Impact Angle and Time Control Guidance Under Field-of-View Constraints and Maneuver Limits

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This paper proposes a guidance law which considers the constraints of seeker field-of-view (FOV) as well as the requirements on impact angle and time. The proposed guidance law is designed for a constant speed missile against a stationary target. The guidance law consists of two terms of acceleration commands. The first one is to achieve zero-miss distance and the desired impact angle, while the second is to meet the desired impact time. To consider the limits of FOV and lateral maneuver capability, a varying-gain approach is applied on the second term. Reduction of realizable impact times due to these limits is then analyzed by finding the longest course among the feasible ones. The performance of the proposed guidance law is demonstrated by numerical simulation for various engagement conditions. © 2018, The Korean Society for Aeronautical & Space Sciences and Springer Nature Singapore Pte Ltd.
Publisher
SPRINGER
Issue Date
2018-03
Language
English
Article Type
Article
Citation

INTERNATIONAL JOURNAL OF AERONAUTICAL AND SPACE SCIENCES, v.19, no.1, pp.217 - 226

ISSN
2093-274X
DOI
10.1007/s42405-018-0004-8
URI
http://hdl.handle.net/10203/248785
Appears in Collection
AE-Journal Papers(저널논문)
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