Fluid reaction surfaces (i.e. – impellers) – Interrelated controls for impeller and drive means
Patent
1991-08-27
1993-02-23
Kwon, John T.
Fluid reaction surfaces (i.e., impellers)
Interrelated controls for impeller and drive means
60 39282, 244 1719, 416 27, 416 31, 416 38, F04D 2918
Patent
active
051885115
ABSTRACT:
The blade angle controlling pitch beam servo (26) of a helicopter tail rotor (22) is responsive to a main rotor torque signal (92) indicative of torque coupled to a helicopter main rotor (10) for providing torque compensation so that the helicopter airframe will not counter-rotate under the main rotor. The torque coupled to the main rotor is that amount of engine torque (76, 114) in excess of torque coupled to the tail rotor (81, 115) and helicopter auxiliaries (84, 116). The amount of torque compensation provided by the tail rotor is reduced by an amount indicative of aerodynamic forces (130) on the helicopter airframe.
REFERENCES:
patent: 2998210 (1961-08-01), Carter, Jr.
patent: 3174284 (1965-03-01), McCarthy
patent: 4392203 (1983-07-01), Fischer et al.
patent: 4436482 (1984-03-01), Inoue et al.
patent: 4466526 (1984-08-01), Howlett et al.
patent: 4493465 (1985-01-01), Howlett et al.
patent: 4628455 (1986-12-01), Skutecki
patent: 4807129 (1989-02-01), Perks
patent: 4934825 (1990-06-01), Martin
patent: 4993919 (1991-02-01), Schneider
patent: 5020316 (1991-06-01), Sweet et al.
patent: 5046923 (1991-09-01), Parsons et al.
Grillo Michael
Kwon John T.
United Technologies Corporation
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