Three-axis attitude stabilization of a flexible satellite using non-linear PD controller

2016 ◽  
Vol 40 (2) ◽  
pp. 591-605 ◽  
Author(s):  
Babak Baghi ◽  
Mansour Kabganian ◽  
Reza Nadafi ◽  
Ehsan Arabi
Keyword(s):  
Control System ◽  
Direct Method ◽  
Pd Controller ◽  
Control Torque ◽  
Parameter Uncertainties ◽  
External Disturbances ◽  
Control Moment Gyroscope ◽  
Attitude Stabilization ◽  
Control Moment ◽  
Non Linear

In this paper, after complete modelling of a flexible satellite equipped with a control moment gyroscope (CMG) actuator, it is shown that a PD-like controller can globally asymptotically stabilize this satellite by using Lyapunov’s direct method. Despite the simplicity, simulations show that the controller can stabilize the flexible satellite in a three-axis manoeuvre even in the presence of external disturbances. Then, using a non-linear variable gains PD controller, which only uses angular velocity of the rigid body and the attitude parameters as the inputs, the performance of the control system is improved in some important aspects such as reducing maximum control torque, reducing maximum peak of deflection of the appendages and increasing robustness of the controller against the orbital disturbances. In addition, locally asymptotically stability of the non-linear variable gain PD controller is guaranteed using a novel Lyapunov candidate function. Considering the difficulty in measuring the appendages’ deflection and the primarily existence of parameter uncertainties, and as this controller is independent of changes in these parameters, such a control system is very useful and applicable. In order to validate the system’s mathematical model and the control system performance, an exact model of the satellite is constructed in the ADAMS/View software that is linked to the MATLAB software. The efficacy of the proposed approach is demonstrated by several numerical examples.

The FPGA-Based Phase-Locked Loop Speed Control System of BLDCM for Magnetically Suspended Control Moment Gyroscope

2011 ◽  
Vol 80-81 ◽  
pp. 1249-1257
Author(s):  
Bang Cheng Han ◽  
Dan He ◽  
Fang Zheng Guo ◽  
Yu Wang ◽  
Bing Nan Huang
Keyword(s):  
Control System ◽  
Integrated Circuit ◽  
High Speed ◽  
Speed Control ◽  
Phase Locked Loop ◽  
Buck Converter ◽  
Current Loop ◽  
Loop Control ◽  
Control Moment Gyroscope ◽  
Control Moment

A phase-locked loop (PLL) control system based on field programmable gates array (FPGA) is proposed through analyzing the model of three-phase unipolar-driven BLDCM (brushless direct current motor) to enhance the reliability and accurate steady-state speed for magnetically suspended control moment gyroscope (MSCMG). The numerical operation module, PLL module and current-loop control module are designed based on FPGA using very-high-speed integrated circuit hardware description language (VHDL) to realize the control law of the digital system. The pulse width modulation (PWM) generating module for Buck converter, the commutation signal generating module for the inverter and ADC module are designed for driving the motor and sampling the current signal. The PLL is analyzed and optimized in the paper and all the modules are verified using the software of ModelSim and the experiments. The simulation and experiment results on BLDCM of MSCMG show that the stability of the motor velocity can reach 0.01% and 0.02% respectively by the PLL technology based on FPGA, which is difficult to be obtained by conventional proportion integral different (PID) speed control.

Robust Control Research for AUV Trajectory Control System

2011 ◽  
Vol 148-149 ◽  
pp. 93-96
Author(s):  
Juan Li ◽  
Xin Qian Bian ◽  
Hua Sheng Xiong ◽  
Hong Jian Wang
Keyword(s):  
Control System ◽  
Robust Control ◽  
Control Problem ◽  
Horizontal Plane ◽  
Vertical Plane ◽  
Trajectory Control ◽  
Parameter Uncertainties ◽  
External Disturbances ◽  
Heading Control ◽  
Control Research

A robust trajectory control problem for an underactuated AUV with parameter uncertainties and external disturbances was considered. The trajectory control was decomposed in the horizontal plane and vertical plane. Based on the robust theory, the AUV model for heading control was proposed, and the heading controller was designed. The simulated results show that the method can effectively overcome disturbances of constant ocean currents to ensure the precision track.

