首页 | 本学科首页   官方微博 | 高级检索  
     检索      

高超声速飞行器发射坐标系导航算法
引用本文:陈凯,沈付强,孙晗彦,周钧.高超声速飞行器发射坐标系导航算法[J].宇航学报,2019,40(10):1212-1218.
作者姓名:陈凯  沈付强  孙晗彦  周钧
作者单位:西北工业大学航天学院,西安 710072
基金项目:航天科技创新基金(2016KC020028);航天科学技术基金(2017HTXG)
摘    要:针对高超声速飞行器弹道特点和导航参数的需求,提出基于发射坐标系(LCEF)的高超声速飞行器导航算法。首先,介绍发射坐标系下捷联惯导(SINS)算法编排,推导发射坐标系下姿态、速度和位置离散递推方程。然后,介绍地心地固系(ECEF)下的卫星位置和速度转换到发射坐标系的方法,推导发射坐标系的SINS/BDS组合导航滤波器状态方程和量测方程。最后,以助推-滑翔飞行器为对象,进行了发射坐标系下组合导航仿真,位置精度小于10 m,速度精度小于0.2 m/s。

关 键 词:高超声速飞行器  临近空间  发射坐标系  捷联惯导算法  组合导航  
收稿时间:2019-06-12

Hypersonic Vehicle Navigation Algorithm in Launch Centered Earth Fixed Frame
CHEN Kai,SHEN Fu qiang,SUN Han yan,ZHOU Jun.Hypersonic Vehicle Navigation Algorithm in Launch Centered Earth Fixed Frame[J].Journal of Astronautics,2019,40(10):1212-1218.
Authors:CHEN Kai  SHEN Fu qiang  SUN Han yan  ZHOU Jun
Institution:School of Astronautics, Northwestern Polytechnical University, Xi’an 710072, China
Abstract: Aiming at the trajectory characteristics of hypersonic vehicles and the navigation needs of flight control systems, a hypersonic vehicle integrated navigation algorithm in the launch centered Earth-fixed (LCEF) frame is proposed. Firstly, the strapdown inertial navigation system (SINS) algorithm in the LCEF frame is introduced, and the discrete recursive equations of attitude, velocity and position are derived. Then, how to convert the position and velocity of the BeiDou navigation satellite system (BDS) from the Earth-centered Earth-fixed (ECEF) frame to the LCEF frame is introduced, and the state equations and measurement equations in the LCEF frame of the SINS/BDS integrated navigation filter are derived. Taking the trajectory of a hypersonic boost-glide vehicle as an example, the SINS/BDS integrated navigation simulation is carried out. The position accuracy is less than 10 m and the speed precision is less than 0.2 m/s.
Keywords:Hypersonic vehicle  Near space  Launch centered Earth-fixed frame  Strapdown inertial navigation algorithm  Integrated navigation system  
本文献已被 CNKI 等数据库收录!
点击此处可从《宇航学报》浏览原始摘要信息
点击此处可从《宇航学报》下载免费的PDF全文
设为首页 | 免责声明 | 关于勤云 | 加入收藏

Copyright©北京勤云科技发展有限公司  京ICP备09084417号