Optimal Control of Maneuver-Induced Vibration in Flexible AERO and Space Vehicles

摘要

Forces applied to a large, flexible aero or space vehicle in order to change the vehicle's attitude or position will in general also excite undesirable vibration. The added cost in terms of time, complexity of thrust pattern and fuel or total control effort required to effect a given maneuver when the unwanted vibration is suppressed is studied in this paper. Techniques for interpreting optimal solutions to these problems are given based on the use of multiple phase plane plots. (Author)