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User Manual - Clyde Space

1. BCR Battery Charge Regulator PCM Power Conditioning Module PDM Power Distribution Module MPPT Maximum Power Point Tracker USB Universal Serial Bus ESD Electro Static Discharge TLM Telemetry EPS Electrical Power System EoC End of Charge AMUX Analogue Multiplexer ADC Analogue to Digital Converter AIT Assembly Integration and Testing 3U 3 Unit DEPS Deployed Electrical Power System rh Relative Humidity DoD Depth of Discharge Kbits Kilobits per second Voc Open Circuit Voltage Isc Short Circuit Current SOLUTIONS FOR A NEW AGE IN SPace wwwdydespacecom PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 User Manual CS XUEPS2 60 FleXU CubeSat Electronic Power System Part 01 00732 and 01 01120 USM 01 00732 Helix Building WSSP Issue D Date 20 03 2014 Page 3 of 51 Glasgow G20 OSP UK Related Documents No Document Name Doc Ref RD 1 CubeSat Design Specification CubeSat Design Specification Rev 12 Warning Risk Ensure headers H1 and H2 are correctly aligned before mating boards If misaligned battery positive can short to ground causing failure of the battery and EPS Ensure switching configuration is implemented correctly before applying power to EPS If power is applied with incorrect switch configuration the output of the BCR can be blown causing failure of the EPS Observe ESD precautions at all times The
2. The EPS is robust and designed to withstand flight conditions However care must be taken when handling the device Do not drop the device as this can damage the EPS There are live connections between the battery systems and the EPS on the CubeSat Kit headers All metal objects including probes should be kept clear of these headers 5 3 Shipping and Storage The devices are shipped in anti static vacuum sealed packaging enclosed in a hard protective case This case should be used for storage All hardware should be stored in anti static containers at temperatures between 20 C and 40 C and in a humidity controlled environment of 40 60 rh SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 User Manual CS XUEPS2 60 FleXU CubeSat Electronic Power System Part 01 00732 and 01 01120 Issue D Date 20 03 2014 Page 12 of 51 USM 01 00732 Helix Building WSSP Glasgow G20 OSP UK 6 MATERIALS AND PROCESSES 6 1 Materials Used Material Manufacturer TML CVCM WVR Application 1 Araldite 2014 Epoxy Adhesive fixing Conf l Coating E amp i a sete EE Cuming PCB material 5 FR4 Adhesive fixing on modifications Thermally Conductive RTV Note worst case on NASA out gassing list Solder Resist CARAPACE 0 95 6 EMP110 or 0 995 Or 0 001 XV501T 4 il g Sn62 or Sn63 7 Tin Lead a i Alpha Rosin ESA 8 Flux Flux RF800
3. User Manual CS XUEPS2 60 FleXU CubeSat Electronic Power System Part 01 00732 Author Updated Andrew Strain Approved Clyde Space Ltd Helix Building Kelvin Campus West of Scotland Science Park Glasgow G20 OSP UK t 44 0 141 946 4440 e enquiries clyde space com w www clyde space com Registered in Scotland No SC285287 at 123 St Vincent Street Glasgow G2 5EA Alan Kane and 01 01120 Document No USM 01 00732 Issue D Date 20 03 2014 Signed SOLUTIONS FOR A NEW AGE IN SPACE User Manual CS XUEPS2 60 FleXU CubeSat Electronic Power System Part 01 00732 and 01 01120 Issue D Date 20 03 2014 Page 2 of 51 USM 01 00732 Helix Building WSSP Glasgow G20 OSP UK Document Control Issue Date Section Description of Change Reason for Change 27 01 12 All First Draft based on C3D N A USM 5023 DLR EPS2 30 1 13 All Update to reflect Respin of daughterboard hardware update to Rev B PCB to implement improvements from first build c 06 09 2013 All Update of TLM equations to match build revision 20 03 13 Table 8 2 Table 8 3 Update Array naming Customer Request Table 11 5 connector naming and BCR connection to simplify Revision Control Correction of errors as detailed in ECN 174 Product Part Number Build Revision FleXU Electronic Power System 01 00732 with 6x12W BCR and 12V regulator Acronyms and Abbreviations
4. Current temp voltage current Lg Sensing temperture curren pt C data bus C NODE m Signal line Control line Figure 11 1 Telemetry functional diagram 11 1 12C Command Interface All communications to the Telemetry and Telecommand TTC node are made using an I2C interface which is configured as a slave and only responds to direct commands from a master I C node no unsolicited telemetry is transmitted The 7 bit 1 C address of the TTC Node is factory set at 0x2B and the I C node will operate at up to 100kHz bus clock Command Protocol Two message structures are available to the master a write command and a read command The write command is used to initiate an event and the read command returns the result All commands start with the 7 bit slave address and are followed by two data bytes When reading data responses both data bytes should be read together A delay of at least 1 2ms should be inserted between sending a command and reading the telemetry response This is required to allow the microcontroller to select the appropriate analogue channel allow it to settle and then sample the telemetry reading In a write command the first data byte will determine the command to be initiated and the second data byte will hold a parameter associated with that command For SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 User Manual CS XUEPS2 6
5. Noise Filter Off 400ms Figure 12 6 Waveform of Solar Array Input EoC Operation Using the test setup detailed in Figure 12 5 the EoC operation can be demonstrated By raising the voltage of the simulated battery above 8 26V the EoC mode will be activated This can be observed using an ammeter coming from the Array input which will decrease towards OA 16V Charging Figure 12 7 shows the test setup for the 16V charging SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 ER User Manual CS XUEPS2 60 FleXU CubeSat du gt Electronic Power System Part 01 00732 and 01 eo J4Qes 5 01120 Helix Building WSSP Glasgow G20 OSP UK Issue D Date 20 03 2014 Page 48 of 51 CLYDE SPACE EPS BCR_OUT ELECTRONIC LOAD DUMMY_LOAD DUMMY_LOAD PULL PIN BATT_POS BATTERY Figure 12 7 16V charge setup This setup should only be used for top up charge on the battery not for mission simulation testing SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 Ed GOD User Manual CS XUEPS2 60 FleXU CubeSat CLYDE re Electronic Power System Part 01 00732 and 01 lam 01120 Issue D Date 20 03 2014 Page 49 of 51 Helix Building WSSP Glasgow G20 OSP UK 13 DEVELOPER AIT AIT of the EPS with other CubeSat modules or subsystems is the respons
6. SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 User Manual CS XUEPS2 60 FleXU CubeSat Electronic Power System Part 01 00732 and 01 01120 Issue D Date 20 03 2014 Page 10 of 51 USM 01 00732 Helix Building WSSP Glasgow G20 OSP UK 4 ELECTRICAL CHARACTERISTICS Description Conditions Min Typical Max Unit 12W BCR 1 6 Input Voltage lt 8 26 lt Output Voltage gt Output Current EE al a 1 m ee OON DANS AAN Switching Frequency Efficiency 16 5V input Full Load Unregulated Battery Bus lt Output Voltage gt Output Current 62 Continuous operation Be E 4 1 Em ae Operating Frequency Efficiency 5V Bus Output Voltage 8 2V input Full Load gt Output Current Operating Frequency kHz Continuous operation EE 4 1 SV input Full Load 98 480 Efficiency 3 3V Bus Output Voltage lt Continuous operation E N 4 1 Operating Frequency Efficiency 3 3V input Full Load 98 12V Bus Output Voltage gt Output Current kHz Ples Output Current Continuous operation Fa FAN 12V input Full Load 96 Fa ii Transmission speed 100 Quiescent Operation Flight Configuration of Power Draw lm a ELE 0 15 w Switches L w H Physical Dimensions HREN kom Peg ig 95 15 24 mm bottom of next PCB in stack T
7. CS XUEPS2 60 FleXU CubeSat d m qT Electronic Power System Part 01 00732 and 01 io J4Yes 01120 Issue D Date 20 03 2014 Page 16 of 51 Helix Building WSSP Glasgow G20 OSP UK 7 2 Autonomy and Redundancy All BCR power stages feature full system autonomy operating solely from the solar array input and not requiring any power from the battery systems This feature offers inbuilt redundancy since failure of one BCR does not affect remaining BCRs The remainder of the power system is a robustly designed single string 7 3 Quiescent Power Consumption The quiescent power consumption of the EPS is 0 1W This number does not include the power used in the control circuitry of the power converters BCRs and PCMs as these numbers are included in the efficiency specifications 7 4 Mass and Mechanical Configuration The mass of the system is approximately 170g and is contained on a PC 104 size mother card and mounted daughter card compatible with the Cubesat Kit bus Other versions of the EPS are available without the Cubesat Kit bus header Figure 7 3 shows the connector configuration on the PCB 90 805 85 725 5 080 Figure 7 3 Connector layout SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 USM 01 00732 User Manual CS XUEPS2 60 FleXU CubeSat CLYDE gt Electronic Power System Part 01 00732
