Sliding Mode Attitude Control of Spacecraft Considering Angular Rate Constraints

2021 ◽  
Vol 49 (2) ◽  
pp. 129-138
Author(s):  
Min-young Kim ◽  
Seok-ho Jang ◽  
Henzeh Leeghim
Keyword(s):  
Attitude Control ◽  
Sliding Mode ◽  
Angular Rate ◽  
Rate Constraints

scholarly journals Angular Rate Constrained Sliding Mode Control of UAVs for Path Following

Electronics ◽  
2021 ◽  
Vol 10 (22) ◽  
pp. 2776
Author(s):  
Seok-ho Jang ◽  
Youyoung Yang ◽  
Henzeh Leeghim
Keyword(s):  
Sliding Mode Control ◽  
Attitude Control ◽  
Sliding Mode ◽  
Angular Rate ◽  
Equilibrium Points ◽  
Path Following ◽  
Lyapunov Stability Theory ◽  
Control Measures ◽  
Control Technique ◽  
Mode Control

In this work, a sliding-mode-based attitude controller constrained with the angular rate for unmanned aerial vehicles (UAVs) is addressed to withstand conditions below the allowable maximum angular velocity of UAVs in order to avoid the possibility of structural failure and to operate UAVs safely. The sliding mode controller suggested in this work defines a new sliding surface, inherently having two equilibrium points. These equilibrium points are carefully inspected, and the stability of the system controlled by means of the proposed approach is also analyzed using Lyapunov stability theory. To highlight the angular-rate constrained attitude control technique, a three-dimensional path is constructed using the Dubins path technique, and three-axis attitude commands for UAV are also generated by augmenting the line-of-sight algorithm. Compared with conventional sliding mode control measures, the excellent performance of the suggested control algorithm has been demonstrated by conducting numerical simulations.

Rotational and relative translational control for satellite electromagnetic formation flying in low earth orbit

2017 ◽  
Vol 89 (6) ◽  
pp. 815-825 ◽  
Author(s):  
Li Fan ◽  
Min Hu ◽  
Mingqi Yang
Keyword(s):  
Control Problem ◽  
Translational Control ◽  
Attitude Control ◽  
Formation Flying ◽  
Sliding Mode ◽  
Large Angle ◽  
Translation Control ◽  
Nonlinear Controller ◽  
Content Type ◽  
Hybrid Particle Swarm Optimization

Purpose The purpose of this paper is to develop a theoretical design for the attitude control of electromagnetic formation flying (EMFF) satellites, present a nonlinear controller for the relative translational control of EMFF satellites and propose a novel method for the allocation of electromagnetic dipoles. Design/methodology/approach The feedback attitude control law, magnetic unloading algorithm and large angle manoeuvre algorithm are presented. Then, a terminal sliding mode controller for the relative translation control is put forward and the convergence is proved. Finally, the control allocation problem of electromagnetic dipoles is formulated as an optimization issue, and a hybrid particle swarm optimization (PSO) – sequential quadratic programming (SQP) algorithm to optimize the free dipoles. Three numerical simulations are carried out and results are compared. Findings The proposed attitude controller is effective for the sun-tracking process of EMFF satellites, and the magnetic unloading algorithm is valid. The formation-keeping scenario simulation demonstrates the effectiveness of the terminal sliding model controller and electromagnetic dipole calculation method. Practical implications The proposed method can be applied to solve the attitude and relative translation control problem of EMFF satellites in low earth orbits. Originality/value The paper analyses the attitude control problem of EMFF satellites systematically and proposes an innovative way for relative translational control and electromagnetic dipole allocation.

