| タイトル | Dynamic analysis of satellites with deployable hinged appendages |
| 著者（英） | Oakes, Kevin F. |
| 著者所属（英） | Flight Mechanics and Control, Inc. |
| 発行日 | 1987-01-01 |
| 言語 | eng |
| 内容記述 | The nonlinear equations of motion determining the planar dynamical behavior of an orbiting satellite deploying both one and two rigid appendages have been formulated using Lagrange's equations. The analysis accounts for large angle rotations, Coriolis effects, and the gravitational gradient, and the resulting coupled governing equations are integrated numerically. The analysis is applied to the Space Shuttle based deployment of rigid truss-like members, and results show that spacecraft inertia parameters, appendage mass and length, deployment velocity, and initial conditions all influence the system response. It is found that the resulting librational movement is related to the size of the deployment payload, and that gravitational forces lead to vehicle stabilization. |
| NASA分類 | SPACECRAFT DESIGN, TESTING AND PERFORMANCE |
| レポートNO | 87A22364
AIAA PAPER 87-0020 |
| 権利 | Copyright |
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