JEMペイロードアコモデーションハンドブック 小型衛星放出インタフェース
Contents
1. 2 32. 1 3 1 3 1 gt 1 2 3 4 5 6 7 8 9 JSX 2009032 JSX 2008041 HTV Cargo Safety Review Process JMR 006 JSX 2004011 SSP30231 FMEA CIL CR 99117 JAXA CR 99218 JEM MSFC HDBK 527F JSC 0904F MAT
3. 2 X A 2 1 21 JMX 2010292NC A 3 1 2 3 4 G Gi HTV m gue G G Gi
4. MIL BABE JAXA 1 TRES JAXA PARES IVa TAT ABST EAZ Fel d A 1 3 JAXA lt
5. 4 18 4 4 iti 1 2 3 4 4 5 JAXA JMX 2010292NC WERA Phase0 1 E S Phase2 Phas3 JAXA JAXA WO firi 4 7
6. 3 1 1 a b O
7. JAXA 2 JEM MSDS a b 3 JAXA
8. BLOG A CubeSat CubeSat Design Specification rev 12 2009 8 1 C CubeSat imi 1 2 JAXA
9. Gi O Gi Gi Qv 22 JMX 2010292NC 5 Q Gi Gi v
10. 3 HTV 1 COTS HTV JSX 2008041A Attachment JAXA JAXA ATV X NA 2 COTS HTV ATV
11. NASA JAXA JAXA 7 8 25 uj 12 JMX 2010292NC 2 4 2 4 1 1 a 81 8 m sec X Y Z Rx Ry Rz m sec m sec m sec rad sec2 rad sec2 rad sec2 49 8 21 1 22 9 13
12. Ra1 6 m 1 3 1 11 MIL A 86225 Anodic Coatings for Aluminum and Aluminum Alloys Type3 10 u m 21 1 1 1U 2U McMaster Carr P N 84985A76 2 1 7 1 2 1 7 2 Z 2 2 3 1 27mm 0 05inch 4 3U T CARET mi 2 1 7 1 T
13. 2 2 8 1 2 1 8 11 JMX 2010292NC 2 3 1 1 2 3 4 80 b RF 30 6 ISS RF
14. B 4 ISS A 38 1 4a 30 5 1 ISS A 200m 3 1 4b c 100kg m2 3 3 ISS 5km ISS 1 50 Es 6 A 3 1 4d 5cm sec 7 25 B 1 A ISS Jettison Policy B 2 SSN 3 ISS
15. 3 1 4 TR JAXA ISS ERE MIUL 1 3 1 6 CR 99218 JEM MSFC HDBK 527F JSC 0904F MATERIALS SELECTION LIST FOR SPACE HARDWARE SYSTEMS MAPTTS2 CR 99218 MSFC HDBK 527F JSC 0904FP MAPTIS A H K Stress Clacking Corrosion N RTD 4 MUA
16. LN JAXA 23 JAXA JAXA 4 1 3 1 3 JMR 006 JAXA 14 JMX 2010292NC 3 2 3 2 1 1 HTV Gafety Analysis Report 1 38 1 2 JSX 2008041 HTV Cargo Safety Review
17. 1 A4 1 ISS X SM Lab SM Lab LY P6 8S6 A IR Z ISS X A4 2 ISS Gpace Station Body Coordinate System 24 JMX 2010292NC B CubeSat Design Specification Rev 12 2 1 2 2 CubeSat CubeSat Design Specification X B 1 CubeSat A Applicable X CubeSat A M Applicable with modification X CubeSat E Equivalent CubeSat
18. 4 X Y 2 2 2 2 RFB 6 5mm 5 RBF 6 mm 1 2 3 Esa 100 0 0 1 R1 0 0 1 100 0 0 1 X tY mom X 3 JMX 2010292NC 1 6
19. 2 1 1 1 2 1 2 1 2 1 2 1 2 1 2 1 2 X Y 100 0 1mm 3 1U 118 5 0 1mm 4 2U Z 227 0 0 2mm 5 3U Z 340 5 0 83mm 2 1 2 1 X 100xY 100xZ 113 5mm 8 5mm 2U X 100xY 100xZ 227 0mm 8 5mm 2 1 2 1 3U X 100xY 100xZ 340 5mm 8 5mm 1 10cm JMX 2010292NC 23 3 1 Z 4 s 2 2 1 2 2 1 2 1 3 8 5mm 4 1 6 um b R1
20. A 1 A 2
21. 1ISS JEM E NA e ng vA NN 25 JMX 2010292NC X B 1 CubeSat Design Specification Rev 12 1 4 No Requirement Description Introduction 1 1 Overview NA P POD 1 2 Purpose NA 1 8 Waiver Process E 3 1 4 JMR 006 1 4 Interface NA P POD 2 CubeSat Specification 2 1 General Requirements 2 1 1 CubeSats which incorporate any deviation from the CDS shall submit a DAR and adhere to E 3 1 4 JMR 006 the waiver process 2 1 2 All parts shall remain attached to the CubeSats during launch ejection and operation No A 2 3 7 additional space debris shall be created 2 1 3 Pyrotechnics shall not be permitted A 3 2 2 6 2 1 4 No pressure vessels over 1 2 standard atmosphere shall be permitted E 3 2 2 2 1 4 1 Press
