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Particles and Fields Package (PFP) Instrument Preliminary Design Review Thermal

Particles and Fields Package (PFP) Instrument Preliminary Design Review Thermal. Christopher Smith. Responsibilities. UCB builds individual instrument thermal models SWIA, STATIC, SEP, LPW, PFDPU UCB and Goddard (John Hawk) currently both working on SWEA. Will transition to UCB only.

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Particles and Fields Package (PFP) Instrument Preliminary Design Review Thermal

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  1. Particles and Fields Package (PFP) Instrument Preliminary Design Review Thermal Christopher Smith

  2. Responsibilities UCB builds individual instrument thermal models SWIA, STATIC, SEP, LPW, PFDPU UCB and Goddard (John Hawk) currently both working on SWEA. Will transition to UCB only. UCB submits these models to spacecraft provider (LM) who incorporates them into the spacecraft thermal model. LM generates sink couplings for each instrument node for environments and delivers these to UCB UCB incorporates LM environments and goes through a design cycle to meet ERD requirements. UCB returns new generation of instrument models to LM. Cycle repeats as necessary LM responsible for producing official predicts for mission

  3. Current Status Spacecraft has not yet delivered a set of environments to UCB Consequently we have yet to complete the first design cycle To mitigate this delay UCB has generated a boundary node spacecraft Global deck temperatures set to the minimum and maximum seen in LMs Pre-PDR presentations Radiation environments created from spacecraft provided orbit definitions These models predicts should envelope spacecraft instrument predicts UCB will deliver a second generation of instrument models post IPDR which LM will be able to incorporate in time for their PDR

  4. Current Status Complete Paul Turin did early work with a spreadsheet to choose coatings given Aero and Thruster flux Initial instrument models delivered to LM in April Completed building boundary node spacecraft Completed initial runs with boundary node spacecraft Initial instrument heater predicts To do before Spacecraft PDR Find solution for warm SEP Board level thermal analysis To do after Spacecraft PDR Complete more detailed deep dip heating and thrusters heating Receive environmental loads from LM Optimize heater power

  5. RFAs and Recommendations White indicates RFA, Grey indicates Recommendation from peer review All will be closed by July 01 2010

  6. 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

  7. ERD Highlights 1 Solar Flux at 1 AU At Earth: 1400 to (1290?) to 0 W Solar, 0 to .32 Albedo, 0 to 270 Planetary IR Cruise: 0 1414 W Solar Mars: 0 to 490 to 410 W Solar, .18 to .35 Albedo by latitude, -125 to 25 C Planetary IR Deep Dip Heating “Aerothermal heating rates for deep dip science operations shall be assumed to be a constant 0.1 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.”

  8. ERD Highlights 2 200 failure free vacuum operations, minimum 48 hrs hot, 72 cold 8 cycles total per component over all TVAC testing, minimum of 4 at component level. Minimum of 4 hrs operating at each hot and cold Thermal balance called out for SWIA and STATIC Thermally Isolate Instruments Design for deck temperatures of -50 to 50

  9. MRD Highlights

  10. Case Set Parameters

  11. Optical Properties • All Materials approved by GSFC and JPL on previous missions • 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

  12. Thermophysical Properties

  13. Thermal Limits and Margins Allowable Flight Temperature (AFT) at least +/- 5 from model predictions Flight Acceptance +/- 5 from Predicts Protoflight / Qual +/- 10 from Predicts

  14. SWIA Thermal Model Germanium Black Kapton Blanket DAG 213 Power Disipation: 1.48 W +/- 15% Mass: 2.03 kg Blanket Conduction to SC Isolated 4 #8 Titanium with .25" G10 Isolator = .013 W/C each

  15. STATIC Thermal Model Blanket DAG 213 Power Disipation: 3.98 W +/- 15% Mass: 2.33 kg Blanket Conduction to SC Isolated 4 #8 Titanium with .25" G10 Isolator = .013 W/C each

  16. SWEA Thermal Model Blanket Power Disipation: .867 W +/- 15% Mass: 1.64 kg SC Balance Mass: ~ 20 kg DAG 213 Blanket Conduction to SC Isolated 4 #8 Titanium with .25" G10 Isolator = .013 W/C each Hole in Blanket, DAG 213, Absorber / Radiator

  17. Original SEP Thermal Model Silver Teflon Ebanol C Black Body Power Disipation: .015 W +/- 15% Mass: .687 kg Clear Alodine Conduction to SC Isolated 4 #8 Titanium with .25" G10 Isolator = .083 W/C each (LM)

  18. Current SEP Thermal Model Blanket Power Disipation: .015 W +/- 15% Mass: .687 kg DAG 213 Clear Alodine Conduction to SC Isolated 4 #8 Titanium with .25" ULTEM 1000 Isolator = .011 W/C each

  19. PFDPU Thermal Model Power Disipation: 11.5 W +/- 15% Mass: 4.78 kg Conduction to SC 6 #10 bolts 1.32 each = 7.92 W/C Black Anodize

