Micro Arcsecond Xray Imaging Mission Pathfinder MAXIMPF Mechanical

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

Overview Final Version ¨ 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 – 5 m x 14. 3 m launch vehicle shroud MAXIM-PF 17 May 2002 Goddard Space Flight Centers 2

Launch Configuration Final Version Delta IV 5 m X 14. 3 m fairing Delta IV Heavy 5 m X 19. 1 m fairing Propulsion/Hub Space. Craft Sta. 7600 Delta IV 5 m X 14. 3 m fairing Sta. 4300 Hub Space. Craft/Detector Space. Craft C. G. Sta. 2500 Sta. 1550 Propulsion/Hub Space. Craft P/L Sta. 0. 00 3

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

Component Layout Hub Core & Petal Final Version 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 5

Component Layout Detector Final Version Solar Array (4. 5 m 2) Comm Antenna (Ground/Space. Craft 0. 5 m) Thermal Shade (2. 3 m 2) Comm Antenna (S/C to S/C 0. 3 m) (Ground/Space. Craft 0. 5 m) CCD Electronics LOS laser receiver MAXIM-PF 17 May 2002 Goddard Space Flight Centers CCD Camera 6

Structure Mass Final Version ¨ 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 7

Issues and Concerns Final Version ¨ 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 Multi. Mission 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 8

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

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

OPTIC HUB to FREE FLYER Latching Concept (example) Final Version 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. Final Version 2500 mm 3264 kg MAXIM-PF 17 May 2002 Goddard Space Flight Centers 13

Detector Mass Properties and Area’s Final Version 1. 9^2 m 3. 3^2 m 5. 6^2 m X MAXIM-PF 17 May 2002 Goddard Space Flight Centers Y Z 14