A composite anti-disturbance control scheme for attitude stabilization and vibration suppression of flexible spacecrafts

2015 ◽  
Vol 23 (15) ◽  
pp. 2470-2477 ◽  
Author(s):  
Zhen Wang ◽  
Zhong Wu ◽  
Lijun Li ◽  
Jun Yuan
Keyword(s):  
Attitude Control ◽  
Disturbance Observer ◽  
Vibration Suppression ◽  
Disturbance Attenuation ◽  
Pd Controller ◽  
Parameter Uncertainties ◽  
Performance Simulation ◽  
Attitude Stabilization ◽  
Multiple Disturbances ◽  
Control Scheme

Abstract: There exist multiple disturbances resulting from the structural vibrations of flexible appendages, unknown external and internal disturbances, and parameter uncertainties, which affect the attitude control performance seriously. To enhance the disturbance attenuation performance and vibration suppression ability, a composite anti-disturbance control scheme (CADCS) based on disturbance observer is proposed for attitude stabilization and vibration reduction of flexible spacecraft. The CADCS combines a composite disturbance observer (CDO) and a PD controller with feedforward. The multiple disturbances are equivalent to slowly varying disturbance and harmonic disturbance. The CDO can estimate two types of disturbance and compensate for them through feedforward. The PD controller realizes the asymptotic convergence by compensating the disturbance from CDO. The CADCS based on CDO and PD controller is not only simple and easy to realize, but also yields better vibration suppression and anti-disturbance performance. Simulation results of a certain spacecraft demonstrate the effectiveness of the proposed CADCS.

Adaptive fault-tolerant control for hybrid attitude tracking control system with quantized control torque and measurement

2020 ◽  
pp. 095441002095330
Author(s):  
Min Li ◽  
Yingchun Zhang ◽  
Yunhai Geng
Keyword(s):  
Control System ◽  
Tracking Control ◽  
Fault Tolerant ◽  
Fault Tolerant Control ◽  
Actuator Faults ◽  
Control Torque ◽  
External Disturbances ◽  
Quantized Control ◽  
Attitude Tracking ◽  
Attitude Tracking Control

In this paper, the problem of fault tolerant control for spacecraft attitude tracking control system in the presence of actuator faults/failures, quantized control torque and measurement, uncertain inertial matrix and external disturbances is taken into account. The dynamical uniform quantizers are developed to quantize the signals of control torque and measurement, which can reduce the data transmission rate. In combination with the CA and FTC technique, a robust adaptive fault tolerant control scheme is proposed to cope with the effects of quantization errors in control torque and measurement, the unknown actuator faults/failures, uncertain inertial matrix and external disturbances. The developed control strategy combined with quantized control torque and measurement can guarantee the stability of overall closed-loop system and achieve satisfactory attitude tracking performance. Finally, simulation results are presented to verify the effectiveness of the proposed methods.

scholarly journals Finite-Time Stabilization Control for a Rigid Spacecraft under Parameter Uncertainties

2014 ◽  
Vol 2014 ◽  
pp. 1-11 ◽  
Author(s):  
Aihua Zhang ◽  
Jianfei Ni ◽  
Xing Huo
Keyword(s):  
Finite Time ◽  
Parameter Uncertainties ◽  
External Disturbances ◽  
Attitude Stabilization ◽  
Stabilization Control ◽  
Time Control ◽  
Control Scheme ◽  
Lyapunov Stability Analysis ◽  
Homogeneous Method ◽  
Rigid Spacecraft

A novel finite-time control scheme is investigated for a rigid spacecraft in present of parameter uncertainties and external disturbances. Firstly, the spacecraft mathematical model is transformed into a cascading system by introducing an adaptive variable. Then a novel finite-time attitude stabilization control scheme for a rigid spacecraft is proposed based on the homogeneous method. Lyapunov stability analysis shows that the resulting closed-loop attitude system is proven to be stable in finite time without parameter uncertainties and asymptotically stable with parameter uncertainties. Finally, numerical simulation examples are also presented to demonstrate that the control strategy developed is feasible and effective for spacecraft attitude stabilization mission.

Investigation of the stability of periodic motions in a nonlinear automatic control system based on the fast fourier transform

2003 ◽  
Vol 3 ◽  
pp. 297-307
Author(s):  
V.V. Denisov
Keyword(s):  
Fourier Transform ◽  
Control System ◽  
Automatic Control ◽  
Fast Fourier Transform ◽  
Automatic Control System ◽  
Resonance Phenomenon ◽  
Periodic Motions ◽  
Multiply Connected ◽  
Non Linear ◽  
The Stability

An approach to the study of the stability of non-linear multiply connected systems of automatic control by means of a fast Fourier transform and the resonance phenomenon is considered.

Sign in / Sign up

Export Citation Format

Share Document