8. Oscilloscope e Multimeter e Electronic Load e Aardvark I C interface or other means of communicating on the IC bus CLYDE SPACE EPS ELECTRONIC LOAD DUMMY_LOAD PULL PIN BATT_POS BATTERY Figure 12 1 Suggested Test Setup The breakout connector should be wired with the switch configuration to be used under mission conditions 12 1 Power up Down Procedure The test setup should be assembled following the order detailed below e Breakout connector assembled with switches set to launch vehicle configuration as shown in Figure 12 1 e Fit Breakout connector to EPS e Connect battery to stack e Connect electronic load no load to buses e Remove Pull Pin e Connect array input When powering down this process should be followed in reverse SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 pena ie Electronic Power System Part 01 00732 and 01 SPACE 01120 p Helix Building WSSP Issue D Date 20 03 2014 Page 45 of 51 Glasgow G20 OSP UK User Manual CS XUEPS2 60 FleXU CubeSat CLYDE qT 12 2 Battery Setup The system should be tested with a battery in the system This can be done using a Clyde Space Battery by stacking the boards or by using a power supply and load to simulate the behavior of a battery This setup is shown in Figure 12 2 CLYDE SPACE EPS BATT_POS H2 33 34 Electronic Load Power Supply
9. ROL a 3 0 Recommended Table 6 1 Materials List Part Used Manufacturer Contact Insulator Use Solar Array DF13 6P ieee Gold Beide Connectors and 1 25DSA 50 Plated Pretinned Y Charging Connector Gold Solar Array DF13 6P 1 25H 50 H Pol id 50 Plated Pretinned Connectors i CubeSat Kit ESQ 126 39 G D Samtec Gold Plated piach beastie Compatible Polyester Headers Harness for Solar DF13 6S 1 25C Hirose Polyamide i i Arrays sold separately Harness for Solar DF13 2630SCFA 04 Hirose Gold Plated i Arrays sold separately COPPER ALLOY PER MIL DTL LIQUID CRYSTAL Solar Array a Snes 32139 GOLD POLYMER LCP Connectors PLATED COPPER ALLOY PER MIL DTL LIQUID CRYSTAL Solar Array A23100 021 Omnetics 32139 GOLD POLYMER LCP MY Connectors PLATED Table 6 2 Connector Headers 6 2 Processes and Procedures All PCB assembly is carried out and inspected to ESA Workmanship Standards ECSS O ST 70 08C and ECSS Q ST 70 38C SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 pean ie Electronic Power System Part 01 00732 and 01 SPACE 01120 Issue D Date 20 03 2014 Page 13 of 51 User Manual CS XUEPS2 60 FleXU CubeSat e 4 re Helix Building WSSP Glasgow G20 OSP UK 7 SYSTEM DESCRIPTION This Clyde Space EPS is optimised for Low Earth Orbit LEO missions with a maximum altitude of 850km and is designed for integration w
10. SYS 3 3V Regulated Bus Output BATT POS 2 33 34 SWO Positive Terminal of Battery not Battery Bus DO NOT CONNECT TO ANYTHING OTHER THAN PULL PIN TERMINAL PCM IN 2 35 36 SW1 Input to PCMs and PDMs Switches gt DUMMY LOAD 2 37 38 SW2 Switches gt N C 2 39 40 SW3 Switches N C BCR OUT 2 41 44 sw4 Output of BCRs gt Switches BCR OUT 2 41 44 SW5 Output of BCRs 3 Switches BATTERY BUS 2 45 46 VBATT Battery Unregulated Bus Output Table 8 12 Header pin name descriptions relating CubeSat Kit names to CS names SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 USM 01 00732 User Manual CS XUEPS2 60 FleXU CubeSat CLYDE rs Electronic Power System Part 01 00732 and 01 io J4Yes 01120 Issue D Date 20 03 2014 Page 29 of 51 Helix Building WSSP Glasgow G20 OSP UK 8 6 Switch Options The Clyde Space EPS 01 00732 has three connection points for switch attachments as shown in Figure 8 6 There are a number of possible switch configurations for implementation Each configuration must ensure the buses are isolated from the arrays and battery during launch The batteries should also be isolated from the BCRs during launch in order to conform to CubeSat standard RD 1 CLYDE SPACE EPS 1 BATT_POS CLYDE SPACE BATTERY Figure 8 6 Switch Configuration Options 1 and 2 below are two suggested methods of switch configu
11. Set to 0 5A draw 7 74V 1 2A Figure 12 2 Simulated Battery Setup 12 3 Solar Array Input There are 3 options for the array input section e Asolar array e Asolar array simulator e A benchtop power supply with current limiting resistor When using a solar array or solar array simulator the limits should not exceed those outlined in Table 12 1 Isc mA Table 12 1 solar array limits When using a power supply and resistor setup to simulate a solar panel the required configuration is shown in Figure 12 3 SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 USM 01 00732 User Manual CS XUEPS2 60 FleXU CubeSat CLYDE gt Electronic Power System Part 01 00732 and 01 lam 01120 Issue D Date 20 03 2014 Page 46 of 51 Helix Building WSSP Glasgow G20 OSP UK Array Input CLYDE SPACE DEPS Power Supply Set limits V 20V I 1 24 Figure 12 3 Solar Panel using power supply 124 Configuration and Testing The following section outlines the procedure for performing basic functional testing PCM Testing In order to test the PCMs connection to a battery source must be implemented In order to do this the Pull Pin and Separation Switch should be removed connecting the battery as shown in Figure 12 4 CLYDE SPACE EPS BCR_OUT SEPARATION SWITCH No Input ELECTRONIC LOAD DUMMY_LOAD PULL PIN BATT_POS Figure 12 4 Test
12. The use of a BUCK converter offers significant increases in efficiency under most conditions over a SEPIC topology With input voltages between 10V and 24V the design will operate at peak efficiency If the input voltage drops to between 8 9V and 10V the solar panels will move away from their Maximum Power Point This is because the converter will reach its maximum allowable duty cycle The loss in efficiency will only occur under the worst case conditions of hot temperatures at end of life as the solar panel output voltages decrease 9 3 MPPT Each of the BCRs can have two solar arrays connected at any given time only one array can be illuminated by sunlight although the other may receive illumination by albedo reflection from earth The dominant array is in sunlight and this will operate the MPPT for that BCR string The MPPT monitors the power supplied from the solar array shown in Figure 9 2 This data is used to calculate the maximum power point of the array The system tracks this point by periodically adjusting the BCRs to maintain the maximum power derived from the arrays This technique ensures that the solar arrays can deliver much greater usable power increasing the overall system performance Increasing Temperature VERRE ERK ene ene Maximum Power Point Array Current Increasing Temperature Vmpp Vo c Array Voltage Figure 9 2 Solar Array Maximum Power Point The monitoring of the MPP is done approximately every 2 5 se
13. and 01 lay 01120 Issue D Date 20 03 2014 Page 17 of 51 Helix Building WSSP Glasgow G20 OSP UK 8 INTERFACING The interface to the EPS is outlined in Figure 8 1 including the solar array inputs connection to the switch configuration output of the power buses and communication to the 1 C node In the following section it is assumed that the EPS will be integrated with a Clyde Space 3U Battery BCR_OUT Switch Configuratio As Defined B User i2c node BEEK vyyvy TELEMETRY Figure 8 1 Clyde Space EPS and Battery Simplified Connection Diagram 8 1 Connector Layout The connector positions are shown in Figure 7 3 and described in Table 8 1 Connectors J1 and J2 are only available on the 01 01120 version of the FlexU 6 0 EPS Connectors SA1 to SA6 are available on both the 01 01120 and 01 00732 versions SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 Hos ie Electronic Power System Part 01 00732 and 01 SPACE 01120 Issue D Date 20 03 2014 Page 18 of 51 User Manual CS XUEPS2 60 FleXU CubeSat CLYDE re Helix Building WSSP Glasgow G20 OSP UK Connector Function Connector Type J1 only on 01 Solar Array connector for BCRs A29200 021 01120 1 3 J2 only on 01 Solar Array connector for BCRs A29100 021 01120 4 6 SA1 Array connector for 12W DF13 6P 1 25DSA 50
