A Variable Structure Attitude Control System Design Based on Finite Time Stability

2013 ◽  
Vol 446-447 ◽  
pp. 1141-1145
Author(s):  
Rui Min Jiang ◽  
Jun Zhou ◽  
Jian Guo Guo
Keyword(s):  
Control System ◽  
Finite Time ◽  
Attitude Control ◽  
Angular Rate ◽  
Variable Structure ◽  
Control System Design ◽  
Control Loop ◽  
Time Stability ◽  
Attitude Control System ◽  
Finite Time Stability

A variable structure attitude control system design method that guarantees the finite-time stability is proposed for hypersonic vehicle attitude control. According to the characteristics of the hypersonic vehicle longitudinal attitude model, it is considered to comprise attack angle control loop and angular rate control loop. The attack angle controller and pitch angular rate controller based on variable structure control are designed respectively which ensure the finite-time stability. The finite-time stability of the whole attitude control system has been proved .The simulation results illustrated that the proposed attitude controller has good rapidity and robustness.

Model reference adaptive attitude control for near space hypersonic vehicle with mismatched uncertainties

2018 ◽  
Vol 41 (5) ◽  
pp. 1301-1312
Author(s):  
Jianguo Guo ◽  
Tianbao Zhang ◽  
Cheng Cheng ◽  
Jun Zhou
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Angular Rate ◽  
Hypersonic Vehicle ◽  
Control Loop ◽  
Attitude Control System ◽  
Model Reference ◽  
Near Space ◽  
Mismatched Uncertainties ◽  
Model Reference Adaptive

In this paper, a new model reference adaptive attitude control based on backstepping approach is presented for near space hypersonic vehicle with mismatched uncertainties. Firstly, the attitude dynamic model of near space hypersonic vehicle is divided into two control loops, which is composed of an attitude angle control loop and an attitude angular rate control loop. Secondly, a novel model reference adaptive attitude control approach is proposed by introducing reference model to avoid the calculating expansion problem in backstepping technique. Meanwhile, the reference models for every loop are independently designed to improve the tracking performance. The stability of attitude control system is strictly proven by using Lyapunov stability theory. Finally, the simulation results demonstrate that the attitude control system by applying the proposed method has good stability, dynamic property and strong robustness in the presence of input constraints and parameters perturbation.

scholarly journals Quaternion-Based Attitude Control System Design of Single and Cooperative Spacecrafts: Boundedness of Solution Approach

2014 ◽  
Vol 2014 ◽  
pp. 1-13 ◽  
Author(s):  
Harry Septanto ◽  
Riyanto T. Bambang ◽  
Arief Syaichu-Rohman ◽  
Ridanto Eko Poetro ◽  
Adrianto Ravi Ibrahim
Keyword(s):  
Control System ◽  
System Design ◽  
Attitude Control ◽  
Equilibrium Points ◽  
External Disturbance ◽  
Control System Design ◽  
Attitude Control System ◽  
Control Effort ◽  
Solution Approach ◽  
Boundedness Of Solution

It is well known that single equilibrium orientation point in matrix rotation is represented by two equilibrium points in quaternion. This fact would imply nonefficient control effort as well as problem in guaranteeing stability of the two equilibrium points in quaternion. This paper presents a solution to design quaternion-based spacecraft attitude control system whose saturation element is in its control law such that those problems are overcome. The proposed feature of methodology is the consideration on boundedness of solution in the control system design even in the presence of unknown external disturbance. The same methodology is also used to design cooperative spacecrafts attitude control system. Through the proposed method, the most relaxed information-state topology requirement is obtained, that is, the directed graph that contains a directed spanning tree. Some numerical simulations demonstrate effectiveness of the proposed feature of methodology.

Research on Attitude Law of Mass Moment Missile Based on Mulriple Control

2011 ◽  
Vol 181-182 ◽  
pp. 919-925
Author(s):  
Peng Wu ◽  
Qi Chao Chen ◽  
Jiao Ding Ning
Keyword(s):  
Attitude Control ◽  
Variable Structure ◽  
Control System Design ◽  
Control Law ◽  
Attitude Control System ◽  
Sign Function ◽  
Structure Control ◽  
System A ◽  
Mass Moment ◽  
Simulation Results

Aimed at characteristics of mass moment of missiles in exo-atmosphere, it’s inferred that 6-DOF mathematical model based on mass moment controlling stabilities on three axes. Considering the problem of harmoniously controlling two moving masses, moving mass based non-linear theorem was used to solve a series of problems met in attitude control system design. In order to weaken the chattering of the system, a saturation function is introduced to substitute for Sign function to improve the variable structure control law so that the chattering can be depressed. The simulation results illustrate the efficiency of this method.

Analysis and Attitude Control of Spacecraft with Input Uncertainty

2011 ◽  
Vol 268-270 ◽  
pp. 2041-2047
Author(s):  
Sheng Qi Chen ◽  
Jun Zhou
Keyword(s):  
Control System ◽  
Nonlinear Equations ◽  
Attitude Control ◽  
Equations Of Motion ◽  
Variable Structure ◽  
Integral Form ◽  
Control Mode ◽  
Attitude Control System ◽  
Non Linear ◽  
Command Signals

A moving mass control of rotating spacecraft is a kind of new control mode, it differs from other control modes because it generates an angle of attack and an angle of sideslip directly from the mass motion.The nonlinear equations of motion for rotating Maneuverable Spacecraft are derived. the variable structure attitude controller is presented according to the nonlinear equations, It’s based on two-timescale separation and with two loops, faster loop and slower loop respectively. Inertial uncertainties and aerodynamic moment uncertainties are considered simultaneously, In order to track the command signals perfectly, the sliding surface is of integral form, results of the simulation shows that this kind of attitude control system is potentially practical and robust in the presence of inertial uncertainties of guided missile and uncertainties of aerodynamic moments. Compared with the common attitude control system, it has the following advantages:(1) non linear model is directly controlled,(2)it has robust. Because the non-linear factor is considered, it has the practical use for the engineering field.

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