1. 1-1 MAVEN IPER May 22-23, 2012 Particles and Fields Package Pre-Ship Review November 19, 2012 STATIC Thermal Status Millan F. Diaz-Aguado Mars Atmosphere and Volatile EvolutioN (MAVEN) Mission

2. 1-2 MAVEN November 19, 2012 Overview ERD Verifications Thermal testing temperatures Thermal vacuum test –Survival soaks –Operational cycles –Thermal balance –Heater tests Changes to model Changes to STATIC thermal design New STATIC temperatures and heater power budget

3. 1-3 MAVEN November 19, 2012 ERD Verification IDSTATUS 576 Completed through analysis 580 Completed through analysis 506 Completed through testing 1107 Completed through testing 505 Completed through testing 1108 Completed through testing 509 Completed through testing 508 Completed through testing 510 N/A Testing done in vacuum 601 Completed through testing 602 Completed through analysis 603 N/A 604 N/A 605 N/A 606 N/A 607 Completed 608 Verified through testing IDSTATUS 1120 Verified through testing 609 Completed 610 Completed 613 Completed 1121 Completed during first cycle 1122 Completed 614 Completed during later cycles of thermal-vacuum testing 615 Completed 1123 Completed during first cycle 1124 Completed 616 Completed 1125 Completed 1126 Completed 617 Completed 1127 Completed, CPTs and LPTs performed at various extremes 618 Completed with temperature extremes 619 Completed

4. 1-4 MAVEN November 19, 2012 STATIC Testing Temperatures Instrument Operating Temperatures (°C)Non Operating Temperatures (°C) AFT MinAFT MaxFA MinFA MaxPF MinPF MaxAFT MinAFT MaxPF MinPF Max STATIC*-3040-3045-3050-3040-3550 *Survival and operational heater setpoint at -25 °C

5. 1-5 MAVEN November 19, 2012 STATIC Thermal Vacuum/Balance Hot Survival/Operational Cold Survival LPT, TB LPT, TB, Heater Test Heater Balance Chamber Break, Reset Cover LPT CPT LPT CPT Cycle:123456 Cold Operational LPT CPT HV on 78

6. 1-6 MAVEN November 19, 2012 Thermal Balance Notes Nine TCs used for model correlation TCs needed to be calibrated probably due to junction through the chamber Two TCs on electronics box One on top cover Maximum ΔT of 3ºC between model and test for Cold/Hot Thermal Balance Maximum ΔT of 5.9ºC with heaters functional on electronics box –This large ΔT on the box probably due to temperature gradients on the TC locations Model was changed to reflect correct balance temperatures –Thermal coupling was reduced between the electronics box and the aperture, grid and cover The radiation optical properties were not changed. Testing on optical surface properties had been done before.

7. 1-7 MAVEN November 19, 2012 STATIC Thermal Vacuum/Balance Thermal balance results (after contact value changed) Hot TB (Plate at 50°C, shroud at 50°C) Test Temp. (°C) Model Temp. (°C) Δ T (°C) Heat Source (W) Cover16.214.91.30 Electronics Box51.848.63.22.7 TOF25.1 00 Heater A,B (@6.8W or 56%) Test Temp. (°C) Model Temp. (°C) Δ T (°C) Heat Source (W) Cover-30.2-32.4-2.40 Electronics Box-20-25.95.93.3 TOF-31-30.30.70 Cold TB (Plate at -30°C, shroud at -30°C) Test Temp. (°C) Model Temp. (°C) Δ T (°C) Heat Source (W) Cover9.311.21.90 Electronics Box-23.9-21.42.5 TOF1.41.00.40 Heater results (plate at -32ºC, shroud at -49ºC, setpoint -25ºC) Model predicting colder, closer to set-point temp.

