1 2 2 2 RTOF scientificoperation modes The RTOF flight instrument will provide several scientific operation modes to assure optimal scientific data acquisition under diverse mission conditions The gas and ion Reference RO ROS Man 1009 Rosetta r a Issue Rev Date 01 11 06 ROSINA Section 1 Page 34 modes with their dedicated ion sources have their own optimized data acquisition system The RTOF sensor on the Rosetta spacecraft will have the following operational modes all of which were tested with the RTOF laboratory prototype Single and triple reflection mode The single reflection mode refers to the ion trajectories starting at the ion source being one time reflected in the reflectron and ending at the detector see left drawing in Figure 1 10 In the triple reflection mode the ions leave the ion source reverse their direction of motion for the first time in the reflectron and experience a second reflection in the hard mirror After a third reversal of their direction of motion in the reflectron they will hit the detector The reflectron is used twice in this mode and the hard mirror is passed only once Switching b
149. zers is given in fig 1 1 The requirements listed in Table 1 are unprecedented in space mass spectrometry So far no single instrument is able to fulfill all of these requirements We have therefore adopted a three sensor approach each sensor is optimized for part of the scientific objectives while at the same time complementing the other sensors In view of the very long mission duration they also provide the necessary redundancy Sensor I DFMS is a double focusing magnetic mass spectrometer with a mass range 1 100 amu and a mass resolution of 3000 at 1 peak height Th sensor is optimized for very high mass resolution and large dynamic range Sensor Il RTOF is a reflectron type time of flight mass spectrometer with a mass range 1 gt 300 amu and a high sensitivity The mass resolution is better than 500 at 1 96 peak height This sensor is optimized for high sensitivity over a very broad mass range Sensor Ill COPS consists of two pressure gauges providing density and velocity measurements of the cometary gas Table 1 1 Science objectives and measurement requirements for ROSINA Scientific Associated critical Measurement Objectives measurements requirements Determine elemental Separate CO from N2 Mass resolution 22500 at 1 abundances in the of peak height at mass gas 28 amu Determine molecular Measure and separate Mass range 1 300 amu composition of heavy hydrocarbons with a resolution of 2300 at volatiles neutrals and ions

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