摘要
弹道导弹反激光滚动突防,给制导和稳定技术带来了困难和挑战。为保证弹头命中精度,要求研究鲁棒性、稳定性和精度较高的制导方法。本文结合美国航天飞机的制导律,开发了能满足较大初始偏差、推力偏差和姿态稳定偏差的弹上可实现的鲁棒自适应制导方法。数值仿真结果验证了其可行性和有效性,方法具有实用的参考意义。
The difficulties and challenges are brought to the guidance and stability for the rolling breakthrough of ballistic missile. To keep the shooting precision, the adopted guidance method should be robust, stable and highly precise. The paper exploited a new kind of robust self-adaptive method on the basis of the Space Shuttle, which is feasible and efficient by the demonstration of numerical simulation, also can be realized for the missile, in the cases of large initial state bias, thrust bias and attitude control bias.
出处
《系统仿真学报》
EI
CAS
CSCD
2004年第11期2597-2600,共4页
Journal of System Simulation
关键词
导弹突防
鲁棒制导
自适应
滚动
missile control
robust guidance
adaptive
spin
