Adaptive preload controller design and analysis for electrostatic suspension system

2021 ◽  
pp. 2140012
Author(s):  
Yukun Wang ◽  
Zhi Wang ◽  
Keyword(s):  
Control System ◽  
Control Method ◽  
Controller Design ◽  
Inertial Sensor ◽  
Stability Margin ◽  
Adaptive Controller ◽  
Satellite Platform ◽  
Solid Foundation ◽  
The Stability ◽  
Control System Model

The electrostatic suspension control system (ESCS) is the core component of the inertial sensor in space gravitational wave detection. To adapt to the changes in orbit environment and satellite platform vibration, the test mass stable is kept in the center of the electrode cage, the ESCS requires high-precision parameters calibration and high-stability verification of the control system. This paper studied the ESCS method, an adaptive controller with variable preload was proposed, and the stability conditions of the control system are given to provide a theoretical basis for the design of the controller. The structure and working principle of the system were also introduced. The electrostatic control system model was derived, and the performance of adaptive preload controller was analyzed. Finally, a simulation was conducted under different disturbance conditions. The results show that the control method proposed in this paper can achieve stable control in difference disturbance, and the preload voltage will change with the conditions. Compared with the traditional fixed preload method, we can see that our method has significantly improved the stability margin and the control quality during the process of dynamic response. This paper provides a solid foundation for the future exploration of space gravitational waves in China and clears the optimization direction for the next step.

scholarly journals An adaptive dynamic inversion control method based on improved piecewise constant for flight control system

2021 ◽  
Vol 39 (1) ◽  
pp. 167-174
Author(s):  
Yu Li ◽  
Xiaoxiong Liu ◽  
Qizhi He ◽  
Weiguo Zhang ◽  
Tianpeng Huang
Keyword(s):  
Control System ◽  
Flight Control ◽  
Present Method ◽  
Control Method ◽  
Controller Design ◽  
Dynamic Performance ◽  
Sudden Change ◽  
Dynamic Inversion ◽  
Piecewise Constant ◽  
The Stability

To overcome the lack of robustness of the nonlinear dynamic inversion (NDI) control, a simple and practical adaptive NDI control method based on an improved piecewise constant is proposed in this paper to enhance its robustness to disturbances and improve the accuracy of response tracking. Firstly, reasonable assumptions and analyses are made for the system with the influence of disturbance. Secondly, an improved piecewise constant adaptive NDI control method suitable for general flight control systems is proposed. The stability of the control system with disturbance and the error convergence range of the improved piecewise constant adaptive control are proved and analyzed theoretically. Finally, taking into account the fighter actual control requirements, the angular rates control strategy is given, and the proposed method is applied to the angular rates flight controller design. Matlab simulations are carried out under the disturbance of the actuator failure and the sudden change of the center of gravity, and the robustness and dynamic performance of the controller designed based on the present method is compared and verified. The results illustrate that our present method has stronger robustness and higher control accuracy.

A finite-time H-infinite adaptive fault-tolerant controller considering time delay for flutter suppression of airfoil flutter

2019 ◽  
Vol 234 (2) ◽  
pp. 293-307
Author(s):  
Gao Ming-Zhou ◽  
Chen Xin-Yi ◽  
Han Rong ◽  
Yao Jian-Yong
Keyword(s):  
Finite Time ◽  
Control Method ◽  
Controller Design ◽  
Fault Tolerant ◽  
Linear Matrix ◽  
Control Methods ◽  
Actuator Faults ◽  
Control Delay ◽  
Modeling Uncertainties ◽  
The Stability

To suppress airfoil flutter, a lot of control methods have been proposed, such as classical control methods and optimal control methods. However, these methods did not consider the influence of actuator faults and control delay. This paper proposes a new finite-time H∞ adaptive fault-tolerant flutter controller by radial basis function neural network technology and adaptive fault-tolerant control method, taking into account actuator faults, control delay, modeling uncertainties, and external disturbances. The theoretic section of this paper is about airfoil flutter dynamic modeling and adaptive fault-tolerant controller design. Lyapunov function and linear matrix inequality are employed to prove the stability of the proposed control method of this paper. The numeral simulation section further proves the effectiveness and robustness of the proposed control algorithm of this paper.

