地球同步轨道薄膜太阳帆的姿态轨道控制方法

武云丽; 赵天一; 左华平; 孟斌

doi:10.7527/S1000-6893.2020.24291

航空学报 >

2020 , Vol. 41 >Issue S2: 724291 - 724291

DOI: https://doi.org/10.7527/S1000-6893.2020.24291

地球同步轨道薄膜太阳帆的姿态轨道控制方法

武云丽 ,
赵天一 ,
左华平 ,
孟斌

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1. 北京控制工程研究所, 北京 100190;
2. 空间智能控制技术重点实验室, 北京 100190;
3. 哈尔滨工业大学控制理论与制导技术中心, 哈尔滨 150001;
4. 兰州空间技术物理研究所真空技术与物理重点实验室, 兰州 730000

收稿日期: 2020-05-26

修回日期: 2020-05-29

网络出版日期: 2020-06-12

基金资助

国家重点研发计划（2018YFA0703800）；空间智能控制技术重点实验室基金（ZDSYS-2018-04）

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Orbit and attitude control design for film solar sailcrafts on geosynchronous orbit

WU Yunli ,
ZHAO Tianyi ,
ZUO Huaping ,
MENG Bin

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1. Beijing Institute of Control Engineering, Beijing 100190, China;
2. Key Laboratory of Space Intelligent Control Technology, Beijing 100190, China;
3. Center for Control Theory and Guidance Technology, Harbin Institute of Technology, Harbin 150001, China;
4. Key Laboratory of Vacuum Technology and Physics, Lanzhou Institute of Space Technical Physics, Lanzhou 730000, China

Received date: 2020-05-26

Revised date: 2020-05-29

Online published: 2020-06-12

Supported by

National Key Research and Development Program (2018YFA0703800); The Foundation of Key Laboratory of Space Intelligent Control Technology (ZDSYS-2018-04)

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摘要

薄膜太阳帆（FSS）是集推进、发电和姿轨控功能于一体化的超大型挠性太阳帆式航天器，通过调整薄膜反射率产生可变推力和力矩，实现其姿态和轨道运动控制。结合薄膜太阳帆在地球同步轨道运行时的受力特性进行了轨道漂移分析。通过建立薄膜太阳帆动力学模型及受力模型，提出了调整帆面角度轨道修正方法以及基于薄膜光压力矩角动量卸载的长期在轨对日定向面内双轴动量轮稳定控制方法。通过系统仿真验证表明所提的轨道修正和对日定向控制方法是合理有效的，可使薄膜太阳帆长期在定点位置维持对日定向。

关键词： 薄膜太阳帆; 地球同步轨道; 姿态和轨道控制; 超大型挠性航天器; 薄膜反射率

本文引用格式

武云丽 , 赵天一 , 左华平 , 孟斌 . 地球同步轨道薄膜太阳帆的姿态轨道控制方法[J]. 航空学报, 2020 , 41(S2) : 724291 -724291 . DOI: 10.7527/S1000-6893.2020.24291

Abstract

The film solar sailcraft (FSS) with variable reflectivity is a huge flexible spacecraft capable of propulsion, electric power generation, and attitude and orbit control. The FSS can generate force and torque for attitude and orbit control via varying film reflectivity. In this paper, the orbit drifting motion is analyzed according to the force characteristics of the FSS on the geostationary orbit, and the dynamics model and force and torque model of variable film reflectivity for the FSS are built respectively. Based on the proposed models, an orbit correction method is presented to change the attitudes of the FSS. A stable and reliable attitude control method with double momentum wheels fixed in the plane of the FSS is also proposed. The momentum accumulation of the wheels for attitude control can be unloaded by the solar torque produced from variable film reflectivity. The mathematical simulations show that the proposed methods are reasonable and fit for engineering applications, enabling the FSS to work at a fixed longitude position over a long period of time.

Key words： film solar sailcraft; geosynchronous orbits; attitude and orbit control; super large flexible spacecraft; film reflectivity

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