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Particles and Fields Package Critical Design Review May 23 -25, 2011

Mars Atmosphere and Volatile EvolutioN (MAVEN) Mission. Particles and Fields Package Critical Design Review May 23 -25, 2011 Christopher Smith, Thermal Engineer. Current Work Flow. UCB builds individual instrument thermal models (DONE) SWIA, STATIC, SEP, LPW, PFDPU, and SWEA

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Particles and Fields Package Critical Design Review May 23 -25, 2011

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  1. Mars Atmosphere and Volatile EvolutioN (MAVEN) Mission Particles and Fields Package Critical Design Review May 23 -25, 2011 Christopher Smith, Thermal Engineer

  2. Current Work Flow UCB builds individual instrument thermal models (DONE) SWIA, STATIC, SEP, LPW, PFDPU, and SWEA LM provides sink temperatures for UCB boundary node spacecraft UCB modifies instruments to meet requirements in all provided environments (DONE) UCB submits these models to spacecraft provider (LM) who incorporates them into the spacecraft thermal model. (DONE) LM returns spacecraft thermal model with integrated instrument models (DONE) LM had some issues, so far it looks like they are all modeling problems with the reduced instrument models (IN PROGRESS) UCB uses spacecraft model to address any issues and returns updates to LM (IN PROGRESS) LM responsible for producing official predicts for mission

  3. Current Status Instrument Thermal Predicts (Complete) Spacecraft model running at UCB with full instrument models integrated Instrument updates on to be delivered to LM by 06/06/11 Deep Dip and Thruster heating analysis (Complete) Spacecraft case sets include proper deep dip environments Deep dips bound thruster environments 650 W/m2 vs. 300 W/m2 LPW boom thermal treatment changed (Complete) Black Nickel originally specified but it alters the mechanical behavior of the boom DAG 213 susceptible to AO degradation Single coat satisfies nominal mission life Thicker coat in evaluation for increased margin PFDPU detailed board analysis not complete (In Progress) Analysis using distributed board properties complete Initial modeling and lessons learned from RBSP indicate detailed board analysis should be performed on 4 highest dissipation boards Detailed Preamp to Whip thermal model needed (In Progress)

  4. Peer Review Action Items

  5. Environmental Loads Values above from LM Case Sets Thruster flux combination of ACS and TCM firings

  6. Optical Properties All Materials approved by GSFC and JPL on previous missions Added testing for AO exposure Clear Alodine done by one plater with specified soak time. Extensive sampling with THEMIS. Occasional sampling with other missions. Wide BOL/EOL variance assumed in design

  7. Thermophysical Properties

  8. Thermal Limits

  9. SWIA Thermal Model Germanium Black Kapton Blanket Black Nickel + Grid (Not Shown) Blanket, 1.5 Sides Black Nickel Power Dissipation: 1.85 W +/- 10% Mass: 2.5 kg Conduction to SC Isolated 4 #8 Titanium with .25" G10 Isolator = .013 W/C each

  10. STATIC Thermal Model Germanium Black Kapton Blanket Black Nickel + Grid (Not Shown) Blanket, 1 Side Black Nickel Power Dissipation: 3.96 W +/- 10% Mass: 2.9 kg Conduction to APP Isolated 4 #8 Titanium with .25" G10 Isolator = .013 W/C each

  11. SWEA Thermal Model Blanket Black Nickel 50 % Blanket 50% Black Nickel Power Disipation: .89 W +/- 10% Mass: 1.8 kg SC Balance Mass: ~ 17 kg Conduction to SC Isolated 4 #8 Titanium with .25" G10 Isolator = .013 W/C each Blanketed Balance Mass

  12. SEP Thermal Model Blanket White Paint, Z-93-C55 Power Disipation: 0.16 W +/- 10% Mass: .63 kg White Paint, Z-93-C55 Conduction to SC Isolated 4 #8 Titanium with .25" ULTEM 1000 Isolator = .011 W/C each

  13. PFDPU Thermal Model Black Nickel Boards to Frame Conduction: Epoxied to frame at lip = .386 W/C 8 #4 Screws (screw path only)=.1 W/C total Frame Conduction to Adapter Plate: 22 #6 screws 0.42 = 9.24 W/C Adapter Plate Conduction to SC: 6 #10 bolts 1.32 each = 7.92 W/C Simple Distributed Board Models Power Disipation: 12.1 W +/- 10% Mass: 5.9 kg