Super-twisting disturbance observer-based finite- time attitude stabilization of flexible spacecraft subject to complex disturbances

2018 ◽  
Vol 25 (5) ◽  
pp. 1008-1018 ◽  
Author(s):  
Ruidong Yan ◽  
Zhong Wu
Keyword(s):  
Attitude Control ◽  
Disturbance Observer ◽  
Sliding Mode ◽  
State Variables ◽  
Attitude Dynamics ◽  
Attitude Control System ◽  
Terminal Sliding Mode ◽  
Nonlinear Disturbance Observer ◽  
Attitude Stabilization ◽  
Nonsingular Terminal Sliding Mode

There exist complex disturbances in the attitude control system of flexible spacecrafts, such as space environmental disturbances, flexible vibrations, inertia uncertainties, payload motions, etc. To suppress the effects of these disturbances on the performance of attitude stabilization, a super-twisting disturbance observer (STDO)-based nonsingular terminal sliding mode controller (NTSMC) is proposed in this paper. First, STDO is designed for a second-order dynamical system constructed by applying the lumped disturbance and its integral as state variables, and applying the integral as virtual measurement. Since the virtual measurement is obtained by integrating the inverse attitude dynamics, STDO not only avoids the differential operation of angular velocity, but also fully utilizes the information of a nonlinear model. By combining STDO with NTSMC, a composite controller is designed to achieve high-accuracy spacecraft attitude stabilization. Since most of the disturbances are compensated for by a STDO-based feedforward compensator, only a small switching gain is required to deal with the residual disturbances and uncertainties. Thus, the chattering phenomenon of the controller can be alleviated to a great extent. Finally, numerical simulations for the comparison between STDO-based NTSMC and nonlinear disturbance observer-based NTSMC are carried out in the presence of complex disturbances to verify the effectiveness of the proposed approach.

scholarly journals Fault Reconstruction Approach for Distributed Coordinated Spacecraft Attitude Control System

2015 ◽  
Vol 2015 ◽  
pp. 1-9
Author(s):  
Mingyi Huo ◽  
Yanning Guo ◽  
Xing Huo
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Large Scale ◽  
Sliding Mode ◽  
Reconstruction Error ◽  
Spacecraft Attitude ◽  
Alignment Error ◽  
Spacecraft Attitude Control ◽  
Attitude Control System ◽  
Fault Reconstruction

This work presents a novel fault reconstruction approach for a large-scale system, that is, a distributed coordinated spacecraft attitude control system. The attitude of all the spacecrafts in this distributed system is controlled by using thrusters. All possible faults of thruster including thrust magnitude error and alignment error are investigated. As a stepping stone, the mathematical model of thruster is firstly established based on the thruster configuration. On the basis of this, a sliding mode observer is then proposed to reconstruct faults in each agent of the coordinated control system. A Lyapunov-based analysis shows that the observer asymptotically converges to the actual faults. The key feature of this fault reconstruction approach is that it can achieve a faster reconstruction of the fault in comparison with the conventional fault reconstruction schemes. It can globally reconstruct thruster faults with zero reconstruction error, and this is accomplished within finite time. The effectiveness of the proposed approach is analytically authenticated via simulation study.

scholarly journals Design And Development Of Power And Attitude Control Subsystems For RYESAT

2021 ◽  
Author(s):  
Michael William Richard. Alger
Keyword(s):  
Attitude Control ◽  
Sliding Mode ◽  
Attitude Motion ◽  
Critical Systems ◽  
Magnetic Torque ◽  
Design And Development ◽  
Control Laws ◽  
Spacecraft Control ◽  
Standard Interface ◽  
Data Bus

This thesis describes the design and development of Ryerson University's first CubeSat (RyeSat) with a focus on power and attitude control subsystems. This satellite is intended to become the initial of a series of CubeSats built by Ryerson University to perform research in spacecraft control algorithms and actuators. RyeSat is built around a standard interface, which specifies both a data-bus and a switchable power supply system for non critical systems. To facilitate the development of this satellite a prototype power subsystem was created, programmed and tested. In addition to developing the system's architecture and power subsystem; analysis was preformed to size both reaction wheels and magnetic torquers. This analysis showed that a commercially available motor could be adapted to fulfill the attitude control requirements of a CubeSat and also showed that miniature magnetic torque rods would be more efficient that magnetic torque coils typically used on CubeSats. Finally, control laws for these actuators were designed and an adaptive nonlinear sliding mode controller for reaction wheels was applied to control the 3-axis attitude motion of RyeSat.

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