The goal of the Hyper-X program is to demonstrate and validate technology for design and performance predictions of hypersonic aircraft with an airframe-integrated supersonic-combustion ramjet propulsion system. Accomplishing this goal requires flight demonstration of a hydrogen-fueled scramjet powered hypersonic aircraft. A key enabling technology for this flight demonstration is flight controls. Closed-loop flight control is required to enable a successful stage separation, to achieve and maintain the design condition during the engine test, and to provide a controlled descent. Before the contract award, NASA developed preliminary flight control laws for the Hyper-X to evaluate the feasibility of the proposed scramjet test sequence and descent trajectory. After the contract award, a Boeing/NASA partnership worked to develop the current control laws. This paper presents a description of the Hyper-X Research Vehicle control law architectures with performance and robustness analyses. Assessments of simulated flight trajectories and stability margin analyses demonstrate that these control laws meet the flight test requirements.


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    Titel :

    Flight Control Laws for NASA's Hyper-X Research Vehicle


    Beteiligte:
    Davidson, J. (Autor:in) / Lallman, F. (Autor:in) / McMinn, J. D. (Autor:in) / Martin, J. (Autor:in) / Pahle, J. (Autor:in) / Stephenson, M. (Autor:in) / Selmon, J. (Autor:in) / Bose, D. (Autor:in)

    Erscheinungsdatum :

    01.01.1999


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch




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