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Robust Nonlinear Terminal Guidance of Agile anti-air Missile
GuangQianCao #
Astronautic College of Northwestern Polytechnic University
*Correspondence author
#Submitted by
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Funding: none
Opened online:10 July 2004
Accepted by: none
Citation: GuangQianCao.Robust Nonlinear Terminal Guidance of Agile anti-air Missile[OL]. [10 July 2004] http://en.paper.edu.cn/en_releasepaper/content/916
 
 
For a limited-maneuverability agile missile capturing a high-maneuverable target aircraft, the three -dimensional nonlinear terminal guidance issue is addressed based on the analysis of the general relative target kinematics to the missile and on the insight of the importance of an alignment angle to stability, a sliding mode guidance law is synthesized. To suppress the vibration of the error dynamics impacting the sliding surface when including the effects of the modeling errors and non perfect switching control and seeker dynamics in real-life environment, a dynamic error feedback is introduced to acceleration feedback-loop. The simulation results demonstrate that the guidance scheme can successfully suppress the chattering of the error dynamics to minimum and capture the high maneuverable target with larger initial off-bore-sight angle comparing with PNG law.
Keywords:agile missile; nonlinear guidance law; sliding mode control; chattering suppressing;
 
 
 

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