  14. LPW Thermal Model Whip PreAmp Power: 0.10 W +/- 10% Stowed Stacer and DAD Mass: 2.6kg Base Mech to Bracket Conductance: 6 #8 Ti with .25" G10 Isolator = .013 W/C each

  15. LPW Thermal Model Clear Alodine (Inside Spacecraft Body Blanket) Titanium Nitride DAG 213 Black Nickel

  16. Spacecraft Thermal Model Full Spacecraft Model • Boundary Node Spacecraft • All Surface Temps from LM Output • MLI Unbound

  17. LM Launch/Initial Acquisition Case Definitions

  18. LM Cruise Case Definitions

  19. LM MOI Case Definitions

  20. LM Science Case Definitions Science Cases Deep Dip Cases

  21. Lockheed Thermal Memos #1 • SEP modeling issue found, LM Notified and producing new predicts

  22. Lockheed Thermal Memos #2

  23. Science Predicts

  24. Science Plot, Stacer

  25. Science Case Heater Power

  26. PFDPU Analysis Create detailed thermal model of high dissipation boards Include actual ground plane layout Include all components dissipating more than .1 W Current simple distributed property model is a good start Thermal / Ground planes need to grow as much as possible and overlap as much as possible. Thermal planes need to be brought to the edge of the board Maintain electrical isolation while improving thermal connections much as possible

  27. LPW Stacer LPW Stacer needs to be black to help reject deep dip heat load Black Nickel was identified as a candidate and sent out for AO testing and it did well However when it was applied to a stacer it modified its mechanical behavior DAG 213 was identified as an alternative We have lots of experience with it and has been used on stacers before DAG 213 is susceptible to AO Testing shows it meets requirements for nominal mission life Investigating a thicker coat to add margin Plan to run a half-DAG Stacer model as well Current Deep Dip Stacer Max Temp = 55 C

  28. LPW Whip LPW Whip is coated in titanium nitride, a=.46, e=.13 EOL Modeling error had this surface high emissivity until recently Thin wall titanium tube that is well isolated from preamp Whip doesn’t mind these temperatures but a detailed thermal model of the whip to preamp connection is required to be sure the preamp board is unaffected Whip End Titanium Whip Nut Bronze Hypertronics Socket Isolators PEEK PreAmp Board Whip .016” Titanium Wall Tube

  29. LPW Launch Case (System Model) System Model is worst case for preamp temperature It has a simple high (100 W/mC) contact conductance between the whip tube and preamp body Preamp cap not modeled

  30. LPW Launch Case (Detailed Model) Simple spreadsheet model of isolation shows a highly isolated path Detailed Model (SolidWorks) contains more detail also shows High isolation

  31. Backup Slides Back Up Slides

  32. Requirements Documents Performance Requirements Document MAVEN-program-plan-appendix-v28_L1Req.doc (Level 1) MAVEN-PM-RQMT-0005, Mission Requirements (Level 2) MAVEN-PFIS-RQMT-0016, PFP Requirements (Level 3) MAVEN-PF-STATIC-001A-Requirements_&_Specifications.xls (Level 4) Mission Assurance Requirements MAVEN-PM-RQMT-0006, Mission Assurance Requirements MAVEN_PF_QA_002, PFP Mission Assurance Implementation Plan Mission Operations MAVEN-MOPS-RQMT-0027, Mission Operations Requirements Environmental Requirements Document MAVEN-SYS-RQMT-0010 Spacecraft to PFP ICD MAVEN-SC-ICD-0007

  33. Launch Open Hot Predicts

  34. Launch Open Hot Plot, Whip

  35. Launch Mid Cold Predicts

  36. Launch Mid Cold Plot, Whip

  37. Launch Close Cold Predicts

  38. Launch Close Cold Plot, Whip

  39. Cruise Predicts

  40. MOI Predicts

  41. MOI Plot, Whip

  42. Deep Dip Predicts

  43. Deep Dip Plot, Stacer

  44. Relay Predicts

  45. Relay Plot, SEP

  46. Launch Case Heater Power

  47. Cruise Case Heater Power

  48. Deep Dip Heater Power

  49. MOI and Relay Case Heater Power

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