8. 1-8 MAVEN November 19, 2012 STATIC Heater Test Heaters tested at nominal voltage Heater control tested at higher than expected duty cycle Operational Size (@26V) Maximum Individual (all op. cases) Maximum (peak)Maximum Average Heater(Ω)(Ω)(W) (% Duty Cycle @26V) STATIC 5612.1 1.32.420 Survival Size (@26V) Maximum Individual (all survival cases) Maximum (peak)Maximum Average Heater(Ω)(Ω)(W) (% Duty Cycle @26V) STATIC 5612.14.97.058 Duty Cycle (%)Heater AHeater B Setpoint -25ºC, 35 V33% (.633A) 33% (.625A) Setpoint -25ºC, 28 V52% (.507A)52% (.500A) Setpoint -25ºC, 26 V60% (.470A) 60% (.464A)

9. 1-9 MAVEN November 19, 2012 STATIC Temperatures from Correlated Model = Achieved Margin = Within 5 ° C of AFT Limit = > AFT Limit Ref: ERD P_Aug 22, 2012Init. AcquisitionCruise Safe ModeMOI SummaryScience Safe Mode Temperature Limits (°C )TemperatureCase IDTemperatureCase IDTemperatureCase IDTemperatureCase ID NON-OP LIMITS AFT (Non-Op) PF (Non-Op)(°C) MinMaxMinMaxMinMaxMinMaxMinMaxMinMaxMinMaxMinMaxMinMaxMinMax STATIC -3040-3550 1323 10021001 -24 2050 -24-23 30043003 -24-23 50502050 Ref:ERD P_Aug 22, 2012Cruise SummaryScience SummaryDeep Dip Summary Temperature Limits (°C )TemperatureCase IDTemperatureCase IDTemperatureCase ID OP LIMITSAFT (Op)FA (Op)PF (Op)(°C) MinMaxMinMaxMinMaxMinMaxMinMaxMinMaxMinMaxMinMaxMinMax STATIC -3040-3045-3050 -191420132001-23850015014192460036002 Ref:ERD P_Aug 22, 2012Relay Summary Temperature Limits (°C )TemperatureCase ID OP LIMITSAFT (Op)FA (Op)PF (Op)(°C) MinMaxMinMaxMinMaxMinMaxMinMax STATIC -3040-3045-3050 -21770017010 Used SWIA thermal decoupling values for STATIC

10. 1-10 MAVEN November 19, 2012 Heater Budget Post Model Correlation Operational*5004_Cold_Eclip_Sci_Type1_Orbit Size (@26V) Maximum Individual (all op. cases)MaximumMaximum IndividualMargin Margin on Requirement Heater(Ω)(Ω)(W) (% Duty Cycle @26V)(%) STA_Box 5612.1 2.51.1208050 SWE_Box 4913.8 3.8 287242 SWI_Box 4714.4 2.62.1188252 SEP1_Box_1 1215.59 2.42.3435727 SEP2_Box_1 1215.59 2.3 415929 Total Maximum Orbit Average (W) 11.6 Survival*5050_Science_Safe_Mode Size (@26V) Maximum Individual (all survival cases)Maximum CaseMaximum IndividualMargin Margin on Requirement Heater(Ω)(Ω)(W) (% Duty Cycle @26V)(%) STA_Box 5612.1 7.04.9594111 SWE_Box 4913.8 4.7 346636 SWI_Box 4714.4 1.9 138757 SEP1_Box_2 1215.59 2.71.7307040 SEP2_Box_2 1215.59 1.61.5277343 Total Maximum Orbit Average (W) 14.7 Size (@24V)Maximum MarginMargin on Requirement Heater(Ω)(Ω)(W) (% Duty Cycle @26V)(%) LPW_1 1613.581.93544616 LPW_2 1613.580.030.89969 LPW Deployment Need at least 30% Duty Cycle Margin on Individual Heaters *PFDPU has no survival or operational heaters

11. 1-11 MAVEN November 19, 2012 Conclusions Thermal Balance done on STATIC TMM correlated –Maximum ΔT of 3ºC between model and test for Cold/Hot Thermal Balance –Maximum ΔT of 5.9ºC with heaters functional on electronics box due to temperature gradients on the TC locations Heaters tested provided temperature control of STATIC Temperatures of correlated model within ERD limits Heater budget remains unchanged

