Characterization and verification of the optimal feedback gain of a satellite magnetorquer-based attitude control system

IF 2.8 3区地球科学 Q2 ASTRONOMY & ASTROPHYSICS

Advances in Space Research Pub Date : 2024-08-23 DOI:10.1016/j.asr.2024.08.047

Thanayuth Panyalert , Shariff Manuthasna , Jormpon Chaisakulsurin , Tanawish Masri , Kritsada Palee , Pakawat Prasit , Peerapong Torteeka , Poom Konghuayrob

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Abstract

In spacecraft mission planning and operation, the attitude determination and control subsystem (ADCS) of a satellite provides information about the orientation of the satellite in the inertial reference frame. Furthermore, this subsystem produces the control actions required to adjust the orientation of the satellite, especially in the low-Earth orbit (LEO) regime. This paper focuses on the satellite’s three-axis attitude control problem within the context of active and passive control, which includes detumbling control, pointing control, magnetic control, and attitude stabilization after solar panel wing deployment using magnetorquers as the primary actuators. The objective is to stabilize and reduce the angular rate while orienting the satellite to the desired attitude. The proposed satellite attitude control system (ACS) strategies are designed, developed, characterized, and verified. These strategies encompass the B-dot control algorithm for detumbling control along with pointing control and attitude stabilization after solar panel wing deployment. hardware-in-the-loop simulation (HiLs) tests are conducted to assess the performance of the satellite magnetorquer-based ACS in the presence of noise. These tests involve a relative Earth’s magnetic field (EMF) generator in conjunction with SGP-4-based satellite orbital propagator high-level control software. Additionally, cascade proportional-integral-derivative (PID) and state-dependent Riccati equation (SDRE) controllers are implemented to generate sufficient torque using three-axis magnetorquers on a frictionless air-bearing platform. The platform is balanced to closely simulate the dynamic motion of a spacecraft in space. The testing includes a single initial condition and three inertia conditions for stabilization after solar panel wing deployment. Finally, the effectiveness of the cosimulation as a primary experiment through an integrated HiLs process is validated. This comprehensive approach confirms the control system’s performance and its ability to meet mission requirements.

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卫星磁尺式姿态控制系统最佳反馈增益的特性分析与验证

在航天器任务规划和运行中，卫星的姿态确定和控制子系统（ADCS）提供卫星在惯性参考框架中的方位信息。此外，该子系统还提供调整卫星方位所需的控制行动，尤其是在低地球轨道（LEO）状态下。本文重点讨论了卫星在主动和被动控制背景下的三轴姿态控制问题，其中包括惯性控制、指向控制、磁控制以及使用磁扭杆作为主要执行器的太阳能电池板翼展开后的姿态稳定。其目标是在将卫星定向到所需姿态的同时稳定和降低角速率。对所提出的卫星姿态控制系统（ACS）策略进行了设计、开发、表征和验证。这些策略包括B-dot控制算法，用于太阳电池板翼展开后的解体控制、指向控制和姿态稳定。进行了硬件在环仿真（HiLs）测试，以评估基于卫星磁性漆的姿态控制系统在噪声情况下的性能。这些测试包括一个相对地球磁场（EMF）发生器和基于 SGP-4 的卫星轨道传播器高级控制软件。此外，还实施了级联比例-积分-派生（PID）和状态相关里卡提方程（SDRE）控制器，以便在无摩擦气浮平台上使用三轴磁拐子产生足够的扭矩。该平台是平衡的，可近似模拟航天器在太空中的动态运动。测试包括一个初始条件和三个惯性条件，用于太阳能电池板机翼展开后的稳定。最后，通过综合 HiLs 流程验证了模拟作为主要实验的有效性。这种综合方法证实了控制系统的性能及其满足任务要求的能力。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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来源期刊

Advances in Space Research 地学天文-地球科学综合

CiteScore

5.20

自引率

11.50%

发文量

800

审稿时长

5.8 months

期刊介绍： The COSPAR publication Advances in Space Research (ASR) is an open journal covering all areas of space research including: space studies of the Earth''s surface, meteorology, climate, the Earth-Moon system, planets and small bodies of the solar system, upper atmospheres, ionospheres and magnetospheres of the Earth and planets including reference atmospheres, space plasmas in the solar system, astrophysics from space, materials sciences in space, fundamental physics in space, space debris, space weather, Earth observations of space phenomena, etc. NB: Please note that manuscripts related to life sciences as related to space are no more accepted for submission to Advances in Space Research. Such manuscripts should now be submitted to the new COSPAR Journal Life Sciences in Space Research (LSSR). All submissions are reviewed by two scientists in the field. COSPAR is an interdisciplinary scientific organization concerned with the progress of space research on an international scale. Operating under the rules of ICSU, COSPAR ignores political considerations and considers all questions solely from the scientific viewpoint.