14. be shorted to ground leading to catastrophic failure of the battery and damage to the EPS Failure to observe these precautions will result in the voiding of any warranty When the battery is connected to the EPS the battery will be isolated until implementing and connecting a switch configuration as discussed in Section 8 6 Ensure that the battery is fully isolated during periods of extended storage SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 coio User Manual CS XUEPS2 60 FleXU CubeSat CLYDE re Electronic Power System Part 01 00732 and 01 lay 01120 A y p Helix Building WSSP Issue D Date 20 03 2014 Page 31 of 51 Glasgow G20 OSP UK When a battery board is connected to the CubeSat Kit header there are live unprotected battery pins accessible H2 33 34 These pins should not be routed to any connections other than the switches and Clyde Space EPS otherwise all protections will be bypassed and significant battery damage can be sustained 8 8 Buses All power buses are accessible via the CubeSat Kit headers and are listed and described in Table 8 11 These are the only power connections that should be used by the platform since they follow all battery and bus over current protections SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 SE Electronic Power S
15. fitted on the EPS Option 2 CLYDE SPACE EPS SEPARATION SWITCH 1 mM NC DUMMY_LOAD SEPARATION SWITCH 2 BATT_POS CLYDE SPACE BATTERY Figure 8 8 Switch Configuration Option 2 Option 2 shown in Figure 8 8 is compatible with structures incorporating two separation switches providing complete isolation in the launch configuration In the configuration shown above the dummy load will be in circuit until deployment of separation switch 2 Care should be taken to ensure that the switches used are rated to the appropriate current levels Please contact Clyde Space for information on implementing alternative switch or dummy load configurations Dummy Load The Dummy Load provides an additional ground support protection system providing a load for the BCRs when the pull pin is inserted using the normally open NO connection of the Pull Pin By connecting this Dummy Load to the NO pin BCR damage can be circumvented The wiring arrangement for the dummy load is indicated in Figure 8 8 The load protects the battery charge regulator from damage when the 16V charge or array power is attached and the batteries are not connected This system is not operational during flight and is only included as a ground support protection 8 7 Battery connection Connection of the battery systems on the EPS is via the Cubesat kit bus Ensure that the pins are aligned and located in the correct position as any offset can cause the battery to
16. set up with Pull Pin Removed In this configuration all buses will be activated and can be measured with a multimeter By increasing the load on each of the buses you will be able to see the current trip points activation as discussed in section 10 1 Undervoltage Protection When using a simulated battery it is possible to trigger the undervoltage protection Using the same test setup as detailed in Figure 12 2 and Figure 12 4 if the voltage is dropped to below 6 2V the undervoltage will be activated This can be observed by the buses shutting down SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 USM 01 00732 User Manual CS XUEPS2 60 FleXU CubeSat e 4 e b Electronic Power System Part 01 00732 and 01 io J4Yes 01120 Issue D Date 20 03 2014 Page 47 of 51 Helix Building WSSP Glasgow G20 OSP UK BCR Testing In order to test the operation of the BCRs the separation switches and pull pin should be placed in their flight configuration as shown in Figure 12 5 Once this is done the array input can be connected CLYDE SPACE EPS Array Input ELECTRONIC LOAD DUMMY_LOAD ay PULL PIN Figure 12 5 Test set up in Flight Configuration To check the operation of the BCR MPPT an oscilloscope probe should be placed at pin 1 of the active solar array connector not at the power supply The wave form should resemble Figure 12 6
17. 0 FleXU CubeSat Electronic Power System Part 01 00732 and 01 01120 Date 20 03 2014 USM 01 00732 Helix Building WSSP Glasgow G20 OSP UK Issue D Page 38 of 51 commands which have no specific requirement for a parameter input the second data byte should be set to 0x00 In a read command the first data byte represents the most significant byte of the result and the second data byte represents the least significant byte Before sending a command the master is required to set a start condition on the I C bus Between each byte the receiving device is required to acknowledge receipt of the previous byte in accordance with the I C protocol This will often be accommodated within the driver hardware or software of the I C master being used as the OBC however the user should ensure that this is the case The read and write command definitions are illustrated in Table 11 1 Address Byte Byte 1 Byte 2 wile S 7 bit node address w E Command A Parameter A Command nend S 7bitnodeaddress R mA Reply MSB A Reply LSB NP Command Ply DIY S Start Condition P Stop Condition Transmitted from Master OBC A Acknowledge W Write bit N Not Acknowledged R Read bit Ej Transmitted from Slave TTC node Table 11 1 C Write and Read command packets An example of using the read and write commands is provided below In this example the OBC is requesting a tel
18. 20 03 2014 Page 26 of 51 eee 8 4 CubeSat Kit Compatible Headers Connections from the EPS to the buses of the satellite are made via the CubeSat Kit compatible headers H1 and H2 as shown in Figure 8 5 H2 H1 BATT BAT BUS siele 33VBUS GND pos PCM IN BCR OUT 12V BUS DUMMY LOAD 12C DATA 12C CLK Figure 8 5 EPS Connector Pin Identification SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 User Manual CS XUEPS2 60 FleXU CubeSat Electronic Power System Part 01 00732 and 01 USM 01 00732 Issue D Date 01120 20 03 2014 Page 27 of 51 Helix Building WSSP Glasgow G20 OSP UK 8 5 Cubesat Kit Header EE 2 E m D gt le m a a Use Not Connected Ne z 5 Not Connected Not Connected o Not Connected Not Connected Not Connected Not Connected Not Connected women OU ff Not Connected Pin Out Notes Not Connected Not Connected Not Connected Not Connected Not Connected Not Connected Not Connected Not Connected Not Connected pp i z z ojojojojo NC Not Connected Not Connected Not Connected Not Connected 5 re N e 10 11 HEADER 2 U se Not Connected Not Connected Name NC NC NC NC NC NC Not Connected Not Connected Not Connected Not Connected NC Not Connected NC Not Connected NC Not Connected Notes Not Connected Not C
19. 4 Electrical Characteristics AR RA OE EE N 10 Ad BCR Safe Operating Area ARE EE DE EE AEST E eee eee 11 5 Handling and Storages ed ee ged ee ie Ed ke ee ee Vee gee Ge ed coo 11 5 1 Electro Static Discharge ESD Protection cscccssccssscessecsseeceeecsseceseessneceseessnsesaeessaeeseessaeessneeenees 11 PA Handling SA RE N EO EO N 11 5 3 Shipping arid Storage OE RE A EE EE EE 11 6 Materials and N dels ON EE N N N osiinsa soisi di antea 12 6 1 SA EE OE AE EE IG 12 6 2 Processes and Procedures cesccesecceccesseereseecsenecsnereaeeceeesanecseeeeseecseeeconereaeeeaeesaneseneneseessenensnereaees 12 7 System Description ada EE 13 7 1 System OVENWVI ARE EE IR EE EA ER EE EG 15 1 2 Autonomy and Redundancy sie cine EER Ke ORR Eg ERGE KERSE RR eN ee dea ee bg Fee rede Ese 16 73 Quiescent Power Consumption ees ee RA RA RA ee ee ee ee ee ee ee ee 16 7 4 Mass and Mechanical Configuration oooocccnnccnonnnoncnonnncnonnnonnnnnnnnonn Re Re Re Re RA Re ede Re ee ee 16 8 Mid ei RE OE OE RE N 17 8 1 Connector LAV OUT ii ee A EE DE ee Ge 17 8 2 Solar Array CONNECTION OR N EE N 18 8 3 Solar Array Harness sree OE IE tt ET ER EE 25 84 CubeSat Kit Compatible HeaderS iese ee Re ER RA Re RA Re Re Re ee Re ee ee ee ee ee ee ee ee 26 8 5 Cubesat Kit Header Pin OUE ies ESE EER EG GEE oe e 27 S6 SWITCHIOPTIONS AE a e N EO EE EE N RO N ON 29 8 7 BatteryconnectOR is EER EIERS EE ees SG a asias 30 8 8 EVER EE EE 31 9 AE Te ooi
