Design of Variable Structure Attitude Control System for Unmanned Underwater Vehicle

Author(s):  
Guanshan Liu ◽  
Jing Fang ◽  
Qiaogao Huang ◽  
Suhe Huang
Author(s):  
Norimitsu Sakagami ◽  
Mizuho Shibata ◽  
Sadao Kawamura ◽  
Toshifumi Inoue ◽  
Hiroyuki Onishi ◽  
...  

2021 ◽  
Vol 54 (2) ◽  
pp. 106-112
Author(s):  
GAVRILINA EKATERINA A. ◽  
◽  
VELTISHEV VADIM V. ◽  

Traditionally, unmanned underwater vehicles are operated at low angles of inclination (pitch and roll). However, there are tasks that require high maneuverability and controllability of the underwater vehicle in the entire range of orientation angles. At the same time, traditional control systems use the Euler angles and have limitations associated with the degeneration of the kinematic equations at a picth angle of ± 90 °, the problem of the non-uniqueness of the Euler angles, and the deterioration of the system performance at large inclinations of the vehicle. Thus, the question of developing a synthesis method for a control system for highly maneuverable unmanned underwater vehicles arises. The paper provides a review and comparative analysis of existing approaches to attitude control, on the basis of which an approach using quaternions is chosen. The law of attitude control based on quaternions was approved during field tests on a hybrid unmanned underwater vehicle "Iznos", developed at Bauman Moscow State Technical University. The results obtained during the tests are given in the article. The quaternion-based approach has better performance in comparison with the traditional control system. In addition, control system based on quaternion approach has a simple structure and can be used to increase the maneuverability of unmanned underwater vehicles with average requirements for positioning accuracy.


2011 ◽  
Vol 268-270 ◽  
pp. 2041-2047
Author(s):  
Sheng Qi Chen ◽  
Jun Zhou

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.


2013 ◽  
Vol 446-447 ◽  
pp. 1141-1145
Author(s):  
Rui Min Jiang ◽  
Jun Zhou ◽  
Jian Guo Guo

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.


Author(s):  
Shinya FUJITA ◽  
Yuji SATO ◽  
Toshinori KUWAHARA ◽  
Yuji SAKAMOTO ◽  
Yoshihiko SHIBUYA ◽  
...  

1980 ◽  
Author(s):  
F. FLOYD ◽  
C. MUCH ◽  
N. SMITH ◽  
J. VERNAU ◽  
J. WOODS

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