scholarly journals Research on High-Precision Attitude Control of Joint Actuator of Three-Axis Air-Bearing Test Bed

2021 ◽  
Vol 2021 ◽  
pp. 1-11
Author(s):  
Zhiming Chen ◽  
Zhouhuai Luo ◽  
Yunhua Wu ◽  
Wei Xue ◽  
Wenxing Li
Keyword(s):  
Attitude Control ◽  
Control Algorithm ◽  
Large Angle ◽  
High Energy ◽  
Air Bearing ◽  
Air Conditioner ◽  
Test Bed ◽  
External Interference ◽  
Automatic Balancing ◽  
Control Accuracy

Three-axis air-bearing test bed is important semiphysical simulation equipment for spacecraft, which can simulate spacecraft attitude control, rendezvous, and docking with high confidence. When the three-axis air-bearing table is maneuvering at a large angle, if it is only controlled by the flywheel, it will cause the problems of slow maneuvering speed and high energy consumption, and when the external interference torque becomes large, the control accuracy will decline. A combined actuator including flywheel, air-conditioner thruster, and automatic balancing device is designed, and a hierarchical saturation PD control algorithm is proposed to improve the control accuracy and anti-interference ability of the three-axis air-bearing test bed. Finally, the mathematical simulation of the proposed control algorithm is carried out, and the physical verification is carried out on the three-axis air-bearing test bed. The results show that the control algorithm has higher control accuracy than the traditional control algorithm, and the control accuracy is better than 0.1 ∘ and basically meets the attitude control requirements of the ground simulation in-orbit satellite.

scholarly journals Design of Satellite Attitude Control Algorithm Based on the SDRE Method Using Gas Jets and Reaction Wheels

2013 ◽  
Vol 2013 ◽  
pp. 1-8 ◽  
Author(s):  
Luiz C. G. de Souza ◽  
Victor M. R. Arena
Keyword(s):  
Attitude Control ◽  
Control Algorithm ◽  
Controller Design ◽  
Algorithm Design ◽  
Large Angle ◽  
Space Mission ◽  
Control Technique ◽  
Gas Jets ◽  
State Dependent ◽  
Highly Nonlinear

An experimental attitude control algorithm design using prototypes can minimize space mission costs by reducing the number of errors transmitted to the next phase of the project. The Space Mechanics and Control Division (DMC) of INPE is constructing a 3D simulator to supply the conditions for implementing and testing satellite control hardware and software. Satellite large angle maneuver makes the plant highly nonlinear and if the parameters of the system are not well determined, the plant can also present some level of uncertainty. As a result, controller designed by a linear control technique can have its performance and robustness degraded. In this paper the standard LQR linear controller and the SDRE controller associated with an SDRE filter are applied to design a controller for a nonlinear plant. The plant is similar to the DMC 3D satellite simulator where the unstructured uncertainties of the system are represented by process and measurements noise. In the sequel the State-Dependent Riccati Equation (SDRE) method is used to design and test an attitude control algorithm based on gas jets and reaction wheel torques to perform large angle maneuver in three axes. The SDRE controller design takes into account the effects of the plant nonlinearities and system noise which represents uncertainty. The SDRE controller performance and robustness are tested during the transition phase from angular velocity reductions to normal mode of operation with stringent pointing accuracy using a switching control algorithm based on minimum system energy. This work serves to validate the numerical simulator model and to verify the functionality of the control algorithm designed by the SDRE method.

Robust Attitude Control and Virtual Reality Model for Quadrotor

2015 ◽  
Vol 9 (3) ◽  
pp. 283-290 ◽  
Author(s):  
To Xuan Dinh ◽  
◽  
Doan Ngoc Chi Nam ◽  
Kyoung Kwan Ahn ◽  
Keyword(s):  
Virtual Reality ◽  
Attitude Control ◽  
Control Algorithm ◽  
Test Bed ◽  
Adaptive Backstepping ◽  
Motion Equations ◽  
Quadrotor Helicopter ◽  
Control Scheme ◽  
Virtual Reality Model ◽  
Backstepping Algorithm

This paper introduces an adaptive attitude control based on a backstepping control scheme for a quadrotor helicopter test bed. First, aerodynamics and motion equations are provided to model the dynamics of the quadrotor and a Virtual Reality (VR) model is developed incorporating the dynamic model to the virtual results of simulation. Then, an adaptive backstepping algorithm is applied to the attitude control and this algorithm is adaptive according to Lyapunov-based stability analysis. Finally, the simulation results with many types of reference signals are provided to demonstrate the good tracking performance of the proposed control algorithm.

Study of Hydraulic Servo System Based on Fuzzy Sliding Mode Algorithm

2013 ◽  
Vol 753-755 ◽  
pp. 2674-2678
Author(s):  
Kun Yang ◽  
Cai Jun Liu ◽  
Shu Min Liu
Keyword(s):  
Control Algorithm ◽  
Sliding Mode ◽  
Servo System ◽  
Time Varying ◽  
External Interference ◽  
System A ◽  
Hydraulic Servo ◽  
Fuzzy Sliding Mode ◽  
Hydraulic Servo System ◽  
Position Servo

Based on the situation that the hydraulic position servo system is easily influenced by the external interference and the parameters of which are different with time-varying, the fuzzy control can soften the buffeting and the sliding algorithm has no the same problems as the hydraulic position servo system, a brandly-new fuzzy sliding control algorithm is designed. In the simulation process, within the parameters of simulated time-varying and outside strong interference, the results show that the hydraulic servo system based on fuzzy sliding mode control algorithm has a greater resistance to internal and external interference and time-varying parameters.

Permanent Magnet Chatter Absorber with Fuzzy Logic Control

2009 ◽  
Vol 147-149 ◽  
pp. 290-295 ◽  
Author(s):  
Bogdan Broel-Plater ◽  
Stefan Domek ◽  
Arkadiusz Parus
Keyword(s):  
Fuzzy Logic ◽  
Control System ◽  
Fuzzy Control ◽  
Fuzzy Logic Control ◽  
Control Algorithm ◽  
Permanent Magnets ◽  
Practical Experience ◽  
High Energy ◽  
Logic Control ◽  
Machine Operators

The paper deals with semi-active chatter absorber based on an electrodynamic transducer built around high-energy permanent magnets. Also, a fuzzy logic control system for the absorber control system has been designed. The principal advantage of fuzzy control is the possibility to implement practical experience gained by machine operators in the control algorithm. Hence, the possibility of factoring such quantities, as vibrations experienced by selected points of the machine-tool, and sound emitted by working machine into the analyzed chatter absorber fuzzy control system has been studied in the paper. The control system has been tested by way of simulation with the use of the process and cutting force models.

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.

The Improved Design of Test Machine Linear-Velocity Closed-Loop Control Circuit

2013 ◽  
Vol 365-366 ◽  
pp. 874-877
Author(s):  
Chang Hai Li ◽  
Yuan Tao Yu ◽  
Shi Yang Ma ◽  
Yan Chun Liu
Keyword(s):  
Pid Control ◽  
Control Algorithm ◽  
Response Speed ◽  
Test Machine ◽  
Static Error ◽  
Loop Control ◽  
Improved Design ◽  
Value Changes ◽  
The Given ◽  
Control Accuracy

Incremental PID has its shortcomings: great integral truncation effect, static error and spillover affect. In the control system, the controller system is required having a quick response speed, and also a certain anti-interference ability. When adopting the improved differential PID control algorithm, only the output differential is made, instead of the given values. So, when a given value changes, the output will not change, and the controlled quantity change is usually mild, in which case the control accuracy is improved, and the system dynamic characteristics is greatly improved.

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