1. RBSP Radiation Belt Storm Probes RBSP Radiation Belt Storm Probes RBSP/EFW CDR 2009 9/30-10/1 Thermal Design Christopher Smith RBSP Thermal Engineer Space Sciences Lab University of California, Berkeley

2. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith Outline Requirements APL – UCB Interface Thermal Model Description IDPU Board Level Thermal Analysis Thermal Model Case Set Inputs Current Predicts Current Testing Overview

3. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith Spacecraft Level Thermal Requirements Orbit: 500-675 km x 30,050 - 31,250 km (EFW-7, EFW-8) Inclination: 10 degrees +/- 0.25 (EFW-6) 2 year design life, plus 60 days (EFW-1) Spacecraft top deck pointed to sun within: 25 degrees N/S and E/W, normal operation (EFW-201) 27 degrees composite, normal operation (EFW-202) 33 degrees, Safe mode (SCRD 3.10.4.4) (Was 47) S/C spin rate (about top deck): 4 to 6 RPM, normal and safe modes (EFW-9) 3 to 15 RPM, instrument commissioning (EFW-203) S/C shall survive 112 minute eclipse (Derived EFW-6, EFW-7, EFW-8)

4. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith EFW Thermal Requirements Conductive external surfaces with 10 5 Ohms/Sq. (EFW-133) Contamination: 100,000 class (EFW-132) Instruments to operate within specification with -25 to +55 spacecraft boundary conditions. (EFW-76, EFW-77) –-25 to +70 for top deck interface, new since PDR Instruments to survive without damage with -30 to +60 spacecraft boundary conditions. (EFW-79, EFW-80) –-30 to +75 for top deck interface, new since PDR Comply with contamination control plan. APL document 7417- 9007. (EFW-132) Comply with Environmental Design and Test Requirements Document. APL document 7417-9019. (EFW-136) Comply with RBSP_EFW_SYS_301_ETM, RBSP engineering test matrix

5. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith Engineering Test Matrix 7 total cycles per instrument, 5 at component level, 2 at suite level. Pre-Amps cycled separately due to larger temperature swing. No need for thermal balance as all instruments are conductively coupled to the spacecraft.

6. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith APL Thermal Modeling Interface Berkeley maintains a Thermal Desktop model of the EFW instrument and a boundary node definition of the spacecraft. APL Maintains a TSS geometry and SINDA network model of the spacecraft. APL integrates Berkeley geometry via Thermal Desktop TSS export. –Provides environmental heat flux data to instruments. APL integrates Berkeley SINDA network model into the SINDA spacecraft network model. –APL specifies spacecraft connection nodes. APL runs integrated model and provides temperature predicts back to Berkeley. Design cycles as necessary. APL is responsible for producing high fidelity temperature predicts.

7. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith Thermal Model Overview Instruments and Boundary Spacecraft IDPU SPBs AXBs

8. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith Thermal Model Overview AXB -Stowed Stacer (Elgiloy) Mounting Tube (M55J) Rod to Stacer Hinge (DAG 213) Sphere / Preamp in Caging Mechanism (Clear Alodine, GeBK Blanket) Sphere / Preamp (DAG 213)

9. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith Thermal Model Overview AXB -Deployed DAD (AntiSun: Clear Alodine) (Sun: Clear Alodine / GeBk Tape mix) Sphere (DAG 213) Sphere Caging Mechanism (AntiSun: Clear Alodine) (Sun: GeBk Blanket / Clear Alodine mix) Stacer (Elgiloy)

10. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith Thermal Model Overview SPB Deployed Elements Thin Wire SPB Preamp SPB Sphere Thick Wire

11. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith Thermal Model Overview SPB & IDPU SPB - Stowed SPB - Deployed IDPU (Mostly Black Kapton XC Tape, Some Gold Alodine) (Clear Alodine) (Black Kapton XC Tape) (Black Kapton Blanket, Shown in Green)

12. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith DCB Component Dissipations

13. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith DFB Component Dissipations

14. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith LVPS Component Dissipations

15. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith LVPS Board Distribution

16. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith Optical Materials Most properties tested, used, and correlated for the THEMIS mission Properties approved by the GSFC coatings committee July 07, 2008.

17. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith Thermophysical Properties Hot Cases Use Low e* Anti-Sunward and High e* Sunward Cold Cases Use High e* Anti-Sunward and Low e* Sunward

18. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith Interfaces IDPU –Conductively mounted to spacecraft side panel. –9 #10 Bolts = 0.75 W/C each. –Radiative coupling to spacecraft interior, Black Kapton XCTape SPB –Conductively mounted to spacecraft side panel. –4 #10 Bolts = 0.75 W/C each. –Deployed elements are completely isolated from the spacecraft by wire. –Low radiative coupling to spacecraft interior, Clear Alodined Aluminum AXB –Conductively mounted to the top and bottom spacecraft deck. –6 #8 Bolts at each end = 0.75 W/C each. –Radiative coupling somewhat isolated from major portions of the spacecraft since the mechanical units are stowed inside a carbon fiber tube which is also stored inside a spacecraft carbon fiber tube. –Deployed elements are isolated from spacecraft influence by stacer. –Caging mechanisms conductively mounted to top deck, 4 #8 Bolts = 0.75 W/C each.

19. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith Power, Heaters Current power used in model IDPU, SPB and AXB do not have any survival heaters

20. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith General Case Sets APL Case Set Parameters UCB Case Set Parameters

21. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith Limit Categories Science Operation Limit –Limits placed on an operating instrument –Specifies the range of temperatures the instrument will provide calibrated / useful science data Operation – Out of Spec –Limits placed on an operating instrument –May represent a wider range that is survivable but may be out of spec –Temperatures beyond Science Op Limit need not be calibrated to Non-Operation –Limits placed on a non operating instrument Pre-Deployment Limit –Limits placed on a mechanical system before it is actuated Deployment Limit –Limits placed on a mechanical system at the time of actuation Post-Deployment Limit –Limits placed on a mechanical system after it has executed its one-time deployment

22. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith Current Thermal Limits

23. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith Predicts, Deployed Case Sets

24. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith Margins, Deployed Case Sets

25. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith APL and UCB Predict Comparison, Table Each case set compared at a specific time and a representative node All case sets agree to within 1.5 degrees

26. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith APL and UCB Predict Comparison, Plot

27. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith Environmental Testing AXB Cage – Whip: – ETU qualified to values above (from Environmental Design & Test Requirements Document, dated 07/05/09). –Project Thermal has requested an increase in the Survival (Non-Op) and Op High temperatures to 75 C and 70 C, respectively (5-deg increase). –Current AXB Cage-Whip interface temp predict: 53 C.

28. RBSP/EFW CDR 2009 9/30-10/1Christopher Smith Status