Time-optimal slewing of flexible spacecraft
نویسندگان
چکیده
منابع مشابه
Robust Optimal Control of Flexible Spacecraft During Slewing Maneuvers
In this paper, slewing maneuver of a flexible spacecraft with large angle of rotation is considered and assuming structural frequency uncertainties a robust minimum-time optimal control law is developed. Considering typical bang-bang control commands with multiple symmetrical switches, a parameter optimization procedure is introduced to find the control forces/torques. The constrained minimizat...
متن کاملNear-Minimum Time Optimal Control of Flexible Spacecraft during Slewing Maneuver
The rapid growth of space utilization requires extensive construction, and maintenance of space structures and satellites in orbit. This will, in turn, substantiate application of robotic systems in space. In this paper, a near-minimum-time optimal control law is developed for a rigid space platform with flexible links during an orientating maneuver with large angle of rotation. The time opti...
متن کاملNear-Minimum Time Optimal Control of Flexible Spacecraft during Slewing Maneuver
The rapid growth of space utilization requires extensive construction, and maintenance of space structures and satellites in orbit. 
This will, in turn, substantiate application of robotic systems in space. In this paper, a near-minimum-time optimal control law is developed for a rigid space platform with flexible links during an orientating maneuver with large angle of rotation. The time op...
متن کاملCOMPARISON BETWEEN MINIMUM AND NEAR MINIMUM TIME OPTIMAL CONTROL OF A FLEXIBLE SLEWING SPACECRAFT
In this paper, a minimum and near-minimum time optimal control laws are developed and compared for a rigid space platform with flexible links during an orientating maneuver with large angle of rotation. The control commands are considered as typical bang-bang with multiple symmetrical switches, the time optimal control solution for the rigid-body mode is obtained as a bang-bang function and app...
متن کاملTime-optimal Rest-to-rest Slewing of Multi-mode Flexible Spacecraft Using Zvd Robustness Constraints
A procedure for obtaining robust time-optimal command profiles for multi-mode flexible spacecraft is presented. The command profiles are required to move a spacecraft from rest-to-rest with zero residual vibration. Furthermore, the commands are subject to a robustness constraint in an attempt to keep the residual vibration at a low level in the presence of modeling errors. The robustness constr...
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ژورنال
عنوان ژورنال: Journal of Guidance, Control, and Dynamics
سال: 1992
ISSN: 0731-5090,1533-3884
DOI: 10.2514/3.20844