"Optimal control will be used to derive four guidance laws for the purpose of defending an aircraft from incoming missiles. The dynamics of the defending missile, and the overall engagement are used in these derivations. They are evaluated first in two degrees of freedom, then in six degrees. The guidance objective is to move a defending missile between the aircraft and the attacker. Optimal control is used to derive different commanded accelerations. Utilizing small changes in the cost functions, four applications will be derived. Triangle Guidance is used for inspiration, and initially a direct approach is attempted. In the course of this application a linear weight on the time-to-go, and a hyperbolic on the control weight are used. Three more variations are derived by changing how the dynamics are expressed, and the cost function that is minimized. The results are mixed, with unique problems appearing for each derivation. The final derivation provides a simple expression that proves to be effective. The capture envelope is increased while keeping the control effort low"--Abstract, page iii.
Balakrishnan, S. N.
Sarangapani, Jagannathan, 1965-
Mechanical and Aerospace Engineering
M.S. in Aerospace Engineering
Missouri University of Science and Technology
viii, 54 pages
© 2012 Andrew John Friedrichs, All rights reserved.
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Electronic access to the full-text of this document is restricted to Missouri S&T users. Otherwise, request this publication directly from Missouri S&T Library or contact your local library.http://merlin.lib.umsystem.edu/record=b10721253~S5
Friedrichs, Andrew John, "Analysis of optimal control derivations for aerial defense" (2012). Masters Theses. 7353.
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