| タイトル | A simplified rotor system mathematical model for piloted flight dynamics simulation |
| 本文（外部サイト） | http://hdl.handle.net/2060/19790015806 |
| 著者（英） | Chen, R. T. N. |
| 著者所属（英） | NASA Ames Research Center |
| 発行日 | 1979-05-01 |
| 言語 | eng |
| 内容記述 | The model was developed for real-time pilot-in-the-loop investigation of helicopter flying qualities. The mathematical model included the tip-path plane dynamics and several primary rotor design parameters, such as flapping hinge restraint, flapping hinge offset, blade Lock number, and pitch-flap coupling. The model was used in several exploratory studies of the flying qualities of helicopters with a variety of rotor systems. The basic assumptions used and the major steps involved in the development of the set of equations listed are described. The equations consisted of the tip-path plane dynamic equation, the equations for the main rotor forces and moments, and the equation for control phasing required to achieve decoupling in pitch and roll due to cyclic inputs. |
| NASA分類 | AIRCRAFT STABILITY AND CONTROL |
| レポートNO | 79N23977
A-7538
NASA-TM-78575 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/175543 |