A New Iterative Identification and Control Method of Closed-Loop Power System Based on Ambient Signals

2015 ◽  
Vol 798 ◽  
pp. 261-265
Author(s):  
Miao Yu ◽  
Chao Lu
Keyword(s):  
Power System ◽  
Closed Loop ◽  
Control Method ◽  
Controller Design ◽  
Design Method ◽  
Stability Margin ◽  
System Stability ◽  
Iterative Identification ◽  
Effective Performance ◽  
And Control

Identification and control are important problems of power system based on ambient signals. In order to avoid the model error influence of the controller design, a new iterative identification and control method is proposed in this paper. This method can solve model set and controller design of closed-loop power system. First, an uncertain model of power system is established. Then, according to the stability margin of power system, stability theorem is put forward. And then controller design method and the whole algorithm procedure are given. Simulation results show the effective performance of the proposed method based on the four-machine-two-region system.

Design and Implementation of Large-Scale Temperature Stability Control System

2014 ◽  
Vol 644-650 ◽  
pp. 313-316
Author(s):  
Wen Lai Liu
Keyword(s):  
Control System ◽  
System Design ◽  
Large Scale ◽  
Control Method ◽  
Temperature Stability ◽  
Stability Control ◽  
Control System Design ◽  
Scale Temperature ◽  
Stability Control System ◽  
The Stability

large-scale temperature stability control method is studied in this paper. In the process of large-scale temperature control, the stability of control is a very important indicator. To this end, this paper proposes a large-scale temperature stability control algorithm based on hierarchical control method. Balance equation of large-scale temperature stability control is created for the effective transmission of control data. According to the constant control theory, large-scale temperature stability control system design is achieved. Experimental results show that the proposed algorithm for large-scale temperature stability control system design, can greatly improve the stability of control, and get the satisfactory results.

A Fuzzy Adaptive Force Controller Design of Robotic Manipulators for Pick-and-Placing Thin Brittle Materials

2013 ◽  
Vol 303-306 ◽  
pp. 1666-1673
Author(s):  
Chong Dong He ◽  
Hai Chen Qin ◽  
Jian Kui Chen
Keyword(s):  
Control Method ◽  
Controller Design ◽  
Control Strategies ◽  
Pid Algorithm ◽  
Feed Forward Control ◽  
Pick And Place ◽  
Position Controller ◽  
Motion Characteristics ◽  
Control System Model ◽  
Fuzzy Adaptive

For the pick-and-place operations of GDL, this paper presents and obtains the control system model using system identification method, and analyzes three distinct stages for the motion characteristics in pick-and-place operations. To satisfy the stick requirements for contact force control, a force controller based on fuzzy adaptive PID algorithm and a position controller based on feed-forward control are presented and designed. Simulations are carried out to verify the feasibility and effectiveness of the proposed control method. The above control strategies and methods are applied to pick up and place GDL. They can also be extended to the pick-and-place operations of the chips and other filed, which has broad application prospects.

PID Control Based Missile Sub-Channel Simulation

2012 ◽  
Vol 433-440 ◽  
pp. 7011-7016 ◽  
Author(s):  
Chao Bo Chen ◽  
Bing Liu ◽  
Ning He ◽  
Song Gao ◽  
Quan Pan
Keyword(s):  
Control System ◽  
Real Time ◽  
Flight Control ◽  
Pid Control ◽  
Pid Controller ◽  
Channel Model ◽  
Control Method ◽  
Flight Control System ◽  
Aerodynamic Control ◽  
The Stability

The accuracy and real-time of modern missile flight control system of traditional aerodynamic can not be satisfied. In this paper a new method is presented to improve the accuracy and real-time of missiles under this condition. First of all, a missile sub-channel model of the dynamic equations and steering gear is established, then based on the established model, using PID controller to control steering gear and three channels of missile pitch, yaw, roll respectively which is called missile sub-channel PID control method, and finally making use of MATLAB/Simulink to complete the simulation. Simulation results show that compared with traditional aerodynamic control system, this method can reduce the response time of aerodynamic missile and enhance the stability of the control system obviously.

