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Dick Bolt Code 302 May 13-17, 2002 PowerPoint Presentation
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Dick Bolt Code 302 May 13-17, 2002

Dick Bolt Code 302 May 13-17, 2002

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Dick Bolt Code 302 May 13-17, 2002

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  1. Micro-Arcsecond Imaging Mission, Pathfinder (MAXIM-PF) Mission Success Dick Bolt Code 302 May 13-17, 2002

  2. Summary • Mission Success • Even with Fully Redundant S/C buses, the continuing Phase I & II operation is expected to have low probability of completing the full four (4) Year mission • Design Considerations • Hub S/C • Recommend either redundant Laser ranger devices or Laser beams from at least (2) separate Laser devices of both wide & narrow beam • Detector S/C • Redundant design looks good • Free Flyer S/Cs • Redundant design looks good • Mission Success Alternatives • From a Reliability standpoint, other designs should be considered • Two separate Detector S/C (single string) with: • Single Hub S/C (Fully Redundant) with Free Flyers or: • Two separate Hubs ( single string ) without Free Flyers • R&S Support Cost • 1 Million $ To support both Reliability & System Safety effort for at least 3 years MAXIM-PF, May 13-17, 2002Goddard Space Flight Center

  3. Assumptions • Mission Length • Phase I • Mission length to be 1 Yr with Phase II to follow. Six (6) Months to get in orbit • Phase II • Mission length to be 3 Yrs / 5 Year Goal • Total ( Phase I & II ) • Four (4) Years with 5 Year Goal • Redundancy • Hub S/C –-Put Redundancy into Hub design & not Free Flyer • Detector S/C –Fully redundant design needed MAXIM-PF, May 13-17, 2002Goddard Space Flight Center

  4. S/C Components • Phase I • Lens S/C (Hub) • Tunable X-Ray Optical System • Star Tracker • S/C Bus • Propulsion System • ACS • Laser Ranger to Detector S/C • Six(6) attached Free Flyers acting as extra X-Ray reflectors • Detector S/C • RF Com to Earth • Propulsion System • ACS ############################################## • Phase II • Lens S/C (Hub) • Tunable X-Ray Optical System • Star Tracker • S/C Bus • Propulsion System • ACS • Laser Ranger • Detachable Lens sections ( 6 units ) • Release Mech. • Tunable X-Ray Optical System • Detector S/C • Super Star Tracker • Cryo Cooler • RF Com to Earth • Propulsion System • ACS MAXIM-PF, May 13-17, 2002Goddard Space Flight Center

  5. Reliability Block DiagramPhase I Hub S/C Bus Hub Devices Detector S/C Bus Detector Devices FF Bus Launch Vehicle Delta IV Hydrazine Injection Propulsion System MAXIM-PF, May 13-17, 2002Goddard Space Flight Center

  6. Reliability Block DiagramPhase II Hub S/C Detector Devices Detector S/C Bus Hub Devices Hub Tunable Mirrors Hub S/C Bus FF Bus FF Laser Com Detector S/C Free Flyer (FF #1) S/C #1 of 6 FF #2 FF # 3 Hydrazine Injection Propulsion System FF # 4 Launch Vehicle Delta IV FF # 5 FF # 6 MAXIM-PF, May 13-17, 2002Goddard Space Flight Center

  7. Quick Mission Reliability Estimate • Phase I • Best Case Est. Mode I ( 2 Yr Mission ) 1? Without LV & Injector Prop. : .9 X.98 X.9 X.98 = 78% @ 1 Yr With LV & Injector Prop.: .78 X .94 X .99 = 72 % @ 1 Yr • Phase I & II • Best Case Est. Mode I & II ( 4 Yr Mission Total ) Without LV & Injector Prop. : .9 X.95 X.9 X.95 = 63% @ 4 Yrs With LV & Injector Prop.: .63 X .94 X .99 = 58.6% @ 4 Yrs LV=Launch Vehicle MAXIM-PF, May 13-17, 2002Goddard Space Flight Center

  8. Launch Vehicle • Delta IV • 94% Launch success Est. by Mfg. • Air Force committed to future launches • 1st stage is new design • Hydrazine Propulsion L-2 Orbit Injection System • No Reliability info, assume similar to S/C Hydrazine propulsion system • 99% or better MAXIM-PF, May 13-17, 2002Goddard Space Flight Center

  9. Deployments • Hub S/C • Laser Lens Cap • 6 Detachable Free Flyers • Detector S/C • 2 RF X-Band High Gain (dish) Antennas • Free Flyer S/Cs • None on S/C • Separation Systems • Separation of Hydrazine Propulsion Orbit Insertion System • Separation of Hub from Detector & attached Free Flyers • Separation of Six(6) separate Free Flyer units from the Hub MAXIM-PF, May 13-17, 2002Goddard Space Flight Center

  10. PRA Support & CostsReliability & System Safety Full PRA Version Requirement Assumed Will likely include Fault Tree Success Diagram Full Reliability evaluation for both Spacecraft Bus & all Instruments Reliability GSFC Code 302 would likely play the coordinator of the operation even if an RSDO bus was chosen Instrument Reliability will likely be done by design & builder of each. System Safety GSFC Code 302 would likely play the coordinator of the Safety Data Package ( Only one(1) expected to cover all) even if an RSDO bus was chosen Cost Estimate: 1.0 Million $ Basis is: 1 FTE ( based on GSFC contractor $ ) for each discipline for 3 years . Likely more if GSFC Code 302 monitors or supervises coordination of effort by other contractors MAXIM-PF, May 13-17, 2002Goddard Space Flight Center

  11. Back-Up Slides See RSDO S/C Bus Reliability Information Graph MAXIM-PF, May 13-17, 2002Goddard Space Flight Center

  12. RSDO S/C Bus Reliability For One (1) Year Mission S/C Bus Reliability Curve Fully Redundant Reliability % Single String Failure Rate in Failures / Million Hrs MAXIM-PF, May 13-17, 2002Goddard Space Flight Center

  13. Single S/C 3 YearBus Reliability 3 Year Mission—Spacecraft Bus Only (Based On RSDO S/C Bus Reliability Info) Fully Redundant S/C Bus Partially Redundant S/C Bus Area Single String S/C Bus MAXIM-PF, May 13-17, 2002Goddard Space Flight Center

  14. RSDO S/C Bus Reliability For Four (4) Year Mission Fully Redundant S/C Bus area Reliability Failure Rate MAXIM-PF, May 13-17, 2002Goddard Space Flight Center