  20. STATIC Thermal Model Stowed Stowed Stacer and DAD PreAmp Power: .015 W +/- 15% Mass: 2.31kg Bit light of 2.9 in resource table Rod Caging Mechanism Base Mech: 6 #8 Ti with .25" G10 Isolator = .013 W/C each Cage: 4 #8 Ti with .25" G10 Isolator = .013 W/C each

  21. STATIC Thermal Model Deployed Clear Alodine DAG 213 Titanium Nitride

  22. Spacecraft Boundary Model Solar Arrays -158 to 80 C MLI Unbound All Panels and Gussets -35 to +30 C

  23. ESA Deflector and Grid Finish • The STATIC, SWIA, SWEA Electrostatic Analyser (ESA) deflectors and grids are thermally isolated and open to space. • As a result, they are subject to heating from solar radiation, atmospheric friction during deep dips, and in the case of SWEA exposure to thruster plumes. • SWEA had gold plated surfaces on STEREO Deflectors Grids

  24. SWEA Peer Review Thermal RFAs • Two thermal RFA’s came out of SWEA peer review to examine grid and deflector temperatures under environmental conditions including thruster firings and aero heating • Paul Turin did initial study, single node, steady state • Results indicated the need to switch to something that could transport and radiate heat. • Current baseline is DAG 213.

  25. SWEA Deflector Predicts and Finish Options (Periapsis) Deflector Finish: Predicts:

  26. LPW heating from Thrusters Heat flux (W/m2) on LPW booms - Scale has been adjusted to highlight heat flux on LPW booms - Includes all 1 N and 22 N thrusters - Most heat flux is from TCM-1 and TCM-2 - Max heat flux is 194 W/m2 = 0.14 Suns UCB to use 242 W/m2 (with margin) for analysis LPW LPW SWEA boom

  27. LPW temps with Bare and Painted The use of DAG213 on Stacers has a long history on sounding rocket and spacecraft missions (POLAR, FAST, THEMIS)

  28. Thruster and Aero Heating Summary Gold plated Ultem will fail (SWEA deflectors, changing to Al) Gold plated anything will get very hot Paints reduce temps, but concern about possible degradation due to atomic Oxygen. Ebanol C, Black Chrome and Black Electroless Nickel are candidates An AO test will be performed at Glen Research Center on samples of DAG213, Z307, Ebanol C, Black Chrome, and Black Nickel

  29. Inner Cruise Analysis Cases 62° Offpoint 5° Offpoint 38° Offpoint Views as seen from the Sun

  30. Transition Analysis Cases 25° Offpoint – Last Inner Cruise Attitude 45° Offpoint – First Outer Cruise Attitude Views as seen from the Sun

  31. Outer Cruise Analysis Cases 9° Offpoint 45° Offpoint Views as seen from the Sun

  32. Mapping Orbit Timing and Geometry Slew DESAT Slew Slew Slew Apoapse Outbound Side Periapse Inbound Side 5400 5000 1170 500 500 1570 5000 5000 5400 ALTITUDE (km) -89.6 -79.6 -21.1 -11.1 11.5 26.5 79.3 -190.0 -180.0 TIME (rel to Per.) Actual Periapsis (~150-170 km) • Modeling assumptions: • Slews are fixed 10 minute duration. • Desat is 5 minutes. • Segment/Slew boundaries are fixed, regardless of activity. • Settling periods are not explicitly modeled (included in segment time periods).

  33. Mapping Orbit Mixture of Activities Apoapse Outbound Side Periapse Inbound Side Orbit A Earth Point Earth Point Earth Point Earth Point Orbit B Limb Scan (IP) Coronal-DH (IP) Deep Dip Coronal-DH (IP) Orbit C Limb Scan (IP) Sun-Nadir (SP) Y-Velocity/X-Nadir Sun-Nadir (SP) Orbit D Limb Scan (IP) Coronal-O (IP) Z-Sun/Y-Velocity Stellar Occ (IP) • NOTES: • IP= IUVS Priority; SP=STATIC Priority; NP=NGIMS Priority • Stellar Occultation observations involve “staring” at a star near the orbit plane as it rises from behind the planet (10 min duration)

  34. Sun Pointed Mapping Analysis Cases • Keplerianorbits • Sun pointed through these orbits (+Z and HGA) • Planet Assumptions • Cold:Albedo= 0.18, Planetshine = -38.5 (sun); -125 (dark) • Hot:Albedo= 0.35, Planetshine = -27.7 (sun); -100 (dark) View of max eclipse orbit looking at planet North View of max eclipse orbit as seen from the Sun

  35. Cruise Predicts

  36. Mapping, Cold Predicts

  37. Mapping Hot Predicts

  38. Lockheed Predicts

  39. Heater Predicts, Cruise Hot and Cold

  40. Heater Predicts, Mapping, Hot

  41. Heater Predicts, Mapping, Cold

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