1. Micro Arcsecond X-ray Imaging Mission Pathfinder (MAXIM-PF) Mechanical George Roach Dave Peters 17 May 2002 “Technological progress is like an axe in the hands of a pathological criminal” Albert Einstein

2. Final Version MAXIM-PF 17 May 2002 Goddard Space Flight Centers Mechanical Page 2  Design Mission Unique spacecraft bus  HUB spacecraft consists of one Core S/C and 6 Petal S/C. These petal S/C will eventually become free flyer S/C.  Core S/C and Petal S/C are structurally the same.  A Detector spacecraft will attached to the HUB spacecraft then separate on orbit.  Accommodate a orbit Transfer Module (propulsion).  For payload accommodation use:  Use standard, highly successful mechanical designs with heritage, I.e. fixtures, bracket and fittings where possibly.  Minimize complex procedures.  Baseline Delta IV –5m x 14.3m launch vehicle shroud Overview

3. Final Version MAXIM-PF 17 May 2002 Goddard Space Flight Centers Mechanical Page 3 Launch Configuration Delta IV Heavy 5m X 19.1m fairing Delta IV 5m X 14.3m fairing P/L Sta. 0.00 Sta. 1550 C.G. Sta. 2500 Sta. 4300 Sta. 7600 Propulsion/Hub SpaceCraft Hub SpaceCraft/Detector SpaceCraft Propulsion/Hub SpaceCraft Delta IV 5m X 14.3m fairing

4. Final Version MAXIM-PF 17 May 2002 Goddard Space Flight Centers Mechanical Page 4 Mission Sequence Launch Transfer Stage Science Phase #1 Low Resolution 200 km Science Phase #2 High Resolution 1 km 20,000 km

5. Final Version MAXIM-PF 17 May 2002 Goddard Space Flight Centers Mechanical Page 5 Component Layout Hub Core & Petal Hub Core Hub Petal (6) LOS Laser Detector S/C Payload Adapter Fitting Optical Module (9) Optical Module (11) Comm Antenna (S/C to S/C 0.3 m)

6. Final Version MAXIM-PF 17 May 2002 Goddard Space Flight Centers Mechanical Page 6 Component Layout Detector Solar Array (4.5 m 2 ) Comm Antenna (Ground/SpaceCraft 0.5 m) Comm Antenna (S/C to S/C 0.3 m) Comm Antenna (Ground/SpaceCraft 0.5 m) LOS laser receiver CCD Camera CCD Electronics Thermal Shade (2.3 m 2 )

7. Final Version MAXIM-PF 17 May 2002 Goddard Space Flight Centers Mechanical Page 7 Structure Mass  Structure Mass  Hub Core – 57 kg  Hub Petal – 56 kg  Detector Payload Adapter Fitting – 12 kg  Detector – 85 kg

8. Final Version MAXIM-PF 17 May 2002 Goddard Space Flight Centers Mechanical Page 8  No spacecraft clearance issues  Ample clearance inside the launch vehicle fairing for all spacecraft appendages  Ample volume for spacecraft subsystems inside the bus  Mechanical interfaces:  Mission axial C.G. height within limits for launch vehicle PAF  Mission lateral C.G. are within limits for launch vehicle PAF  Mission stiffness for launch vehicle is TBD at this phase of the study  The concept of latching / unlatching the Freeflyer spacecraft has not been looked into for this phase of the study. However the concept has been used successfully many times in the past. One example is the MultiMission Spacecraft concept used for several satellites including, Solar Maximum, UARS, and EUVE. It has also been adapted for use on some Hubble components.  The actual spacecraft subsystems are not shown due to the time element. The spacecraft density is low enough to accommodate these volumes. Issues and Concerns

9. Final Version MAXIM-PF 17 May 2002 Goddard Space Flight Centers Mechanical Page 9 MECHANICAL BACK-UP SLIDES

10. Final Version MAXIM-PF 17 May 2002 Goddard Space Flight Centers Mechanical Page 10 Launch Vehicle Capabilities

11. Final Version MAXIM-PF 17 May 2002 Goddard Space Flight Centers Mechanical Page 11 Spacecraft Bus Densities

12. Final Version MAXIM-PF 17 May 2002 Goddard Space Flight Centers Mechanical Page 12 OPTIC HUB to FREE FLYER Latching Concept (example) This picture shows the latching / unlatching of Multi-Mission Modular Spacecraft. This basic concept could be used for the LAI-MAXIN “OPTIC HUB” to “FREE FLYER” configuration Free Flyer (s) Spacecraft Optic Hub Spacecraft

13. Final Version MAXIM-PF 17 May 2002 Goddard Space Flight Centers Mechanical Page 13 DELTA IV- 1666-4 PAF C.G. 3264 kg 2500 mm

14. Final Version MAXIM-PF 17 May 2002 Goddard Space Flight Centers Mechanical Page 14 Detector Mass Properties and Area’s 3.3^2m 1.9^2m 5.6^2m YZX