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.

Fuzzy Adaptive Variable Structure Active Attitude Control of Flexible Spacecraft

2010 ◽  
Vol 44-47 ◽  
pp. 2070-2074
Author(s):  
Fa Yi Qu ◽  
Liang Kuan Zhu ◽  
Wen Long Song
Keyword(s):  
Attitude Control ◽  
Design Method ◽  
Variable Structure ◽  
Attitude Motion ◽  
Control System Design ◽  
Control Law ◽  
Control Methods ◽  
Fuzzy Methods ◽  
Rate Feedback ◽  
Fuzzy Adaptive

This paper presents a novel control system design method for the three-axis-rotational tracking and vibration stabilization of a spacecraft with flexible appendages. Based on the sliding control theory, a robust attitude control law is derived to control the attitude motion of spacecraft. For actively suppressing the induced vibration, both fuzzy methods and strain rate feedback (SRF) control methods are presented. Numerical simulations are performed to show the feasibility and effeteness of the proposed methods.

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.

scholarly journals Output Feedback Variable Structure Control Design for Uncertain Nonlinear Lipschitz Systems

2015 ◽  
Vol 2015 ◽  
pp. 1-6 ◽  
Author(s):  
Jeang-Lin Chang ◽  
Tsui-Chou Wu
Keyword(s):  
Output Feedback ◽  
Control Design ◽  
Variable Structure Control ◽  
Variable Structure ◽  
Control Law ◽  
Sufficient Condition ◽  
Structure Control ◽  
Control Scheme ◽  
Simulation Results ◽  
Lipschitz Systems

This paper develops a full-order compensator-based output feedback variable structure control law for uncertain nonlinear Lipschitz systems having matched perturbations. Given that the sufficient condition is satisfied, the developed control scheme, with the observer-like technique incorporated into the design of the compensator, can achieve global exponential stabilization. An illustrative example is provided with simulation results to show the effectiveness of the proposed method.

CONTROLLING THE UNCERTAIN MULTI-SCROLL CRITICAL CHAOTIC SYSTEM WITH INPUT NONLINEAR USING SLIDING MODE CONTROL

2009 ◽  
Vol 23 (16) ◽  
pp. 2021-2034 ◽  
Author(s):  
XINGYUAN WANG ◽  
DA LIN ◽  
ZHANJIE WANG
Keyword(s):  
Chaotic System ◽  
Sliding Mode ◽  
Equilibrium Points ◽  
Dead Zone ◽  
Variable Structure ◽  
Sliding Mode Controller ◽  
Global Stabilization ◽  
Structure Control ◽  
Control Scheme ◽  
Simulation Results

In this paper, control of the uncertain multi-scroll critical chaotic system is studied. According to variable structure control theory, we design the sliding mode controller of the uncertain multi-scroll critical chaotic system, which contains sector nonlinearity and dead zone inputs. For an arbitrarily given equilibrium point of the uncertain multi-scroll chaotic system, we achieve global stabilization for the equilibrium points. Particularly, a class of proportional integral (PI) switching surface is introduced for determining the convergence rate. Furthermore, the proposed control scheme can be extended to complex multi-scroll networks. Finally, simulation results are presented to demonstrate the effectiveness of the proposed control scheme.

Integrated Aircraft Modeling Research for Accurate Flight Control System Design

2013 ◽  
Vol 791-793 ◽  
pp. 658-662
Author(s):  
Chao Zhang ◽  
Yi Nan Liu ◽  
Jian Hui Xu
Keyword(s):  
Control System ◽  
System Design ◽  
Flight Control ◽  
Time Delays ◽  
Flight Dynamics ◽  
Control System Design ◽  
Control Law ◽  
Flight Control System ◽  
Aircraft Model ◽  
Simulation Results

In order to realize accurate flight control system design and simulation, an integrated scheme of aircraft model which consists of flight dynamics, fly-by-wire (FBW) platform and flight environment is proposed. Flight environment includes gravity, wind, and atmosphere. And the actuator and sensors such as gyroscope and accelerometer models are considered in the FBW platform. All parts of the integrated model are closely connected and interacted with each other. Simulation results confirm the effectiveness of the integrated aircraft model and also indicate that the (Flight Control Law) FCL must be designed with robustness to sensor noise and time delays with the FBW platform in addition to the required robustness to model uncertainty in flight dynamics.

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