Guidance Law for Agile Turn of Air-to-Air Missile During Boost Phase

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This paper proposes the guidance laws for an agile turn of air-to-air missiles during the initial boost phase. Optimal solution for the agile turn is obtained based on the optimal control theory with a simplified missile dynamic model. Angle-of-attack command generating methods for completion of agile turn are then proposed from the optimal solution. Collision triangle condition for non-maneuvering target is reviewed and implemented for update of terminal condition for the agile turn. The performance of the proposed method is compared with an existing homing guidance law and the minimum-time optimal solution through simulations under various initial engagement scenarios. Simulation results verify that transition to homing phase after boost phase with the proposed method is more effective than direct usage of the homing guidance law.
Publisher
KOREAN SOC AERONAUTICAL & SPACE SCIENCES
Issue Date
2017-12
Language
English
Article Type
Article
Citation

INTERNATIONAL JOURNAL OF AERONAUTICAL AND SPACE SCIENCES, v.18, no.4, pp.709 - 718

ISSN
2093-274X
DOI
10.5139/IJASS.2017.18.4.709
URI
http://hdl.handle.net/10203/239470
Appears in Collection
AE-Journal Papers(저널논문)
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