In this paper, trajectory optimization is used as a tool to better understand the performance characteristics of hypersonic Single-Stage-To-Orbit(SSTO) vehicle exhibiting significant aeropropulsive interactions. The energy state approximation is used to determine a straightforward method of determining the scramjet-powered phase of the mission. The energy state method is then used to generate fuel-optimal trajectory results over this portion of the mission for a vehicle configuration of this class. The fuel-optimal unconstrained trajectory is marked by low-altitude acceleration, while a dynamic pressure-constrained trajectory is seen to ride the dynamic pressure constraint for the entire scramjet mission phase. The significance of aeropropulsive interactions in affecting vehicle performance is also investigated.


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    Titel :

    Effect of Aeropropulsive Interactions and Design Sensitivities on Optimal Hypersonic Ascent Trajectories


    Beteiligte:

    Erscheinungsdatum :

    01.01.1994


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Effect of Aeropropulsive Interactions and Design Sensitivities on Optimal Hypersonic Ascent Trajectories

    Schmidt, D. / Lovell, T. / AIAA | British Library Conference Proceedings | 1994



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    Lovell, T. A. / Schmidt, David K. / Chavez, Frank R. | NTRS | 1993


    Minimum-fuel trajectories for hypersonic vehicles with aeropropulsive interactions

    LOVELL, T. / SCHMIDT, DAVID / CHAVEZ, FRANK | AIAA | 1993


    Minimum-Fuel Trajectories for Hypersonic Vehicles with Aeropropulsive Interactions

    Lovell, A. / Schmidt, D. / Chavez, F. et al. | British Library Conference Proceedings | 1993