[1]邹纫秋,张加友,宋祥帅,等.天基遥感中航天器挠性对成像区域的影响[J].智能系统学报,2023,18(3):489-495.[doi:10.11992/tis.202203043]
ZOU Renqiu,ZHANG Jiayou,SONG Xiangshuai,et al.Influence of spacecraft flexibility on imaging area in space remote sensing[J].CAAI Transactions on Intelligent Systems,2023,18(3):489-495.[doi:10.11992/tis.202203043]
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《智能系统学报》[ISSN 1673-4785/CN 23-1538/TP] 卷:
18
期数:
2023年第3期
页码:
489-495
栏目:
学术论文—机器感知与模式识别
出版日期:
2023-07-05
- Title:
-
Influence of spacecraft flexibility on imaging area in space remote sensing
- 作者:
-
邹纫秋1, 张加友2, 宋祥帅2, 谢亚恩2, 吴限德2
-
1. 北京航天长征飞行器研究所, 北京 100076;
2. 哈尔滨工程大学 航天与建筑工程学院, 黑龙江 哈尔滨 150001
- Author(s):
-
ZOU Renqiu1, ZHANG Jiayou2, SONG Xiangshuai2, XIE Yaen2, WU Xiande2
-
1. Beijing Institute of Space Long March Vehicle, Beijing 100076;
2. College of Aerospace and Civil Engineering, Harbin Engineering University, Harbin 150001, China
-
- 关键词:
-
遥感卫星; 成像观测; 挠性附件; 有限元法; 拉格朗日法; 敏捷卫星; 成像区域; 星地几何
- Keywords:
-
remote sensing satellite; imaging observation; flexible appendix; finite element method; Lagrange method; agile satellite; imaging region; satellite earth geometry
- 分类号:
-
TP73
- DOI:
-
10.11992/tis.202203043
- 摘要:
-
针对遥感敏捷卫星机动模式对地成像观测,分析挠性附件振动对卫星成像区域和质量的影响。首先利用有限元法和拉格朗日法建立带挠性附卫星的动力学模型;然后通过星地几何法计算成像条带;最后分别选取太阳同步轨道和地球同步轨道,以两个对称的太阳能帆板作为挠性附件,给出数值仿真结果。仿真结果表明,卫星机动完成后,成像区域横滚方向与俯仰方向均偏差较大,导致成像区域错位;太阳帆板振动对成像区域的影响随着其振动减弱而减弱,并逐渐趋于稳定。卫星轨道高度越高,扰动对于卫星成像区域的影响越大,需要更长时间稳定自身姿态。
- Abstract:
-
Aiming at the earth imaging observation of remote sensing agile satellite maneuvering mode, the influence of flexible accessory vibration on satellite imaging area and quality is analyzed in this paper. Firstly, the dynamics model of satellite with flexible appendage is established by using finite element method and Lagrange method; Then, the imaging strip is calculated by satellite earth geometry method; Finally, the numerical simulation results are derived by selecting the sun-synchronous orbit and geostationary orbit as examples, and using two symmetrical solar panels as flexible accessories. The simulation results show that after the satellite maneuver is completed, the deviation between the roll direction and the pitch direction of the imaging area is large, resulting in dislocation of the imaging area; The influence of solar panel vibration on the imaging area decreases with the weakening of its vibration, and tends to stability gradually. The higher the altitude of satellite orbit, the greater the impact of disturbance on the satellite imaging area, which takes longer time to stabilize the attitude.
备注/Memo
收稿日期:2022-03-23。
基金项目:国家自然科学基金面上项目(11772185).
作者简介:邹纫秋,高级工程师,主要研究方向为飞行器结构设计,获国防专利5项;张加友,硕士研究生,主要研究方向为飞行器控制、任务规划、人工智能。参与科研项目10余项。;吴限德,教授,博士,主要研究方向为航天系统动力学与规划控制、复杂系统建模仿真,主持国防基础科研、国防技术基础、民用航天等横纵向项目50余项,获发明专利授权2项、软件著作权6项,发表学术论文50余篇,出版专著和译著2部
通讯作者:吴限德.E-mail:xiande_wu@163.com
更新日期/Last Update:
1900-01-01