发明名称 |
Anhedral tip blades for tiltrotor aircraft |
摘要 |
A tiltrotor aircraft having a fixed wing and tilting rotors has a rotor blade with a shaped tip portion that provides improved hover performance. The shaped tip portion preferably has a terminal anhedral of at least 20° with respect to its stacking line, and the blade has an overall twist from root to tip of at least 20°, and a thickness ratio between 19% and 30% at a radial station of 10%. These features advantageously conspire to provide a hover figure of merit of at least 0.84 and a cruise propulsive efficiency of at least 0.85. A controller preferably limits the rotor speed in sustained airplane-mode forward flight cruise of at most 40% of a hover maximum rotor speed, and alternatively or additionally limits a rotor edgewise advance ratio to at most 0.20. |
申请公布号 |
US8066219(B2) |
申请公布日期 |
2011.11.29 |
申请号 |
US20100903928 |
申请日期 |
2010.10.13 |
申请人 |
PATT DAN;KAREM ABE;KAREM AIRCRAFT, INC. |
发明人 |
PATT DAN;KAREM ABE |
分类号 |
B64C15/12;B64C27/22;B64C27/467 |
主分类号 |
B64C15/12 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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