Robust Nonlinear Terminal Guidance of Agile anti-air Missile
首发时间:2004-07-10
Abstract: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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敏捷对空导弹的鲁棒末制导
摘要:针对高机动性目标,研究了机动能力受限的导弹三维非线性制导问题。在配平角误差动力学稳定性分析的基础上,提出了一个变结构鲁棒律。并针对计入导引头动力学后的系统震荡,采用了误差动力学补偿信号反馈。仿真结果证明相对比例导引而言,该方法能使导弹在更大的瞄准线滞后角条件下发射命中目标。
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No.9165171108945241****
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