快速仅测角相对导航初始相对轨道确定方法

doi:10.12305/j.issn.1001-506X.2021.04.24

Abstract

Abstract:

For the problem of unobservable inter-satellite distance of angles-only relative navigation caused by the linear measurement model and relative motion model, a fast initial relative orbit determination (IROD) method of angles-only relative navigation is proposed. Firstly, the relative orbit elements (ROE) is used to establish a nonlinear relative motion model, which can decouple the inter-satellite distance and the relative orbital shape. Then, the inter-satellite distance near the collinear solution obtained by linear theory is changed, systematically, and a series of least-square fitting is performed, and then the dichotomy or Newton iteration method is used to find the optimal solution of the minimum fitting residual quickly in the global range. Finally, a semi-physical simulation platform is built to test the performances of the method in 4 orbital scenarios, and the effectiveness of the proposed method is verified.

Key words: angles-only relative navigation, initial relative orbit determination (IROD), dichotomy method, Newton iteration method, least-square fitting

CLC Number:

V249.32

Ronghua DU, Xiang ZHANG, Wenhe LIAO. Fast initial relative orbit determination method of angles-only relative navigation[J]. Systems Engineering and Electronics, 2021, 43(4): 1057-1068.

Figures/Tables 17

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参数	变量	仿真值
空间目标初始轨道根数	(a, e, i, Ω, ω, M)	(6 878.137 km, 0, 40°, 120°, 0°, 50°)
初始ROE (场景1)	(aδa, aδe_x, aδe_y, aδi_x, aδi_y, aδλ)	(0, 0.5, 0, -0.5, 0, -30)km
初始ROE (场景2)	(aδa, aδe_x, aδe_y, aδi_x, aδi_y, aδλ)	(-0.15, 0.3, 0, -0.3, 0, -20)km
初始ROE (场景3)	(aδa, aδe_x, aδe_y, aδi_x, aδi_y, aδλ)	(0, 0, -0.2, 0, 0.2, -5)km
初始ROE (场景4)	(aδa, aδe_x, aδe_y, aδi_x, aδi_y, aδλ)	(0, 0, 0, 0, 0, -0.5)km
相机测量误差标准差	σ_α=σ_ε	18″
相机测量偏差标准差	σ_{b, α}=σ_{b, ε}	5″
姿态测量误差标准差	(σ_{att, off-axis}, σ_{att, roll})	(6, 40)″

轨道场景	方法	用时/s
场景1	批量搜索法	13.74
	二分法	2.32
	牛顿迭代法	0.65
场景2	批量搜索法	14.78
	二分法	3.13
	牛顿迭代法	0.82
场景3	批量搜索法	13.51
	二分法	2.16
	牛顿迭代法	0.53
场景4	批量搜索法	23.22
	二分法	4.14
	牛顿迭代法	1.03

轨道场景	百分比误差P_x/%
轨道场景	批量搜索法	二分法	牛顿迭代法
场景1	7.07	7.03	5.87
场景2	6.55	5.45	5.35
场景3	5.20	3.80	3.80
场景4	35.8	34.0	32.4

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Fast initial relative orbit determination method of angles-only relative navigation

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