سال انتشار: ۱۳۸۶

محل انتشار: هفتمین همایش انجمن هوافضای ایران

تعداد صفحات: ۶

نویسنده(ها):

J. Roshanian – Department of Aerospace Engineering, KNT University of Technology, Tehran, Iran, Aerospace Research Institute, Tehran, Iran
B. Ebrahimi – Department of Mechanical Engineering, Amirkabir University of Technology, Tehran, Iran, Aerospace Research Institute, Tehran, Iran
M. Esfahanian – Department of Aerospace Engineering, KNT University of Technology, Tehran, Iran
M. Bahrami – Department of Mechanical Engineering, Amirkabir University of Technology, Tehran, Iran, Aerospace Research Institute, Tehran, Iran

چکیده:

Tracking of guidance commands with unmatched disturbances is considered for a linear time-varying aerospace launch vehicle during the atmospheric flight in sliding mode control theory. Dynamics of aerospace launch vehicle is rendered into a regular form and a practical application of dynamic sliding manifold is employed to circumvent restrictive performance of conventional sliding manifolds in accommodating unmatched perturbations. Results of simulations are presented to demonstrate the performance, robustness, and stability of the considered autopilot.