发明名称 |
Helicopter engine torque compensator |
摘要 |
The blade angle controlling pitch beam servo (26) of a helicopter tail rotor (22) is responsive to a signal manifestation (76) indicative of free turbine engine (20) gas generator speed (78) to provide torque compensation so that the helicopter airframe will not counter-rotate under the main rotor (10) of a helicopter as a consequence of the torque provided thereto by the airframe-mounted engine (20), or in the absence thereof. A trimming embodiment (FIG. 2) provides only sufficient blade angle command (82a) to compensate for that provided by fixed, collective/tail mixing (110-114). Torque compensation tail rotor blade angle commands may be applied through existing stability and autopilot actuators (30-32) or through an additional torque servo (120, FIG. 3).
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申请公布号 |
US4493465(A) |
申请公布日期 |
1985.01.15 |
申请号 |
US19820369481 |
申请日期 |
1982.04.16 |
申请人 |
CHANDLER EVANS INC. |
发明人 |
HOWLETT, JAMES J.;ZAGRANSKI, RAYMOND D. |
分类号 |
B64C27/14;G05D1/08;(IPC1-7):B64C27/78 |
主分类号 |
B64C27/14 |
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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