Time-to-go weighted optimal guidance with impact angle constraints

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In this paper, the optimal guidance law with terminal constraints of miss distance and impact angle is presented for a constant speed missile against the stationary target. The proposed guidance law is obtained as the solution of a linear quadratic optimal control problem with the energy cost weighted by a power of the time-to-go. Systematic selection of guidance gains and trajectory shaping are possible by adjusting the exponent of the weighting function. A new time-to-go calculation method taking account of the trajectory curve is also proposed for implementation of the proposed law. Nonlinear and adjoint simulations are performed to investigate the performance of the proposed guidance law and time-to-go calculation method.
Publisher
IEEE-INST ELECTRICAL ELECTRONICS ENGINEERS INC
Issue Date
2006-05
Language
English
Article Type
Article
Keywords

DESIGN

Citation

IEEE TRANSACTIONS ON CONTROL SYSTEMS TECHNOLOGY, v.14, no.3, pp.483 - 492

ISSN
1063-6536
DOI
10.1109/TCST.2006.872525
URI
http://hdl.handle.net/10203/91747
Appears in Collection
AE-Journal Papers(저널논문)
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