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    HELICOPTER CRUISE FUEL CONSERVING ENGINE CONTROL
    6.
    发明专利
    HELICOPTER CRUISE FUEL CONSERVING ENGINE CONTROL 未知

    公开(公告)号：DE3376992D1

    公开(公告)日：1988-07-14

    申请号：DE3376992

    申请日：1983-04-15

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MORRISON TERRY ,  ZAGRANSKI RAYMOND D ,  HOWLETT JAMES J

    IPC: F02C3/10 ,  F02C9/28 ,  G05D1/00 ,  G05D1/08

    Abstract: A digital fuel control (53) for a helicopter engine (20) controls fuel flow (52) to the engine in response to a turbine reference speed (62) determined in a normal mode (Fig. 5) to be a rated speed, in a fade-in mode (Fig. 6) to be incremented (117, 120) to an estimated optimum minimum speed (114, 115, 125), in an optimizer mode (Fig. 7) to be incremented (138) in a direction (137) leading to least fuel consumption (135), and in a fade-out mode (Fig. 8) to be incremented (151, 153) back to rated speed (154). The invention provides an engine reference speed which results in minimum fuel consumption during cruise flight.

    Rotorcraft automatic autorotation entry device
    8.
    发明专利
    Rotorcraft automatic autorotation entry device 未知

    公开(公告)号：GB2192163A

    公开(公告)日：1988-01-06

    申请号：GB8616150

    申请日：1986-07-02

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HOWLETT JAMES J ,  ALANSKY IRVIN B

    IPC: B64C27/57 ,  G05D1/00 ,  G05D1/08

    Abstract: During the first few seconds after an engine failure, autorotation is established automatically by an Automatic Flight Control System, thereby avoiding undesirable transients and allowing the pilot time to react. The system has collective, pitch, roll, and yaw channels and receives engine failure signal, and signals of rotor speed, a rotor speed reference value for autorotation, rotor acceleration, load factor limit for the helicopter, a load factor as measured, pitch rate, airspeed, roll angular acceleration, yaw acceleration, yaw reference signal of desired yaw attitude during autorotation.

    HELICOPTER ENGINE TORQUE COMPENSATOR
    9.
    发明专利
    HELICOPTER ENGINE TORQUE COMPENSATOR 未知

    公开(公告)号：CA1214149A

    公开(公告)日：1986-11-18

    申请号：CA425724

    申请日：1983-04-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HOWLETT JAMES J ,  ZAGRANSKI RAYMOND D

    IPC: B64C27/14 ,  G05D1/08 ,  B64C27/78

    Abstract: Helicopter Engine Torque Compensator 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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