کد مقاله | کد نشریه | سال انتشار | مقاله انگلیسی | نسخه تمام متن |
---|---|---|---|---|
1717925 | 1520092 | 2015 | 8 صفحه PDF | دانلود رایگان |
The attitude control of a launch vehicle is a challenging task due to the dramatically varying vehicle dynamics along a flight path. The objective of this paper is to design a switching robust control strategy for launch vehicles, applied here to a notional nanosat launch vehicle. In order to control the rocket along a trajectory ascending through the Earth's atmosphere, a set of operating points at different times along the flight path are selected, the corresponding dynamics models of the rocket are obtained via linearization, and a robust H∞H∞ controller is designed for each operating point using the linear matrix inequality approach. These controllers are applied to the nonlinear plant model via a switching strategy when the rocket flies along the flight path. Both linear and nonlinear simulation results are given to show the performance of the closed-loop system.
Journal: Aerospace Science and Technology - Volume 42, April–May 2015, Pages 259–266