Stability Analysis of the Microsatellite Attitude Control System

2015 ◽  
Vol 798 ◽  
pp. 297-302
Author(s):  
Meirbek Moldabekov ◽  
Suleimen Yelubayev ◽  
Kuanysh Alipbayev ◽  
Anna Sukhenko ◽  
Timur Bopeyev ◽  
...  
Keyword(s):  
Mathematical Model ◽  
Control System ◽  
Stability Analysis ◽  
Electric Motor ◽  
Attitude Control ◽  
Control Process ◽  
Control Voltage ◽  
Control Law ◽  
Attitude Control System ◽  
Technical Specifications

The problem of development of the microsatellite attitude control system on the base of reaction wheels positioned along its principal central axes of inertia is considered in this article. As difference from the classical mathematical models describing the microsatellite motion, this article includes the mathematical model of reaction wheel which is controlled by the input voltage of the electric motor. PD-controller is used as the basis for the development of the control law for microsatellite attitude. The stability analysis of the microsatellite attitude control process was carried out with the help of Lyapunov function method. This analysis allowed to prove that obtained attitude control law provides the asymptotic stability of the microsatellite rotational motion. Further, the function of control voltage for the reaction wheel’s electric motor with account of its technical specifications was obtained based on the derived mathematical model of the reaction wheel’s dynamics. The results of performed simulation showed the effectiveness of developed control. Obtained results of the study provide a base for the use of presented approach to the development of attitude control system for microsatellites with various missions.

scholarly journals Modelling the attitude dynamics of small spacecraft with a magnetic attitude control system in three-axis stabilization mode

2019 ◽  
Vol 488 (4) ◽  
pp. 377-382
Author(s):  
V. M. Kulkov ◽  
Yu. G. Egorov ◽  
S. O. Firsyuk ◽  
V. V. Terentyev ◽  
A. O. Shemyakov
Keyword(s):  
Magnetic Field ◽  
Mathematical Model ◽  
Control System ◽  
Attitude Control ◽  
Control Law ◽  
Attitude Dynamics ◽  
Attitude Control System ◽  
Small Spacecraft ◽  
Magnetic Attitude Control ◽  
System Movement

The problem of modeling the attitude-control modes of small spacecraft with the use of electromagnetic systems, interacting with the Earths magnetic field is considered. A small spacecraft angular motion mathematical model is developed. A control law for magnetic attitude control system of small spacecraft is formulated. Results of satellite with magnetic attitude control system movement numerical modelling are presented.

scholarly journals Nonlinear suboptimal attitude control law for near-space hypersonic vehicle: Eigenvalue analysis and weight matrices design

2022 ◽  
Author(s):  
Peichao Mi ◽  
Qingxian Wu ◽  
Yuhui Wang
Keyword(s):  
Optimal Control ◽  
Control System ◽  
Attitude Control ◽  
Stable Manifold ◽  
Closed Loop ◽  
Suboptimal Control ◽  
Control Law ◽  
Attitude Dynamics ◽  
Attitude Control System ◽  
Near Space

Abstract This paper considers a nonlinear suboptimal control problem for a near-space hypersonic vehicle's (NSHV's) attitude dynamics. The least-square and stable manifold methods first solve an unconstrained approximately optimal control law corresponding to the nonlinear attitude model. Then, to further meet the dynamic performance requirement of the attitude control system, a novel strategy based on the Koopman operator, symplectic geometric theory, and the stable manifold theorem is proposed to approximate the eigenvalues of the closed-loop nonlinear unconstrained approximated optimal control system. The weight matrices in the optimal performance index, which directly determine the output responses of the nonlinear attitude dynamics, can be appropriately designed according to the eigenvalues. The final control law considers the actuator constraints. The NSHV's closed-loop attitude control system is proved to be locally exponentially stable, and the suboptimality of the control law is analyzed. Numerical simulation demonstrates the effectiveness of the proposed scheme.

Optimization of Satellite Momentum Wheel Control System Based on Genetic Programming

2013 ◽  
Vol 748 ◽  
pp. 771-778
Author(s):  
Yu Song Huang ◽  
Yun Feng Dong
Keyword(s):  
Mathematical Model ◽  
Control System ◽  
Genetic Programming ◽  
Design Process ◽  
Attitude Control ◽  
Control Method ◽  
Complex Structure ◽  
Control Law ◽  
Reaction Wheel ◽  
The Mathematical Model

Due to reliability requirements, the reaction wheel actuator of the satellite attitude control system always use traditional control method. For the satellite which has complex structure, it's difficult to build the mathematical model with classical control method. The selection of control parameters is also difficult. The design process last long and the model have poor adaptability when the parameters change. Compare to genetic algorithms, genetic programming which have the capabilities to evolve automatically, have the advantage of being able to optimize the structure of the mathematical model. Results of optimization and simulation show that design the reaction wheel actuator control law with genetic programming can simplify the design process. And the evolved control law is better than traditional PD control law.

scholarly journals Design of Attitude Control System for UAV Based on Feedback Linearization and Adaptive Control

2014 ◽  
Vol 2014 ◽  
pp. 1-8 ◽  
Author(s):  
Wenya Zhou ◽  
Kuilong Yin ◽  
Rui Wang ◽  
Yue-E Wang
Keyword(s):  
Adaptive Control ◽  
Control System ◽  
Attitude Control ◽  
Feedback Linearization ◽  
Control Law ◽  
Attitude Control System ◽  
Model Uncertainties ◽  
Performance Indexes ◽  
Attitude Dynamic ◽  
Adaptive Control Law

Attitude dynamic model of unmanned aerial vehicles (UAVs) is multi-input multioutput (MIMO), strong coupling, and nonlinear. Model uncertainties and external gust disturbances should be considered during designing the attitude control system for UAVs. In this paper, feedback linearization and model reference adaptive control (MRAC) are integrated to design the attitude control system for a fixed wing UAV. First of all, the complicated attitude dynamic model is decoupled into three single-input single-output (SISO) channels by input-output feedback linearization. Secondly, the reference models are determined, respectively, according to the performance indexes of each channel. Subsequently, the adaptive control law is obtained using MRAC theory. In order to demonstrate the performance of attitude control system, the adaptive control law and the proportional-integral-derivative (PID) control law are, respectively, used in the coupling nonlinear simulation model. Simulation results indicate that the system performance indexes including maximum overshoot, settling time (2% error range), and rise time obtained by MRAC are better than those by PID. Moreover, MRAC system has stronger robustness with respect to the model uncertainties and gust disturbance.

Modeling and Attitude Control of a Spinning Spacecraft with Internal Moving Mass

2013 ◽  
Vol 760-762 ◽  
pp. 1216-1220 ◽  
Author(s):  
Peng Fei Guo ◽  
Liang Yu Zhao
Keyword(s):  
Nonlinear Dynamics ◽  
Control System ◽  
Attitude Control ◽  
Linear Quadratic Regulator ◽  
Control Law ◽  
Moving Mass ◽  
Newtonian Mechanics ◽  
Attitude Control System ◽  
Linear Quadratic ◽  
The Mathematical Model

An attitude control system of a spinning spacecraft with internal moving mass is presented in this paper. This system consists of a rigid body and two internal radial moving masses. The mathematical model, including attitude kinematics and nonlinear dynamics equations, is established based on Newtonian mechanics. The control law is designed based on the linear-quadratic-regulator (LQR) theory. The performance of the controller is demonstrated in numerical simulation, and the response shows that the attitude control system is stable and effective.

scholarly journals Nonlinear suboptimal attitude control law for near-space hypersonic vehicle: Eigenvalue analysis and weight matrices design

2021 ◽  
Author(s):  
Peichao Mi ◽  
Qingxian Wu ◽  
Yuhui Wang
Keyword(s):  
Optimal Control ◽  
Control System ◽  
Attitude Control ◽  
Stable Manifold ◽  
Closed Loop ◽  
Suboptimal Control ◽  
Control Law ◽  
Attitude Dynamics ◽  
Attitude Control System ◽  
Near Space

Abstract This paper considers a nonlinear suboptimal control problem for a near-space hypersonic vehicle's (NSHV's) attitude dynamics. The least-square and stable manifold methods first solve an unconstrained approximately optimal control law corresponding to the nonlinear attitude model. Then, to further meet the dynamic performance requirement of the attitude control system, a novel strategy based on the Koopman operator, symplectic geometric theory, and the stable manifold theorem is proposed to approximate the eigenvalues of the closed-loop nonlinear unconstrained approximated optimal control system. The weight matrices in the optimal performance index, which directly determine the output responses of the nonlinear attitude dynamics, can be appropriately designed according to the eigenvalues. The final control law considers the actuator constraints. The NSHV's closed-loop attitude control system is proved to be locally exponentially stable, and the suboptimality of the control law is analyzed. Numerical simulation demonstrates the effectiveness of the proposed scheme.

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