直瞄式近程旋转火箭弹的捷联惯导系统建模研究

Modeling for Strap-down Inertial Navigation System of Direct-fire Spinning Rockets with Short Range

捷联惯导系统通常应用于较远射程的导弹等飞行器上,近年来,随着惯性器件的微型化和低成本化,使其在近程小口径火箭武器上的应用成为可能,在近程武器上仍采用原有的捷联惯导解算方法则过于复杂,文中推导了在近射程、滚转体制条件下直瞄式火箭弹的捷联惯导基本方程,建立了相应的解算模型。在此基础上,以某型直瞄式反坦克火箭弹为例进行了仿真,验证了所建立的惯导方程及解算模型的正确性。

Strap-down Inertial Navigation System(SINS)is usually applied to relatively long-range missiles and so on. How,wet,it is possible for SINS to be adopted in small-caliber rockets with short range because inertial instruments be- come smaller and cheaper in recent years.The traditional solving method of SINS is too complex when applied to short- range weapons.In this paper,a general inertial equation is deduced which fits for spinning rockets with short range. and the corresponding SINS model is also set up.Furthermore.they are proved to be right by simulation of one anti- tank rocket as an example.