带末端角度约束的多导弹协同制导律设计

为了实现饱和攻击与饱和防御,提出了一种针对机动目标的多导弹协同制导律。建立了视线坐标系下的弹目相对运动数学模型,设计了三阶扩张状态观测器,对目标机动加速度项和运动方程中的耦合项进行观测与跟踪。在导弹飞行前段,基于滑模变结构理论设计了攻击时间可控的多导弹时间协同制导律; 在导弹攻击末段,基于有限时间控制理论设计了满足终端角度约束的制导律,给出了导引律切换条件。仿真结果表明:该复合导引律能够使多枚导弹在满足攻击末端角度约束的条件下实现攻击时间协同; 该制导律采用完备的空空导弹轨迹控制系统进行仿真,能够满足实际工程应用的要求。

Cooperative Guidance Law for Multiple Missiles With Terminal Impact Angle Constraint

A cooperative guidance law was proposed for multiple missiles in order to attack or defense against maneuvering targets at the same time.The equation of missile-target relative motion was established in sight line coordinate-system,and the third-order extended state observer was designed to observe and track acceleration of targets and coupling terms in the motion equation.The 4D impact-time control guidance law(ITCG)was designed in the forepart of interception based on the sliding mode control theory to ensure the attack time to be controlled.In the terminal ballistic trajectory,another guidance law based on the finite time control theory was designed to meet the terminal angle constraint.Switching conditions of guidance law was also designed considering aspects of time and space.Numerical simulation results show that the attack time of multiple missiles is basically the same under the terminal attack angle constraint,and this guidance law can be used to combat maneuvering targets.The simulation is conducted using complete model of air-to-air missile,and this guidance law can be applied in actual projects.