冗余惯组初始基准现场校准装置研究

航天飞行器需要满足长时间待机、长轨迹飞行及高准确入轨的要求。新一代运载火箭从单一的惯性平台导航方式，改进为多套捷联惯组冗余制导方式。火箭飞行时，其中一套惯组作为主份，控制火箭飞行，其它惯组则处于热备份状态，参与冗余判断，并在主份出现故障时接管其工作。这就要求在火箭飞行前，需对冗余惯组之间的初始角度差进行现场标定。提出了利用光电测角技术原理，对冗余惯组之间的初始安装相对角度差进行测量，论述了标定方法及测量设备的研制方案，并对测量结果进行解算和原理验证，试验表明其具有测量原理正确、测试结果准确以及可操作性强等优点。

Research on Redundancy Inertial Guidance Used to Set the Initial Reference Field Calibration Device

Spacecraft need to meet the requirements of long standby, long trajectories and high accurate orbit . Generation of carrier rockets from a single inertial platform navigation way, improved redundant guidance system for multiple sets of Strapdown Inertial Measurement Unit. when rocket in the flight of the heaven, a customary group as the main parts control of rocket flight, the other IMU is a hot backup state involved in the redundancy judgment and takes over the main parts work while the main parts failure . This requires site calibration of the initial angle difference between the Redundant Inertial Measurement Unit before the rocket flight. The use of photoelectric goniometer principle measure the installed initial relative angle difference between Redundant Inertial Measurement Unit . We discussed the calibration methods and measurement equipment development program, calculated the measurement result and the proof of principle. The experiments show that the measuring principle is correct, the test results are accurate and strong maneuverability advantages.