سال انتشار: ۱۳۸۵

محل انتشار: چهاردهمین کنفرانس سالانه مهندسی مکانیک

تعداد صفحات: ۱۱

نویسنده(ها):

Elham Vakil Asadollahei – Research Assistant, Department of Mechanical Engineering, Amirkabir Uuniversity of Technology , Tehran, Iran
Mansour Kabganian – Associate Prof, Department of Mechanical Engineering, Amirkabir Uuniversity of Technology , Tehran, Iran

چکیده:

A criterion for determining degree of stability (D.O.S) of a flexible spacecraft during slew maneuver is presented in this paper. Hybrid differential equations governing the flexible spacecraft motion are derived via the generalized Lagrange’s equations, using Euler- Bernoulli beam theory for flexible parts bending in one direction. Spacecraft stability is proved via Lyapunov direct method. Degree of stability of spacecraft with PD controller is obtained analytically, based on a new criterion, determining the rate of the energy decreasing during and after the control action. Then, the assumed mode method is used to spatially discretizing equations to finite dimensional linear model. The behavior of the spacecraft is studied with computer simulation and analytical results are verified.