Impact Angle Control Guidance Synthesis for Evasive Maneuver against Intercept Missile

被引:6
|
作者
Yogaswara, Y. H. [1 ,2 ]
Hong, Seong-Min [1 ]
Tahk, Min-Jea [1 ]
Shin, Hyo-Sang [3 ]
机构
[1] Korea Adv Inst Sci & Technol, Daejeon 34141, South Korea
[2] Indonesian Air Force, Dept Res & Dev, Bandung 40174, Indonesia
[3] Cranfield Univ, Bedford MK43 0AL, England
关键词
Missile guidance; Evasive maneuver; Impact angle control; Artificial potential field; OBSTACLE AVOIDANCE; LAWS;
D O I
10.5139/IJASS.2017.18.4.719
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
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.
引用
收藏
页码:719 / 728
页数:10
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