Effect of Aeropropulsive Interactions and Design Sensitivities on Optimal Hypersonic Ascent TrajectoriesIn 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.
Document ID
19970003025
Acquisition Source
Langley Research Center
Document Type
Contractor Report (CR)
Authors
Lovell, T. Alan (Maryland Univ. College Park, MD United States)
Schmidt, David K. (Maryland Univ. College Park, MD United States)
Date Acquired
August 17, 2013
Publication Date
January 1, 1994
Publication Information
Publisher: American Inst. of Aeronautics and Astronautics