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.

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 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.

scholarly journals Modeling the angular momentum control of small spacecraft with a magnetic attitude control system

2019 ◽  
Vol 484 (4) ◽  
pp. 415-419
Author(s):  
V. M. Kulkov ◽  
Yu. G. Egorov ◽  
S. O. Firsyuk ◽  
V. V. Terentyev ◽  
A. O. Shemyakov
Keyword(s):  
Angular Momentum ◽  
Control System ◽  
Attitude Control ◽  
Experimental Studies ◽  
Control Mode ◽  
System Control ◽  
Attitude Control System ◽  
Electromagnetic System ◽  
Small Spacecraft ◽  
Magnetic Attitude Control

The problem of modeling the angular momentum control modes of small spacecraft using electromagnetic systems interacting with the Earth’s magnetic field is considered. The electromagnetic system control law has been constructed for various compositions of measurable parameters. A set of scale factors has been formed to investigate the angular momentum control mode of dynamically similar models. Based on a dynamical test stand, we have carried out experimental studies to model the angular motion dynamics of small spacecraft with a magnetic attitude control system.

Modeling the Angular Momentum Control of Small Spacecraft with a Magnetic Attitude Control System

2019 ◽  
Vol 64 (2) ◽  
pp. 57-60
Author(s):  
V. M. Kulkov ◽  
Yu. G. Egorov ◽  
S. O. Firsyuk ◽  
V. V. Terentyev ◽  
A. O. Shemyakov
Keyword(s):  
Angular Momentum ◽  
Control System ◽  
Attitude Control ◽  
Attitude Control System ◽  
Small Spacecraft ◽  
Magnetic Attitude Control

scholarly journals PICO-SATELLITE DETUMBLING SIMULATION USING MAGNETIC ATITUDE ACTUATOR (SIMULASI DETUMBLING PADA SATELIT PIKO MENGGUNAKAN AKTUATOR SIKAP MAGNETIK)

2017 ◽  
Vol 15 (1) ◽  
pp. 11 ◽  
Author(s):  
Ali Muksin ◽  
Ridanto Eko Poetro ◽  
Robertus Heru Triharjanto
Keyword(s):  
Magnetic Field ◽  
Control System ◽  
Attitude Control ◽  
The Other ◽  
Local Magnetic Field ◽  
Control Law ◽  
Attitude Control System ◽  
Transient Time ◽  
Matlab Simulink ◽  
The Moment

One of the methods to control Nano/pico-satellite’s attitude is using magneto-torquers as attitude actuators. ITB, at the moment is planning to develop a cubesat. Therefore, the objective of the research was to investigate the performance of such attitude control system for 3U class cubesat. The research used Matlab/simulink-based satellite simulator developed by LAPAN and ITB, and B-dot control law. The advantages of the method are that the actuators are small and lighter compared to the other type of actuators, such as momentum wheels or reaction wheels. However, the disadvantages is that the torques can be created only when the actuator oriented at non-zero angle with local magnetic field. The results showed that the attitude control system could performed the detumbling operation, with the best transient time at about two orbits period. Varying the gain parameter in the controller may result into variation of transient time and even unstability.   AbstrakSalah satu cara untuk mengendalikan sikap satelit nano/piko adalah dengan menggunakan magneto-torquer sebagai aktuator. Saat ini ITB tengah mewacanakan pengembangan cubesat, sehinggga tujuan dari penelitian ini adalah untuk mengevaluasi kinerja sistem kendali sikap berdasarkan medan magnet Bumi pada cubesat kelas 3U. Penelitian ini menggunakan simulator satelit berbasis MATLAB/simulink yang dikembangkan oleh LAPAN dan ITB, moda kendalinya berbasis hukum kendali b-dot. Keuntungan dari sistem kendali ini adalah ukuran dan beratnya yang kecil, dibandingkan dengan moda kendali lain, seperti momentum wheel atau reaction wheel. Sementara kerugiannya adalah hanya bisa menghasilkan torsi saat aktuator mempunyai sudut tidak nol dengan medan magnet Bumi. Hasil menunjukkan bahwa moda kendali tersebut dapat melakukan manuver de-tumbling, dengan waktu transient terbaik mendekati dua periode orbit. Juga ditunjukkan bahwa variasi waktu transient dan ketidakstabilan dapat diperoleh dengan memvariasikan parameter gain pada kontroler. 

Attitude Controller Design of Multiple Independently Targeted Reentry Vehicle Based on Internal Model Control

2013 ◽  
Vol 462-463 ◽  
pp. 809-814
Author(s):  
Fei Zhao ◽  
Fan Li ◽  
Jian Hui Zhao
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Internal Model ◽  
Internal Model Control ◽  
Attitude Dynamics ◽  
Attitude Control System ◽  
Reentry Vehicle ◽  
Model Control ◽  
Internal Model Controller ◽  
Attitude Controller

A Multiple Independently Targeted Reentry Vehicle (MIRV) is a ballistic missile payload containing several warheads each capable of hitting one of a group of targets. In the process of missile flight control, the release of warheads brings about coupling to the missile attitude control system which will lower the flight stability. In order to solve this problem, a missile attitude controller, which combined the α-order integral inverse system with internal model principle, was presented. Firstly, determine the Post Boost Vehicle (PBV) attitude dynamics model. Then, combine the linearization of attitude dynamics equation with feed-forward decoupling method to implement the attitude decoupling. Finally, a two-degree of freedom (TOF) multivariable internal model controller was set up to optimize the control system performance. Simulation results show that the coupling of attitude control system has been eliminated. Compared with the original system, the internal model controller provides the control system better input-tracking performance, robust stability and interference suppression capacity.

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