Masters Theses

Abstract

"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.

Advisor(s)

Balakrishnan, S. N.

Committee Member(s)

Pernicka, Hank
Sarangapani, Jagannathan, 1965-
Yamasaki, Takeshi

Department(s)

Mechanical and Aerospace Engineering

Degree Name

M.S. in Aerospace Engineering

Publisher

Missouri University of Science and Technology

Publication Date

2012

Pagination

viii, 54 pages

Note about bibliography

Includes bibliographical references (pages 52-53).

Rights

© 2012 Andrew John Friedrichs, All rights reserved.

Document Type

Thesis - Open Access

File Type

text

Language

English

Subject Headings

Air defensesMathematical optimizationGuided missiles

Thesis Number

T 10548

Print OCLC #

903603699

Electronic OCLC #

904023526

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