2026-09-19T17:14:55Zhttps://dspace.mit.edu/server/oai/requestoai:dspace.mit.edu:1721.1/465722022-01-13T07:54:11Zcom_1721.1_7582com_1721.1_7581col_1721.1_131023
David W. Miller and Ronald J. Proulx.
Undurti, Aditya
Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics.
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
2009-08-26T16:54:06Z
2009-08-26T16:54:06Z
2007
2007
http://hdl.handle.net/1721.1/46572
422604216
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2007.
Includes bibliographical references (p. 187-189).
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.
by Aditya Undurti.
S.M.
189 p.
eng
Massachusetts Institute of Technology
M.I.T. theses are protected by
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http://dspace.mit.edu/handle/1721.1/7582
Aeronautics and Astronautics.
Optimal trajectories for maneuvering reentry vehicles
Thesis
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