Boiler Plate

1
MAXIM
Mechanical Configuration
Aug.19, 1999
George T. Roach Integration Mission Design
Center NASA- GSFC Code 543 Greenbelt, MD.
20771 301-286-2213 FAX [phone] E-Mail-
groach_at_mscmail.gsfc.nasa.gov
2
MAXIM
Overview

• See if the dual spacecraft MAXIM configuration
  can be accommodated on a
• single U.S. launch vehicle.
• Present a trade study comparing launch vehicles
• Present a concept that can meet mission
  requirements
• - Launch and orbit configuration
• Payload Instruments placements
• Structural mass summary

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MAXIM
Spacecraft Mechanical Overview

• The baseline will be 2 Mission Unique
  Spacecraft ( MUS)
• - Use of commercial parts and subsystems
• - Accommodate the Detector Instruments and Optic
  Instruments
• - Provide accommodations for a dual wing fixed
  solar array panels (total area 6 meters 2),
• for the detector spacecraft.
• - Provide accommodations for a fixed semi ring
  solar array panels (total area 7 meters 2),
• for the optic spacecraft.
• - The Optics spacecraft will interface to the
  Delta IV 5m dia. X 19.8 m long/ 17362 PAF
• - The core structure will be made-up of aluminum
  honeycomb panels, aluminum truss, fittings,
• brackets, diagonals and stringers.
• Note- Due to the time element in preparing this
  presentation, I baseline aluminum material,
  however
• due to the thermal sensitivity the structure
  material most likely would be composite. This
  would increase

• Mechanical Overview (continue)
• Spacecraft Description
• The general shape is circle, cylindrical,
  square, rectangular, hexagonal, octagonal. The
  size is 4m by
• 3 m long.
• Interfaces to the launch via 3712 PAF, and is
  launch on DELTA 11 7925-3
• The core structure will be made-up of aluminum
  honeycomb panels, truss, ring fitting, brackets,
• diagonals, and stringers.
• The spacecraft is considered an
  Open-Architecture-Configuration.
• The subsystems are mounted externally on
  structural members
• They are expose and cover with thermal
  blankets.
• The spacecraft is considered an
  Closed-Architecture-Configuration.
• The subsystems are mounted internally on
  structural members
• These subsystems are mounted shear panels,
  thrust tube or
• radials.

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Launch Vehicle Trade StudyBased on Performance
to C3 0 Mass 4100kgVolume 3.25 dia X
14.5 m
MAXIM

• Access Mode Candidates
• No Foreign Launch Vehicles Investigated (Space
  Policy-buy American)
• Delta II and III do not meet C3 performance
  requirements
• Delta IV
• S,M, M(4,2 5,2 config.) do not meet C3
  performance requirements
• M (5,4) config. meets C3 performance
  requirements but does not meet fairing volume
  envelope
• Heavy meets C3 performance requirements and
  fairing volume envelope
• Atlas V
• Core and core plus 2 strap-on do not meet C3
  performance requirements
• Core plus 4 or 5 strap-on meet C3 performance
  requirements but does not meet fairing volume
  envelop for the 5m short or medium PLF
• Heavy meets C3 performance requirements and
  fairing volume envelope
• Lockheed Martin studying (via a KSC task) whether
  the stretched version of the medium PLF (5.4 m
  dia.X 26.5 m) can be used on the medium EELV
  launch vehicles (Results expected in a couple of
  months)
• Boeing studying (via a KSC task) whether the
  heavy fairing (5 m dia. X 19.8 m) can be used on
  the medium EELV launch vehicles (Results expected
  in a couple of months)

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MAXIM
Launch Vehicle Performance
Baselined 8/18/99
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MAXIM
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MAXIM
LAUNCH VEHICLE

• For this study the Delta IV/5m/19.8m was baseline
• Launch vehicle will
• Meet lift-off (mass) requirements 20
• (actually approx.. 50, as of 8/19 AM)
• Meets volume requirements

8
MAXIM
Baffling
Delta IV (H) 5m diameter x 19.8m long
Payload
Detector Spacecraft (2.2m)
Spacecraft
16.4 m
Launch Fairing Removed
15.5 m
Optics Instruments (10m)
LAUNCH CONFIGURATION
Optic Spacecraft Systems (2.2m)
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MAXIM
ORBIT CONFIGURATION
Detector Spacecraft
Optic Spacecraft
Solar Array (7 m2, projected area)
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MAXIM
OPTIC SPACECRAFT (DIFFERENT VIEWS)
Different views of the Optic space- craft
Spacecraft sub- System
This view the spacecraft subsystems removed
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MAXIM
OPTIC SPACECRAFT (ON ORBIT)
Propulsion Tanks (4)
Solar Array
This is the far end away from the detector
spacecraft
This is the viewing end toward the detector
spacecraft
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MAXIM
Note- The X-Ray Interferometer has been removed
form clarity
Walter Telescope
Aspect Interferometer
X-Ray Interferometer
OPTIC Instrument with support structure
Range lasers (4)
OPTIC Instrument (rotated)
OPTIC INSTRUMENT
Aspect Interferometer
Walter Telescope Electronics
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MAXIM
DETECTOR SPACECRAFT
Payload
Fixed Solar Array (6m2 shown)
Stowed
Orbit
Spacecraft
Spacecraft Subsystems are mounted in this volume
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MAXIM
Detector / CCD/ QC Cryogenics and Baffle
Range Sensors and Baffle
DETECTOR PAYLOAD INSTRUMENTS
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MAXIM
Detector Baffle
Range Sensors Baffle
Detector / CCD/ QC Cryogenics
Payload Volume
Range Sensors
Enlarged View of Baffle
DETECTOR SPACECRAFT
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MAXIM
TOP LEVEL SPACECRAFT BUS MASS SUMMARY
Mass(kg)/per unit
Total Mass(kg)
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MAXIM
TOP LEVEL SPACECRAFT BUS MASS SUMMARY
Mass(kg)/per unit
Total Mass(kg)
Amendment 8/20/99
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SYSTEM LEVEL MASS SUMMARY (preliminary)
Amendment 8/20/99
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MAXIM
Conclusions

• Mechanically this mission is feasible
• - As of this phase of the study the dual
  spacecraft configuration can be accommodated
• on a single launch vehicle.
• Using the Delta IV, DIV-H 5 m diameter x 19.8 m
  long fairing
• Meets the minimum 20 mass margin
• Meets the volume margin
• Launching two spacecraft always lower the
  frequencies due to the two separations, however
  with
• the extra mass margins you can increase the
  structural integrity of the structure by
• adding structural members and increasing cross
  sectional areas.
• The separation system between the Optic
  spacecraft and Detector spacecraft has yet to be
  worked out.
• This is not a trivial matter, Im not aware of a
  3 m diameter marman ring at this time.
• Note- According with the Titan IV folks, anything
  that fit's inside this fairing the PAF can handle
• with reference to C.G. locations.