Hypersonic aeroelasticity and aerothermoelasticity was an active area of research in the late 1950's and during the 1960's. This research was instrumental in providing the basis for the aerothermoelastic design of the space shuttle. For a considerable time period there was only limited interest in this area until the advent of the National AeroSpace Plane (NASP). In recent years, renewed activity in hypersonic flight research has been stimulated by the need for a low cost, reusable launch vehicle (RLV) and the recently completed Hyper-X program at NASA. Other activities are motivated by the design requirements for unmanned hypersonic vehicles that meet the needs of the U.S. Air Force. Vehicles in this category are based on a lifting body design. However, stringent minimum-weight requirements imply a degree of fuselage flexibility. Aerodynamic surfaces, needed for control, are also flexible. Furthermore, to meet the requirement of a flight profile that spans the Mach number range from 0 to 15, the vehicle must withstand severe aerodynamic heating. These factors combine to produce unusual aeroelastic problems that have received only limited attention in the past. Furthermore, it is important to emphasize that testing of aeroelastically scaled wind tunnel models, a conventional practice in subsonic and supersonic flow, is not feasible in the hypersonic regime. Thus, the role of aeroelastic simulations is critical for this flight regime.


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    Title :

    Three-dimensional Aeroelastic and Aerothermoelastic Behavior in Hypersonic Flow


    Contributors:

    Publication date :

    2005


    Size :

    52 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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