单天线GPS姿态测量系统在制导火箭中的应用

了解决火箭横向尺寸不足以安装多天线GPS的技术问题, 提高制导火箭飞行姿态 的测量精度, 研究了利用单天线GPS进行姿态测量的方法. 引入伪姿态的概念, 分析了由伪姿态测量辅助求取载体姿态的具体算法, 建立了单天线GPS姿态测量的数 学模型, 利用卡尔曼滤波模型对状态矢量模型进行滤波, 得到相应的速度、加速度信息, 根据常规姿态与伪姿态的关系, 得到火箭的常规姿态信息. 通过仿真研究, 验证了这种姿态测量系统在制导火箭上的可行性和有效性. 

Research on the Application of Single-antenna GPS Measurement System on Guided Rocket

In order to improve the attitude determination accuracy of the guided rocket which transverse size is not enough for fixing multiple antennae, a single-antenna GPS aiding attitude determination method was proposed. The pseudo attitude was introduced, using which the concrete algorithm for obtaining the altitude is analyzed. And the model of the single-antenna GPS aiding attitude is established. The Kalman filtering is adopted to filter the state vector model. And the relative velocity and acceleration is obtained. According to the relationship between ordinary and pseudo attitude, the ordinary attitude of guided rocket is obtained. Throughout the simulation research, the feasibility and effectiveness of the application of single-antenna GPS system on rocket projectiles is demonstrated.