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Identification of structural parameters from helicopter dynamic test data
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Flannelly, W. G. Giansante, N. |
| Copyright Year | 1974 |
| Description | A method is presented for obtaining the mass, stiffness, and damping parameters of a linear mathematical model, having fewer degrees of freedom than the structure it represents, directly from dynamic response measurements on the actual helicopter without a priori knowledge of the physical characteristics of the fuselage. The only input information required in the formulation is the approximate natural frequency of each mode and mobility data measured proximate to these frequencies with sinusoidal force excitation applied at only one point on the vehicle. The practicality and numerical soundness of the theoretical development was demonstrated through a computer simulation of an experimental program. |
| File Size | 514414 |
| Page Count | 10 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19740026400 |
| Archival Resource Key | ark:/13960/t51g5g75j |
| Language | English |
| Publisher Date | 1974-01-01 |
| Access Restriction | Open |
| Subject Keyword | Structural Mechanics Damping Dynamic Response Dynamic Structural Analysis Resonant Frequencies Helicopters Fuselages Mathematical Models Computerized Simulation Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
