对地指向偏差为约束的卫星平稳对日定向方法

季浩然; 黄頔

doi:10.13700/j.bh.1001-5965.2020.0293

对地指向偏差为约束的卫星平稳对日定向方法

doi: 10.13700/j.bh.1001-5965.2020.0293

季浩然^{1, 2},
黄頔^1, ,

1.
武汉大学遥感信息工程学院宇航科学与技术研究院, 武汉 430072
2.
国防科技大学空天科学学院, 长沙 410073

基金项目:

国家自然科学基金 61903278

湖北省自然科学基金 2018CFB180

中央高校基本科研业务费专项资金 2042019kf0044

测绘遥感信息工程国家重点实验室专项科研经费

详细信息

作者简介:
季浩然男, 博士研究生。主要研究方向: 航天器结构、姿态、轨道动力学与控制

黄頔男, 博士, 副研究员。主要研究方向: 航天器导航制导控制

通讯作者:
黄頔. E-mail: dhuang@whu.edu.cn

中图分类号: V448.21;V412.4⁺2
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- 被引次数: 0
出版历程
- 收稿日期: 2020-06-23
- 录用日期: 2020-08-07
- 网络出版日期: 2021-02-20

A smooth Sun-pointing guidance method for satellites constrained by deviation of Earth-pointing

JI Haoran^{1, 2},
HUANG Di^{1
, ,}

1.
Institute of Aerospace Science and Technology, School of Remote Sensing and Information Engineering, Wuhan University, Wuhan 430072
2.
College of Aerospace Science and Technology, National University of Defense Technology, Changsha 410073, China

Funds:

National Natural Science Foundation of China 61903278

Hubei Provincial Natural Science Foundation of China 2018CFB180

the Fundamental Research Funds for the Central Universities 2042019kf0044

LIESMARS Special Research Funding

More Information

Corresponding author: HUANG Di. E-mail: dhuang@whu.edu.cn

摘要

摘要:
传统以对地指向偏差为约束的对日定向方法在星-日、星-地连线的夹角达到极值后，卫星期望姿态会发生大幅度快速翻转，导致较大的峰值功耗和寿命损伤。针对该现象，提出了一种可使期望姿态平稳变化的以对地指向偏差为约束的对日定向方法，将卫星的期望姿态设置为绕一基准姿态周期性地旋转。在不显著牺牲对日定向效能的同时，既确保卫星期望对地轴与对地方向的夹角小于约束角，又使得卫星姿态总体平稳变化。数值仿真表明：所提出的平稳对日定向方法能够大幅降低卫星期望角速度的峰值，同时能够满足对日指向和对地指向的需求。
- 对日定向 /
- 对地指向偏差 /
- 期望姿态建立 /
- 欧拉轴 /
- 平稳对日定向方法
Abstract:
Under traditional Sun-pointing guidance method constrained by the deviation of Earth-pointing, the expected attitude of the satellite would rapidly flip when the angle between the satellite-Sun line and the satellite-Earth line reaches the extreme value, leading to the large peak power consumption and lifetime damage. Aimed at this problem, this paper provides a novel Sun-pointing method constrained by the deviation of Earth-pointing, which can make the expected attitude change smoothly. By this method, the expected attitude of the satellite is set to rotate periodically around a reference attitude. The deviation of Earth-pointing is kept less than the constraint angle with the attitude moving smoothly, while the effectiveness of Sun-pointing is not evidently reduced. Numerical simulation results show that the proposed method can greatly reduce the peak angular velocity of the satellite, and can meet the requirements of both Sun-pointing and Earth-pointing.
- Sun-pointing /
- deviation of Earth-pointing /
- expected attitude establishment /
- Euler axis /
- Smooth Sun-pointing method

HTML全文

图 1 对日定向期望姿态建立步骤

Figure 1. Process of establishing expected Sun-pointing attitude

下载: 全尺寸图片幻灯片

图 2 卫星中间姿态示意图

Figure 2. Schematic diagram of intermediate attitude of satellite

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图 3 卫星期望姿态示意图

Figure 3. Schematic diagram of expected attitude of satellite

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图 4 对地偏差角在1.5年时间内的变化规律

Figure 4. Development of deviation of Earth-pointing within 1.5 years

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图 5 对日偏差角在1.5年时间内的变化规律

Figure 5. Development of deviation of Sun-pointing within 1.5 years

下载: 全尺寸图片幻灯片

图 6 连续6小时内对日偏差角的变化规律(2019年1月22日)

Figure 6. Development of deviation of Sun-pointing within consecutive 6 hours (2019-01-22)

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图 7 依据期望姿态差分得到的卫星x轴角速度

Figure 7. Angular velocity in x-axis obtained by difference of expected attitude

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图 8 依据期望姿态差分得到的卫星y轴角速度

Figure 8. Angular velocity in y-axis obtained by difference of expected attitude

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图 9 依据期望姿态差分得到的卫星z轴角速度

Figure 9. Angular velocity in z-axis obtained by difference of expected attitude

下载: 全尺寸图片幻灯片

图 10 卫星-地心连线和卫星-日心连线夹角的变化规律

Figure 10. Development of included angle between the satellite-Earth vector and the satellite-sun vector

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图 11 传统对日定向方法在1.5年时间内对期望姿态差分得到的角速度

Figure 11. Angular velocity obtained by difference of traditional expected attitude with 1.5 years

下载: 全尺寸图片幻灯片

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