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Effects of vibration on inertial wind-tunnel model attitude measurement devices
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Kilgore, W. Allen Young Jr., Clarence P. Balakrishna, S. Buehrle, Ralph D. |
| Copyright Year | 1994 |
| Description | Results of an experimental study of a wind tunnel model inertial angle-of-attack sensor response to a simulated dynamic environment are presented. The inertial device cannot distinguish between the gravity vector and the centrifugal accelerations associated with wind tunnel model vibration, this situation results in a model attitude measurement bias error. Significant bias error in model attitude measurement was found for the model system tested. The model attitude bias error was found to be vibration mode and amplitude dependent. A first order correction model was developed and used for estimating attitude measurement bias error due to dynamic motion. A method for correcting the output of the model attitude inertial sensor in the presence of model dynamics during on-line wind tunnel operation is proposed. |
| File Size | 2077370 |
| Page Count | 36 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19950005053 |
| Archival Resource Key | ark:/13960/t4xh4j20g |
| Language | English |
| Publisher Date | 1994-07-01 |
| Access Restriction | Open |
| Subject Keyword | Research And Support Facilities (air) Accelerometers Error Analysis Bias Wind Tunnel Tests Centrifugal Force Instrument Errors Vibration Effects Wind Tunnel Models Angle of Attack Drag Measurement Correction Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |