摘要
弹性弹体的建模研究是摆动喷管推力矢量技术应用于我国未来防空导弹上面临的首要任务。以俯仰通道为例,对弹性弹体在飞行过程中受到的力和力矩进行了详细的分析,其中包括单喷管模型以及弹性振动模型的分析。基于某些可行性的假设条件,建立了弹性弹体俯仰通道的小扰动线性化方程组,并进一步给出了弹性弹体俯仰运动系统的状态空间模型。根据等效性原则,同时给出了一个降阶的、可面向弹性振动主动控制的状态空间模型。最后,在选取的飞行特征点附近,通过对某型防空导弹的幅频特性仿真,验证了该弹体存在的弹性振动对其运动系统的影响。
When swing nozzle thrust vector control （SNTVC） technique is applied in domestic antiaircraft missile, the modeling of elastic missile body will become the primary task. Taking the pitch channel for example, the force and moment of flying elastic missile were elaborated, where the models of single swing nozzle and elastic vibration were analyzed. Based on some assumed conditions, the linear attitude motion equations with small disturbance on pitch plane were established. Furthermore, a state-space model of pitch motion system was constructed. On the basis of equivalent principle, a reduced order state-space model for active control against elastic vibration was given. Finally, at the chosen feature point of flight, the simulation result on amplitude-frequency characteristic of one antiaircraft missile presents the influence of elastic vibration on missile motion system.
出处
《系统仿真学报》
CAS
CSCD
北大核心
2014年第3期650-656,681,共8页
Journal of System Simulation
基金
国家自然基金项目(91216304)
关键词
摆动喷管
推力矢量
防空导弹
弹性振动
建模
主动控制
swing nozzle
thrust vector
antiaircraft missile
elastic vibration
modeling
active control
