越肩发射空空导弹大攻角飞行自动驾驶仪设计  

Design of Pitch Autopilot for High Angle of Attack of Over the Shoulder of Air-to-Air Missile

作　　者：何素娟[1] 周凤岐[1] 周军[1] 

机构地区：[1]西北工业大学精确制导与控制研究所,西安710072

出　　处：《火力与指挥控制》2011年第5期129-132,共4页Fire Control & Command Control

摘　　要：研究了越肩发射空空导弹大攻角飞行时的两种自动驾驶仪的设计方法。一种是利用双时标的方法将导弹的姿态动力学和运动学系统分别看作快子系统和慢子系统,解决由气动力剧烈变化引起的非线性。另一种采用了变结构控制策略。这两种方法均使用了反作用喷气装置来增强在大攻角情况下的转弯能力和机动能力。数学仿真显示出两种自动驾驶仪的良好性能。Two autopilot design approaches for high angle of attack over the shoulder of air-to-air missile are studied.In order to manage the nonlinear produced by the aerodynamics change drastically,the attitude dynamics and kinematics of the missile are divided in to fast subsystem and slow subsystem by two-time scale method in the first method.A control strategy based on variable structure systems is used in the second method.The purpose of reaction jets is to increase the angle of attack envelope for improved turn rare capabilities and maneuverability.Performances of the two autopilots are illustrated in a nonlinear simulation.

关 键 词：越肩发射 大攻角机动 非线性自动驾驶仪设计 变结构控制 

分 类 号：V448.12[航空宇航科学与技术—飞行器设计]