scholarly journals Adaptive Neural Network-Based Satellite Attitude Control by Using the Dynamic Inversion Technique and a VSCMG Pyramidal Cluster

Complexity ◽  
2019 ◽  
Vol 2019 ◽  
pp. 1-16 ◽  
Author(s):  
Mihai Lungu ◽  
Romulus Lungu
Keyword(s):  
Neural Network ◽  
Attitude Control ◽  
Approximation Error ◽  
Inversion Method ◽  
Dynamic Inversion ◽  
Control Law ◽  
Feed Forward Neural Network ◽  
Small Satellites ◽  
Control Moment ◽  
Satellite Attitude Control

The paper presents an adaptive system for the control of small satellites’ attitude by using a pyramidal cluster of four variable-speed control moment gyros as actuators. Starting from the dynamic model of the pyramidal cluster, an adaptive control law is designed by means of the dynamic inversion method and a feed-forward neural network-based nonlinear subsystem; the control law has a proportional-integrator component (for the control of the reduced-order linear subsystem) and an adaptive component (for the compensation of the approximation error associated with the function describing the dynamics of the nonlinear system). The software implementation and validation of the new control architecture are achieved by using the Matlab/Simulink environment.

scholarly journals Application Research of Network Learning Algorithm Based on Neural Network Disturbance Compensation in Satellite Attitude Control

2021 ◽  
Author(s):  
F Leo John ◽  
Deeksha Dogra
Keyword(s):  
Neural Network ◽  
Attitude Control ◽  
Control Method ◽  
Learning Algorithm ◽  
Disturbance Compensation ◽  
Small Satellites ◽  
Network Learning ◽  
Satellite Attitude ◽  
The Neural Network ◽  
Satellite Attitude Control

Based on the satellite attitude control method, this paper proposes an attitude control method based on neural network disturbance compensation. The paper firstly analyzes the neural network algorithm and proposes an orthogonal least squares algorithm to implement network learning. In this paper, a set of high-precision directional neural network compensation controllers is designed for the attitude control of acupuncture small satellites. The feasibility of the improved orthogonal least-squared algorithm combined with the neural network supplementary control method in satellite attitude control is verified by experiments.

The Satellite Attitude Control Law Design Based on Machine Learning

2014 ◽  
Vol 519-520 ◽  
pp. 741-746 ◽  
Author(s):  
Guo Jiang Sun ◽  
Jin Hui Li ◽  
Shi Ming Chen ◽  
Yun Feng Dong
Keyword(s):  
Machine Learning ◽  
Attitude Control ◽  
Fitness Function ◽  
Control Law ◽  
Sensors And Actuators ◽  
Control Laws ◽  
Satellite Attitude ◽  
Control Precision ◽  
Attitude Error ◽  
Satellite Attitude Control

Traditional optimization algorithms can only optimize parameters in control laws. Machine learning method can optimize parameters and evolve satellite attitude control law automatically under certain criterion. Single axis satellite attitude simulation system with noise was built up, which included satellite attitude dynamic model, sensors and actuators model. The control laws inputs were attitude error, attitude errors integral and angular velocity error, and outputs were actuators control instructions. Control laws fitness function was an attitude errors statistical function. With suitable function set selected for genetic programming (GP) and parse tree used to represent a control law expression, GP was used to evolve control law expression automatically. Simulation result shows that this method can evolve control law with uncertainties noise better. The evolved control law response and control precision are better than PID, and it can be used in satellite attitude control.

scholarly journals Adaptive Neural Network Sliding Mode Control for Quad Tilt Rotor Aircraft

Complexity ◽  
2017 ◽  
Vol 2017 ◽  
pp. 1-13 ◽  
Author(s):  
Yanchao Yin ◽  
Hongwei Niu ◽  
Xiaobao Liu
Keyword(s):  
Neural Network ◽  
Sliding Mode Control ◽  
Sliding Mode ◽  
Approximation Error ◽  
Model Parameters ◽  
Control Law ◽  
The Novel ◽  
Adaptive Neural Network ◽  
Mode Control ◽  
Attitude Tracking

