Title :
Trajectory optimization for satellite fast attitude maneuver based on collocation method
Author :
Jiang Bingqiang ; Ye Dong ; Sun Zhaowei
Author_Institution :
Sch. of Astronaut., Harbin Inst. of Technol., Harbin, China
Abstract :
Aircraft trajectory optimization is the key to overall aircraft design, it plays an important role in modern aircraft design. In this paper, agile satellite attitude maneuver problem, is studied based on Time-Optimal and direct collocation method to get the agile satellite maneuvering trajectory optimization and simulation verification. The results is bang-bang mode, and the size of the deviation affect the accuracy of the result, the control torque change times will depends on the manuvering.
Keywords :
aerospace simulation; aircraft control; attitude control; trajectory optimisation (aerospace); agile satellite attitude maneuver problem; aircraft design; aircraft trajectory optimization; bang-bang mode; control torque; direct collocation method; satellite simulation verification; time-optimal method; Angular velocity; Attitude control; Optimal control; Polynomials; Satellites; Torque; Agile satellite; Direct collocation method; Optimal-time Attitude maneuver;
Conference_Titel :
Mechatronics and Control (ICMC), 2014 International Conference on
Print_ISBN :
978-1-4799-2537-7
DOI :
10.1109/ICMC.2014.7231761
