基于动基座重力梯度仪的导弹主动段飞行状态估计

弹道导弹主动段由于惯导系统工具误差和扰动引力的影响,使得导弹关机点状态参数偏离标准关机状态参数,大大影响了导弹的命中精度.为此,提出了基于动基座重力梯度仪的导弹主动段飞行状态估计方案,利用动基座重力梯度仪测得的导弹实际位置引力梯度信息,采用卡尔曼滤波方法,修正导弹当前的飞行状态.通过初步仿真,证明该方法理论上是可行的.

Flight States Estimate of the Missile Active Phase Based on Moving-Based Gravity Gradiometer

The fight states errors between practical shutdown point and standard shutdown point of a ballistic missile are caused by the guidance instrument error and the disturbing gravity for the missile active phase and the precision of points of all is influenced.In this paper,the flight states estimate project of the missile active phase based on moving-base gravity gradiometer is put forward.The real-time flight states of a missile are revised by using moving-base gravity gradiometer,measuring the gravity gradie...