SINS制导工具误差补偿研究  

Study on SINS Guidance Instrument Error Compensation

作　　者：贺杰[1] 黄显林[1] 李学峰 

机构地区：[1]哈尔滨工业大学控制理论与制导技术研究中心,黑龙江哈尔滨150001 [2]航天科技集团运载火箭研究院,北京100076

出　　处：《航空学报》2007年第1期182-186,共5页Acta Aeronautica et Astronautica Sinica

基　　金：航天支撑技术基金(HTZC0405)

摘　　要：针对现有捷联惯性导航系统(SINS)制导工具误差模型不能满足“天地一致性”的问题,提出了基于实际弹道数据的SINS制导工具误差补偿方法,即首先建立SINS制导工具误差模型,然后采用改进的特征值有偏估计(LRE)方法估计具有复共线性特性的误差模型,最后利用该误差模型对捷联惯性仪表进行误差补偿。半物理仿真试验的结果表明,高度通道的最大测量误差由补偿前的52m降低到补偿后的8m,其余通道的补偿效果类似。这证明了该误差模型的正确性和估计方法的有效性,为将来SINS制导工具误差补偿和提高SINS制导精度提供了充分的依据。In view of the difference between the strapdown inertial navigation system（SINS） guidance instrument error parameters in the ground experiment environment and those in the flight environment, the approach to compensate SINS guidance instrument errors based on tracking data and telemetry data is developed. Firstly the error models are established. Secondly the improved latent root estimation（LRE） is applied in order to overcome the multicolinearities of the error models and estimate the error parameters. Thus the error models are determined based on the estimated error parameters. Finally the strapdown inertial instrument errors are compensated based on the identified error models. Semi-physical simulation results show that the maximum height error decreases from 52 m to 8 m after error compensation. It demonstrates the accuracies of the error models and the effectiveness of LRE. It provides a foundation for the error compensation of SINS guidance instruments and improvement on SINS guidance precision.

关 键 词：捷联惯性导航系统 制导工具误差建模 特征值估计 误差补偿 遥测数据 外测数据 

分 类 号：V249.322[航空宇航科学与技术—飞行器设计] V441