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.

Vibration suppression and attitude control for the formation flight of flexible satellites by optimally tuned on-off state-dependent Riccati equation approach

2020 ◽  
Vol 42 (15) ◽  
pp. 2984-3001
Author(s):  
Hossein Rouzegar ◽  
Alireza Khosravi ◽  
Pouria Sarhadi
Keyword(s):  
Riccati Equation ◽  
Attitude Control ◽  
Vibration Suppression ◽  
Pso Algorithm ◽  
Formation Flight ◽  
Equation Approach ◽  
Coordination Control ◽  
Suggested Approach ◽  
State Dependent ◽  
Highly Nonlinear

In this paper, vibration suppression and attitude control for the formation flight of flexible satellites using optimally tuned on-off SDRE (state-dependent Riccati equation) approach is discussed. A formation consisting of flexible satellites has highly nonlinear dynamics and the corresponding satellites are subject to vibrations as well as uncertainties due to the practical conditions. Vibrations that are mainly caused by flexible modes of the satellites disorganize the coordination and hinder the formation stability as well as decreasing its performance and lifetime. Hence, flexibility should be considered in formation model and the coordination control needs to address such challenges. Owing to capabilities of SDRE approach for nonlinear systems, it is used as the coordination control. Satellites are assumed to be equipped with thrusters as their actuators which requires the control to be applied as on-off pulses. To this end, an algorithm is suggested to efficiently convert SDRE control into on-off pulses. For optimal tuning of the controller, the particle swarm optimization (PSO) algorithm is employed. Stability of the system has also been analyzed via a Lyapunov-based approach utilizing the region of attraction concept. The proposed on-off SDRE approach has shown to effectively suppress the vibrations in the presence of uncertainties leading to the accurate coordination of the whole formation while consuming less energy. Simulation results show the capability, efficiency, robustness and stability of the suggested approach.

The Optimal Attitude Controller Design and Simulation of Three-Axis Dual Rotor Helicopter

2011 ◽  
Vol 128-129 ◽  
pp. 1265-1268 ◽  
Author(s):  
Cai Zheng Xu ◽  
Ting Zhang
Keyword(s):  
Optimal Control ◽  
Attitude Control ◽  
Control Algorithm ◽  
Controller Design ◽  
Dead Zone ◽  
Control Law ◽  
Attitude Control System ◽  
Environment Simulation ◽  
Attitude Controller ◽  
Time And Energy

In this paper, the model of three-axis dual rotor helicopter is built, through a new motor control algorithm of real-time grouping, the decoupling and independent control of pitch, yaw and roll channels is realized; then the “dead zone” is introduced to design the attitude controller on the basis of the optimal control law which minimize the weighted sum of response time and energy consumption, to achieve optimal control of the attitude of the helicopter; finally, the simulation model of the attitude control system is established in the MATLAB/Simulink environment. Simulation results show the feasibility of the optimal attitude controller design.

Position and Attitude Control of Deep-Space Spacecraft Formation Flying Via Virtual Structure and θ-D Technique

2007 ◽  
Vol 129 (5) ◽  
pp. 689-698 ◽  
Author(s):  
Ming Xin ◽  
S. N. Balakrishnan ◽  
H. J. Pernicka
Keyword(s):  
Attitude Control ◽  
Formation Flying ◽  
Libration Point ◽  
Suboptimal Control ◽  
Control Technique ◽  
Deep Space ◽  
Control Approach ◽  
Spacecraft Formation ◽  
Spacecraft Formation Flying ◽  
Highly Nonlinear

Control of deep-space spacecraft formation flying is investigated in this paper using the virtual structure approach and the θ-D suboptimal control technique. The circular restricted three-body problem with the Sun and the Earth as the two primaries is utilized as a framework for study and a two-satellite formation flying scheme is considered. The virtual structure is stationkept in a nominal orbit around the L2 libration point. A maneuver mode of formation flying is then considered. Each spacecraft is required to maneuver to a new position and the formation line of sight is required to rotate to a desired orientation to acquire new science targets. During the rotation, the formation needs to be maintained and each spacecraft’s attitude must align with the rotating formation orientation. The basic strategy is based on a “virtual structure” topology. A nonlinear model is developed that describes the relative formation dynamics. This highly nonlinear position and attitude control problem is solved by employing a recently developed nonlinear control approach, called the θ-D technique. This method is based on an approximate solution to the Hamilton-Jacobi-Bellman equation and yields a closed-form suboptimal feedback solution. The controller is designed such that the relative position error of the formation is maintained within 1cm accuracy.

