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MAXIM-PF, May 13-17, 2002 Goddard Space Flight Center. Mission Success Page 2 . Summary. Mission SuccessEven with Fully Redundant S/C buses, the continuing Phase I
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2. MAXIM-PF, May 13-17, 2002Goddard Space Flight Center Mission SuccessPage 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
3. MAXIM-PF, May 13-17, 2002Goddard Space Flight Center Mission SuccessPage 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
4. MAXIM-PF, May 13-17, 2002Goddard Space Flight Center Mission SuccessPage 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
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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
5. MAXIM-PF, May 13-17, 2002Goddard Space Flight Center Mission SuccessPage 5 Reliability Block DiagramPhase I
6. MAXIM-PF, May 13-17, 2002Goddard Space Flight Center Mission SuccessPage 6 Reliability Block DiagramPhase II
7. MAXIM-PF, May 13-17, 2002Goddard Space Flight Center Mission SuccessPage 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
8. MAXIM-PF, May 13-17, 2002Goddard Space Flight Center Mission SuccessPage 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
9. MAXIM-PF, May 13-17, 2002Goddard Space Flight Center Mission SuccessPage 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
10. MAXIM-PF, May 13-17, 2002Goddard Space Flight Center Mission SuccessPage 10
11. MAXIM-PF, May 13-17, 2002Goddard Space Flight Center Mission SuccessPage 11 Back-Up Slides See RSDO S/C Bus Reliability Information Graph
12. MAXIM-PF, May 13-17, 2002Goddard Space Flight Center Mission SuccessPage 12
13. MAXIM-PF, May 13-17, 2002Goddard Space Flight Center Mission SuccessPage 13
14. MAXIM-PF, May 13-17, 2002Goddard Space Flight Center Mission SuccessPage 14 RSDO S/C Bus Reliability For Four (4) Year Mission