考虑导弹视场约束及落点姿态的协同制导律设计

Design of Cooperative Guidance Law Considering Missile Field-of-View Constraint and Impact Point Attitude Constraint

针对空空导弹协同攻击过程中视场受限的问题,提出一种带有视场角和弹着点姿态约束的协同制导律。在二维平面内建立导弹与机动目标的交战几何模型后,进行制导律的设计。首先,基于时变滑模面,设计视线法向的制导律,选取积分障碍李雅普诺夫函数,保证导弹在攻击过程始终稳定地跟踪目标,且导弹能以期望的落角攻击目标,选取积分障碍李雅普诺夫函数证明制导律收敛;其次,在对攻击剩余时间进行估计的基础上,设计具有时间约束的制导律,保证导弹在预设时间命中目标。最后,在三种假设情景中进行仿真,验证了制导律的可行性。

Aiming at the problem of limited field-of-view of air-to-air missile during cooperative attack,a cooperative guidance law with field-of-view angle and impact point attitude constraints is proposed.After the engagement geometric model between the missile and the maneuvering target is established in the vertical plane,the guidance law is designed.Firstly,based on the time-varying sliding mode surface,the guidance law of the normal direction of the line of sight is designed,and the integral obstacle Lyapunov function is selected to ensure that the missile can stably track the target during the attacking process,and the missile can attack the target at the expected impact point angle.The integral obstacle Lyapunov function is selected to prove the convergence of the guidance law.Secondly,on the basis of estimating the remaining time of the attack,a guidance law with time constraints is designed to ensure that the missile hits the target at the preset time.Finally,the feasibility of the guidance law is verified by simulation in three scenarios.