Augmented Polynomial Guidance With Impact Time and Angle Constraints

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In this paper, a new impact time and impact angle control guidance law for homing missiles against a stationary target is proposed. To derive a state feedback command for the proposed law with terminal constraints on the impact time and angle, we introduce a polynomial function of the guidance command with three unknown coefficients, one of which is determined to achieve the impact time requirement. The others are determined to satisfy the terminal impact angle constraint, as well as the zero miss distance. Because the proposed guidance law has arbitrary guidance gains, it is possible to shape the intercept trajectory and acceleration command profile by choosing proper gains in relation to the missile's capability, operational conditions, and so on.
Publisher
IEEE-INST ELECTRICAL ELECTRONICS ENGINEERS INC
Issue Date
2013-10
Language
English
Article Type
Article
Citation

IEEE TRANSACTIONS ON AEROSPACE AND ELECTRONIC SYSTEMS, v.49, no.4, pp.2806 - 2817

ISSN
0018-9251
URI
http://hdl.handle.net/10203/188517
Appears in Collection
AE-Journal Papers(저널논문)
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