内嵌飞行动力学的高动态飞行器惯性基深耦合导航方法  

Inertial-based Deep-coupling Navigation Method with Embedded Flight Dynamics

作　　者：杨子傲 曲麒富 孙海文 李烨 嵇振涛 YANG Ziao;QU Qifu;SUN Haiwen;LI Ye;JI Zhentao(School of Automation,Beijing Institute of Technology,Beijing 100081,China;Engineering Research Center of Navigation,Guidance and Control Technology of Ministry of Education,Beijing 100081,China;China Academy of Aerospace Systems Science and Engineering,Beijing 100037,China;Naval Research Institute,Beijing 100161,China;Hua an Industry Group Co.,Ltd.,Qiqihaer 161046,Heilongjiang,China)

机构地区：[1]北京理工大学自动化学院,北京100081 [2]导航、制导与控制技术教育部工程研究中心,北京100081 [3]中国航天系统科学与工程研究院,北京100037 [4]海军研究院,北京100161 [5]北方华安工业集团有限公司,黑龙江齐齐哈尔161046

出　　处：《兵工学报》2024年第S02期240-250,共11页Acta Armamentarii

基　　金：国家自然科学基金项目(U2341215)。

摘　　要：为研究不依赖卫星的高动态飞行器自主导航方法,建立高动态飞行器的飞行动力学模型。采用数值积分法,解算出高动态飞行器轨迹信息,分析高动态飞行器飞行误差特性,并生成虚拟惯导数据。基于飞行误差特性,提出一种利用实测惯导数据与虚拟惯导数据动态加权的导航解算方法,并依靠“速度+姿态”匹配卡尔曼滤波方法进一步抑制导航误差。通过对内嵌飞行动力学的惯性基深耦合导航方法进行仿真,验证所提出的深耦合导航方法。仿真结果表明,新方法能够大幅度提升导航精度,在预置飞行轨迹偏差程度不同的情况下,新方法对导航效果的提升幅度分别达到97.1%、72.9%和40%。To study the autonomous navigation method of high dynamic flight vehicle that does not rely on satellites,a flight dynamics model of high dynamic flight vehicle is established.The numerical integration method is used to solve the trajectory information of high dynamic flight vehicle,the flight error characteristics of high dynamic flight vehicle is analyzed,and generate the virtual inertial navigation data is generated.A navigation solution method using the dynamic weighting of measured inertial navigation data and virtual inertial navigation data is proposed based on the characteristics of flight errors,and the“velocity+attitude”matching Kalman filter method is used to further suppress the navigation errors.The inertial-based deep-coupling navigation method with embedded flight dynamics is proposed and proven through simulation.The results show that the proposed deep-coupling navigation method can significantly improve navigation accuracy.The improvement in navigation performance of the proposed method reaches 97.1%,72.9%,and 40%under different degrees of preset flight trajectory deviation.

关 键 词：高动态飞行器 飞行动力学 惯性基深耦合 自主导航 误差特性 卡尔曼滤波 

分 类 号：V249.3[航空宇航科学与技术—飞行器设计]