22. gt 4 2 R ll JMX 2010292NC 1 2 ZH 3 FERRER BEE 4 4 3 2 3 C 1
23. ISS Internatioanl Space Station IVA Intra Vehicular Activity JEM Japanese Experiment Module JEMRMS JEM Remote Manipulator System MAPTIS Materials And Processes Technical Information System MS Margin of Safety MSDS Material Safety Data Sheet RBF Remove Before Flight RF Radio Frequency SAR Safety Analysis Report SSN Space Surveillance Network TBD To Be Determined TML Total Mass Loss VCM Volatile Condensable Material VV Velocity Vector 34
24. JAXA JAXA 4 MUA 1 3 1 5 CR 99117 JAXA 3 1 2 MUA JAXA EC MAPTIS Materials and Processes Technical Information System http maptis nasa gov home aspx 15 JMX 2010292NC b VUA 1 3 1 5 CR 99117 JAXA
25. 1U H 113 5 0 1 2U H 227 0 0 2 3U H 340 5 0 3 2 1 2 1 6 6 5 1 mm 2 Z 3 JMX 2010292NC 0 5 9 2 2 1 4 1 7 JMX 2010292NC 2 1 5 1 1U 1 33kg 2 100kg mz 1 3 2 1 2 4 20mm 2 1 6 1 7075 6061 2 Z
26. JAXA 4 7 1 2 4 5 2 3 2 1 1 4 4 1 3 2 4 4 2 4 4 4 3 5 m 3 4 4 4 6 FMEA 3 2 1 2 7 QMIUT 3 2 1 3 8 MUA 3 2 1 9 3 2 1 5 VUA 10 4 6 4 11 3 1 20 JMX 2010292NC A
27. JAXA 4 4 19 lt JMX 2010292NC 4 6 JAXA 1 zs B St 2 a 5 c 3 4 JAXA 7 4 7 1
28. 6 Z 6 5mm X6 5mm 7 Z 75 25 1U 85 1mm 2U 170 83mm 3U 255 4mm 2 1 4 1 2 1 4 1 2 Z 4 Z 7 0mm x 0 5mm 3 Z 4 Z 6 5mm
29. v vi vii 6 Gi 23 JMX 2010292NC A A A3 1 A4 1 cA IRH 1 ISS 350 400km 51 6 2 5cm sec 3 ISS 45 Ed A4 1 I ISS 4
30. 9 ISS Jettison Policy PPD 1101 9 JAXA K 3 1 3 1 JAXA D 1 1 10000 A 8 1 1 Es TET 2 Space Surveillance Network SSN A 3 1 2 100cmz 3 A 3 1 3
31. 1 JSX 2009032 a 4 5 2FT 6 7 gt 16 JMX 2010292NC 3 3 ISS Jettison Pohcy 1 3 1
32. J8X 2008041 Attachment JAXA JAXA 3 JSX 2009032 SAR JAXA IP SAR gt gt 32 JMX 2010292NC D 1 Er GA ES rs COTS HTV ATV NA l l JAXA Al JAXA HTV NASA GSRPIA EC JAXA AE KHB 1700 7B JMR 002 NSTS 13830C JERG 1 007 Check List JSX 2008041 Check List Form476 ir JAXA Al JAXA Al NASA PSRP C NASA PSRP C ESA PSRP C
33. 1 mm 2 1 8 1 Ys CY Xs X 10 JMX 2010292NC 2 2 2 2 1 1 2 CZ 2 1 7 2 2 3 2 2 2 RBF Remove Before Flight 1 2 1 8 RBF 2 RBF 3 RBF 2 1 4
34. NPE BER 3 30 JMX 2010292NC X C L ae an SS ee Be E oa Eee oue secl enl M 2 2 ui o m EARE ok ZH RED SOMBER NA NA NA NA NA NA NA NA ah FREEDOM DAS REN o fys wae Es EM RECS a EUM EE RESI d Sy GRE i ae eon CO 31 JMX 2010292NC D
