Micro Arcsecond Xray Imaging Mission Pathfinder MAXIMPF

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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
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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

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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
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Mission Sequence
1 km
Science Phase 2 High Resolution
Science Phase 1 Low Resolution
Launch
200 km
20,000 km
Transfer Stage
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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
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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
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Structure Mass

• Structure Mass
• Hub Core 57 kg
• Hub Petal 56 kg
• Detector Payload Adapter Fitting 12 kg
• Detector 85 kg

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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.