摘要
针对两个航天器的最终逼近,对采用光学成像敏感器进行测量的相对导航算法进行了研究。结合航天器相对运动的动力学模型和光学成像敏感器的测量模型,在分析系统噪声和测量噪声的基础上提出一种基于线性卡尔曼滤波的相对导航算法。在滤波器具体设计过程中,对由于星体姿态和安装引起的测量偏差进行了补偿,并在考虑光学测量敏感器测量时延的情况下对相对导航算法进行了改进。最后进行了光学敏感器在回路中的实时仿真,仿真结果验证了相对导航算法的有效性和合理性。
A relative navigation scheme for the final approach phase was proposed, with the target spacecraft information measured by optical sensor. Firstly, a linear Kalman filter we designed, combining the relative motion dynamics （between two spacecrafts） with the measure principle of optimal sensor. The second, the relative navigation algorithm was improved by the coordinate transformation and the devices calibration. So the effects on the accuracy resulting from the attitude bias of spacecraft and the mounted errors of the optical sensors were largely reduced. Considering optical sensor time delay, an improved relative navigation was proposed. At last, a hardware-in-loop test-bed was introduced, on which the navigation algorithm was evaluated. The experiment results verified the developed algorithm.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2008年第4期1245-1251,共7页
Journal of Astronautics
基金
国家863计划资助项目(2005AA745060)
关键词
光学测量
相对导航
卡尔曼滤波
半物理仿真
Optical measure
Relative navigation
Kalman filter
Hardware-in-loop simulation