Neural Networks Attitude Decoupling Controller Design of Dual-Ducted SUAV Based on ADRC System

2014 ◽  
Vol 915-916 ◽  
pp. 411-417
Author(s):  
Tong Yue Gao ◽  
Dong Dong Wang ◽  
Tao Fei ◽  
Hai Lang Ge
Keyword(s):  
Neural Network ◽  
Strong Coupling ◽  
Attitude Control ◽  
Control Algorithm ◽  
Controller Design ◽  
Learning Ability ◽  
Effective Control ◽  
Operating Characteristics ◽  
Learning Condition ◽  
Neural Network Algorithm

This dual-ducted SUAV is a nonlinear and strong coupling of multiple-input and multiple-output system, and particularly between the pitch and roll channels channel coupling is strong, in order to implement effective control, it must be decoupled. The traditional methods are difficult to achieve effective control of the strong coupling of multivariable systems. Neural network which has a strong learning ability, is able to learn from the sample and can adapt to changing learning condition. Thus, the neural network can be used to simulate the learning process of operator, and operating characteristics information of objects can be excavated from the measured data, and accordingly change the parameters of the controller and decoupling network. This paper presents a attitude control algorithm of the dual-ducted SUAV which combine ADRC algorithms with neural network decoupling control algorithm, to design a SUAV decoupling controller. The simulation results showed that the attitude control channels between the pitch and roll were independently of each other, indicating a good solution to decouple the coupling between the pitch and roll channels based on neural network algorithm.

Design of Auto-Stabilization Control Technique for a Quadrotor System

2013 ◽  
Vol 313-314 ◽  
pp. 559-564
Author(s):  
Norafizah Abas ◽  
Rini Akmeliawati ◽  
Zulkiflie Ibrahim ◽  
M. Zamzuri A. Rashid ◽  
N. Hazahsha Samsudin
Keyword(s):  
Pid Controller ◽  
Feedback Linearization ◽  
Control Algorithm ◽  
Equations Of Motion ◽  
Control Technique ◽  
Proportional Integral Derivative ◽  
Stabilization Control ◽  
Highly Nonlinear ◽  
Quadrotor System ◽  
Manual Mode

This paper presents the design of auto-stabilization control technique for a quadrotor system. Aquadrotor is a highly nonlinear and has to be stabilized by a suitable control technique. Therefore, the main focus of this research is to design an appropriate control algorithm that able to auto-stabilize the quadrotor at hover. The dynamic modeling of the quadrotor is described by sets of equations of motion that are derived based on the Newton-Euler formalism with the implementation of UKF for parameter identification and state estimation. The control strategy adopted includes feedback linearization coupled with Proportional-Derivative (PD) controller for the translational subsystem and backstepping based Proportional-Integral-Derivative (PID) controller for the rotational subsystem. It is developed in MATLAB/Simulink platform and is validated via real-time implementation. Both controllers give satisfactory simulation results, where acceptable peak of overshoot and small steady state errors are achieved. Experimentally, the throttle is controlled in manual mode while attitude angles are stabilized automatically. The simulation and experimental results show that the proposed controller is able to effectively stabillized the quadrotor.

