智能炮弹姿态测量新方法

A New Attitude Determination Approach for Intelligent Projectile

研究炮弹姿态制导和测量问题,智能炮弹的制导与控制,不但要求能精确测量弹体的姿态,还要求惯性敏感元件和电子系统能承受发射时的高g冲击。针对智能炮弹发射时的高冲击性及惯性短时飞行的特点,为了姿态控制稳定性,提出了一种弹体姿态测量的新方法。根据智能炮弹的特定运动规律,仅采用三个MEMS加速度计对比力矢量进行测量,建立系统的线性状态方程和非线性量测方程,采用平方根无轨迹Kalman滤波器估计系统的状态,有效的抑制了滤波发散,增强了滤波的稳定性。经三轴飞行测试转台仿真实验表明,方法测量弹体姿态的可行性。

During the guidance and control of intelligent projectiles, it is necessary for the inertial sensors and electronic system to accurately detect the attitude of the projectile and endure the high g impulse while launching. In this paper, considering the performance of high impulse of launch, inertial flight and short -time working for intelligent projectile, a new attitude determination approach is proposed. According to the special motional rule of intelligent projectile, only use three MEMS aeeelerometers to measure the specific force vector, and construct the linear state equation and nonlinear measurement equation of nonlinear system. Use the square - root unscented Kalman filter to estimate the state of the system, which effectively restrains the divergence of filter and enhances the stability of filter. The experimental results in a three -axis flight test rotary table show the proposed approach is feasible.