某型探空火箭组合导航系统设计

MIMU/GPS Integrated Navigation System Design of Certain Space Exploration Rocket

为解决某型探空火箭由于无控制系统造成的飞行弹道偏差及落点散布较大的问题,提出由MIMU/GPS组合导航设备、液体姿控发动机、飞控计算机等组成的低成本简控系统方案;组合导航算法采用速度位置间接匹配、反馈校正的Kalman滤波组合法;组合导航设备选用TMS32C67完成导航算法实时解算及信息融合,CPLD完成MIMU及温度传感器的数据采集,MCS51单片机完成GPS板的串口通信;数学仿真结果表明:在475s飞行时间内,火箭姿态控制精度不大于1°,飞行轨迹与理想弹道基本重合,相比原无控火箭有很大改善。

To solve the issue of the flying trajectory error and bigger falling points of a uncontrolled space exploration rocket due to an uncontrol system,this paper proposed an low cost simple control method composed of the MIMU/GPS integrated navigation,liquid attitude control engine,flying control computer.The algorithm of the integrated navigation applied indirect matching method of velocity and position and Kalman algorithm with feedback and emendation.The integrated navigation equipment applied TMS32C67 to complete the real-time computation of the navigation algorithm and information fusion,applied CPLD to complete the data collection of the MIMU and the temperature sensors,applied MCS51 to complete the serial communications of the GPS boards.The digital experimental results show that the accuracy of the attitude control of the rocket was keep under 1 degree,the flying trajectory was identical with the ideal trajectory in the all flying time of 475s.So the rocket performance can be improved much more comparing to the one without control system.