A novel neural network sliding mode control based on multicommunity bidirectional drive collaborative search algorithm (M-CBDCS) is proposed to design a flight controller for performing the attitude tracking control of a quad tilt rotors aircraft (QTRA). Firstly, the attitude dynamic model of the QTRA concerning propeller tension, channel arm, and moment of inertia is formulated, and the equivalent sliding mode control law is stated. Secondly, an adaptive control algorithm is presented to eliminate the approximation error, where a radial basis function (RBF) neural network is used to online regulate the equivalent sliding mode control law, and the novel M-CBDCS algorithm is developed to uniformly update the unknown neural network weights and essential model parameters adaptively. The nonlinear approximation error is obtained and serves as a novel leakage term in the adaptations to guarantee the sliding surface convergence and eliminate the chattering phenomenon, which benefit the overall attitude control performance for QTRA. Finally, the appropriate comparisons among the novel adaptive neural network sliding mode control, the classical neural network sliding mode control, and the dynamic inverse PID control are examined, and comparative simulations are included to verify the efficacy of the proposed control method.

scholarly journals Integrated Power and Attitude Control Design of Satellites Based on a Fuzzy Adaptive Disturbance Observer Using Variable-Speed Control Moment Gyros

2016 ◽  
Vol 2016 ◽  
pp. 1-13 ◽  
Author(s):  
Zhongyi Chu ◽  
Jing Cui
Keyword(s):  
Attitude Control ◽  
Disturbance Observer ◽  
Peak Power ◽  
Speed Control ◽  
Variable Speed ◽  
Control Approach ◽  
Small Satellites ◽  
Control Moment ◽  
Fuzzy Adaptive ◽  
Variable Speed Control

To satisfy the requirements for small satellites that seek agile slewing with peak power, this paper investigates integrated power and attitude control using variable-speed control moment gyros (VSCMGs) that consider the mass and inertia of gimbals and wheels. The paper also details the process for developing the controller by considering various environments in which the controller may be implemented. A fuzzy adaptive disturbance observer (FADO) is proposed to estimate and compensate for the effects of equivalent disturbances. The algorithms can simultaneously track attitude and power. The simulation results illustrate the effectiveness of the control approach, which exhibits an improvement of 80 percent compared with alternate approaches that do not employ a FADO.

Robust launch vehicle’s generalized dynamic inversion attitude control

2017 ◽  
Vol 89 (6) ◽  
pp. 902-910 ◽  
Author(s):  
Uzair Ansari ◽  
Abdulrahman H. Bajodah
Keyword(s):  
Attitude Control ◽  
Closed Loop ◽  
Sliding Mode ◽  
Dynamic Scaling ◽  
Dynamic Inversion ◽  
Control Law ◽  
Successful Implementation ◽  
Robust Tracking Control ◽  
Content Type ◽  
Dynamic Constraints

Purpose To design a robust attitude control system for the ascent flight phase of satellite launch vehicles (SLVs). Design/methodology/approach The autopilot is based on generalized dynamic inversion (GDI). Dynamic constraints are prescribed in the form of differential equations that encapsulate the control objectives, and are generalized inverted using the Moore-Penrose Generalized Inverse (MPGI) based Greville formula to obtain the control law. The MPGI is modified via a dynamic scaling factor for assuring generalized inversion singularity-robust tracking control. An additional sliding mode control (SMC) loop is augmented to robustify the GDI closed-loop system against model uncertainties and external disturbances. Findings The robust GDI control law allows for two cooperating controllers that act on two orthogonally complement control spaces: one is the particular controller that realizes the dynamic constraints, and the other is the auxiliary controller that is affined in the null control vector, and is used to enforce global closed-loop stability. Practical implications Orthogonality of the particular and the auxiliary control subspaces ensures noninterference of the two control actions, and thus, it ensures that both actions work toward a unified goal. The robust control loop increases practicality of the GDI control design. Originality/value The first successful implementation of GDI to the SLV control problem.

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