导弹姿态控制系统弹性振动抑制问题研究  

Research on Elastic Vibration Suppression of Missile Attitude Control System

作　　者：宿常鹏 王雪梅 许哲 李骏霄 王兴龙 SU Changpeng;WANG Xuemei;XU Zhe;LI Junxiao;WANG Xinglong(Rocket Force University of Engineering,Xi'an 710025,China;Rocket Force NCO School,Shandong Qingzhou 262500,China)

机构地区：[1]火箭军工程大学,西安710025 [2]火箭军士官学校,山东青州262500

出　　处：《弹箭与制导学报》2019年第5期154-157,162,共5页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：国家自然科学基金(61573365,61174030)资助。

摘　　要：为抑制弹体的弹性振动对导弹姿态控制系统稳定性的干扰,提出了应用时变陷波滤波器进行改进的方法。以某型导弹为例,对其姿态控制系统的模型进行了简化,并建立弹性弹体的数学模型。依据现有的气动数据,完成导弹姿态控制系统加入时变陷波滤波器的改进设计。理论计算和仿真实验表明,改进后的导弹姿态控制系统稳定品质良好,稳定过程满足指标要求,验证了所提方法的有效性。In order to suppress the elastic-vibration disturbance to the stability of missile attitude control system, this paper proposed an improved method using time-varying notch filter. For a certain type of missile, we simplified the model of attitude control system and established the mathematical model of elastic missile body. According to the existing aerodynamic data, this paper finished the modification of missile attitude control system with time-varying notch filter. The theoretical calculation and simulation experiment show that the attitude control system with time-varying notch filter has good stability, and the stability process meets the index requirements, so the effectiveness of the proposed method is verified.

关 键 词：弹性振动 姿态控制 陷波滤波器 稳定裕度 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计] TP273[自动化与计算机技术—检测技术与自动化装置]