摘要
针对飞行实验成本高、难度大的问题,设计并实现了一种大视场星光修正惯性导航系统的半实物仿真试验系统。该系统采用轨迹发生器模拟生成飞行过程中导航传感器数据,利用真实星敏感器与IMU的静态输出获得器件误差,结合时间软同步完成信息采集,通过组合导航模块实现模拟飞行过程的组合导航解算。实验结果表明,该系统具有较强的灵活性和通用性,可在地面验证星光修正惯性导航算法性能,具有一定的工程应用价值。
In order to solve the problem of actual flight test which is expensive and difficult,a hardware-inthe-loop simulation system is designed and realized for strapdown inertial navigation system corrected by star sensor with large view field. The navigation sensor data is generated by the trajectory simulator during the missile flying,and the noise data is obtained from the real star sensor and IMU. All the information is collected with the method of soft synchronization,and the integrated navigation computation is accomplished by using the program. Through a large amount of experimental verification,it is manifested that this system has strong flexibility and versatility and can verify the algorithm performance of star-correcting inertial navigation. The hardware-in-the-loop simulation system is of practical value to reduce the experimental cost and study the system performance of stars-correcting inertial navigation.
作者
刘百奇
刘建设
吕艳
Liu Baiqi;Liu Jianshe;Lv Yan(R＆D Center, China Academy of Launch Vehicle Technology, Beijing 100076, China;Science and Technology Space Physics Laboratory, Beijing 100076, China)
出处
《航天控制》
CSCD
北大核心
2018年第2期70-76,82,共8页
Aerospace Control
关键词
星光修正
捷联惯导
半实物仿真
大视场敏感器
Starlight correction
SINS
Hardware-in-the-loop simulation
Star sensor with large view field
