Abstract
An eigenvalue and modal decoupling method to predict helicopter rotor stability and forced response has been successfully developed. The method is described and its advantages are pointed out. The results obtained using this method illustrate that the major rotor coupling parameters can be chosen in a systematic way to achieve stability and low rotor loads. The sequence indicating the manner in which the parameters could be chosen during preliminary design is presented.
| Original language | English |
|---|---|
| Pages (from-to) | 177-185 |
| Number of pages | 9 |
| Journal | Vertica |
| Volume | 3 |
| Issue number | 2 |
| State | Published - 1979 |