近程导弹捷联惯导系统初始对准方法与误差模型  

METHOD OF INITIAL ALIGNMENTS OF A SHORT RANGE MISSILE WITH STRAPDOWN INERTIAL GUIDANCE SYSTEM

作　　者：齐占元[1] 张靖[1] 朱伯立[1] 

机构地区：[1]北京理工大学,北京100081

出　　处：《兵工学报》2004年第5期567-571,共5页Acta Armamentarii

摘　　要：为了解决近程导弹惯导系统在肩扛瞄准过程中的初始对准问题及惯性器件误差对其影响 ,提出了初始对准方法。该方法是在发射前对扰动加速度进行测量并予以平均并在瞄准试验的基础上建立起来的。通过把比力矢量向一个在惯性空间中稳定的临时平台坐标系中投影 ,可以建立初始对准过程的数学模型 ;再经坐标变换和相似变换建立误差分析数学模型 ,该模型给出了惯性器件的误差分配关系。根据试验数据进行数字仿真 。In order to solve the problem of initial alignment for a short range strapdown inertial guided missile when the launcher was supported on the shoulder of the antitank personnel, and to analyze the influence of the inertial sensor errors to alignment, the method of initial alignment was suggested. The alignment method measures and takes the average of initial disturbance accelerations before firing the missile. Establishment of the method was based on alignment experiments. Mathematical model of initial alignments was set up by projecting the specific force vector to a stable temporary platform coordinate system in an inertial space. An error analysis model was obtained through coordinate and similarity transformations. The initial alignment model was verified and validated through digital simulation experiments. Error distribution of inertial sensors is provided based on the error analysis model.

关 键 词：近程导弹 捷联惯导系统 初始对准 误差 自动控制 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程]