Attitude Control Considering Variable Input Saturation Limit for a Spacecraft Equipped with Flywheels
نویسندگان
چکیده
منابع مشابه
Fault-Tolerant Attitude Control for Flexible Spacecraft with Input Saturation
Fault-tolerant constrained attitude controllers are proposed for flexible spacecraft in the presence of input saturation and actuator fault, as well as model uncertainty and external disturbance. Two input saturations, that is amplitude saturation and, amplitude and rate saturation are considered and simple and effective compensators are designed to deal with the effect of input saturation. Two...
متن کاملIntegrated Power and Attitude Control for a Spacecraft with Flywheels and Control Moment Gyroscopes
A law is designed for simultaneous control of the orientation of an Earth-pointing spacecraft, the energy stored by counter-rotating flywheels, and the angular momentum of the flywheels and control moment gyroscopes used together as an integrated set of actuators for attitude control. General , nonlinear equations of motion are presented in vector-dyadic form, and used to obtain approximate exp...
متن کاملSpacecraft Nonlinear Attitude Control with Bounded Control Input
Copyright and moral rights for this thesis are retained by the author A copy can be downloaded for personal non-commercial research or study, without prior permission or charge This thesis cannot be reproduced or quoted extensively from without first obtaining permission in writing from the Author The content must not be changed in any way or sold commercially in any format or medium without th...
متن کاملRobust Attitude Coordination Control of Formation Flying Spacecraft under Control Input Saturation
The attitude coordination control problem for formation flying spacecraft associated with time-varying reference attitude tracking subject to control input saturation is investigated in this paper. According to different cases, three kinds of continuous and bounded coordination controllers are proposed. With the use of hyperbolic tangent functions, a fundamental controller is presented for an i...
متن کاملSpacecraft Fault Tolerant Attitude Control Design under Control Input Saturation and Uncertainty in Fault Information
In this paper, a continuous stable tracking control algorithm is proposed for spacecraft in the presence of unknown actuator failure, control input saturation and external disturbances. The design method is based on variable structure control and has the following properties: 1) fast and accurate response in the presence of bounded disturbances; 2) robust to the partial loss of actuator effecti...
متن کاملذخیره در منابع من
با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید
ژورنال
عنوان ژورنال: Chinese Journal of Aeronautics
سال: 2012
ISSN: 1000-9361
DOI: 10.1016/s1000-9361(11)60400-7