20. 50ms Test period 31ms 3 3V bus Shutdown period 750ms Test period 31ms 12V bus Shutdown period 750ms Test period 60ms Table 10 1 Bus protection data SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 User Manual CS XUEPS2 60 FleXU CubeSat CLYDE re HARDE NN Electronic Power System Part 01 00732 and 01 oy J4Ye3 01120 Issue D Date 20 03 2014 Page 36 of 51 rei 10 2 Battery Under voltage Protection In order to prevent over discharge of the battery the EPS has in built under voltage shutdown This is controlled by a comparator circuit with hysteresis In the event of the battery discharging to 6 2V the EPS will shut down the supply buses This will also result in the 1 C node shutting down When a power source is applied to the EPS e g an illuminated solar panel the battery will begin charging immediately The buses however will not reactivate until the battery voltage has risen to 7V This allows the battery to charge to a level capable of sustaining the power lines once a load is applied It is recommended that the battery state of charge is monitored by the on board computer of the satellite and loading adjusted appropriately turning off of non critical systems when the battery capacity is approaching the lower limit This will prevent the hard shutdown provided by the EPS SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROP
21. Connected Not Connected DATA connection must fit to operate 24 25 26 27 28 29 30 31 EE 34 35 36 37 38 39 D i Not Connected Not Connected Ground System power GND Tm connection return connection Not Connected connection Dummy Load Prote n Dummy Load Protection E Not Connected Not Connected L ne e e i E E E System power return Not Connected System power return Pull pin normally connected pin Pull pin normally connected pin Sep SW normally connected pin Sep SW normally connected pin Pull pin normally open pin Pull pin normally open pin Not Connected Not Connected Common point PP SS pins Common point PP SS pins Common point PP SS pins Common point PP SS pins Output to batt bus Output to batt bus Not Connected Not Connected Not Connected Not Connected Regulated 12 bus Regulated 12 bus Table 8 11 Pin Descriptions for Header H1 and H2 SOLUTIONS FOR A NEW AGE IN SPACE PROPRIETARY amp CONFIDENTIAL INFORMATION www clyde space com Clyde Space Limited 2014 User Manual CS XUEPS2 60 FleXU CubeSat ii Electronic Power System Part 01 00732 and 01 Unused connection of launch switch closed state 01120 Helix Building WSSP Issue D Date 20 03 2014 Page 28 of 51 Glasgow G20 OSP UK NODE HEADER CUBESAT KIT NAME NOTES 5V BUS 2 25 26 5V Regulated Bus Output 3 3V BUS 2 27 28 VEE
22. EPS is a static sensitive system Failure to observe ESD precautions can result in failure of the EPS Ensure not to exceed the maximum stated limits Exceeding any of the stated maximum limits can result in failure of the EPS Ensure batteries are fully isolated during storage If not fully isolated by switch configuration or separation the battery may over discharge resulting in failure of the battery No connection should be made to H2 35 36 These pins are used to connect the battery to the EPS Any connections to the unregulated battery bus should be made to pins H2 43 44 H1 and H2 pins should not be shorted at any time These headers have exposed live pins which should not be shorted at any time Particular care should be taken regarding the surfaces these are placed on SOLUTIONS FOR A NEW AGE IN SPACE PROPRIETARY amp CONFIDENTIAL INFORMATION www clyde space com Clyde Space Limited 2014 User Manual CS XUEPS2 60 FleXU CubeSat A Electronic Power System Part 01 00732 and 01 01120 Issue D Date 20 03 2014 Page 4 of 51 Ep A Table of Contents 1 A EN OE NN 6 1 1 Additional Information Available Online 00 ee ceeceeseseceseeeeeeseceeeseeeeeeaecseceaeeneeeaeceeeeaeeaeeeaesaeeeaeeneeeas 6 1 2 Continuous Improvement EE EE ES REEN iio IE oe GE ee RR 6 1 3 Document REVISIONS EE EE EE EE RE EE RE OE OO NE EE Aaaa 6 2 Bed EE OR RE OE EE ON 7 3 Maximum Ratings NE AA e ata E 8
23. L INFORMATION Clyde Space Limited 2014 USM 01 00732 User Manual CS XUEPS2 60 FleXU CubeSat e 4 e qT Electronic Power System Part 01 00732 and 01 lam 01120 A Helix Building WSSP Issue D Date 20 03 2014 Page 35 of 51 Glasgow G20 OSP UK 10 GENERAL PROTECTION The EPS has a number of inbuilt protections and safety features designed to maintain safe operation of the EPS battery and all subsystems supplied by the EPS buses 10 1 Over Current Bus Protection The EPS features bus protection systems to safeguard the battery EPS and attached satellite sub systems This is achieved using current monitors and a shutdown network within the PDMs Over current shutdowns are present on all buses for sub system protection These are solid state switches that monitor the current and shutdown at predetermined load levels see Table 10 1 The bus protection will then monitor the fault periodically and reset when the fault clears This is illustrated by the waveform in Figure 10 1 EVENT TEST SYSTEM SHUTDOWN TEST PERIOD CLEARS PERIOD RESUME OVER CURRENT SYSTEM EVENT i BUS VOLTAGE Y CURRENT NORMAL LEVEL NORMAL NORMAL OPERATION OPERATION f al Shutdown period Shutdown period Shutdown period Figure 10 1 Current protection system diagram Trip point trip duration approximation Battery Bus Shutdown period 750ms Test period 60ms 5V bus Shutdown period 7
24. Part 01 00732 and 01 01120 Issue D Date 20 03 2014 Page 51 of 51 USM 01 00732 Helix Building WSSP Glasgow G20 OSP UK 14 COMPATIBLE SYSTEMS Compatibility CubeSat Kit Bus CubeSat Kit definition pin compatible Stacking Non standard Wire Connector User defined Connector Other Connectors Please contact Clyde Space Clyde Space 3U Battery Systems 10W hr 30 W hr Lithium lon Polymer Lithium Polymer 8 2v 2s1p to 2s4p More strings can be connected in parallel to increase capacity if required Batteries Lithium lon 8 2v 2s1p to 2s4p More strings can be connected in parallel to increase capacity if required Other Batteries Please contact Clyde Space Clyde Space 12W solar array Connects to BCR 1 6 Sitar ARYE 12W triple junction cell arrays 4 8 in series connection Other array technologies Any that conform to the input ratings for Voltage and Current Pumpkin CubeSat 3U structure Structure ISIS CubeSat 3U compatible Other structures Please contact Clyde Space Table 14 1 Compatible Systems 1 Refers to series and parallel connections of the battery cells within the battery system e g 2s1p indicates a single string of two cells in series 2 Will require some alteration to MPPT Please contact Clyde Space SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014
25. RIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 USM 01 00732 User Manual CS XUEPS2 60 FleXU CubeSat CLYDE gt Electronic Power System Part 01 00732 and 01 lam 01120 Issue D Date 20 03 2014 Page 37 of 51 Helix Building WSSP Glasgow G20 OSP UK 11 Telemetry The telemetry node allows the satellite on board computer OBC to monitor the operation of the EPS and reset the power buses if this is required for payload or platform recovery operations The telemetry node consists of a microcontroller which interfaces to the various telemetry sensing circuits on the EPS through an analogue multiplexer The microcontroller is configured to connect through a buffer circuit to the 1 C bus of the satellite as a slave node In response to I C telemetry requests the microcontroller will configure the analogue multiplexer to connect the desired telemetry channel to the analogue to digital converter ADC within the microcontroller before sampling the desired channel and allowing it to be read back over the I C bus In response to a telecommand the telemetry node will decode the incoming message and reset the desired power bus The key elements of the I C node are illustrated in Figure 11 1 BEE Sensing gt Current Canca CUTARRAY Sense C BCR Sanco Sensing j Current AMUX x2 i as Sensing
26. ROR User Manual CS XUEPS2 60 FleXU CubeSat CLYDE qT Electronic Power System Part 01 00732 and 01 lam 01120 Issue D Date 20 03 2014 Page 23 of 51 Helix Building WSSP Glasgow G20 OSP UK Pin Name Notes Use 1 Array1 Temp Array Telemetry Telemetry P RTN and GND ti 3 Array1 RTN Ground Line OWEN an ea for Temp Sensor 4 Array1 Temp Array Telemetry Telemetry Array2 RTN Ground tide Power RTN and GND connection for Temp Sensor Power Array2 RTN askies connection 1o Array2 Power vi ESA we AS ee E Array1 RTN ese connection Power RTN and GND connection 18 Array3 RTN Ground Line w l for Temp Sensor 21 Array3 RTN Ground time Power RTN and GND connection for Temp Sensor Table 8 9 Pin out for Header J1 SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 ERROR User Manual CS XUEPS2 60 FleXU CubeSat CLYDE qT Electronic Power System Part 01 00732 and 01 io J4Qes 5 01120 Issue D Date 20 03 2014 Page 24 of 51 Helix Building WSSP Glasgow G20 OSP UK Pin Name Notes Use 1 Array4Temp Array Telemetry Telemetry 3 Array4 RTN Ground iine Power RTN and GND connection for Temp Sensor 4 Array4 Temp Array Telemetry Telemetry P RTN and GND ti Array4 RTN Ground Line Pwer di An for Temp Sensor Power Array5 RTN sio de connection Array5 Power vie we HE Mk Ed EE ed Array5 RTN Re
