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Aug.19, 1999

MAXIM. Mechanical Configuration. Aug.19, 1999. George T. Roach Integration Mission Design Center NASA- GSFC Code 543 Greenbelt, MD. 20771 301-286-2213 FAX 301-286-0343 E-Mail- groach@mscmail.gsfc.nasa.gov. MAXIM. Overview.

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Aug.19, 1999

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  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 301-286-0343 E-Mail- groach@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

  3. 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 • cost and fabrication complexity, but would decrease mass. In either case, this is do-able in the design. • 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.

  4. Launch Vehicle Trade StudyBased on Performance to C3 = 0; Mass = 4100kg;Volume = 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)

  5. MAXIM Launch Vehicle Performance Baselined 8/18/99

  6. MAXIM

  7. 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)

  9. MAXIM ORBIT CONFIGURATION Detector Spacecraft Solar Array (7 m^2, projected area) Optic Spacecraft

  10. MAXIM OPTIC SPACECRAFT (DIFFERENT VIEWS) Different views of the Optic space- craft Spacecraft sub- System This view the spacecraft subsystems removed

  11. 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

  12. 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

  13. MAXIM DETECTOR SPACECRAFT Payload Fixed Solar Array (6m^2 shown) Stowed Orbit Spacecraft Spacecraft Subsystems are mounted in this volume

  14. MAXIM Range Sensors and Baffle Detector / CCD/ QC Cryogenics and Baffle DETECTOR PAYLOAD INSTRUMENTS

  15. MAXIM Detector Baffle Range Sensors Baffle Detector / CCD/ QC Cryogenics Payload Volume Range Sensors Enlarged View of Baffle DETECTOR SPACECRAFT

  16. MAXIM TOP LEVEL SPACECRAFT BUS MASS SUMMARY Mass(kg)/per unit Total Mass(kg)

  17. MAXIM TOP LEVEL SPACECRAFT BUS MASS SUMMARY Mass(kg)/per unit Total Mass(kg) Amendment 8/20/99

  18. SYSTEM LEVEL MASS SUMMARY (preliminary) Amendment 8/20/99

  19. 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, I’m 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.

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