35. SSP 51700 JSX 2008041 ESA ATV PR 13830 1BSTS 138800 J Check List ESA ATV1700 7B Check List JSX 2008041 JSX 2009032 SAR Check List JAXA A ii NAS JSX 2003510 JSX 2003510 JSX 2003510 SSP 51700 SSP 51700 SSP 51700 INSTO 8830G 1 oco NSTS 13830C NSTS 13830C JSX 2009032 SAR J8X 2009032 SAR J8X 2009032 SAR EB SAR A Approval C Confirmation COTS 33 JMX 2010292NC AE ATV Automated Transfer Vehicle CIL Critical Item List C O Check Out COTS Commercial Orbital Transportation Services CTB Common Transfer Bag EMC Electromagnetic Compatibility EMGE Electrical and Mechanical Grapple Fixture JEMRMS FMEA Failure Mode Effect Analysis FT Fault Tolerant HTV H II B Transfer Vehicle ICS Inter Communication Syste IP International Partner
36. 1 8 JMX 2010292NC Q X 2 1 7 2 2 1 8 1 Ys Xs 2 1 8 1 2 RBF 2 2 2 2 1 9 1 MS 2 1 10 JMX 2010292NC 4 Z
37. 10cm 100cm2 10cm http www au afmil au awc awcgate usspc fs space htm f H H ISS NASA 100kg m2 E Lon 100kg m2 OSC HA fi ED GEL ER Be JE C TE CHE 17 100kg m2 IS8 2cm sec Et C amp S ISS E f EOD TN HU PC TSS
38. 5 8 5 11 5 X BERE T ory BEI Zr RE Td D 2 4 1 1 2 4 1 1 Frequency PSD Hz G2 Hz dB oct 20 0 005 50 0 02 4 6 120 0 031 1 5 230 0 031 0 0 1000 0 0045 4 0 2000 0 0013 4 5 Composite 4 0Grms 2 4 2 ISS a 2 0m sec2 b 0 69m sec 2 4 3 a 0 104 8 kPa b 1 0 kPa secl 2 4 4 15 60C 2 4 5 SEGA 4 4 15 6 C 25 75 2 5 ASTM E595 84 TML VCM e TML Total Mass Loss lt 1 0 VCM Volatile Condensable Material lt 0 1 13 P 3 JMX 2010292NC 1 3 2 1 NASDA ESPC 1681A JEM
39. CubeSat Design Specification Rev 12 4 4 No Requirement Description 2 3 4 2 The RBF pin shall cut all power to the satellite once it is inserted into the satellite A 2 2 2 2 2 3 4 3 The RBF in shall not protrude more than 6 5 mm from the rails when it is fully inserted in A 2 2 2 3 the satellite 2 4 Operational Requirements 2 4 1 CubeSats with batteries shall have the capability to receive a transmitter shutdown NA command as per Federal Communications Commission FCC regulation 2 4 2 All deployables such as booms antennas and solar panels shall wait to deploy a minimum of A 2 3 4 30 minutes after the CubeSat s deployment switch es are activated from P POD ejection 2 4 3 RF transmitters greater than 1mW shall wait to transmit a minimum of 30 minutes after the A 2 3 5 CubeSat s deployment switch es are activated from P POD ejection 2 4 4 Operators shall obtain and provide documentations of proper licenses for use of frequencies AM 2 3 6 4 2 1 ISS 2 4 4 1 For amateur frequency use this requires proof of frequency coordination by the International A 4 2 1 2 Amateur Radio Union IARU Applications can be found at www iaru org 2 4 5 The orbital decay lifetime of the CubeSat
40. area of 6 5 mm x 6 5 mm A 2 1 3 6 contact area for neighboring CubeSat rails as per Figure 5 2 2 13 At least 75 of the rails shall be in contact with the P POD rails 25 of the rails may be 2 1 3 7 recessed and no part of the rails shall exceed the specification 2 2 13 1 For single CubeSats this means at least 85 1 mm of rail contact 2 2 13 2 For triple CubeSats this means at least 255 4 mm of rail contact 2 2 14 Mass 