空空导弹高抛弹道复合导引律仿真研究

面向空空导弹远距攻击作战需求,提出了一种涵盖中制导、末制导和中末制导平滑过渡3个阶段的高抛弹道复合导引律。针对典型空中目标,建立基本机动飞行模型。在此基础之上,设计开发一套空战仿真软件通过设置对不同发射条件、不同目标机动条件,验证高抛弹道导引律的正确性,并与比例导引在最大攻击距离平均飞行速度、末端命中速度等方面进行对比分析。仿真结果显示,提出的高抛弹道导引律能够在各种发射条件下准确命中目标,具有较强的自适应性。同时,与比例导引相比,能够显著提高空空导弹的综合攻击效能,具有较高的工程应用价值。

Simulation Research on High Projectile Trajectory Integrated GuidanceLaw of Air-to-Air Missile

Aiming at the long-range attack combat requirements of air-to-air missiles , a high-throwtrajectory compound guidance law covering three stages of midcourse guidance , terminal guidanceand smooth transition between midcourse and terminal guidance is proposed. A basic maneuveringflight model is established for typical air targets. On this basis , a set of air combat simulation softwareis designed and developed. By setting different launch conditions and different target maneuveringconditions ,the correctness of the high projectile trajectory guidance law is verified, and comparedwith the proportional guidance in the maximum attack distance , average flight speed, terminal hitspeed and other dimensions. The simulation results show that the high projectile trajectory guidancelaw proposed in this paper can accurately hit the target under various launch conditions, and hasstrong adaptability. At the same time , compared with proportional guidance , it can significantly im.prove the comprehensive attack effectiveness of air-to-air missiles and has high engineering application value.