Lu Rui, Zhang Jianfu, Han Xing, Wu Yanpeng, Li Lin
Appl Opt. 2024 May 10;63(14):3854-3862. doi: 10.1364/AO.507209.
Star trackers are typically used in a spacecraft to provide absolute attitude information to the on-board attitude control system so as to promote high accuracy. The performance of the star tracker is rather important. Attitude incorrectness provided by star trackers may lead to bad navigation with big deviations, even failure of satellites. Therefore, how to realize and verify the accuracy is crucial. As a matter of fact, it is difficult to validate accuracy of star trackers on the ground, especially for star trackers under highly dynamic conditions. In this paper, an accuracy measurement method for star trackers under dynamic conditions is proposed, utilizing a high-accuracy swing table to provide reference to compare. To this end, a swing table, star tracker, and the test equipment are synchronized, in order to reduce systematic errors. As the motion trajectory of the swing table can be set beforehand, the initial attitude of the star tracker can be predicted through a set of coordinate transformations. As a result, the star tracker is able to keep tracking, regardless of the angular velocity of the swing table. This makes the statistical sample points more sufficient and the results more reliable. Moreover, it can evaluate the angular velocity of star trackers up to 20°/s. In comparison with the conventional method with simulated stars, this method utilizes real navigation stars as observation targets making the measurement results much closer to the on-orbit performance. Lastly, but much more importantly, it can also verify the performance of a star tracker in one experiment, such as sensitivity, static performance, capture probability, and so on. Experimental results demonstrate that the proposed method is effective, especially for highly dynamic star trackers. Such a measurement environment is close to the in-orbit conditions, and it can satisfy the stringent requirement for star trackers under high dynamics.
星敏感器通常用于航天器中,为机载姿态控制系统提供绝对姿态信息,以提高精度。星敏感器的性能相当重要。星敏感器提供的姿态不正确可能导致导航偏差大甚至卫星故障。因此,如何实现并验证精度至关重要。事实上,在地面上验证星敏感器的精度很困难,尤其是对于高动态条件下的星敏感器。本文提出了一种动态条件下星敏感器的精度测量方法,利用高精度转台提供参考进行比较。为此,转台、星敏感器和测试设备进行同步,以减少系统误差。由于转台的运动轨迹可以预先设定,通过一组坐标变换可以预测星敏感器的初始姿态。结果,无论转台的角速度如何,星敏感器都能够持续跟踪。这使得统计样本点更加充分,结果更加可靠。此外,它还可以评估高达20°/s的星敏感器角速度。与传统的模拟星方法相比,该方法以真实导航星为观测目标,使测量结果更接近在轨性能。最后但更重要的是,它还可以在一次实验中验证星敏感器的性能,如灵敏度、静态性能、捕获概率等。实验结果表明,所提出的方法是有效的,特别是对于高动态星敏感器。这样的测量环境接近在轨条件,能够满足高动态下星敏感器的严格要求。