PROBLEM TO BE SOLVED: To secure high torsional rigidity while obtaining high figure-of-merit.SOLUTION: A rotor 6 has a solidity of 10% or less and two blades 3. In the shape of each blade 3: there is a maximum chord length in a 10% to 35% region of the radius; the chord length decreases from the position of the maximum chord length to the tip direction, in which the blade chord length decrease becomes maximum at a predetermined position, and the chord length decrease becomes gradual from that position to the tip direction; there is an inflection point in a 70% to 95% region of the radius; the tip is elliptical; the maximum chord length is more than three times as long as the chord length of a virtual wing tip that is formed at the wind tip by the tangent line contacting with the wing chord at two points; the necking size at the middle of the radius is 30% or less of the virtual wing tip; and the wing incidence angle becomes maximum near the point where the chord length becomes maximum and decreases from the position where the chord length becomes maximum to the tip, in which the wing incidence angle at the root decreases from the position where the wing incidence angle takes the maximum value to the root.SELECTED DRAWING: Figure 1
【課題】高いフィギュアオブメリットを得つつ、高い捻れ剛性を確保すること。【解決手段】ソリディティが10%以下となるロータ6でかつ2枚のブレード3を有する。各ブレード3の形状は、半径10%から35%の領域に最大翼弦長をもち、最大翼弦長の位置から先端方向にかけて翼弦長が減少し、翼弦長の減少が所定の位置で最大になり、その位置から先端方向にかけて前記翼弦長の減少がゆるやかになり、半径70%から95%の領域に変曲点があり、先端が楕円形であり、翼弦に2点で接する接線が翼端で作る仮想の翼端の翼弦長に対し、最大翼弦長は3倍以上の長さであり、半径中程のくびれ量は仮想の翼端の30%以下であり、取付け角は翼弦長が最大になる付近で最大となり、翼弦長が最大に位置から先端にかけて減少し、付け根の前記取付け角は当該取り付け角が最大値を取る位置から付け根に行くほど減少している。【選択図】図1
ROTOR, DRONE AND HELICOPTER
ロータ、ドローン及びヘリコプタ
2018-08-23
Patent
Elektronische Ressource
Japanisch
IPC: | B64C AEROPLANES , Flugzeuge |
ADJUSTABLE WEIGHT DISTRIBUTION FOR MULTI-ROTOR HELICOPTER DRONE
Europäisches Patentamt | 2021
|ADJUSTABLE WEIGHT DISTRIBUTION FOR MULTI-ROTOR HELICOPTER DRONE
Europäisches Patentamt | 2016
|