航天器交会计算机视觉系统测距求解新算法

朱仁璋; 林彦; 张磊

航天器交会计算机视觉系统测距求解新算法

北京航空航天大学宇航学院, 北京 100083

详细信息

作者简介:
朱仁璋(1941-),男,江苏扬州人,教授, rz zhu@tom.com.

中图分类号: V 448
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- 被引次数: 0
出版历程
- 收稿日期: 2005-08-09
- 网络出版日期: 2006-07-31

New algorithm of solving for ranges during final approach of spacecraft rendezvous

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要

摘要: 对航天器交会对接最终逼近段应用的计算机视觉系统,提出目标航天器标志点测距求解新算法.该方法根据标志点构型几何特征,建立非线性测距方程组并构造加权目标函数,按最小二乘问题,采用Gauss-Newton数值迭代法求解测距最佳值.获得测距后,即可应用四元数估算法(QUEST)确定相对姿态与相对位置.对非共面标志点构型(如3点T型与5点锥型)和共面标志点构型(如正方形、矩形、菱形),目标函数均含标志点间距比率关系项;对共面构型,目标函数还包含共面条件项.对共面标志点四边形构型,利用对角线交点的虚影像坐标确定测距求解迭代初值.大量模拟计算结果表明,提出的测距求解算法对共面与非共面各种标志点构型普遍适用,满足最终逼近段相对状态确定要求.
- 航天器交会 /
- 航天器导航辅助 /
- 计算机视觉
Abstract: A new algorithm of solving for ranges during the final translation phase of spacecraft rendezvous and docking using computer vision system was presented to determine relative attitude and position between target and chase spacecraft by Quaternion Estimation. In this algorithm for ranges, a weighted objective function was constructed according to target pattern and geometry feature and used for solving for ranges. For both non-planar (such as three-point T-type and five-point pyramid type) and co-planar patterns (such as square, rectangle and rhombus), the objective function contained terms concerning ratios of distances between the target spots; but for co-planar targets, the objective function had another terms which describe co-planar feature. Gauss-Newton method was applied to solve for the optimum range solutions of the least squares problem. For quadrilateral patterns, the initial values for iterations were given by coordinates of virtual image of the intersection point of two diagonal lines. Extensive simulations, conducted for various target patterns with image coordinates errors, show that the range algorithm presented is quite effective for the relative state determination.
- spacecraft rendezvous /
- spacecraft navigation aids /
- computer vision

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参考文献(1)

[1] 朱仁璋,尹艳. 论空间交会最终平移段制导设计[J]. 中国空间科学技术,2004, 24(5):1-8 Zhu Renzhang, Yin Yan. Guidance strategy design for the final translation of space rendezvous[J]. Chinese Space Science and Technology, 2004, 24(5):1-8(in Chinese) [2] 朱仁璋,汤溢,尹艳. 空间交会最终平移轨迹安全模式设计[J]. 宇航学报,2004, 25(4):443-448 Zhu Renzhang, Tang Yi, Yin Yan. Safety mode design of final translation trajectories of space rendezvous[J]. Journal of Astronautics, 2004, 25(4):443-448 (in Chinese) [3] 朱仁璋,尹艳,汤溢. 空间交会最终平移段控制策略. 中国空间科学技术 ,2005, 25(4):31-38 Zhu Renzhang, Yin Yan, Tang Yi. The control strategy for the final translation of space rendezvous[J]. Chinese Space Science and Technology, 2005, 25(4):31-38 (in Chinese) [4] Mukundan R, Ramakrishnan K R. A quaternion solution to the pose determination problem for rendezvous and docking simulations[J]. Mathematics and Computers in Simulation, 1995, 39(2):143-153 [5] Calboun P, Dabney R. A solution to the problem of determining the relative 6DOF state for spacecraft automated rendezvous and docking Fowski W J, Birnbaum M M. Proceedings of SPIE Space Guidance, Control and Tracking II. Orlando USA:SPIE Press, 1995:175-184 [6] 黄玉明,周世安,王立新,等.目标航天器位置姿态的光学测量[J].宇航学报,1993, 14(1):97-103. Huang Yuming, Zhou Shian, Wang Lixin, et al. Optical measurement for the position and attitude of the target spacecraft[J]. Journal of Astronautics, 1993, 14(1):97-103(in Chinese) [7] Ho C-C J, McClamroch N H. Automatic spacecraft docking using computer vision-based guidance and control techniques[J]. Journal of Guidance, Control, and Dynamics, 1993, 16(2):281-288 [8] Shuster M D, Oh S D. Three-axis attitude determination from vector observation[J]. Journal of Guidance, Control, and Dynamics, 1981, 4(1):70-77 [9] 王庆有,何在新,张以谟,等. CCD应用技术发展动向[J]. 光电子技术与信息, 1994, 7(2):2-6 Wang Qingyou, He Zaixin, Zhang Yimo, et al. Development of CCD application techniques[J], Optoelectronic Technology & Information, 1994, 7(2):2-6 (in Chinese)

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