12. 1-12 MAVEN November 19, 2012 Backup Slides

13. 1-13 MAVEN November 19, 2012 IDERD TextStatus 576 For launch environment thermal design and analysis, the following shall be used: * Assume the peak heat flux from the bare skin is 400 W/cm2 with a skin temperature maximum of 205 deg C. * At the acoustic blanket, the temperature is < 50 deg C. * Unless otherwise requested, fairing jettison will occur shortly after the 3-sigma high theoretical free molecular heating for a flat plate normal to the free stream drops below 1135 W/m2 (360 Btu/hr ft2) based on the 1962 US Standard Atmosphere. Completed through analysis 580 Aerothermal heating rates for deep dip science operations shall be assumed to be a constant 0.065 W/cm2 (worst case/fully margined) for a 10 minute drag duration. It should be assumed that the aeroheating flux may impinge on the spacecraft from any direction (with respect to the spacecraft body axes) for the entire drag duration. Completed through analysis 506 Per Table 22, all space hardware shall be subjected to minimum of eight (8) thermal-vacuum temperature cycles before being installed into the orbiter; these may include test cycles performed at the subsystem/instrument level of assembly. Will be completed through testing 1107 During the cycling, the hardware shall be operating and its performance shall be monitored. Will be completed through testing 505 If instrument level Thermal vacuum testing is to be performed, a minimum of four (4) thermal-vacuum temperature cycles shall be performed at the subsystem/instrument level of assembly. Will be completed through testing 1108 During the cycling, the hardware shall be operating and its performance shall be monitored. Will be completed through testing 509 Components shall be exposed for a minimum of four (4) hours at each extreme of each temperature cycle. The thermal soaks must be of sufficient duration to allow time for functional tests for all modes of operation. Will be completed through testing

14. 1-14 MAVEN November 19, 2012 IDERD TextStatus 508 Subsystems and instruments shall be exposed for a minimum of twelve (12) hours at each extreme of each temperature cycle. The thermal soaks must be of sufficient duration to allow time for functional tests for all modes of operation including safehold/survival. Will be completed through testing 510 For components that have been demonstrated by analysis to be insensitive to vacuum effects relative to temperature levels and temperature gradients, the requirements may be satisfied by temperature cycling at normal room pressure in an air or gaseous-nitrogen environment. If this approach is used, the number of cycles at ambient pressure should be increased to account for possible analytical uncertainties and to heighten the probability of detecting workmanship defects. The number of thermal cycles should be increased by fifty (50) percent if testing at ambient pressure (i.e., if 8 cycles would be performed in vacuum, then 12 cycles should be performed at ambient pressure). Further, it is recommended that the qualification margin of +/- 10  C (in vacuum) be increased to no less than +/- 25  C if testing at ambient pressure is performed. Testing will be done in vacuum 601 All flight hardware shall be subjected to thermal-vacuum testing in order to demonstrate satisfactory operation in modes representative of mission functions at the nominal operating temperatures, at temperatures in excess of the extremes predicted for the mission, and during temperature transitions. Table 22 (see Appendix) contains the test level requirements and exceptions for all components. Table 22- - MAVEN Environments Will be completed through testing 602 Electronic card/piece part thermal analyses shall be performed to ensure that the EEE-INST-002 derated temperature limits and the allowable junction temperatures are not exceeded during qualification test conditions. Will be completed through analysis 603 Spare components shall undergo a test program in which the number of thermal cycles is equivalent to the total number of cycles to which other flight components are subjected at the component, subsystem, and Orbiter levels of assembly. As a minimum, spare components shall be subjected to eight thermal cycles prior to integration onto the Orbiter. N/A

15. 1-15 MAVEN November 19, 2012 IDERD TextStatus 604 Redundant components shall be exercised sufficiently during the test program, including cold and hot starts, to verify proper orbital operations. Testing to validate all applicable operational modes shall be performed. The method of conducting the tests shall be described in the environmental verification test specification and procedures N/A 605 For spare and redundant components, the duration and test temperature levels of the tests shall be the same as those for flight components. N/A 606 For repaired equipment, usually a component, subsequent testing shall be sufficient to demonstrate flight worthiness. If additional testing is expected at either the Subsystem or the Orbiter level, the number of cycles can be reduced so long as the total number of cycles satisfies the 12 cycle requirement. N/A 607Thermal testing shall use the thermal margins defined in Table 21 (see Appendix). Will be completed 608 MAVEN components and subsystems shall be designed to operate within specification (including start-up capability) while in vacuum over the PF test limits shown in Table 406 (see Appendix). Table 406 - Component Dynamic Zones and Temperature Ranges Will be verified through testing 1120 Table 406 - Component Dynamic Zones and Temperature Ranges MAVEN components and subsystems shall be designed to survive after exposure to the Non- operational PF limits as shown in Table 406 (see Appendix). Will be verified through testing 609 Survival/Safehold testing shall be performed on that equipment which may experience (non- operating) temperature extremes more severe than operating as given in Table 406 (see Appendix). The equipment tested is not expected to operate properly within specifications until the temperatures have returned to qualification temperatures. Table 406 - Component Dynamic Zones and Temperature Ranges Will be completed 610 The chamber pressure after the electrical discharge checks are conducted shall be less than 1.33 X 10-3 Pa. (1 X 10-5 torr). The ability to function through the voltage breakdown region shall be demonstrated if applicable to mission requirements (those elements that are operational during launch). Will be completed