2 2 15 Each single CubeSat shall not exceed 1 33 kg mass de 2 1 5 1 2 2 16 Each triple CubeSat shall not exceed 4 0kg mass 2 2 17 The CubeSat center of gravity shall be located within a sphere of 2 cm from its geometric A 2 1 5 3 Center 2 2 18 Material 2 2 19 Aluminum 7075 and 6061 shall be used for both the main Cube Sat structure and the rails A 2 1 6 1 2 2 19 If other materials are used the developer shall submit a DAR and adhere to the waiver E 3 2 1 JR 3 5 process MILU MUA VUA 27 JMX 2010292NC B 1 CubeSat Design Specification Rev 12 3 4 No Requirement Description 2 2 20 The CubeSat rails and standoff which contact the P POD rails and adjacent CubeSat A 2 1 6 2 standoffs shall to hard ano
41. i a ARTT 13 DAMES IM te oe ope ces um Uu CL A E EDI 13 DADs Tes OC ORDER ERE e sonora ELEM 13 DIU NOI I C Pr 13 DN NE I MP Xn NA 13 VUE ME Uxor AOT a dd 13 DBs WED et cd ed 13 l ed ed A a a A EE 14 Si e EEOAE M R n T 14 Bi Pee Jami E P 15 Le SEED TI ota cide heec ath nt lav bots aie Ade cad A E LU 1 15 Sp e erected ONDARZA A C OU ed ee boca 16 3 3 ISS Jettison Policy 17 cc lb jupg c0 P 18 41 UM cl D DTE m 18 TOES L5 050221524 Heat add REOR cm 18 JMX 2010292NC D MAC oc o pc MEDI 19 4 5 B 4 6 JAXA 4 7 FEH A 21 B CubeSat Design Specification Rev 12 25 usted EU UP ACC UE AL Ad A uer nexu Un A LR Ame ut hf 30 AA 32 Tiel N cio TN TC PH 34 JMX 2010292NC 1 1 JEM
42. 1 All systems shall be turned off including real time clocks A 2 3 3 2 3 3 To allow for CubeSat diagnostics and battery charging after the CubeSats have been A M 2 2 1 3 2 3 2 integrated into the P POD all CubeSat umbilical connectors shall be within the designated Access Port locations green shaded areas shown in Figure5 2 3 3 1 Triple CubeSats shall use the designated Access Port locations green shaded areas show in A 2 1 8 Appendix C 233 2 Note CubeSat deployment switch shall be depressed while inside the P POD All diagnostics A M 2 2 1 1 3 2 3 2 and battery charging shall be done while the deployment switch is depressed 2 3 4 The CubeSat shall include a Remove Before Flight RBF pin or launch with batteries fully A M 2 2 2 1 discharged The RBF pin shall be removed from the CubeSat after integration into the P POD 2 9 4 1 The RBF pin shall be accessible from the Access Port location green shaded area in Figure 5 A 2 2 2 IR 1 2 3 4 1 1 Triple CubeSats shall located their RBF pin in one of the 3 designated Access Port locations A 2 1 8 green shaded areas show in Appendix C 28 JMX 2010292NC 2 B 1
43. 3 1 7 VUA JAXA 3 2 2 1 0 7mm 10mm 25mm 2 3 2 1 3 5 3 JSC Form 1230 FLIGHT PAYLOAD STANDARDIZED HAZARD CONTROL REPORT 0 9 Battery Failure form EP Form 03 NASA 1 3 1
