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    HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL HAVING AZIMUTH AND PITCH CONTROL
    1.
    发明专利
    HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL HAVING AZIMUTH AND PITCH CONTROL 未知

    公开(公告)号：CA2118024A1

    公开(公告)日：1993-11-25

    申请号：CA2118024

    申请日：1993-05-07

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： LAPPOS NICHOLAS D ,  DRYFOOS JAMES B ,  KELLER JAMES F ,  FOWLER DONALD W

    IPC: B64C13/18 ,  B64C27/04 ,  F41G3/22 ,  G05D1/08

    Abstract: 2118024 9323715 PCTABScor01 A fire control system (55) azimuth command and elevation command provides a flight control system attitude reference in response to operation of the flight control system in a coupled aiming mode. The coupled aiming mode is engaged in response to the continuous operation of a pilot switch (920), the azimuth command and elevation command being below respective threshold magnitudes (940, 941), and the operation of the fire control system (55). During operation in the coupled aiming mode, the azimuth command and elevation command replace the yaw attitude feedback error signal and pitch attitude error signal, respectively, as the aircraft attitude reference. During integration of the fire control system and the flight control system, the flight control system is made less sensitive to small pilot command stick inputs below a stick input threshold magnitude, so that small or inadvertent pilot commanded yaw and pitch maneuvers will not affect the yaw and pitch attitude reference commanded by the fire control system azimuth and elevation commands. However, intended pilot commanded yaw and pitch maneuvers (70) maintain full authority at all times.

    4.
    发明专利
    未知

    公开(公告)号：ES2019059T3

    公开(公告)日：1995-12-16

    申请号：ES90630107

    申请日：1990-05-17

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SWEET DAVID H ,  LAPPOS NICHOLAS D ,  MEISNER RICHARD P ,  GREENBERG CHARLES E ,  WALSH DAVID M

    IPC: B64D31/00 ,  F02C9/28 ,  G05D1/08 ,  G05D1/00

    Abstract: The speed 54,56 of the free turbine 40 of a helicopter engine 22 is compared 134,138 with the speed 142,140 of the helicopter rotor 10 to indicate 106,108 a specific magnitude of autorotation and the deceleration 150 of the rotor above either one of two threshold magnitudes 220,222 (dependent on the magnitude of autorotation) is utilized 81,68,69 to increase fuel flow 72 to the engine according to a specific schedule 160,162, determined by the type of autorotation, in anticipation of rotor speed droop which would otherwise occur during recovery from the autorotation maneuver.

    HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL HAVING A PRE-LAUNCH AND POST-LAUNCH MANEUVER DIRECTOR
    5.
    发明专利
    HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL HAVING A PRE-LAUNCH AND POST-LAUNCH MANEUVER DIRECTOR 未知

    公开(公告)号：CA2174950A1

    公开(公告)日：1995-06-29

    申请号：CA2174950

    申请日：1994-12-02

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： FOWLER DONALD W ,  LAPPOS NICHOLAS D ,  EDWARDS JOAN A

    IPC: B64C13/18 ,  B64C27/57 ,  B64D7/08 ,  F41G5/18 ,  F41G9/00 ,  G05D1/08

    Abstract: An integrated fire and flight control (IFFC) system determines a ballistic firing solution based on the position of targets relative to a helicopter and also based on the type of weapons to be fired. An elevation command is determined based on the required change in helicopter attitude to achieve the ballistic firing solutin that, combined with the estimated time required to perform the aim and release of weapons, provides an estimate of deceleration and velocity loss that will occur. A forward acceleration and velocity profile is determined based on the desire to make a symmetrical maneuver sequence involving a nose down acceleration to achieve the acceleration and velocity profile that will be canceled by the subsequent deceleration and velocity loss during the pitch up maneuver to the ballistic firing solution. The forward acceleration and velocity profile is used to provide a pilot with a forward acceleration command that directs the pilot to fly a nose down attitude until the required forward acceleration and velocity profile is achieved. Alternatively, the acceleration profile is coupled to a flight control wherein a pre-launch maneuver feedforward command signal is summed with a side arm controller control command signal as the primary input to a rotor mixing function and a pre-launch commanded rate signal is summed with a side arm controller commanded rate signal to provide the primary input to an automatic flight control system, to thereby automatically control the aircraft to assume an attitude necessary to achieve the desired forward acceleration and velocity profile. A terminal phase maneuver is calculated to thereby return the aircraft to the previous attitude, velocity hold, hover hold or position hold condition prior to commencement of the pre-launch maneuver.

    Helicopter Integrated Fire and Flight Control System Having Turn Coordination Control
    6.
    发明专利
    Helicopter Integrated Fire and Flight Control System Having Turn Coordination Control 未知

    公开(公告)号：CA2133568A1

    公开(公告)日：1993-11-25

    申请号：CA2133568

    申请日：1993-05-06

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： FOWLER DONALD W ,  LAPPOS NICHOLAS D

    IPC: F41G3/22 ,  G05D1/08

    Abstract: During operation of a flight control system in a coupled aiming mode, wherein a fire control system (55) azimuth command and elevation command provide an aircraft attitude reference, a bank angle calculation function (1077) provides a bank angle signal to place the aircraft in a roll angle which results in a substantially coordinated turn. The bank angle signal is determined primarily as a function of an aiming line of sight heading rate for small azimuth commands, and is determined primarily as a function of aircraft heading rate for large azimuth commands. Additionally, the bank angle initially comprises a component as a function of aircraft lateral acceleration for driving aircraft lateral acceleration to zero, and after the aircraft assumes a roll attitude for turn coordination, the bank angle comprises a component as a function of aircraft side slip for driving aircraft side slip to zero. Automatic turn coordination is disabled if the pilot maneuvers the aircraft to avoid a coordinated turn, and is re-enabled if the pilot maneuvers the aircraft into a coordinated turn attitude. A rate feedback path (143) is provided during operation in the coupled aiming mode wherein aircraft yaw and pitch rate error signals are respectively replaced by the rate of change of the azimuth command and the elevation command. During operation in the coupled aiming mode, intended pilot commanded maneuvers maintain full authority at all times.

    9.
    发明专利
    未知

    公开(公告)号：ES2089550T3

    公开(公告)日：1996-10-01

    申请号：ES92917949

    申请日：1992-07-31

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GOLD PHILLIP J ,  LAPPOS NICHOLAS D ,  ADAMS DON L ,  WRIGHT STUART C

    IPC: G05D1/08

    Abstract: A helicopter flight control system includes an automatic turn coordination system which provides a coordinating yaw command signal to the tail rotor of the helicopter. The system stores on command a trim attitude (e.g., signals indicative of bank angle, lateral ground speed, and lateral acceleration) about which automatic turn coordination is provided, thus providing the pilot with automatic turn coordination about attitudes other than wings level.

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