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A New Stability Criterion for Attitude Dynamics of Flexible Spacecrafts

عنوان مقاله: A New Stability Criterion for Attitude Dynamics of Flexible Spacecrafts
شناسه ملی مقاله: ISME14_600
منتشر شده در چهاردهمین کنفرانس سالانه مهندسی مکانیک در سال 1385
مشخصات نویسندگان مقاله:

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

خلاصه مقاله:
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.

کلمات کلیدی:
Stability, Degree of Stability, Attitude Dynamics, Spacecraf

صفحه اختصاصی مقاله و دریافت فایل کامل: https://civilica.com/doc/28032/