Optimal guidance laws with terminal impact angle constraint

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Optimal guidance laws providing the specified impact angle as well as zero terminal miss distance are generalized for arbitrary missile dynamics. The optimal guidance command is represented by a linear combination of the ramp and the step responses of the missile's lateral acceleration. Optimal guidance laws in the form of the state feedback for the lag-free and the first-order lag system are derived, and their characteristics are investigated. Practical time-to-go calculation methods, which are important for the implementation of the optimal guidance laws, are proposed to consider the path curvature. Nonlinear and adjoint simulations are performed to investigate the performance of the proposed laws.
Publisher
AMER INST AERONAUT ASTRONAUT
Issue Date
2005-07
Language
English
Article Type
Article
Keywords

ENGAGEMENTS

Citation

JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, v.28, no.4, pp.724 - 732

ISSN
0731-5090
DOI
10.2514/1.8392
URI
http://hdl.handle.net/10203/86531
Appears in Collection
AE-Journal Papers(저널논문)
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