44. ERIALS SELECTION LIST FOR SPACE HARDWARE SYSTEMS ISS PPD 1011 Multi lateral ISS Jettison Policy JMR 003 2 JMX 2010292NC 10 ASTM E595 84 Standard Test Method for Total Mass Loss and Collected Volatile Condensable Materials from Outgassing in a Vacuum Environment 11 MIL A 86225 Anodic Coatings for Aluminum and Aluminum Alloys 1 8 2 1 NASDA ESPC 1681A JEM 2 CubeSat Design Specification rev 12 2009 8 1 1 8 8 JMX 2010292NC 2 2 1 2 1 1 Xs Ys Zs e X Y 1 2 2 1 1 1 2 Z Zs Z Zs Y Ys
45. JMX 2010292NC JEM Vol 8 2011 3 JEM JMX 2010292NC ui 03 10 2011 JMX 2010292NC handsome is IE MU cA eden MU n A LCD ME 2 M octies pL rc e Au hu LE UL ac ert 2 2 ECT 2 de NUR TERM NND UNTEN ae 2 2 3 UEM Sar 1 PCS 3 po 4 0 4 Ol T Vut MERCI DUREE 4 DVDS I I 2o 4 Dou 2 Bgd Ug eec Mtl LSU UII LL PT AUT ADD EDI AIP ook ae 5 DNA peer nd ud uo LI Md LEM x Du s 5 OE ees ek MERERETUR RR 8 NS ae ee AE CER 8 VEEUM C PI E 8 RES 9 DANN I o rp 9 9110 KGS A A AUS od cc tae had 9 DIa TERRIA AE D R NG 11 DITF ALEA UI EU ar EE EE OR ETE OREO RN ET NERNEY PR 11 2 2 2 RBF Remove Before FlighDE YY 11 0 NEU SP UL GN PM HD EY 11 Bee Ee AT REA 12 24 Ties
46. Process Check List 1 8 1 JSX 2009082 JAXA uu 2 MEA 1 3 1 JSX 2004011 SSP30231 FMEA CIL 6 2 FMEA 3 MIUL 1 8 1 5 CR 99117 JAXA
47. dized aluminum to prevent any cold welding within the P POD 2 2 21 The CubeSat shall use separation spring Figure 4 with characteristics defined in Table 1 on A 2 1 7 1 the designated rail standoff Separation springs with characteristics can be found using McMaster Carr P N 84985A76 The separation springs provide relative separation between CubeSats after deployment from the P POD 2 2 21 1 The compressed separation springs shall be at or below the level of the standoff A 2 1 7 2 2 2 21 2 The throw of the separation spring shall be a minimum of 0 05 inches above the standoff A 2 1 7 3 Surface 2 2 21 3 Separation springs are not required for 3U CubeSats A 2 1 7 4 2 3 Electrical Requirements 2 3 1 No electronics shall be active during launch to prevent any electrical or RF interference with A M 2 3 2 3 the launch vehicle and primary payloads CubeSats with batteries shall be fully deactivated during launch or launch with discharged batteries 2 3 2 The CubeSat shall include at least one deployment switch on the designated rail standoff A M 2 1 8 2 2 2 1 1 2 shown in Figure 5 to completely turn off satellite power once actuated In the actuated 2 state the deployment switch shall be centered at or below the level of the standoff 2 3 2
48. ecification Rev 12 2 4 No Requirement Description 2 2 1 Exterior Dimensions 5 2 2 2 The CubeSat shall use the coordinate system as defined in Figure 5 The Z face of the A 2 1 1 CubeSat will be inserted first into the P POD 2 2 3 The CubeSat configuration and physical dimensions shall be per Figure 5 A 2 1 2 1 2 9 4 The CubeSat shall be 100 0 0 1mm wide X and Y dimensions per Figure 5 A 2 1 2 2 2 2 5 A single CubeSat shall be 113 5 0 1mm