针对某型通用导弹飞行弹道的特殊性,文中提出了一种给定飞行高度规律的高度下滑飞行方案。考虑到通用导弹采用的是简易捷联惯性导航的控制方案,在飞行速度变化较小或近似不变时的垂直速度,通过积分器对其信号进行积分,即可得到导弹的实时位置。因此在充分利用捷联惯导的加速度计的基础上,通过控制捷联惯导的垂直速度,进行了高度下滑规律的理论推导,最后进行数学仿真和验证,仿真结果表明该方案合理可行。

In view of particularity of common missile's gliding trajectory, in this paper, a glide trajectory scheme was provided based on given height. Considering the common missile using a simple strapdown inertial navigation control program, at the flight speed with few changes or nearly constant vertical velocity, the integrator was adopted for the signal, and the real-time location of the missile can be obtained. So by taking full advantage of the accelerometer of the SSIN, this glide method can be realized by controlling the vertical velocity of inertial navigation systems, then academic discussion and ballistic simulation were conducted. Digital simulation shows that this glide method is reasonable and feasible.