针对动态条件航天测量船惯导系统姿态角精度鉴定和评估这个困扰多年的难题,提出一种利用经纬仪观测恒星对惯导姿态角误差进行解算的方法:用短时间(每颗星记录2 s)观测方位角大致均匀分布的多颗恒星数据解算惯导姿态角误差的稳态分量；用较长时间(每颗星记录200 s以上)观测特殊方位角单颗恒星的数据,观察惯导姿态角误差的动态特性,详细介绍了该方法数学模型的推导过程,从理论上分析了该方法各种数据误差源对解算精度的影响,并利用实际观测数据对惯导姿态角误差稳态分量和动态特性进行了解算和观察,结果与航天测量船惯导系统的设计指标基本吻合,表明该方法可以作为评估航天测量船惯导系统姿态角动态精度的一种有效手段.%Under dynamic conditions, the evaluation of INS's attitude accuracy on an aerospace tracking ship has long been a difficult problem. In this paper, a new method is proposed, which uses theodolite's observation data of fixed star to calculate errors of INS's attitude angle. In this method, many fixed stars which distribute roughly uniformly in azimuth are observed for a short period (2 s per star) to calculate steady components in INS's attitude error. A single star with its specific azimuth is observed for a longer period ( over 200 s) to get dynamic performance of the error. The deduction of mathematical modelis introduced in detail. Different error sources of observation and their effects on the final result are analyzed theoretically. Test result shows the efficiency of this method and the accuracy obtained by it perfectly meets the predetermined requirement.
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