scholarly journals L1 Adaptive for Aircraft Lateral Fault Tolerant Control with Actuator Failure

2019 ◽  
Vol 37 (5) ◽  
pp. 935-942
Author(s):  
Yan Zhou ◽  
Huiying Liu ◽  
Jing Li
Keyword(s):  
Control Method ◽  
Fault Tolerant ◽  
Adaptive Controller ◽  
Actuator Failure ◽  
Bounded Control ◽  
L1 Adaptive Control ◽  
Unmatched Uncertainties ◽  
Fault Mode ◽  
The Stability ◽  
Multiplicative Fault

When aircraft is laterally controlled, actuator failure may cause matched/unmatched uncertainties. In order to deal with the uncertainty, a fault-tolerant controller is designed by using L1 adaptive control method. An aircraft lateral model was established by considering faults and disturbances, the effects of the uncertainty and interference were counteracted by using L1 adaptive controller in order to ensure the rapid adaptation and robustness, and then the stability and transient performance of the closed-loop system were proven through Lyapunov method. In the case of multiplicative fault, additive fault and stuck fault, the uncertainties of model parameter were added to simulate simultaneously. Simulation results showed that the present control method in both single-fault mode and hybrid-failure mode could ensure the uniform bounded control signal and parameter estimation, effectively eliminates the effect of the faults and had the good fault tolerance and robustness.

LQG-Based Robustifying Flight Control System

2003 ◽  
Author(s):  
D. Griffin ◽  
A. G. Kelkar
Keyword(s):  
Control System ◽  
Flight Control ◽  
Controller Design ◽  
Second Step ◽  
Flight Control System ◽  
Robust Controller ◽  
Fighter Aircraft ◽  
Stability Robustness ◽  
Uncertainty Model ◽  
The Stability

This paper presents a robust controller design for an automatic flight control system (AFCS) for a fighter aircraft model with eight inputs and seven outputs. The controller is designed based on McFarlane-Glover robustifying technique using a simple baseline LQG design. Controllers designed purely based on traditional LQG techniques are known to have no guaranteed robustness margins. The McFarlane-Glover technique can be used to enhance the stability robustness of the baseline LQG design using a two-step design process. In the first step, an LQG controller is designed which is optimized only for performance without any consideration to robustness. In the second step, the performance optimized LQG design is rendered robust using McFarlane-Glover procedure. The robustifying procedure uses a coprime factor uncertainty model and H∞ optimization. An important advantage of this procedure is that no problem dependent uncertainty modelling or weight selection is required in the second step of the process. The robustifying procedure also yields the quantitative estimate of the robustness.

The Model-free Adaptive Composite Control Method for Permanent Magnet Linear Motor

2015 ◽  
Vol 7 (2) ◽  
pp. 30-44
Author(s):  
Rongmin Cao ◽  
Su Zhong ◽  
Shizhen Liu
Keyword(s):  
Permanent Magnet ◽  
Control Method ◽  
Controller Design ◽  
Adaptive Controller ◽  
Linear Motor ◽  
Modeling And Control ◽  
Composite Control ◽  
Model Free ◽  
Permanent Magnet Linear Motor ◽  
Force Ripple

A composite control method based on the model-free adaptive control is applied to the position or speed control of the linear motor. The model-free adaptive controller (MFAC) broke through the classical PID controller design of linear framework, is a kind of new controller, it' structure is adaptive and a kind of integration of modeling and control method. The composite control method includes an adaptive feedforward compensator which is designed to eliminate or suppress the effects of inherent force ripple for a permanent magnet linear motor (PMLM). Simulation results show that compared with PID control, the proposed composite control algorithm is more effective for the strong coupling of nonlinear system and difficult to realize stable control. And the response performance of the system is realized.

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