严格回归轨道自动生成算法及实现 *

推进技术 ›› 2018, Vol. 39 ›› Issue (7): 1472-1478.

严格回归轨道自动生成算法及实现 *

张冲难¹,卞燕山²,王西京²,田斌²,黄晓峰²

宇航动力学国家重点实验室，陕西西安 710043,航天器在轨故障诊断与维修重点实验室，陕西西安 710043,航天器在轨故障诊断与维修重点实验室，陕西西安 710043,航天器在轨故障诊断与维修重点实验室，陕西西安 710043,航天器在轨故障诊断与维修重点实验室，陕西西安 710043

发布日期:2021-08-15
作者简介:张冲难，男，学士，高级工程师，研究领域为在轨航天器诊断与维护。 E-mail: 18710417295@139.com 通讯作者:卞燕山，男，博士，工程师，研究领域为卫星管理。

Algorithmand Implementationof Automatic Generationof Rigorous Recursive Orbit

State Key Laboratory of Astronautic Dynamics，Xi’an 710043，China,Key Laboratory of Spacecraft In-Orbit Fault Diagnosis and Maintenance，Xi’an 710043，China,Key Laboratory of Spacecraft In-Orbit Fault Diagnosis and Maintenance，Xi’an 710043，China,Key Laboratory of Spacecraft In-Orbit Fault Diagnosis and Maintenance，Xi’an 710043，China and Key Laboratory of Spacecraft In-Orbit Fault Diagnosis and Maintenance，Xi’an 710043，China

Published:2021-08-15

摘要/Abstract

摘要： 近地太阳同步轨道卫星由平时轨道快速、精确机动至严格回归轨道是实现特定区域周期性重访的必要前提。为提高区域重访的快速响应能力，提出了一种严格回归轨道自动生成算法。首先根据重访区域的交点周期及重访周期要求，利用解析法快速生成初始严格回归轨道；然后基于太阳同步轨道特性并利用数值法进行多次寻优生成严格回归轨道，针对轨控时间、燃料消耗、偏心率等约束条件，给出了多脉冲轨控策略的具体实现；最后构建了轨道衰减的解析表达式，推导出严格回归轨道的控制窗口。结果表明:在国内可见弧度实施 5天共 5次轨道控制，卫星由太阳同步轨道机动至 1天 15圈的日回归轨道，区域重访周期约 23h 59m 50s，燃料消耗 59.9kg；在轨迹漂移量为 5km的要求下，在标称轨道半长轴的基础上增加 110.778m，轨迹网保持周期由 15天延长至一个月以上，满足严格回归轨道重访要求。

关键词: 太阳同步轨道；回归轨道；交点周期；多约束优化

Abstract: The near earth sun-synchronous orbit satellite maneuvering from a normal orbit to a rigorous re.cursive orbit quickly and precisely is a prerequisite for the periodical revisit of the specific area. In order to im.prove the quick response capability of area revisit，an algorithm and implementation of automatic generation ofrigorous recursive orbit is proposed. On the basis of the requirements of revisit area’s nodal period and revisit pe. riod，an analytic method is used to calculate the initial orbit elements of rigorous recursive orbit. Then a numeri.cal method is used to generate the final rigorous recursive orbit by multiple optimizations according to the charac.teristics of sun-synchronous orbit. In the light of orbit control time，fuel consumption，eccentricity and other con. straints，the realization of multi-pulse orbit control strategy is provided. At last，an analytic expression of orbital decay is set up，and the control time of rigorous recursive orbit is deduced. The results show that by means of fivetimes of orbit control implemented in 5 days in the domestic visible arcs，the satellite maneuvers from the solar synchronous orbit to the daily recursive orbit with 15 circles per day. The regional revisit period is about 23h 59m50s，and the total fuel consumption is 59.9kg. Under the requirement of 5km ground-track drifting，an increase of 110.778m is added on the nominal orbital semiaxis，and the ground-track keeping period is prolonged from 15 days to more than one month，which meets the recursive requirements of the rigorous recursive orbit.

Key words: Sun-synchronous orbit；Recursive orbit；Nodal period；Multi-constraint optimization

张冲难,卞燕山,王西京,田斌,黄晓峰. 严格回归轨道自动生成算法及实现 *[J]. 推进技术, 2018, 39(7): 1472-1478.

ZHANG Chong-nan¹,BIAN Yan-shan²,WANG Xi-jing²,TIAN Bin²,HUANG Xiao-feng². Algorithmand Implementationof Automatic Generationof Rigorous Recursive Orbit[J]. Journal of Propulsion Technology, 2018, 39(7): 1472-1478.

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