A New Stability Criterion for Attitude Dynamics of Flexible Spacecrafts
Publish place: 14th Annual Conference of Mechanical Engineering
Publish Year: 1385
نوع سند: مقاله کنفرانسی
زبان: English
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شناسه ملی سند علمی:
ISME14_600
تاریخ نمایه سازی: 1 فروردین 1386
Abstract:
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.
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Authors
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
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