基于外弹道和姿态陀螺的导弹攻角和侧滑角解算方法  

Calculation Method of Missile Attack Angle and Sideslip Angle Based on Exterior Trajectory and Attitude Gyro

作　　者：李庚 高晓波 王鹏 娄江 张瑶 赵洁[2,3] 杜凤怀 Li Geng;Gao Xiaobo;Wang Peng;Lou Jiang;Zhang Yao;Zhao Jie;Du Fenghuai(Xi’an Modern Control Technology Research Institute,Xi’an 710065,China;Beijing Institute of Technology,Beijing 100081,China;North Navigation Control Technology Co.,Ltd.,Beijing 100176,China)

机构地区：[1]西安现代控制技术研究所,西安710065 [2]北京理工大学,北京100081 [3]北方导航控制技术股份有限公司,北京100176

出　　处：《兵工自动化》2024年第11期41-43,共3页Ordnance Industry Automation

摘　　要：为获取导弹攻角和侧滑角信息,提出一种基于外弹道和姿态陀螺信息的导弹攻角和侧滑角解算方法。通过导弹外弹道计算导弹弹道倾角和弹道偏角,综合弹上姿态陀螺信息,解算出导弹攻角和侧滑角,用于分析导弹受控特性及弹体气动参数辨识,进一步优化导弹控制系统设计参数。结果表明:本方法简单、有效,可推广应用到所有弹上有姿态测量装置,且可实现外弹道测量的制导弹药飞行攻角和侧滑角分析。In order to obtain the angle of attack and the angle of sideslip of a missile,a method for calculating the angle of attack and the angle of sideslip of a missile based on the exterior trajectory and the attitude gyro information is proposed.The angle of attack and the angle of sideslip of the missile are calculated by calculating the trajectory angle and the trajectory deflection angle of the missile through the external trajectory of the missile and integrating the attitude gyro information on the missile,which are used to analyse the controlled characteristics of the missile and identify the aerodynamic parameters of the missile body,and further optimize the design parameters of the missile control system.The results show that the method is simple and effective,and it can be applied to the analysis of attack angle and sideslip angle of all guided munitions with attitude measurement device and external trajectory measurement.

关 键 词：外弹道 姿态陀螺 攻角 侧滑角 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]