An strictly-regressive orbit optimization algorithm for L-band differential interferometric SAR satellite

doi:10.11947/j.AGCS.2024.20230250.

Abstract

Abstract:

Compared with the traditional application direction of SAR satellites, the first generation of China's L-band differential interferometric SAR (L-SAR) satellite is mainly used to realize global accurate surface deformation measurement. In order to achieve the deformation measurement index of heavy-orbit differential interferometry better than 5 cm, it is necessary to solve the engineering problem of high-precision regression of satellite reference orbit. In this paper, a precision reference repeating orbit optimization design method is proposed. The high-order dynamic model is established by analyzing the impact of gravity field with different complexities on the precision of regression orbits; The modified sun-synchronous regression orbit parameters achieved by taking into account J4 perturbation are used as the initial value for the algorithm, and carry out the orbit optimization by using a heuristic multi-objective evolutionary algorithm with the goal of satisfying the convergent domain value of the satellite's position and velocity regression accuracy in the WGS-84 coordinate system. Simulation tests show that the regression accuracy of the optimization results can reach centimeter level, which is better than the established engineering indexes, and the validity and correctness of the method have been verified by L-SAR satellites in orbit.

Key words: strictly-regressive orbit, differential interferometric SAR, high gravity order model, optimal orbit design, L-SAR

CLC Number:

P228

Nan LI, Junjian WEN, Yanyang LIU, Huixiang LING, Chun WEI, Junli CHEN. An strictly-regressive orbit optimization algorithm for L-band differential interferometric SAR satellite[J]. Acta Geodaetica et Cartographica Sinica, 2024, 53(10): 1873-1880.

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轨道参数	2阶	4阶	60阶	80阶	90阶	120阶
a	6 948.446 9	6 948.488 1	6 948.519 3	6 948.519 3	6 948.519 4	6 948.519 4
e	0.001 195 3	0.001 195 4	0.001 322 5	0.001 322 9	0.001 323 1	0.001 323 3
i	97.629 903	97.654 108	97.651 711	97.651 713	97.651 717	97.651 719
Ω	159.716 93	159.716 93	159.716 93	159.716 93	159.716 93	159.716 93
ω	113.334 56	113.338 79	110.981 27	110.981 07	110.970 96	110.970 96
M	66.665 542	66.661 309	69.018 849	69.018 962	69.029 158	69.029 211

除数	位置回归精度/m	速度回归精度/(m/s)
2阶	10 089.052 214	11.194 747
4阶	4 457.062 727	4.969 07
60阶	2.243 674	0.167 434
80阶	1.292 636	0.103 657
90阶	0.372 182	0.070 007 1
120阶	0.315 378	0.067 265 4

轨道参数	2阶解析解	4阶修正解
a	6 898.187 8	6 898.230 5
e	0.001 193	0.001 193
i	97.477 8	97.501 8
Ω	11.360 9	11.360 9
ω	113.116 5	113.116 5
M	66.883 6	66.883 6

轨道参数	瞬根	平根
a	6 907.677 1	6 898.263 6
e	0.001 332	0.001 246
i	97.494 4	97.499 5
Ω	11.360 9	11.360 6
ω	111.056 8	90
M	68.943 3	90

地固系位置、速度		初始时刻	终端时刻
位置	x/m	-2 266.347 7	-2 266.346 8
	y/m	-6 986 691.567 8	-6 986 691.568 2
	z/m	-16 530.631 6	-16 530.631 5
速度	v_x/(m/s)	-1 536.571 6	-1 536.566 3
	v_y/(m/s)	9.194 9	9.197 1
	v_z/(m/s)	-7 484.842 9	-7 484.843 6
位置均方回归误差/m			0.001 0
速度均方回归误差/(m/s)			0.005 8