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MAXIM-PF X-ray Imaging Mission Pathfinder Overview

MAXIM-PF is a unique space mission design aiming for high-resolution X-ray imaging. The spacecraft features a core and petal configuration, with a detachable detector spacecraft for advanced imaging. Designed for efficient propulsion and minimal complexity, it leverages proven mechanical designs. This comprehensive overview details the spacecraft's configuration, layout, structure, mass distribution, and launch vehicle capabilities. With a focus on efficiency and innovation, MAXIM-PF presents a pioneering approach in X-ray imaging missions.

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MAXIM-PF X-ray Imaging Mission Pathfinder Overview

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  1. Micro Arcsecond X-ray Imaging MissionPathfinder (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. Overview • 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 MAXIM-PF 17 May 2002 Goddard Space Flight Centers

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

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

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

  6. Component LayoutDetector Solar Array (4.5 m2) Comm Antenna (Ground/SpaceCraft 0.5 m) Thermal Shade (2.3 m2) Comm Antenna (S/C to S/C 0.3 m) Comm Antenna (Ground/SpaceCraft 0.5 m) CCD Electronics CCD Camera LOS laser receiver MAXIM-PF 17 May 2002 Goddard Space Flight Centers

  7. Structure Mass • Structure Mass • Hub Core – 57 kg • Hub Petal – 56 kg • Detector Payload Adapter Fitting – 12 kg • Detector – 85 kg MAXIM-PF 17 May 2002 Goddard Space Flight Centers

  8. Issues and Concerns • 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. MAXIM-PF 17 May 2002 Goddard Space Flight Centers

  9. Launch Vehicle Capabilities MAXIM-PF 17 May 2002 Goddard Space Flight Centers

  10. Spacecraft Bus Densities MAXIM-PF 17 May 2002 Goddard Space Flight Centers

  11. OPTIC HUB to FREE FLYERLatching 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 Optic Hub Spacecraft Free Flyer (s) Spacecraft MAXIM-PF 17 May 2002 Goddard Space Flight Centers

  12. DELTA IV- 1666-4 PAF C.G. 2500 mm 3264 kg MAXIM-PF 17 May 2002 Goddard Space Flight Centers

  13. Detector Mass Propertiesand Area’s 1.9^2m 3.3^2m 5.6^2m X Y Z MAXIM-PF 17 May 2002 Goddard Space Flight Centers

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