tall Z dimension per Figure 5 A 2 1 2 3 2 2 5 1 A Triple CubeSat shall be 340 5 0 3mm tall Z dimension per Figure 5 A 2 1 2 3 2 2 6 All components shall not exceed 6 5 mm normal to the surface of the 100 0 mm cube the A 2 1 4 1 green and yellow shaded sides in Figure 5 2 2 7 Exterior CubeSat components shall not contact the interior surface of the P POD other than A 2 1 4 5 the designated CubeSat rails 2 2 8 Deployables shall be constrained by the CubeSat The P POD rails and walls shall not to be A 2 1 4 6 used constrain CubeSat rails 2 2 9 Rails shall have a minimum width of 8 5 mm A 2 1 3 3 2 2 10 The rails shall not have a surface roughness greater than 1 6 micro m A 2 1 3 4 2 2 11 The edges of the rails shall be rounded to a radius of at least 1mm A 2 1 3 5 2 2 12 The ends of the rails on the Z face shall have a minimum surface
49. s shall be less than 25 years after end of mission A 2 3 8 3 3 7 life 2 4 6 Cal Poly shall conduct a minimum of one fit check in which developer hardware shall be E C inspected and integrated into the P POD A final fit check shall be conducted prior to launch The CubeSat Acceptance Checklist CAC shall be used to verify compliance of the specification Appendix B for single CubeSats and Appendix D for triple CubeSats 3 Testing Requirements E C 3 1 Random Vibration E C 3 2 Thermal Vacuum Bake out E C 3 3 Visual Inspection E C 3 4 Qualification E C 3 5 Protoflight E C 3 6 Acceptance E C P POD J SSOD Cal Poly JAXA 29 C Col 1 NA JAXA WW HE NA NA NA NA NA NA 1 2 JMX 2010292NC Di BERI 777 s AER TO CN LVEF SHER EE eal E HEZ
50. ure vessels shall have a factor of safety no less than 4 NA 2 1 5 Total stored chemical energy shall not exceed 100 Watt Hours E 3 2 2 3 2 1 6 No hazardous materials shall be used on a CubeSat Please contact us if you are unsure if a AM 3 2 1 3 material 1s considered hazardous 2 1 7 CubeSat materials shall satisfy the following low out gassing criterion to prevent 2 5 contamination of other spacecraft during integration testing and launch A 2 1 7 1 Total Mass Loss TML shall be less than or equal 1 096 2 1 7 2 Collected Volatile Condensable Material CVCM shall be less than or equal 0 196 2 1 7 3 Note A list of NASA approved low out gassing materials can be found at NA http outgassing nasa gov 2 1 8 The latest revision of the CubeSat Design Specification shall be the official version NA http cubesat calpoly edu pages documents developers php which all CubeSat developers shall adhere to 2 1 8 1 Cal Poly shall send updates to the CubeSat mailing list upon any changes to the NA specification You can sign up for the CubeSat mailing list here http ati calpoly edu mailman listinfo cubesat 2 2 CubeSat Mechanical Requirements 26 JMX 2010292NC B 1 CubeSat Design Sp
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