The class of hypersonic vehicle configurations with single stage-to-orbit (SSTO) capability reflect highly integrated airframe and propulsion systems. These designs are also known to exhibit a large degree of interaction between the airframe and engine dynamics. Consequently, even simplified hypersonic models are characterized by tightly coupled nonlinear equations of motion. In addition, hypersonic SSTO vehicles present a major system design challenge; the vehicle's overall mission performance is a function of its subsystem efficiencies including structural, aerodynamic, propulsive, and operational. Further, all subsystem efficiencies are interrelated, hence, independent optimization of the subsystems is not likely to lead to an optimum design. Thus, it is desired to know the effect of various subsystem efficiencies on overall mission performance. For the purposes of this analysis, mission performance will be measured in terms of the payload weight inserted into orbit. In this report, a trajectory optimization problem is formulated for a generic hypersonic lifting body for a specified orbit-injection mission. A solution method is outlined, and results are detailed for the generic vehicle, referred to as the baseline model. After evaluating the performance of the baseline model, a sensitivity study is presented to determine the effect of various subsystem efficiencies on mission performance. This consists of performing a parametric analysis of the basic design parameters, generating a matrix of configurations, and determining the mission performance of each configuration. Also, the performance loss due to constraining the total head load experienced by the vehicle is evaluated. The key results from this analysis include the formulation of the sizing problem for this vehicle class using trajectory optimization, characteristics of the optimal trajectories, and the subsystem design sensitivities.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Parametric Sensitivity Study for Single-Stage-to-Orbit Hypersonic Vehicles Using Trajectory Optimization


    Contributors:

    Publication date :

    1994


    Size :

    38 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English






    Desensitized Trajectory Optimization for Hypersonic Vehicles

    Makkapati, Venkata Ramana / Ridderhof, Jack / Tsiotras, Panagiotis et al. | IEEE | 2021



    Adaptive trajectory tracking control system design for hypersonic vehicles with parametric uncertainty

    Liu, Zhen / Tan, Xiangmin / Yuan, Ruyi et al. | SAGE Publications | 2015