发明名称 |
Blade pitch control for main rotor of helicopter |
摘要 |
The hydraulic actuating mechanism is used to set the pitch of the blades (8) of the main rotor of a helicopter. The hydraulic circuit includes a bypass valve (20) in addition to the first valve (34) in the hydraulic line (38A,B) between the working chambers (16,18) of the piston and cylinder assembly (2) connected (6) to a rotor blade. There is a servo control valve (10) connected to the cyclic pitch control lever (14). The system also includes a hydraulic pressure source which varies according to the rotational speed of the main rotor.
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申请公布号 |
DE19505333(A1) |
申请公布日期 |
1996.09.19 |
申请号 |
DE19951005333 |
申请日期 |
1995.02.17 |
申请人 |
EUROCOPTER DEUTSCHLAND GMBH, 80993 MUENCHEN, DE |
发明人 |
SCHULLER, JOHANNES, 83620 FELDKIRCHEN-WESTERHAM, DE |
分类号 |
B64C27/64;(IPC1-7):B64C27/64;B64C11/38 |
主分类号 |
B64C27/64 |
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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