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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Conjugating Binary Systems for Spacecraft Thermal Control. Appendix C: Aeroassist Flight Experiment Carrier Vehicle Preliminary Stress Analysis


    Contributors:
    J. E. Ingram (author) / T. O. Murray (author)

    Publication date :

    1989


    Size :

    426 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





    Nonequilibrium thermal radiation for an aeroassist flight experiment vehicle

    Moss, James N. / Bird, Graeme A. / Dogra, Virendra K. | NTRS | 1988


    Aeroassist Flight Experiment Reaction Control System preliminary design

    Langford, G. K. / Price, D. E. / Gallaher, M. W. | NTRS | 1990


    The Aeroassist Flight Experiment

    Walberg, G. D. / Siemers, P. M., III / Calloway, R. L. et al. | NTRS | 1987


    Aeroassist Flight Experiment Reaction Control System preliminary design

    LANGFORD, G. / PRICE, D. / GALLAHER, M. | AIAA | 1990