16. 1-16 MAVEN November 19, 2012 IDERD TextStatus 613 The temperature controls shall be adjusted to cause the test item to stabilize at the upper test temperature. Will be completed 1121Hot turn-on capability shall be demonstrated, as required. Will be completed 1122 The duration of the hot phase shall be at least sufficient to permit the performance of the functional tests with a minimum soak time as specified in Table 21 (see Appendix). Will be completed 614 The test item shall remain in an operational mode during the transitions between temperatures so that its functioning can be monitored under a changing environment. The requirement may be suspended when turn-on of the test item is to be demonstrated after a particular transition. In certain cases, it may be possible to remove thermal insulation to expedite cool-down rates. Will be completed 615 The temperature controls shall be adjusted to cause the test item to stabilize at the lowest test temperature. Will be completed 1123Cold turn-on capability shall be demonstrated at the start of the cold condition. Will be completed 1124 The duration of the cold phase shall be sufficient to permit the performance of the functional tests with a minimum soak time as specified in section Table 21 (see Appendix). Will be completed 616 Start-up capability shall be demonstrated to verify that the test item will turn on after exposure to the extreme temperatures that may occur in orbit. Test turn-on temperatures are defined by the expected mission operations without any margin; that is, temperatures should be at either survival/safe-hold or qualification temperature conditions, whichever are more extreme, as appropriate. Will be completed 1125 Turn-on capability shall be demonstrated under vacuum at least twice at both the low and high temperatures, as applicable. Will be completed 1126 The duration of the soak with the test item off, or in survival/safe-hold mode, shall be in accordance with Table 21 (see Appendix). Will be completed

17. 1-17 MAVEN November 19, 2012 IDERD TextStatus 617 Component functional tests shall be performed at each hot and cold soak plateau and during transitions, if applicable. Will be completed 1127 For components, a comprehensive performance test (CPT) shall be performed at least once during hot plateau(s) and once during cold plateau(s) unless it is determined to be impractical. In that case, with project approval, a limited functional test may be substituted if satisfactory performance is demonstrated for the major mission critical modes of operation. Otherwise, the requirements of MAVEN TEST PLAN apply. Will be completed 618 The adequacy of the thermal design and the capability of the thermal control system shall be verified under simulated on-orbit worst case hot and worst case cold environments. See Table 22 (see Appendix) Table 22- - MAVEN Environments Will be completed 619 Thermal design margins shall be verified under worst case hot and cold, and if tested, safehold/survival, conditions. Will be completed 1127 For components, a comprehensive performance test (CPT) shall be performed at least once during hot plateau(s) and once during cold plateau(s) unless it is determined to be impractical. In that case, with project approval, a limited functional test may be substituted if satisfactory performance is demonstrated for the major mission critical modes of operation. Otherwise, the requirements of MAVEN TEST PLAN apply. Will be completed

18. 1-18 MAVEN November 19, 2012 STATIC Op. Temperatures (1) Sheet:NodeInfo 2001_Hot_Early_Cruise62SOP 2012_Cold_Late_Cruise_9SOP 2013_Cold_Late_Cruise_45SOP 5001_Cold_Science_Earth_Comm 5004_Cold_Eclip_Sci_Type1_Orbit 5010_Hot_Science_Earth_Com 5014_HotNo_Eclips_Sci_Type1 Parameter: Red High Red LowMinMaxMinMaxMinMaxMinMaxMinMaxMinMaxMinMax Node/Group [°C] STATIC-3035 17.5 -21.5 -22.8 -21.2-17.0-22.5-16.77.78.96.510.8

