发明名称 |
HELICOPTER ROTOR CONTROL SYSTEM WITH INDIVIDUAL BLADE CONTROL |
摘要 |
A method of controlling rotor pitch in a helicopter comprising the steps of: generating at least one blade dynamics signal representing at least one dynamic force acting on at least one of a rotor blade rotating assembly and a helicopter non-rotating assembly, the rotor blade rotating assembly including a plurality of rotor blades and a pitch actuator for each rotor blade; extracting information representing the at least one dynamic force; generating a dynamic force compensation output representing a compensation for at least a portion of the at least one dynamic force; receiving flight control signals directing flight of the helicopter from flight controls of the helicopter; generating from the flight control signals and the dynamic force compensation output a compensated pitch control signal for each blade of the rotor blade rotating assembly, and providing a compensated pitch control signal to compensate for a portion of the at least one dynamic force. |
申请公布号 |
US2012068005(A1) |
申请公布日期 |
2012.03.22 |
申请号 |
US20110986664 |
申请日期 |
2011.01.07 |
申请人 |
KESSLER CHRISTOPH;FURST DANIEL;ZF FRIEDRICHSHAFEN AG |
发明人 |
KESSLER CHRISTOPH;FURST DANIEL |
分类号 |
B64C27/57 |
主分类号 |
B64C27/57 |
代理机构 |
|
代理人 |
|
主权项 |
|
地址 |
|