大攻角导弹舵机时频域特性与飞控系统匹配性研究  

Adaptability Research of Time-frequency Characteristics on Actuator and Flight Control System at High Angle of Attack Missile

作　　者：郭晓楠[1] 罗绪涛[1] 徐挺[1] 

机构地区：[1]中国空空导弹研究院,河南洛阳471099

出　　处：《南昌航空大学学报（自然科学版）》2015年第1期27-32,共6页Journal of Nanchang Hangkong University(Natural Sciences)

基　　金：国家自然科学基金(61263012;U1431118;61263040);中国博士后基金(2012M510593);航空科学基金(20120156001)

摘　　要：导弹的操纵能力是限制其飞控系统性能的主要因素,在导弹设计初期阶段,必须完成飞控对舵系统要求,否则会导致舵系统与飞控系统的性能指标不匹配,从而降低设计工作的实际价值。从工程实际出发,基于法向过载自动驾驶仪结构,首先给出了最小相位系统和非最小相位系统的复合回路指标论证方法,在此基础上,经数学推导获得了飞控系统要求的最大舵偏角、最大舵偏角速度的数学表达式,给出了稳定回路带宽、舵机带宽与一次弹性振型频率之间的相互关系。借助于Matlab计算机仿真手段,给出了典型状态下得定点计算结果,该结果可做为导弹初期设计阶段时飞控对舵系统设计的约束条件和控制裕度设计参考依据。The control ability of the missile is the main factor limiting the performance of system, the requirements for the rudder system must be completed in the early stage of missile flight control design stage, otherwise, it will lead to the performance index of rudder system and flight control system does not match. This paper is based on the law of the autopilot structure to overload, firstly, a method of composite loop index demonstration of minimum phase systems and non-minimum phase system is given, the maximum rudder angle and the maximum rudder angle velocity are obtained, the relationship between the stabilization loop bandwidth, frequency bandwidth of actuator and a flexible mode are given. With the help of Matlab computer simulation method, the fixed-point calculation results typical condition are given, the result can be used as the initial design stage of missile flight control of rudder system design constraints and control margin reference.

关 键 词：空空导弹 舵系统 飞控系统 匹配性 

分 类 号：V448[航空宇航科学与技术—飞行器设计]