27. Review of all AIT procedural plans identifying equipment and personnel needs and outlining clear pass fail criteria e Dry runs of the procedures in the plan Obviously testing and analysis is not possible for all aspects of a subsystem specification and Clyde Space is able to provide data on operations which have been performed on the system as detailed in Table 13 1 SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 USM 01 00732 User Manual CS XUEPS2 60 FleXU CubeSat CLYDE b Electronic Power System Part 01 00732 and 01 Fo J4Qes 01120 Issue D Date 20 03 2014 Page 50 of 51 Helix Building WSSP Glasgow G20 OSP UK Performed on NENE funciona calibration Vacuum Simulation amp modelling Not performed Not available Table 13 1 Acceptance test data Following this review it is recommended the system undergoes further testing for verification against the developer s own requirements An example compliance matrix structure is shown in Table 13 2 ID Reguirement Procedure Result X Success Compliance criteria ke pass fail SYS 0030 The system mass shall TEST O1 0 957 kg X lt 1kg PASS be no more than 1 kg SYS 0040 The error LED remains TEST 02 LED flashing LED off FAIL off at initialisation Table 13 2 Compliance matrix example All procedural plans carried out on the EPS should conform to the test setu
28. XUEPS2 60 FleXU CubeSat Electronic Power System Part 01 00732 and 01 01120 Issue D Date 20 03 2014 Page 43 of 51 USM 01 00732 Helix Building WSSP Glasgow G20 OSP UK ADC Channel Signal Name Connector Equation Units 12 0x0C Array2 Temp SA2 3 Temperature 0 163 x ADCcount 110 8611 i o o 2 E o o o 32 0x20 BatV Bus Current H2 45 H2 46 Current 5 4311 x ADCcount 4636 0085 33 0x21 12V Bus Current H2 51 H2 52 Current 5 4312 x ADCcount 5285 093 Table 11 5 ADC Channels mA mA C mA mA mA mA mA C mA mA mA mA e mA C mA mA mA mA SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 USM 01 00732 User Manual CS XUEPS2 60 FleXU CubeSat e 4 gt Electronic Power System Part 01 00732 and 01 lay 01120 Issue D Date 20 03 2014 Page 44 of 51 12 TEST All EPS are fully tested prior to shipping and test reports are supplied In order to verify the operation of the EPS please use the following outlined instructions Helix Building WSSP Glasgow G20 OSP UK In order to test the functionality of the EPS you will require e Battery compatible with Clyde Space EPS or simulated battery e Breakout Connector with connections as per Figure 12 1 e Array Input test panel solar array simulator or power supply and limiting resistor e
29. able 4 1 Performance Characteristics of the EPS Operating Freguency kHz Efficiency Communications Protocol Kbps i it SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 EO Ne Electronic Power System Part 01 00732 and 01 oy J4Yes gt 01120 Issue D Date 20 03 2014 Page 11 of 51 User Manual CS XUEPS2 60 FleXU CubeSat da du qT Helix Building WSSP Glasgow G20 OSP UK 4 1 BCR Safe Operating Area Single Channel Current A 15 20 Voltage V Figure 4 1 BCR Safe Operating Range The safe operating range of the BCRs is shown in Figure 4 1 Single Channel refers to the maximum power that can be applied to a single pin e g SA1 1 Dual Channel refers to the maximum power that can be applied to two pins connecting to the same BCR e g SA1 1 and SA1 4 5 HANDLING AND STORAGE The EPS requires specific guidelines to be observed for handling transportation and storage These are stated below Failure to follow these guidelines may result in damage to the units or degradation in performance 5 1 Electro Static Discharge ESD Protection The EPS incorporates static sensitive devices and care should be taken during handling Do not touch the EPS without proper electrostatic protection in place All work carried out on the system should be done in a static dissipative environment 5 2 General Handling
30. arrays SA2 Array connector for 12W DF13 6P 1 25DSA 50 arrays SA3 Array connector for 12W DF13 6P 1 25DSA 50 arrays SAA Array connector for 12W DF13 6P 1 25H 50 arrays SAS Array connector for 12W DF13 6P 1 25H 50 arrays SAG Array connector for 12W DF13 6P 1 25H 50 arrays Cubesat Kit bus compatible ESQ 126 39 G D H1 Header 1 Cubesat Kit bus compatible ESQ 126 39 G D H2 Header 2 CH1 Ground Charging for batteries DF13 6P 1 25DSA 50 Table 8 1 Connector functions 8 2 Solar Array Connection The standard approach for connecting solar arrays to the 01 00732 and 01 01120 EPS are through the connectors SA1 to SA6 The 01 01120 EPS also has additional interfaces allowing arrays 1 to 3 to be connected through a single harness to J1 and arrays 4 to 6 through a second harness to J2 Both of these interfaces accommodate power inputs from the arrays with temperature telemetry for each See Section 4 1 for details on limits of safe operation for the BCRs SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 DEE User Manual CS XUEPS2 60 FleXU CubeSat CLYDE b Electronic Power System Part 01 00732 and 01 Hi J4Yes 01120 i Helix Building WSSP Issue D Date 20 03 2014 Page 19 of 51 Glasgow G20 OSP UK Max Cells CLYDE SPACE EPS EIA DINTA S ti rie mm CNM 1 EA Ed 5 E 4 r s BCR OUT S S S S S Solar A
31. at 8 2V i f L 4 8 0 8 Aa 0 6 ri lt vo o 6 5 taper charge end of 04 e he 5 discharge E gt voltage 6 0 2 constant current 55 7 charge again constant current discharge 0 5 charge inode on orbit charge current is proportional to solar panel illumination H 0 2 4 5 7 conditions 4 i 0 4 0 5000 10000 15000 20000 25000 30000 Time s Figure 9 1 Tapered charging method SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 Ed GOD User Manual CS XUEPS2 60 FleXU CubeSat CLYDE re Electronic Power System Part 01 00732 and 01 lay 01120 Issue D Date 20 03 2014 Page 33 of 51 Helix Building WSSP Glasgow G20 OSP UK 9 2 BCR Power Stage Overview As discussed in section 7 the EPS has six separate independent BCRs each designed to interface to two parallel solar arrays configured to have a combined output of no greater than 12W e g a seven cell string on one face of the satellite connected to a seven cell string on the opposing face Each of the 12W BCRs interface to the main body and deployed panels with up to 7 triple junction cells in series The design offers a highly reliable system that can deliver 90 or greater of the power available from the solar array network at full load 12W BCR power stage The 12W BCR is a BUCK converter allowing the BCR to interface to strings with four to seven cells in series
32. ccurred Reset Occurred when read 0 C Error No I C Errors 12C Error Occurred Bit afd when read 1 PC Write Collision NaPewihetollision 16 WHE Colisi n Occurred 2 2 2 C Overflow No I C Overflow re emag Occurred 3 Received Massage to Long Received Messages Last Message Correct Length incorrect Length 4 7 Not Used Reads as 0 Table 11 3 Status Bytes BUS Off The user can turn off any of the power buses in the EPS for a short period in order to trigger a hard reset of any connected systems The command 0x02 is sent followed by a parameter byte which determines which bus should be reset Details of the bus reset flags are provided in Table 11 4 Setting the appropriate bit to 1 will trigger a reset of the bus Any combination of buses can be turned off however it should be noted that if the 3 3V PDM is switched off the 1 C node will be reset SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 User Manual CS XUEPS2 60 FleXU CubeSat Electronic Power System Part 01 00732 and 01 01120 Issue D Date 20 03 2014 Page 41 of 51 USM 01 00732 Helix Building WSSP Glasgow G20 OSP UK Description If Low 0 If High 1 O LSB Battery Bus Reset Flag Bus remains active Bus will be reset a 5V Bus Reset Flag Bus remains active Bus will be reset 2 3V3 Bus Reset Flag Bus remains active Bus will be reset 3 12V Bus Res
