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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。
Spacecraft needs to meet the long standby, long-range flight and high-precision orbit requirements. A new generation of launch vehicles from a single inertial platform navigation mode, improved for multiple sets of SINS redundancy guidance. When a rocket is flying, one of the two habitual groups is used as the primary control rocket flight, while the other inertia groups are in hot backup status, participate in redundancy judgment and take over their work when the main fault occurs. This requires on-site calibration of the initial angular difference between redundant sets of inertia before rocket flight. Proposed the use of photoelectric goniometry technology principle, the relative angle difference between the initial assembly of the redundant sets of measurements to measure, discusses the calibration methods and measurement equipment for the development of programs, and the measurement results are solved and the principle of validation, the experiment shows that its With the measurement principle is correct, the test results are accurate and operability and other advantages.