系统工程与电子技术

• 制导、导航与控制 • 上一篇    下一篇

飞行器动力学信息辅助MEMS惯导系统

李烨1, 郭建国1, 赵斌1, 尤雨骅2, 卢晓东1, 周军1   

  1. (1.西北工业大学精确制导与控制研究所, 陕西 西安 710072;
    2.中国运载火箭技术研究院, 北京 100076)
  • 出版日期:2016-07-22 发布日期:2010-01-03

Aircraft dynamicsaided MEMS inertial navigation system

1, GUO Jianguo1, ZHAO Bin1, YOU YuHua2, LU Xiaodong1, ZHOU Jun1   

  1. (1. Institute of Precision Guidance and Control, Northwestern Polytechnical University, Xi’an 710072, China;2. China Academy of Launch Vehicle Technology, Beijing 100076, China)
  • Online:2016-07-22 Published:2010-01-03

摘要:

使用微机械电子(micro electro mechanical systems, MEMS)惯导系统(inertial navigation system,INS)的飞行器由于其MEMS惯性器件测量精度低,致使导航误差快速发散。针对该问题,提出了一种利用飞行器动力学(aircraft dynamics, AD)信息辅助MEMS惯导解算的方法。〖JP2〗它基于AD建立的飞行器运动模型和运动误差模型,利用实时解算的飞行器运动状态构建卡尔曼滤波器对MEMS惯导误差进行估计和修正。在此基础上,进一步考虑了INS/全球定位系统(global positioning system,GPS)组合导航时该方法的改进算法,提出了一种利用GPS定位信息和预测滤波器对飞行器动力学模型误差估计的方法。最后的半实物仿真实验结果表明,飞行器动力学信息辅助滤波器可以有效地减小系统误差,提高 MEMS惯导系统输出精度。

Abstract:

The micro electro mechanical systems (MEMS) inertial navigation system (INS) of an aircraft has low measure accuracy, so that the navigation error rapidly drifts. For this shortage, an aircraft dynamics (AD)aided MEMS INS method is proposed. The method is based on the AD model and the dynamic error model, using realtime dynamic calculation information to build Kalman filter to estimate and correct MEMS INS error. Further more, considering the improved algorithm when integrating INS/global positioning system (GPS) navigation, an arithmetic is proposed which evaluates aircraft dynamic error by making use of GPS information and the predictive filter. Finally, the hardwareintheloop simulation test result shows that the aircraft dynamicsaided system can effectively reduce INS system error and improve the MEMS INS output accuracy.