考虑振动环境影响及具有落角度约束的制导律设计与仿真

为解决因振动环境下视线角和视线角速度抖动而使打击精度降低的问题,文章研究一种具有抗干扰能力和落角度约束的飞行器(含导弹)制导律。建立了飞行器和目标的相对运动方程组,运用变结构控制理论,设计了一种具有落角度约束的制导律,并在制导律中引入视线角和视线角速度的抖动分量。通过仿真对比分析所设计的制导律与修正比例制导律,在攻击固定目标时,两种制导律的效果都能满足脱靶量和落角度约束的要求;而在攻击机动目标时,所设计的制导律控制效果明显优于修正比例制导律,并且飞行器的控制量能根据视线角速度变化较快地做出反应,从而使打击末段脱靶量较小。

Guidance law design and simulation with impact angle constraints in vibration environment

To address the problem of the attacking accuracy degradation resulting from the jitters of the line of the sight angle and the angular velocity in the vibration environment, the guidance law with anti-interference ability and impact angle constraint is investigated. The relative motion equations between aircraft and target are established. The guidance law with impact angle constraint is obtained by using the variable structure control theory, with introduction of the vibration components of the angle of the line of sight and the angular velocity. The simulation comparative analysis of the proposed guidance law and a modified proportional guidance is made. It is demonstrated that in attacking the fixed targets, both guidance laws can meet the requirements of the missing distance and angle constraint. In attacking maneuvering targets, the attack performance of the proposed guidance law is better than the modified proportional guidance law and the control quantity can response faster when the angular velocity of the line of sight changes.