Optimal trajectories for maneuvering reentry vehicles
Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics.
David W. Miller and Ronald J. Proulx.
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Many demanding aerospace missions today require maneuverable re-entry vehicles that can fly trajectories that have stringent path and terminal constraints, including those that cannot be written as drag or energy constraints. This work presents a method based on trajectory optimization techniques to assess the capabilities of the re-entry vehicle by computing the landing and re-entry footprints while meeting these conditions. The models used also account for important non-linear effects seen during hypersonic flight. Several different vehicles are studied, and the effects of parameters such the maximum G-loading, stagnation point heat rate, and the maximum L/D are analyzed.
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2007.Includes bibliographical references (p. 187-189).
DepartmentMassachusetts Institute of Technology. Dept. of Aeronautics and Astronautics.
Massachusetts Institute of Technology
Aeronautics and Astronautics.