Design and analysis of MHD-based momentum ring for satellite attitude adjustment

Due to unavoidable factors, heavy-tailed noise appears in satellite attitude estimation. Traditional Kalman filter is prone to performance degradation and even filtering divergence when facing non-Gaussian noise. The existing robust algorithms have limited accuracy. To improve the attitude determination accuracy under non-Gaussian noise, we use the centered error entropy (CEE) criterion to derive a new filter named centered error entropy Kalman filter (CEEKF). CEEKF is formed by maximizing the CEE cost function. In the CEEKF algorithm, the prior state values are transmitted the same as the classical Kalman filter, and the posterior states are calculated by the fixed-point iteration method. The CEE EKF (CEE-EKF) algorithm is also derived to improve filtering accuracy in the case of the nonlinear system. We also give the convergence conditions of the iteration algorithm and the computational complexity analysis of CEEKF. The results of the two simulation examples validate the robustness of the algorithm we presented.

Download Full-text

Satellite Attitude Control with Deep Reinforcement Learning

2020 Chinese Automation Congress (CAC) ◽

10.1109/cac51589.2020.9326605 ◽

2020 ◽

Author(s):

Duozhi Gao ◽

Haibo Zhang ◽

Chuanjiang Li ◽

Xinzhou Gao

Keyword(s):

Reinforcement Learning ◽

Attitude Control ◽

Satellite Attitude ◽

Satellite Attitude Control

Download Full-text

Boundary control design based on partial differential equation observer for vibration suppression and attitude control of flexible satellites with multi-section solar panels

Journal of Vibration and Control ◽

10.1177/1077546321990158 ◽

2021 ◽

pp. 107754632199015

Author(s):

Mohammad Mahdi Ataei ◽

Hassan Salarieh ◽

Hossein Nejat Pishkenari ◽

Hadi Jalili

Keyword(s):

Differential Equation ◽

Partial Differential Equation ◽

Attitude Control ◽

Vibration Suppression ◽

Equation System ◽

Solar Panels ◽

Attitude Dynamics ◽

Partial Differential ◽

Satellite Attitude ◽

Element Technique

A novel partial differential equation observer is proposed to be used in boundary attitude and vibration control of flexible satellites. Solar panels’ vibrations and attitude dynamics form a coupled partial differential equation–ordinary differential equation system which is controlled directly without discretization. Few feedback signals from boundaries are required which are estimated via a partial differential equation observer. Consequently, just satellite attitude and angular velocity should be measured and still the control system benefits information from continuous part vibrations. The closed-loop system is proved to be asymptotically stable. Simulations with a finite element technique illustrate good performance of this observer-based boundary controller.

Download Full-text