Study on Optimal Guidance Law Under Multiple-Constrained Condition
Sun Yangping;Lin Wangpeng;Fan Zuoe;Zhou Jing;Administrant Brigade of Postgraduate,Naval Aeronautical & Astronautical University;No. 91640 Unit of PLA;Department of Strategic Missile & Underwater Weapon,Submarine Academy of PLA Navy;No. 92474 Unit of PLA;
In order to meet the requirements of multiple constrain conditions and high-precision guidance of the missile,the article put forwards a new optimal guidance law. Considering the conditions under the constraints with the impact angle and the angle of attack, the new guidance law was deduced by the quadratic optimal control, and approximate expression of zero-order lag-free system was given. At last, use typical trajectory simulation and comparison test to verify great trajectory performance of guidance law. The verified result shows that the optimal guidance laws with the impact angle and the angle of attack constraint is satisfied with the precision guidance in the multi-constraint conditions, and have more predominance of acceleration control in terminal phase and trajectory compensation in early phase.
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