A New Robust Controller for Flight Control System of Hypersonic Flying Vehicle

2012 ◽  
Vol 562-564 ◽  
pp. 1682-1688 ◽  
Author(s):  
Ren Zhang ◽  
Jian Fang Fan ◽  
Jing Jing Li
Keyword(s):  
Flight Control ◽  
Attitude Control ◽  
Controller Design ◽  
Design Method ◽  
Control Technique ◽  
Robust Controller ◽  
Robust Control Design ◽  
Nonlinear Extended State Observer ◽  
The Stability ◽  
Dynamic Inverse

In this paper, a new robust controller design scheme integrating a nominal controller and a compensator is discussed. The nominal controller is designed for good performance of nominal system using nonlinear dynamic inverse control technique. The compensating controller can be seen as a standalone loop added to the system to compensate the effects of uncertainties guaranteeing the stability of the system. A nonlinear extended state observer-based compensator is proposed. The stability of the whole closed-loop system is analyzed. Application of the new robust control design method to attitude control of hypersonic flying vehicle is demonstrated with a 6-DOF simulation example.

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.

The Use of Damping Based Semi-Active Control Algorithms in the Mechanical Smart-Spring System

2017 ◽  
Vol 140 (2) ◽  
Author(s):  
Wander Gustavo Rocha Vieira ◽  
Fred Nitzsche ◽  
Carlos De Marqui
Keyword(s):  
Active Control ◽  
Control Algorithm ◽  
Control Strategies ◽  
Vibration Reduction ◽  
Flow Analysis ◽  
Coupled Systems ◽  
Control Technique ◽  
Control Algorithms ◽  
Control Techniques ◽  
Spring Mechanism

In recent decades, semi-active control strategies have been investigated for vibration reduction. In general, these techniques provide enhanced control performance when compared to traditional passive techniques and lower energy consumption if compared to active control techniques. In semi-active concepts, vibration attenuation is achieved by modulating inertial, stiffness, or damping properties of a dynamic system. The smart spring is a mechanical device originally employed for the effective modulation of its stiffness through the use of semi-active control strategies. This device has been successfully tested to damp aeroelastic oscillations of fixed and rotary wings. In this paper, the modeling of the smart spring mechanism is presented and two semi-active control algorithms are employed to promote vibration reduction through enhanced damping effects. The first control technique is the smart-spring resetting (SSR), which resembles resetting control techniques developed for vibration reduction of civil structures as well as the piezoelectric synchronized switch damping on short (SSDS) technique. The second control algorithm is referred to as the smart-spring inversion (SSI), which presents some similarities with the synchronized switch damping (SSD) on inductor technique previously presented in the literature of electromechanically coupled systems. The effects of the SSR and SSI control algorithms on the free and forced responses of the smart-spring are investigated in time and frequency domains. An energy flow analysis is also presented in order to explain the enhanced damping behavior when the SSI control algorithm is employed.

scholarly journals Fuzzy Stabilization for Nonlinear Discrete Ship Steering Stochastic Systems Subject to State Variance and Passivity Constraints

2014 ◽  
Vol 2014 ◽  
pp. 1-12 ◽  
Author(s):  
Wen-Jer Chang ◽  
Bo-Jyun Huang ◽  
Po-Hsun Chen
Keyword(s):  
Linear Matrix Inequality ◽  
Discrete Time ◽  
Stochastic Systems ◽  
Fuzzy Controller ◽  
Controller Design ◽  
Sufficient Conditions ◽  
Control Technique ◽  
Linear Matrix ◽  
Matrix Inequality ◽  
Ship Steering

For nonlinear discrete-time stochastic systems, a fuzzy controller design methodology is developed in this paper subject to state variance constraint and passivity constraint. According to fuzzy model based control technique, the nonlinear discrete-time stochastic systems considered in this paper are represented by the discrete-time Takagi-Sugeno fuzzy models with multiplicative noise. Employing Lyapunov stability theory, upper bound covariance control theory, and passivity theory, some sufficient conditions are derived to find parallel distributed compensation based fuzzy controllers. In order to solve these sufficient conditions, an iterative linear matrix inequality algorithm is applied based on the linear matrix inequality technique. Finally, the fuzzy stabilization problem for nonlinear discrete ship steering stochastic systems is investigated in the numerical example to illustrate the feasibility and validity of proposed fuzzy controller design method.

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