miniSAR卫星精密参考轨道设计

廖祥; 郑靖; 许永生; 谢成清; 丁强强

doi:10.13700/j.bh.1001-5965.2021.0141

miniSAR卫星精密参考轨道设计

doi: 10.13700/j.bh.1001-5965.2021.0141

1.
深圳市魔方卫星科技有限公司, 深圳 518129
2.
深圳航天东方红卫星有限公司, 深圳 518057

基金项目:

国家自然科学基金 11802073

深圳市科技计划 JSGG20190823094603691

详细信息

通讯作者:
郑靖, E-mail: 29321633@qq.com

中图分类号: V173.1
计量
- 文章访问数: 316
- HTML全文浏览量: 122
- PDF下载量: 23
- 被引次数: 0
出版历程
- 收稿日期: 2021-03-25
- 录用日期: 2021-08-27
- 网络出版日期: 2021-09-15
- 整期出版日期: 2022-12-20

Precise references orbit design of miniSAR satellite

1.
Shenzhen MagicCube Satellite Ltd, Shenzhen 518129, China
2.
Shenzhen Aerospace Dongfanghong Satellite Ltd, Shenzhen 518057, China

Funds:

National Natural Science Foundation of China 11802073

Shenzhen Science and Technology Plan JSGG20190823094603691

More Information

Corresponding author: ZHENG Jing, E-mail: 29321633@qq.com

摘要

摘要:
为满足轻小型合成孔径雷达(miniSAR)卫星干涉测量任务对空间基线的要求，通过分析卫星参考轨道特性，建立了一套精密参考轨道设计算法。所建算法以miniSAR卫星成功入轨后的一组定轨数据及根据参考轨道特性解析得到的参考轨道预估值为输入，基于仅考虑中心天体非球形高阶引力摄动的轨道外推模型、Eckstein-Hechler平根模型及嵌套式迭代修正方法，设计输出其任务周期内使用的参考轨道。数值实验表明：所建算法设计的参考轨道生成的参考轨迹在三维空间的回归精度优于0.01 m，满足实际工程应用需求。
- 轻小型合成孔径雷达 /
- 重轨干涉 /
- 参考轨道 /
- 回归轨道 /
- 冻结轨道
Abstract:
In order to meet the requirements of the mini synthetic aperture radar (miniSAR) satellite interferometry mission for the space baseline, a set of precision reference orbit design algorithms was established by analyzing the features of the satellite reference orbit. The algorithm takes a group of orbit determination data after the successful orbit insertion of the miniSAR satellite and the estimation elements of reference orbit obtained by analyzing the reference orbit features as inputs. The Eckstein-Hechler mean elements model and nested iterative correction method are used to design and output the reference orbit within the mission duration. Numerical simulation shows that the spatial regression accuracy of the reference trajectory formed by the algorithm is better than 0.01 m, which can be applied to real engineering application.
- mini synthetic aperture radar /
- repeat interferometry /
- reference orbit /
- repeating ground track orbit /
- frozen orbit

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图 1 受太阳引力影响的倾角长期项摄动^[15]

Figure 1. Secular perturbation of inclination due to gravity of the Sun^[15]

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图 2 精密参考轨道设计算法流程

Figure 2. Algorithm flow chart of precise reference orbit design

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图 3 偏心率平根矢量修正示意图

Figure 3. Diagram of mean eccentricity vector correction

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图 4 第1轮(a, i) 迭代修正收敛情况

Figure 4. Convergence of first (a, i) iterative correction

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图 5 第2轮(a, i) 迭代修正收敛情况

Figure 5. Convergence of second (a, i) iterative correction

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图 6 偏心率平根矢量收敛情况

Figure 6. Convergence of mean eccentricity vector

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图 7 (e, ω)迭代修正收敛情况

Figure 7. Convergence of (e, ω) iterative correction

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表 1 定位数据

Table 1. Precision positioning data

历元(UTCG)	x_f/m	y_f/m	z_f/m	v_{x_f}/(m·s^-1)	v_{y_f}/(m·s^-1)	v_{z_f}/(m·s^-1)
2021-01-01T 00:26:10.0	-783 574.748 753	-6 863 761.705 245	-26 410.675 743	-1 491.687 930	141.316 578	7 530.503 149
2021-01-01T 00:26:11.0	-785 063.311 452	-6 863 616.424 823	-18 889.864 376	-1 490.723 932	149.784 298	7 530.530 497
2021-01-01T 00:26:12.0	-786 550.909 902	-6 863 462.687 911	-11 369.030 230	-1 489.756 916	158.251 697	7 530.548 764
2021-01-01T 00:26:13.0	-788 037.541 089	-6 863 300.494 834	-3 848.182 376	-1 488.786 875	166.718 766	7 530.557 951
2021-01-01T 00:26:14.0	-789 523.201 997	-6 863 129.845 928	3 672.670 120	-1 487.813 817	175.185 493	7 530.558 057
2021-01-01T 00:26:15.0	-791 007.889 614	-6 862 950.741 538	11 193.518 187	-1 486.837 742	183.651 868	7 530.549 083
2021-01-01T 00:26:16.0	-792 491.600 927	-6 862 763.182 023	18 714.352 756	-1 485.858 651	192.117 880	7 530.531 028
2021-01-01T 00:26:17.0	-793 974.332 924	-6 862 567.167 748	26 235.164 760	-1 484.876 544	200.583 519	7 530.503 892

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表 2 迭代修正过程中所得参考轨道根数(TOD瞬根)

Table 2. Reference orbit elements obtained during process of iterative correction (TOD osculating elements)

轨道参数	a₀	a₁	a₂	a
历元(UTCG)	t₀	t₀	t₀	t₀
半长轴a/m	6 917 784.183 313	6 917 807.832 603	6 917 807.832 603	6 917 808.175 966
偏心率e	0.001 165 858	0.001 165 858	0.001 340 574	0.001 340 574
轨道倾角i/(°)	97.511 721 612	97.534 015 350	97.534 015 350	97.534 027 100
近地点幅角ω/(°)	65.805 305 734	65.805 305 734	69.021 264 985	69.021 264 985
升交点赤经Ω/(°)	10.881 860 946	10.881 860 946	10.881 860 946	10.881 860 946
平近点角M/(°)	294.194 463 246	294.194 463 246	290.978 735 015	290.978 735 015

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表 3 迭代修正收敛数据

Table 3. Convergence data of iterative correction

n	\|\|Δr′\|\|/m	\|\|Δr\|\|/m	Δe	n	\|\|Δr′\|\|/m	\|\|Δr\|\|/m	Δe
1	28 263.230 02	52.167 615 93	0.000 187 929 7	4	0.000 335 849	0.005 178 737	0.000 000 000 2
2	3 073.541 513	0.486 591 513	0.000 002 372 6	5	0.000 005 517
3	0.263 825 008	0.005 720 578	0.000 000 026 5	6	0.000 000 438

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