19. 1-19 MAVEN November 19, 2012 STATIC Op. Temperatures (2) Sheet:NodeInfo 6001_Hot_Deep_Dip_pZ 6002_Hot_Deep_Dip_mZ 6003_Hot_Deep_Dip_pY 6004_Hot_Deep_Dip_mY 6005_Hot_Deep_Dip_pX 6006_Hot_Deep_Dip_mX 7001_Cold_Science_Relay 7010_Hot_Science_Relay Parameter: Red High Red Low MinMaxMinMaxMinMaxMinMaxMinMaxMinMaxMinMaxMinMax Node/Group [°C] STATIC-3035 22.825.123.825.922.022.521.822.422.523.222.122.5-18.6-14.48.19.3

20. 1-20 MAVEN November 19, 2012 STATIC Surv. Temperatures Sheet:NodeInfo 3001_Hot_MOI_Open 3003_Hot_MOI_Close 3004_Cold_MOI_Open 3006_Cold_MOI_Close 1001_Init_Acquis_Open 1002_Init_Acquis_Close 2050_Cruise_Safe_Mode 5050_Science_Safe_Mode Parameter: Red High Red LowMinMaxMinMaxMinMaxMinMaxMinMaxMinMaxMinMaxMinMax Node/Group [°C] STATIC-3035 -23.6-22.8-23.6-22.8-23.7-22.8-23.7-22.813.720.912.419.2-23.1-22.8-23.9-22.8

21. 1-21 MAVEN November 19, 2012 Heaters (avg) Sheet: 2001_Hot_Early_Cruise62SOP 2012_Cold_Late_Cruise_9SOP 2013_Cold_Late_Cruise_45SOP 5001_Cold_Science_Earth_Comm 5004_Cold_Eclip_Sci_Type1_Orbit 5010_Hot_Science_Earth_Com 5014_HotNo_Eclips_Sci_Type1 6001_Hot_Deep_Dip_pZ 6002_Hot_Deep_Dip_mZ 6003_Hot_Deep_Dip_pY 6004_Hot_Deep_Dip_mY 6005_Hot_Deep_Dip_pX 6006_Hot_Deep_Dip_mX 7001_Cold_Science_Relay 7010_Hot_Science_Relay Parameter:WWWWWWWWWWWWWWW STATIC 002.401.00000000000 Sheet: 3001_Hot_MOI_Open 3003_Hot_MOI_Close 3004_Cold_MOI_Open 3006_Cold_MOI_Close 1001_Init_Acquis_Open 1002_Init_Acquis_Close 2050_Cruise_Safe_Mode 5050_Science_Safe_Mode Parameter: WWWWWWWW STATIC 4.74.55.4 002.34.1 Operation Survival

22. 1-22 MAVEN November 19, 2012 Heaters (peak) Sheet: 2001_Hot_Early_Cruise62SOP 2012_Cold_Late_Cruise_9SOP 2013_Cold_Late_Cruise_45SOP 5001_Cold_Science_Earth_Comm 5004_Cold_Eclip_Sci_Type1_Orbit 5010_Hot_Science_Earth_Com 5014_HotNo_Eclips_Sci_Type1 6001_Hot_Deep_Dip_pZ 6002_Hot_Deep_Dip_mZ 6003_Hot_Deep_Dip_pY 6004_Hot_Deep_Dip_mY 6005_Hot_Deep_Dip_pX 6006_Hot_Deep_Dip_mX 7001_Cold_Science_Relay 7010_Hot_Science_Relay Parameter:WWWWWWWWWWWWWWW STATIC001.90 0000000000 Sheet: 3001_Hot_MOI_Open 3003_Hot_MOI_Close 3004_Cold_MOI_Open 3006_Cold_MOI_Close 1001_Init_Acquis_Open 1002_Init_Acquis_Close 2050_Cruise_Safe_Mode 5050_Science_Safe_Mode Parameter: WWWWWWWW STATIC5.95.66.9 003.66.5