QUALITATIVE BEHAVIOR OF EIGENFREQUENCIES FOR FREE VIBRATION OF AEROSPACE VEHICLE APPENDAGES | ||||
| The International Conference on Applied Mechanics and Mechanical Engineering | ||||
| Article 1, Volume 1, 1st Conference on Applied Mechanical Engineering., May 1984, Page 1-10 PDF (2.5 MB) | ||||
| Document Type: Original Article | ||||
| DOI: 10.21608/amme.1984.48575 | ||||
 View on SCiNiTO | ||||
| Authors | ||||
| A. MAHER1; A. L. SCHLACK2 | ||||
| 1Chairman Department of Mechanics and Elasticity, Military Technical College, Cairo, Egypt. | ||||
| 2Professor of Engineering Mechanics. University of Wisconsin-Madison-U.S.A. | ||||
| Abstract | ||||
| In this work, the changes in eigenfrequencies of flexible appendages with • :various mass ratios of space vehicles due to the allowance of a rigid body. motion are studied. These changes are governed by the difference eigen-value problem [2] which is formulated in terms of the generated effective :mass and stiffness matrices. The computation techniques for calculating . • the upper and lower bounds of the dominant eigenfrequencies are performed : by the utilization of the bound formula approach [1] . An example of the transverse vibration analysis of the fuslage-wing combination with diff- erent mass ratios in different zones of vibratory motion is solved . A : 'comparison between the computed calculations and previously published re-sults [0] is presented | ||||
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