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Comparison of three controllers applied to helicopter vibration
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Leyland, Jane A. |
| Copyright Year | 1992 |
| Description | A comparison was made of the applicability and suitability of the deterministic controller, the cautious controller, and the dual controller for the reduction of helicopter vibration by using higher harmonic blade pitch control. A randomly generated linear plant model was assumed and the performance index was defined to be a quadratic output metric of this linear plant. A computer code, designed to check out and evaluate these controllers, was implemented and used to accomplish this comparison. The effects of random measurement noise, the initial estimate of the plant matrix, and the plant matrix propagation rate were determined for each of the controllers. With few exceptions, the deterministic controller yielded the greatest vibration reduction (as characterized by the quadratic output metric) and operated with the greatest reliability. Theoretical limitations of these controllers were defined and appropriate candidate alternative methods, including one method particularly suitable to the cockpit, were identified. |
| File Size | 3746898 |
| Page Count | 82 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19920019214 |
| Archival Resource Key | ark:/13960/t2d847m5q |
| Language | English |
| Publisher Date | 1992-05-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Stability And Control Controllers Random Noise Vibration Checkout Vibration Damping Helicopters Cockpits Harmonic Control Reliability Computer Programs 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 |