33. conds During this tracking the input of the array will step to o c voltage as shown in Figure 9 3 SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 USM 01 00732 User Manual CS XUEPS2 60 FleXU CubeSat CLYDE gt Electronic Power System Part 01 00732 and 01 lam 01120 Issue D Date 20 03 2014 Page 34 of 51 Helix Building WSSP Glasgow G20 OSP UK Noise Filter Off 400ms Figure 9 3 Input waveform with Maximum Power Point Tracking 9 4 5V and 3 3V PCM The 5V and 3 3V regulators both use buck switching topology regulators as their main converter stage The regulator incorporates intelligent feedback systems to ensure the voltage regulation is maintained to 2 deviation The efficiency of each unit at full load is approximately 96 Full load on the 3V3 and 5V regulators have a nominal output current of 4 1A Each regulator operates at a frequency of 480 kHz 9 5 12V PCM The 12V regulator uses a boost switching topology regulator as the main converter stage The regulator incorporates intelligent feedback systems to ensure the voltage regulation is maintained to 1 deviation The efficiency at full load is approximately 95 Full load on each of the regulator have a nominal output current of 1A The regulator operates at a frequency of 700 kHz SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIA
34. e Re eg ee ed AE RE ER N EE ON 32 Ne id Meth LA N EE OE EE OO ONE 32 9 2 BCR Power Stage Overnvie ARE EE EO KEN ER ER OE AE Id 33 9 3 la AE EE OE EE ER EE RR EE EE IG 33 9 4 BV GE VA die ER EE EE EE N N OE OE RE EER AE 34 9 5 AU EE EE EE ER NS LA ER 34 10 General ProtectiON essor OO EE EE EE 35 10 1 OversCutreintBus ProteCtOM iss ia pia 35 10 2 Battery Under voltage Protection ee RA RA Re RA Re Re Re Re Re Re RA ee ee ee ee ee 36 SOLUTIONSFORANEWAGEINSPACE wwwdydespacecom PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 User Manual CS XUEPS2 60 FleXU CubeSat CLYDE re HEN ie Electronic Power Er 01 00732 and 01 SPACE Issue D Date 20 03 2014 Page 5 of 51 EE di 11 Ru EE EE EA RT 37 11 1 C Command Interface RE RE OE EE OO EE EE 37 11 2 Command SUN MV iii Ar idas 38 1153 ADC Channels ainia rin EE EE OE 42 12 DOSE APPO CPES E E 44 12 1 Power up Down Procedure sees ee Re ee AR AR AR AR ee Re ee ee ee ee ee ee ee ee ee ee ee 44 12 2 Battery SQtup EE EE OE EE EE EE EE Heres a 45 123 Solar Array Input A A de aaa 45 12 4 Configuration and Testing oooconccoconicnncnoncconanoncnonnnnannn ran Ge crac norris 46 13 Developer ORE EE EE EE AE EE EE EER N 49 14 Compatible RE EE EG 51 SOLUTIONS FOR A NEW AGE IN SPace wwwdydespacecom PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 USM 01 00732 User Manual CS XUEPS2 60 FleXU CubeSat CLYDE gt Electronic Power System Par
35. emetry reading of the solar array 1 input voltage Address Byte Byte 1 Byte 2 Address 0x2B write flag Command type 0 read ADC ADC Channel 5 Array 1 V wrie slo 1 o 1 01 lo o 0000000RM000001 01M Command Delay gt 1 2ms Address 0x2B read flag ADC result MSB AOE raun mee AE ele as Sii 1 91 Eo 00 000 01100 001 0 Command S Start Condition A Acknowledge N Not Acknowledged P Stop Condition W Write bit R Read bit Transmitted from Master OBC Ml transmitted from Slave TTC node If a read message which does not have a preceding write message is received by the telemetry node the value OxFOOO is returned All bit level communication to and from the board is done by sending the MSB first 11 2 Command Summary Table 11 2 provides a list of the commands for the EPS The parameter that should accompany the commands is included in the table Descriptions of the commands follow the table SOLUTIONS FOR A NEW AGE IN SPACE PROPRIETARY amp CONFIDENTIAL INFORMATION www clyde space com Clyde Space Limited 2014 USM 01 00732 User Manual CS XUEPS2 60 FleXU CubeSat CLYDE gt Electronic Power System Part 01 00732 and 01 io z7 e 01120 Issue D Date 20 03 2014 Page 39 of 51 Helix Building WSSP Glasgow G20 OSP UK Command Parameter Description Decimal Name Decimal o O suis l
36. et Flag Bus remains active Bus will be reset 4 Not Used a s 5 Not Used 6 Not Used 7 MSB Not Used Table 11 4 Bus Reset Parameter bit functions Version The firmware version number can be accessed by the user using this command Please contact Clyde Space to learn the version number on your board WatchDog The Watchdog command allows the user to force a reset of the I C node If the user detects or suspects an error in the operation of the IC node then this command should be issued When issued the 1 C node will reset and return to an initial state SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 User Manual CS XUEPS2 60 FleXU CubeSat e 4 re lea Electronic Power System Part 01 00732 and 01 io J4Yes dd 01120 A y p Helix Building WSSP Issue D Date 20 03 2014 Page 42 of 51 Glasgow G20 OSP UK 11 3 ADC Channels Each of the analogue channels when read returns a number between 0 1023 To retrieve the value of the signal this number represents it is to be entered into an equation Table 11 5 contains conversion equations for each of the channels Tailored equations for each individual build will be provided in the test report document supplied with the hardware SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 User Manual CS
37. etail in Sections 10 and 11 respectively SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 HEN ie Electronic Power System Part 01 00732 and 01 SPACE 01120 Issue D Date 20 03 2014 Page 14 of 51 User Manual CS XUEPS2 60 FleXU CubeSat e gm qT Helix Building WSSP Glasgow G20 OSP UK Z Array1 Y Array2 Z Array2 Y Arrayl X Array2 X Arrayl Y Array2 X Array2 Y Array1 X Arrayl Figure 7 1 Example Array Configuration SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 a User Manual CS XUEPS2 60 FleXU CubeSat CLYDE T Electronic Power System Part 01 00732 and 01 SPACE 01120 Issue D Date 20 03 2014 Page 15 of 51 Helix Building WSSP Glasgow G20 OSP UK 7 1 System Overview Figure 7 2 shows a details block diagram of the EPS H143 120 CLOCK HY dT aaa l BC DATA E g F 7 5149 2 17 BUS gt Fr H 77 28 2 2 2526 7 0 BUS HO 4546 RATTERY BUS E 8 hm 2 35 PE 8 H2 36 36 POM_IN hal INIA scr our Cr af bs a of Wes zl El d mol 2 Figure 7 2 Function Diagram SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 das User Manual
38. for every EPS manufactured and therefore may be different between flight and engineering model hardware Status The status bytes are designed to supply operational data about the 1 C Node To retrieve the two bytes that represent the status the command 0x01 should be sent followed by 0x00 as the status command has no parameter associated with it The meaning of each bit of the status byte is shown in Table 11 2 SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 User Manual CS XUEPS2 60 FleXU CubeSat Electronic Power System Part 01 00732 and 01 01120 Issue D Date 20 03 2014 Page 40 of 51 USM 01 00732 Helix Building WSSP Glasgow G20 OSP UK Bit Description If Low 0 If High 1 Last d Bit cl d 0 Unknown Command Type Last command OK ad SEER EA Unknown when read 1 A Last Command Value Last Command Bit cleared OK Value Out of Range when read 2 ADC Result Not Ready ADC Result Ready PDE SE Cit Ge aeara Ready when read 3 Not used Reads as 0 1 5 5 4 Er External Oscillator External Oscillator g running failure Watchd Reset Bit cl d 5 Watchdog Reset Occurred No Watchdog Reset PR oe do ME Occurred when read 6 Sawer OnResetOcc rted Power On Reset No Power On Reset Bit cleared Occurred Occurred when read 7 ER OE Brown Out Reset No Brown Out Bit cleared O
39. i 6 ARRAY6_TEMP_TELEM Array Telemetry Power RTN and GND connection for Temp Sensor Telemetry Power RTN and GND connection for Temp Sensor Telemetry Table 8 7 Pin out for Header SA6 SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 USM 01 00732 User Manual CS XUEPS2 60 FleXU CubeSat e 4 e gt Electronic Power System Part 01 00732 and 01 lam 01120 Issue D Date 20 03 2014 Page 22 of 51 Helix Building WSSP Glasgow G20 OSP UK Ground Charging connector Connector CH1 is designed to be used as a charging connector The pinout is shown in Table 8 8 Pin Name Use ve O Table 8 8 Pin out for Charging Header CH1 For Ground charging of battery For Ground charging of battery 1 2 3 4 Ground Return 5 Ground Return Grouped Connectors only present on 01 01120 model EPS An Omnetics connector A29200 021 is used on the 01 01120 mother board to route to BCRs 1 2 and 3 as described in Table 8 9 Similarly on the 01 01120 daughter board an Omnetics A29100 021 is used to interface to BCRs 4 5 and 6 as described in Table 8 10 These connectors are only fitted on the 01 01120 model EPS and are not included on the 01 00732 SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 ER
40. i connection Table 8 10 Pin out for Header J2 SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 USM 01 00732 User Manual CS XUEPS2 60 FleXU CubeSat CLYDE rs Electronic Power System Part 01 00732 and 01 io J4Yes 01120 Issue D Date 20 03 2014 Page 25 of 51 Helix Building WSSP Glasgow G20 OSP UK 8 3 Solar Array Harness Clyde Space supply harnesses sold separately to connect the solar panels to the EPS Temperature sensing telemetry is provided for each solar array connected to the EPS A compatible temperature sensor LM335M is fitted as standard on Clyde Space solar arrays The output from the LM335M sensor is then passed to the telemetry system via on board signal conditioning Due to the nature of the signal conditioning the system is only compatible with zener based temperature sensors i e LM335M or equivalent Thermistor or thermocouple type sensors are incompatible with the conditioning circuit Figure 8 4 provides a block diagram showing the connection of the temperature sensor CLYDE SPACE EPS Solar Array Figure 8 4 Temperature sensor block diagram SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 User Manual CS XUEPS2 60 FleXU CubeSat e M qT ARA Electronic Power System Part 01 00732 and 01 SPACE 01120 Issue D Date
41. ibility of the CubeSat developer Whilst Clyde Space outlines a generic process which could be applicable to your particular system in this section we are not able to offer more specific advice unless integration is between other Clyde Space products or compatible products see Table 14 1 AIT is at the risk of the developer and particular care must be taken that all subsystems are cross compatible Throughout the AIT process it is recommended that comprehensive records of all actions be maintained tracking each subsystem specifically Photo or video detailing of any procedure also helps to document this process Comprehensive records are useful to both the developer and Clyde Space in the event of any anomalies complete and rapid resolution will only be possible if good records are kept The record should contain at least e Subsystem and activity e Dates and times of activity start finish key milestones e Operator s and QAs e Calibration of any equipment e Other subsystems involved e Method followed e Success condition or results e Any anomalous behaviour Before integration each module or element should undergo an acceptance or pre integration review to ensure that the developer is satisfied that the subsystem meets its specification through analysis inspection review testing or otherwise Activities might include e Satisfactory inspection and functional test of the subsystem e Review of all supporting documentation e
42. ith spacecraft utilising up to 12 solar panel strings Various solar panel configurations can be accommodated including body mounted and deployable panels of various string lengths and has been designed to be versatile Please consult our support team if you have specific requirements for connecting the EPS to your spacecraft The Clyde Space EPS connects to the solar panels via six independent Battery Charge Regulators BCRs Each BCR can be connected to two solar arrays in parallel provided the connected panels cannot output a combined power greater than 12W There are a number of possible configurations that can be used depending on the deployment configuration An Example is shown in Figure 7 1 Please contact Clyde Space to discuss possible configurations Each of the BCRs has an inbuilt Maximum Power Point Tracker MPPT This MPPT will track the dominant panel of the connected pair the directly illuminated panel The output of the six BCRs are then connected together and via the switch network described in Section 7 2 supply charge to the battery Power Conditioning Modules PCMs and Power Distribution Modules PDMs The EPS has an unregulated Battery Voltage Bus a regulated 5V supply a regulated 3 3V supply and a regulated 12V supply available on the satellite bus The EPS also has multiple inbuilt protection methods to ensure safe operation during the mission and a range of telemetry via the 1 C network These are discussed in d
43. lding WSSP Glasgow G20 OSP UK 3 MAXIMUM Ratincs OVER OPERATING TEMPERATURE RANGE UNLESS OTHERWISE STATED BCR EI J1 pins 2 amp 5 or EE lame J1 pins 8 amp 11 or s J1 pins 13 or eran J2 pins 11 amp 8 or Unit lt lt lt V J2 pins 5 amp 2 or J2 pins 13 or SA6 pins 1 amp 4 BCR6 12W 30 V an S e E wu EE S E Gx f fes fh Paves ie i Value Unit mA mA mA mA mA mA mA mA mA Input Current mA mA mA mA SASA LECAS mA mA 55118040 mA mA mA mA A SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 User Manual CS XUEPS2 60 FleXU CubeSat Electronic Power System Part 01 00732 and 01 01120 Issue D Date 20 03 2014 Page 9 of 51 USM 01 00732 Helix Building WSSP Glasgow G20 OSP UK 3 3V Bus 3 3V 4 1 12V Bus 12V 1 1 Operating Temperature 40 to 85 is Storage Temperature 50 to 100 C gt ad eT EX Vacuum 10 torr kRad p UI Radiation Tolerance Table 3 1 Performance Characteristics of the EPS 1 Stresses beyond those listed under maximum ratings may cause permanent damage to the EPS These are the stress ratings only Operation of the EPS at conditions beyond those indicated is not recommended Exposure to absolute maximum ratings for extended periods may affect EPS reliability 2 De rating of power critical components is in accordance with ECSS guidelines
44. nection for Temp Sensor Telemetry Table 8 3 Pin out for Header SA2 Pin Name Us e ARRAYS 20 ARRAY3_TEMP_TELEM Array Telemetry ARRAYS 20 ARRAY3_TEMP_TELEM Array Telemetry Power RTN and GND connection for Temp Sensor Telemetry Power RTN and GND connection for Temp Sensor Telemetry Table 8 4 Pin out for Header SA3 SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 Hoes ie Electronic Power System Part 01 00732 and 01 SPACE 01120 Issue D Date 20 03 2014 Page 21 of 51 User Manual CS XUEPS2 60 FleXU CubeSat CLYDE qT Helix Building WSSP Glasgow G20 OSP UK Pin NET 0 se 1 E 3 ARRAY4_TEMP_TELEM Array Telemetry EME i 6 ARRAY4 TEMP TELEM Array Telemetry Power RTN and GND connection for Temp Sensor Telemetry Power RTN and GND connection for Temp Sensor Telemetry Table 8 5 Pin out for Header SA4 Pin Name U se ss 20 3 3 ARRAY5_TEMP_TELEM Array Telemetry N E 6 ARRAYS TEMP TELEM Array Telemetry Power RTN and GND connection for Temp Sensor Telemetry Power RTN and GND connection for Temp Sensor Telemetry Table 8 6 Pin out for Header SA5 Pin NET U se 1 SE 3 ARRAY6_TEMP_TELEM Array Telemetry EG
45. o N POM os 4 Version Read ADC Channel Request Status Bytes Turns off the selected PDM for a short time Request Firmware Version Watchdog Causes a soft reset of the microcontroller Table 11 2 Command Summary ADC Read This command is used to read a telemetry value from the EPS The command accepts a parameter which determines which ADC channel should be read A list of the ADC channels available is provided in Table 11 5 The data response to an ADC read command is a 10 bit unsigned value encoded in the two data bytes as shown in Figure 11 2 The first byte received contains the two most significant bits and the second byte received the remaining 8 bits If the ADC reading is not yet ready OxFOOO is returned MSB LSB PTT ET TE VA TENE First byte x wo Second byte Used bits Figure 11 2 ADC 10bit data packet The result received should then be entered into the conversion equations covered in section 11 3 which calculate the requested parameter in physical units The equations provided in section 11 3 are the theoretical equations for the system If more accurate telemetry results are required tailored equations are available from the test report for the individual board which will be supplied with the hardware The advantage of using tailored equations is that they compensate for component tolerances and parasitic losses in an individual build of an EPS however the tailored equations will vary slightly
46. onnected Not Connected Not Connected Not Connected Not Connected Not Connected Not Connected Not Connected Not Connected NC Not Connected NC Not Connected Not Connected 12 12 p w a ALT IC Alt IC clock Oohm resistor R265 Not Connected Not Connected e e ul 16 N w N N 4 Not Connected Not Connected Not Connected Not Connected N u E A EES oe 26 Not Connected Not Connected Not Connected Not Connected NC Not Connected Not Connected C NN o N N wo z Not Connected Not Connected w o Zz Not Connected NC Not Connected w N z O Not Connected w w O Not Connected w EF Not Connected Not Connected w a o Not Connected w N C Not Connected z Not Connected w A ow 2 C C Not Connected Not Connected PC DATA IC data A ad A N 2 C Not Connected PC CLK 1 C clock A w A A 2 Not Connected A uw NC NC Not Connected NC 9 o 1 2 Not Connected A uuu Ba 00 Not Connected Not Connected Not Connected Not Connected Not Connected Not Connected Not Connected Not Connected Not Connected Not Connected Not Connected 2 Data for I C communications Not Connected Clock for IC communications Not Connected Not Connected Not Connected 13 14 15 16 17 18 19 20 21 22 2 gt oT aly MEFE d sonm resistor nae 23 NC Not
