气动力／推力矢量复合控制空空导弹最佳转弯规律  

The Optimal Agile Turn Control of Air-to-air Missile Launching in Large Off-boresight

作　　者：孙杰[1] 杨军[1] 楚德强[2] 

机构地区：[1]西北工业大学航天学院,陕西西安710072 [2]第二炮兵工程学院,陕西西安710025

出　　处：《火力与指挥控制》2009年第5期122-124,共3页Fire Control & Command Control

摘　　要：针对气动力/推力矢量复合控制空空导弹大离轴角发射的快速转弯问题,根据bang-bang控制理论,给出了导弹终端弹道角受限情况下,以最大末速为性能指标的最佳转弯规律。针对空空导弹纯气动力控制和复合控制两种情况,分别进行了初制导弹道的设计和仿真。结果显示,在中空低速发射时,采用后者转弯性能明显高于纯气动力控制导弹,而当初速高于1.2 Ma时,二者转弯性能非常接近。The agile turning problem of Air-to-Air missile launching in large off-boresight was investigated using theory of optimal control. The optimal turning law of maximal terminal velocity was drawn in horizontal level when the terminal trajectory angle of missile was restricted. The design and simulations of original guidance trajectory of Air-to-Air missile, controlled by pure aerodynamic and aerodynamic/thrust vector have been completed separately, based on this turning law. The results showed the turning performance of the later excel the later when the missile was launched in mid-air and low velocity. And the performance of the two cases became similar when the original velocity exceeds 1.2 mach.

关 键 词：大离轴角发射 气动力/推力矢量控制 BANG-BANG控制 最佳转弯规律 

分 类 号：TJ762.2[兵器科学与技术—武器系统与运用工程]