发明名称 |
Helicopter engine torque compensator. |
摘要 |
<p>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).</p> |
申请公布号 |
EP0092500(A2) |
申请公布日期 |
1983.10.26 |
申请号 |
EP19830630061 |
申请日期 |
1983.04.15 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
HOWLETT, JAMES J.;ZAGRANSKI, RAYMOND D. |
分类号 |
B64C27/14;G05D1/08;(IPC1-7):05D1/08;64C27/06 |
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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