47. ps and procedures covered in Section 0 During testing it is recommended that a buddy system is employed where one individual acts as the quality assurance manager and one or more perform the actions working from a documented and reviewed test procedure The operator s should clearly announce each action and wait for confirmation from their QA This simple practice provides a useful first check and helps to eliminate common errors or mistakes which could catastrophically damage the subsystem Verification is project dependant but should typically start with lower level subsystem specific requirements which can be verified before subsystems are integrated in particular attention should be paid to the subsystem interfaces to ensure cross compatibility Verification should work upwards towards confirming top level requirements as the system integration continues This could be achieved by selecting a base subsystem such as the EPS OBC or payload and progressively integrating modules into a stack before structural integration Dependent upon the specific systems and qualification requirements further system level tests can be undertaken When a subsystem or system is not being operated upon it should be stowed in a suitable container as per Section 5 SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 User Manual CS XUEPS2 60 FleXU CubeSat Electronic Power System
48. ration but are by no means exhaustive If you wish to discuss other possible configurations please contact Clyde Space Option 1 CLYDE SPACE EPS SEPARATION SWITCH m NIC a BCR_OUT o m DUMMY_LOAD L BATT POS CLYDE SPACE BATTERY Figure 8 7 Switch Configuration Option 1 Option 1 shown in Figure 8 7 accommodates the CubeSat Kit bus available switches offering two stage isolation The separation switch provides isolation of the power buses during the launch The pull pin may be used for ground based isolation of the batteries though it does not provide any isolation during launch NOTE The second generation Clyde Space EPS has zero current draw when the pull pin is removed i e there will be no current drawn from the battery while on the launch vehicle SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 USM 01 00732 User Manual CS XUEPS2 60 FleXU CubeSat e 4 b Electronic Power System Part 01 00732 and 01 Hi J4Yes 01120 Issue D Date 20 03 2014 Page 30 of 51 Helix Building WSSP Glasgow G20 OSP UK When pull pin is inserted the battery is isolated from the output of the BCRs Under these conditions if power is applied to the input of the arrays or by connecting the USB or charging connector there is a possibility of damaging the system In order to mitigate this risk a Dummy Load is
49. rray Figure 8 2 Solar Array Configuration Individual Connectors 01 00732 and 01 01120 HIROSE DP12 6P 1 25 DSA connector sockets are used on the EPS mother board and HIROSE DP12 6P 1 25H on the daughter board These are labelled SA1 SA6 and are routed to BCRs1 6 All BCRs are capable of interfacing to 12W panels and should be harnessed to arrays with multiples of 4 8 cell strings The pinouts of the connectors are shown in Table 8 2 to Table 8 7 with a figure indicating pin 1 of the connector shown in Figure 8 3 000000 2N0A00 Figure 8 3 Solar Array Pin Numbering SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 Hoes ie Electronic Power System Part 01 00732 and 01 SPACE 01120 Issue D Date 20 03 2014 Page 20 of 51 User Manual CS XUEPS2 60 FleXU CubeSat CLYDE qT Helix Building WSSP Glasgow G20 OSP UK Pin Name Use ARK 12 E ARRAY1 TEMP TELEM Array Telemetry EET WE ARRAY1 TEMP_TELEM Array Telemetry Power RTN and GND connection for Temp Sensor Telemetry Power RTN and GND connection for Temp Sensor Telemetry Table 8 2 Pin out for Header SA1 Pin Name Use SAKKE 12 ARRAY2_TEMP_TELEM Array Telemetry ARRAY 12 ARRAY2_TEMP_TELEM Array Telemetry Power RTN and GND connection for Temp Sensor Telemetry Power RTN and GND con
50. t 01 00732 and 01 E zJ e 5 01120 Issue D Date 20 03 2014 Page 6 of 51 Helix Building WSSP Glasgow G20 OSP UK 1 INTRODUCTION This document provides information on the features operation handling and storage of the Clyde Space FlexU 6 0 EPS The FlexU 6 0 EPS is designed to integrate with a suitable battery and with a maximum of 12 solar array strings to form a complete power system for use on a CubeSat or NanoSat Figure 1 1 provides a top level system diagram of the FlexU 6 0 EPS There are two variations on the FlexU 6 0 EPS the standard version has Clyde Space part number 01 00732 while the second version contains additional Omnetics connectors for solar array harnessing and is part number 01 01120 BCR_OUT Figure 1 1 System Diagram 1 1 Additional Information Available Online Additional information on CubeSats and Clyde Space Systems can be found at www clyde space com 1 2 Continuous Improvement Clyde Space is continuously improving its processes and products We aim to provide full visibility of changes and updates This information can be found at www clyde space com 1 3 Document Revisions In addition to hardware and software updates we also make regular updates to our documentation and online information Notes of updates to documents can also be found at www clyde space com SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limi
51. ted 2014 Ed GOD User Manual CS XUEPS2 60 FleXU CubeSat CLYDE re Electronic Power System Part 01 00732 and 01 oe J4Y e 5 01120 Issue D Date 20 03 2014 Page 7 of 51 Helix Building WSSP Glasgow G20 OSP UK 2 OVERVIEW This is the second generation of Clyde Space CubeSat Electronic Power System EPS developed by our team of highly experienced Spacecraft Power Systems and Electronics Engineers Since introducing the first generation in 2006 Clyde Space has shipped over 250 EPS to customers in Europe Asia and North America The second generation EPS builds on the heritage gained with the first whilst adding over 50 additional power delivery capability Furthermore we have also implemented an ideal diode mechanism to ensure zero draw on the battery in launch configuration Clyde Space is the World leading supplier of power system components for CubeSats We have been designing manufacturing testing and supplying batteries power system electronics and solar panels for space programmes since 2006 Our customers range from universities running student led missions to major space companies and government organisations SOLUTIONS FOR A NEW AGE IN SPACE www clyde space com PROPRIETARY amp CONFIDENTIAL INFORMATION Clyde Space Limited 2014 User Manual CS XUEPS2 60 FleXU CubeSat Electronic Power System Part 01 00732 and 01 01120 Issue D Date 20 03 2014 Page 8 of 51 USM 01 00732 Helix Bui
52. ystem Part 01 00732 and 01 SPACE 01120 Issue D Date 20 03 2014 Page 32 of 51 User Manual CS XUEPS2 60 FleXU CubeSat 21M4 e qT Helix Building WSSP Glasgow G20 OSP UK 9 TECHNICAL DESCRIPTION This section gives a complete overview of the operational modes of the EPS 9 1 Charge Method The BCR charging system has two modes of operation Maximum Power Point Tracking MPPT mode and End of Charge EoC mode These modes are governed by the state of charge of the battery MPPT Mode If the battery voltage is below the preset EoC voltage the system is in MPPT mode This is based on a constant current charge method operating at the maximum power point of the solar panel for maximum power transfer EoC Mode Once the EoC voltage has been reached the BCR changes to EoC mode which is a constant voltage charging regime The EoC voltage is held constant and a tapering current from the panels is supplied to top up the battery until at full capacity In EoC mode the MPPT circuitry moves the solar array operation point away from the maximum power point of the array drawing only the required power from the panels The excess power is left on the arrays as heat which is transferred to the structure via the array s thermal dissipation methods incorporated in the panels The operation of these two modes can be seen in Figure 9 1 9 f i i r 12 end of charge voltage i B constant battery 8 5 i B voltage

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