Impact Angle Control Guidance Synthesis for Evasive Maneuver against Intercept Missile

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This paper proposes a synthesis of new guidance law to generate an evasive maneuver against enemy's missile interception while considering its impact angle, acceleration, and field-of-view constraints. The first component of the synthesis is a new function of repulsive Artificial Potential Field to generate the evasive maneuver as a real-time dynamic obstacle avoidance. The terminal impact angle and terminal acceleration constraints compliance are based on Time-to-Go Polynomial Guidance as the second component. The last component is the Logarithmic Barrier Function to satisfy the field-of-view limitation constraint by compensating the excessive total acceleration command. These three components are synthesized into a new guidance law, which involves three design parameter gains. Parameter study and numerical simulations are delivered to demonstrate the performance of the proposed repulsive function and guidance law. Finally, the guidance law simulations effectively achieve the zero terminal miss distance, while satisfying an evasive maneuver against intercept missile, considering impact angle, acceleration, and field-of-view limitation constraints simultaneously.
Publisher
KOREAN SOC AERONAUTICAL & SPACE SCIENCES
Issue Date
2017-12
Language
English
Article Type
Article
Keywords

OBSTACLE AVOIDANCE; ANTISHIP MISSILES; MOBILE ROBOTS; LAWS; CONSTRAINT

Citation

INTERNATIONAL JOURNAL OF AERONAUTICAL AND SPACE SCIENCES, v.18, no.4, pp.719 - 728

ISSN
2093-274X
DOI
10.5139/IJASS.2017.18.4.719
URI
http://hdl.handle.net/10203/239471
Appears in Collection
AE-Journal Papers(저널논문)
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