| タイトル | Effects of primary rotor parameters on flapping dynamics |
| 本文（外部サイト） | http://hdl.handle.net/2060/19800006879 |
| 著者（英） | Chen, R. T. N. |
| 著者所属（英） | NASA Ames Research Center |
| 発行日 | 1980-01-01 |
| 言語 | eng |
| 内容記述 | The effects of flapping dynamics of four main rotor design features that influence the agility, stability, and operational safety of helicopters are studied. The parameters include flapping hinge offset, flapping hinge restraint, pitch-flap coupling, and blade lock number. First, the flapping equations of motion are derived that explicitly contain the design parameters. The dynamic equations are then developed for the tip-path plane, and the influence of individual and combined variations in the design parameters determined. The steady state flapping response is examined with respect to control input and aircraft angular rate which leads to a feedforward control law for control decoupling through cross feed, and a feedback control law to decouple the steady state flapping response. The condition for achieving perfect decoupling of the flapping response due to aircraft pitch and roll rates without using feedback control is also found for the hover case. It is indicated that the frequency of the regressing flapping mode of the rotor system can become low enough to require consideration in the assessment of handling characteristics. |
| NASA分類 | AIRCRAFT STABILITY AND CONTROL |
| レポートNO | 80N15138
A-7777
NASA-TP-1431 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/173699 |
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