大配平角起始条件下的非线性末制导律研究

Research on nonlinear terminal guidance law under high alignment angle condition

针对大配平角误差起始条件下导弹捕获高机动性目标问题 ,分析了一般非线性末制导运动 ,得到了稳定性充要条件。基于滑模态控制技术 ,综合了一种新型的梆 -梆末制导律。它是一般非线性末制导运动方程的通解 ,相对于线性二次型理论解具有明显的优点 :不需目标加速度和剩余时间信息 ;能够在各种起始大配平角误差条件下收敛。最后给出的仿真算例证明了理论分析的正确性和该制导律的实用价值。

To miniaturize the miss distance for a missile to capture a high maneuverable target under high off-bore-sight angle condition, based on the sliding mode control technique, after analyzing the general nonlinear terminal relative motion and then with the help of the gained insight of a key variable defined as alignment angle (the angle between the relative velocity and the line-of-sight) and the obtained sufficient necessary condition for capture, a new guidance law is synthesized which has the prominent advantages over LQ theory law in that: first the target acceleration information and time-to-go is unneeded;second,it is easy realizable in future versatile missile guidance systems with reasonable cost. Numerical simulation results demonstrate that a missile-autopilot model of second-order with limited normal acceleration can capture an evasive target with smaller miss distance under the condition of higher initial alignment error angle ranges comparing with the LQ theory law.