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摘要:
为了实现大前置角拦截下的时间一致性饱和攻击，利用非线性导引方程，采取基于预测命中点（PIP）的剩余时间估计方法，结合等效滑模控制理论和Lyapunov稳定性定理，设计了一种大前置角拦截攻击时间控制导引律（ITCG）。针对固定目标和非机动运动目标，在弹目接近速度为负的情况下也能保证准确命中，实现了任意初始前置角下的指定时间到达，拓宽了导弹的制导初始条件，并给出了严格的理论证明。不同初始条件下的仿真结果验证了导引律的有效性。
Abstract:In order to achieve salvo attack for large heading errors with integrated time, an impact time control guidance (ITCG) law for large heading errors is proposed based on equivalent sliding mode control theory and Lyapunov stability theorem by adopting the nonlinear guidance equation and the time-to-go approximation algorithm according to predicting interception point (PIP). For stationary and non-maneuvering constant velocity targets, the proposed guidance law achieves impact time successfully with any designated initial heading error even when the closing speed is negative. Initial conditions of the missile guidance are widely broadened. Rigorous theoretical proof demonstrates the validity of the guidance law. The simulation results under different initial conditions verify the effectiveness of the proposed guidance law.
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Key words:
- large heading errors /
- impact time control /
- salvo attack /
- equivalent sliding mode /
- guidance law
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图 2 固定目标拦截时不同攻击时间仿真
Figure 2. Simulation of different impact time for intercepting stationary target
图 3 固定目标拦截时不同前置角仿真
Figure 3. Simulation of different heading errors for intercepting stationary target
图 4 运动目标拦截时不同攻击时间仿真
Figure 4. Simulation of different impact time for intercepting moving target
图 5 运动目标拦截时不同前置角仿真
Figure 5. Simulation of different heading errors for intercepting moving target
表 1 仿真参数值
Table 1. Value of simulation parameters
初始参数 数值 导弹初始位置/m (0，0) 目标初始位置/m (10 000，0) 导弹弹道倾角θM0/(°) 60 目标弹道倾角θT0/(°) 180 导弹速度VM/(m·s-1) 300 目标速度VT/(m·s-1) 0、120 导弹最大法向加速度aMmax/(m·s-2) 250 
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