Dick Bolt Code 302 May 13-17, 2002

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 ############################################## 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