scholarly journals Application of MPC to Spacecraft Attitude Maneuver using RCS and/or RW

2013 ◽  
Vol 6 (1) ◽  
pp. 1-14 ◽  
Author(s):  
Takeya ASAKAWA ◽  
Takashi KIDA
Keyword(s):  
Spacecraft Attitude ◽  
Attitude Maneuver

Flexible spacecraft attitude maneuver by application of sliding mode control

2005 ◽  
Vol 57 (11) ◽  
pp. 841-850 ◽  
Author(s):  
Hyochoong Bang ◽  
Cheol-Keun Ha ◽  
Jin Hyoung Kim
Keyword(s):  
Sliding Mode Control ◽  
Sliding Mode ◽  
Flexible Spacecraft ◽  
Spacecraft Attitude ◽  
Mode Control ◽  
Attitude Maneuver

Robust Finite-Time Control for Flexible Spacecraft Attitude Maneuver

2014 ◽  
Vol 27 (1) ◽  
pp. 185-190 ◽  
Author(s):  
Shunan Wu ◽  
Gianmarco Radice ◽  
Zhaowei Sun
Keyword(s):  
Finite Time ◽  
Flexible Spacecraft ◽  
Spacecraft Attitude ◽  
Time Control ◽  
Attitude Maneuver

Envelope oriented singularity robust steering law of control moment gyros for spacecraft attitude maneuver

2018 ◽  
Vol 41 (4) ◽  
pp. 954-962 ◽  
Author(s):  
Yanning Guo ◽  
Pengyu Wang ◽  
Guangfu Ma ◽  
Liangyue Wang
Keyword(s):  
Angular Momentum ◽  
Open Loop ◽  
Spacecraft Attitude ◽  
Momentum Exchange ◽  
Control Moment ◽  
Attitude Error ◽  
Attitude Maneuver ◽  
Steering Law ◽  
The Difference ◽  
Control Moment Gyro

The problem of steering pyramid control moment gyro (CMG) cluster for fast spacecraft attitude maneuver along eigenaxis is investigated. A novel steering law is proposed to continuously attempt to reduce the difference between the current gimbal angle and the desired one corresponding to the angular momentum envelop of the CMG cluster. The proposed steering law can be decomposed into two parts: the first one is a singularity robust term to keep maneuverability and produce control torque, and the other is a null motion term to rearrange the gimbal angles toward momentum envelope. By involving this steering law, it is expected to possess both rapid angular momentum exchange and singularity avoidance ability. In addition, by introducing a new limit vector on attitude error, classical cascade-saturation control algorithm is revised to guarantee spacecraft eigenaxis rotation. Both open-loop steering law test and closed-loop attitude maneuver simulations are performed to evaluate the efficacy of the proposed methods.

scholarly journals Spacecraft attitude maneuver control using two parallel mounted 3-DOF spherical actuators

2017 ◽  
Vol 30 (1) ◽  
pp. 419-425 ◽  
Author(s):  
Guidan Li ◽  
Haike Li ◽  
Bin Li
Keyword(s):  
Spacecraft Attitude ◽  
Attitude Maneuver
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