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首页> 外文期刊>IEEE Transactions on Aerospace and Electronic Systems >Interplanetary Magnetic Attitude Control Based on an IMF Kalman filter in Small Spacecraft
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Interplanetary Magnetic Attitude Control Based on an IMF Kalman filter in Small Spacecraft

机译：基于IMF Kalman滤波器在小型航天器中的行星磁姿态控制

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摘要

Recently, a variety of small spacecraft have been launched and used for interplanetary missions. Conventionally, reaction wheels (RWs) and thrusters are used for these attitude control systems in almost all interplanetary spacecraft. While these actuators are promising for attitude control, the lifetime of the spacecraft mission is limited by the extra fuel needed for the thrusters. Moreover, it is difficult to install thrusters in all small spacecraft due to low reliability and strict limitations on mass and power consumption. To obtain both fuel-free and available attitude control for small spacecraft, this study proposes an interplanetary magnetic attitude control system including attitude stabilization and angular momentum unloading based on an interplanetary magnetic field (IMF) Kalman filter. In the proposed method, an electromagnetic coil interacting with the IMF is used for an attitude control system. To achieve the proposed method, the faint magnetic field must be detected. However, the IMF is too weak to sense using only on-board magnetic sensors. To deal with the technical issue, this study proposes a magnetic attitude control system with an unscented Kalman filter using gyro measurements and generated magnetic moment by the electromagnetic coil to estimate the weak magnetic field. With the estimated magnetic field vector, the spacecraft can achieve fuel-free attitude stabilization and RW unloading under the constraints. This proposed system does not require fuel for attitude control. Furthermore, the simple structure and electronic circuits of the electromagnetic coil allow the spacecraft to achieve a simple and reliable attitude control system. Numerical simulations demonstrate the effectiveness of the proposed attitude stabilization and RW unloading methods.
机译：最近，已经推出了各种小型航天器并用于行星际任务。传统上，反应轮（RWS）和推动器在几乎所有行星间航天器中用于这些姿态控制系统。虽然这些执行器对姿态控制有前途，但航天器任务的寿命受推进器所需的额外燃料的限制。此外，由于低可靠性和对质量和功耗的严格限制，难以在所有小型航天器中安装推进器。为了获得针对小型航天器的无燃料和可用的态度控制，本研究提出了一种基于行星际磁场（IMF）Kalman滤波器的行星磁姿态控制系统，包括姿态稳定和角动量卸载。在该方法中，使用与IMF相互作用的电磁线圈用于姿态控制系统。为了实现所提出的方法，必须检测到微弱的磁场。但是，IMF太弱而无法使用板载磁传感器感。为了处理技术问题，本研究提出了一种磁姿态控制系统，其使用陀螺仪测量和产生磁矩的磁态控制系统，并通过电磁线圈产生磁矩以估计弱磁场。利用估计的磁场矢量，航天器可以在约束下实现无款姿态稳定和RW卸载。这一提出的系统不需要燃料进行态度控制。此外，电磁线圈的简单结构和电子电路允许宇宙飞船实现简单可靠的姿态控制系统。数值模拟证明了所提出的姿态稳定和RW卸载方法的有效性。

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