Conjugating Binary Systems for Spacecraft Thermal Control. Appendix C: Aeroassist Flight Experiment Carrier Vehicle Preliminary Stress Analysis
Conjugating Binary Systems for Spacecraft Thermal Control. Appendix C: Aeroassist Flight Experiment Carrier Vehicle Preliminary Stress Analysis
- Neue Suche nach: J. E. Ingram
- Neue Suche nach: T. O. Murray
- Neue Suche nach: J. E. Ingram
- Neue Suche nach: T. O. Murray
An assessment of the static strength of the Aeroassist Flight Experiment (AFE) Carrier Vehicle is presented. The Carrier Vehicle is the structural component which provides the mounting platform for the experiments, on-board computers, batteries, and other black boxes. In addition, the Solid Rocket Motor (SRM), the Thrusters, and the Aerobrake are all attached directly to the Carrier Vehicle. The basic approach in this analysis was to develop a NASTRAN Finite Element Model as a parallel effort to the preliminary design, and to use the internal loads from this model to perform the stress analysis. The NASTRAN method of Inertial Relief was employed. This method involves either specifying a set of CG (center of gravity) accelerations or applying forces at the CG and representing the Carrier Vehicle and all its mounted devices with the proper stiffness and mass properties.
Dokumentinformationen
Conjugating Binary Systems for Spacecraft Thermal Control. Appendix C: Aeroassist Flight Experiment Carrier Vehicle Preliminary Stress Analysis
1989
426 pages
Report
Keine Angabe
Englisch
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