| 地对空导弹空间最优制导律 |
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| 引用本文： | 李秋月,李忠应.地对空导弹空间最优制导律[J].战术导弹技术,1992(3):30-36. |
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| 作者姓名： | 李秋月 李忠应 |
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| 作者单位： | 北京航空航天大学，北京航空航天大学 |
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| 摘 要： | 本文运用最优控制理论中的伴随矩阵变换法,推导了一种用于地对空导弹的空间最优制导律.将发射瞬时所确定的空间平行接近弹道作为基准弹道,把由于各种干扰而产生的相对基准弹道的偏离作为偏差来处理,最优控制律使这种偏差最小.计算机仿真结果表明该空间最优制导律可拦截机动目标,具有较好的制导精度.制导算法在导引头坐标系中以反馈形式给出,在弹上使用,实现起来比较简便,适用于在线运算.
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| 关 键 词： | 地对空导弹 最优导引规律 空间制导律 |
AN OPTIMAL GUIDANCE LAW OF SURFACE TO AIR MISSILE |
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| Li Qiuyue Li Zhongying Beijing University of Aeronautics and Astronautics.AN OPTIMAL GUIDANCE LAW OF SURFACE TO AIR MISSILE[J].Tactical Missile Technology,1992(3):30-36. |
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| Authors: | Li Qiuyue Li Zhongying Beijing University of Aeronautics and Astronautics |
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| Affiliation: | Li Qiuyue Li Zhongying Beijing University of Aeronautics and Astronautics |
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| Abstract: | A space optimal guidance law for surface to air missile is derived from the optimal control theory's matrix transfer approach. Taking the missile flight path of space constant bearing navigation decided at launch moment as a reference trajectory, the deviation compared with the reference trajectory is produced by all kinds of disturbance and it is regarded as deviation. The optimal guidanre law makes the deviation minimum. The simulation results confirm that the law has good adjustability to intercepting the rnanoeuvrable targets and its guidance precision is high. The law takes the direct feedback form in the seeker coordinate and it is simple to be applied to missile. It can be used for on-line calculation. |
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| Keywords: | Surface to air missile Optimal guidance law Space guidance law |
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