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    SISTEMA DE CONTROL AUTOMATICO DE RUMBO PARA AERONAVES Y HELICOPTEROS DE ROTOR INCLINABLE.
    31.
    发明专利
    SISTEMA DE CONTROL AUTOMATICO DE RUMBO PARA AERONAVES Y HELICOPTEROS DE ROTOR INCLINABLE. 未知

    公开(公告)号：MX2009003067A

    公开(公告)日：2009-04-02

    申请号：MX2009003067

    申请日：2007-09-18

    Applicant: BELL HELICOPTER TEXTRON INC

    Inventor： BUILTA KENNETH E

    IPC: G05D1/08

    Abstract: Una modalidad de la presente invención es un método para reducir automáticamente el efecto de de un componente de una fuerza externa que es lateralmente incidente sobre una aeronave de rotor. Una señal de la nave de rotor indicadora de y proporcional al componente, es monitorizada. Se compara un valor absoluto de la señal y un límite alto preestablecido. Si el valor absoluto es mayor que el límite alto preestablecido, se habilita control de rumbo manual de la nave de rotor y el rumbo de la nave de rotor es ajustado con respecto a la fuerza externa para disminuir así el componente lateral de la fuerza externa experimentada por la nave de rotor.

    32.
    发明专利
    未知

    公开(公告)号：BRPI0519214A2

    公开(公告)日：2009-01-06

    申请号：BRPI0519214

    申请日：2005-11-15

    Applicant: BELL HELICOPTER TEXTRON INC

    Inventor： BUILTA KENNETH E ,  HARRIS JAMES E ,  GORE BILLY K

    IPC: G05D1/00

    Abstract: A flight control system for an aircraft is configured for receiving command signals representing commanded values of a location of a geospatial point and a radius about the geospatial point for defining a circular groundtrack. A sensor determines a geospatial location of the aircraft and provides a location signal representing the location of the aircraft. A controller for commanding flight control devices on the aircraft controls the flight of the aircraft and is configured to receive the command signals and the location signal. The controller uses the command signals and location signal to operate the flight control devices to control the flight of the aircraft for directing the aircraft generally toward a tangent point of the circular groundtrack and then maintaining a flight path along the circular groundtrack.

    33.
    发明专利
    未知

    公开(公告)号：BRPI0516143A

    公开(公告)日：2008-08-26

    申请号：BRPI0516143

    申请日：2005-09-12

    Applicant: BELL HELICOPTER TEXTRON INC

    Inventor： BUILTA KENNETH E ,  SCHULTE KYNN J

    IPC: B64C19/00

    Abstract: A flight control system for an aircraft receives a selected value of a first parameter, which is either the airspeed or inertial velocity of the aircraft. A primary feedback loop generates a primary error signal that is proportional to the difference between the selected value and a measured value of the first parameter. A secondary feedback loop generates a secondary error signal that is proportional to the difference between the selected value of the first parameter and a measured value of a second flight parameter, which is the other of the airspeed and inertial velocity. The primary and secondary error signals are summed to produce a velocity error signal, and the velocity error signal and an integrated value of the primary error signal are summed to produce an actuator command signal. The actuator command signal is then used for operating aircraft devices to control the first parameter to minimize the primary error signal.

    Automatic conversion system for tiltrotor aircraft
    34.
    发明专利
    Automatic conversion system for tiltrotor aircraft 未知

    公开(公告)号：AU2007342334A1

    公开(公告)日：2008-07-17

    申请号：AU2007342334

    申请日：2007-09-13

    Applicant: BELL HELICOPTER TEXTRON INC

    Inventor： SCHULTE KYNN J ,  BUILTA KENNETH E ,  HARRIS JAMES E ,  GORE BILLY K

    IPC: B64C29/00

    Abstract: One embodiment of the present invention is a method for automatically controlling the conversion of a tiltrotor aircraft. An airspeed command for the tiltrotor aircraft is received. The airspeed command is converted to a pylon position. A difference between the airspeed command and a measured airspeed is calculated. The difference between the airspeed command and a measured airspeed is converted to a dynamic pylon position. A total pylon position is calculated from the pylon position and the dynamic pylon position. A pylon of the tiltrotor aircraft is moved to the total pylon position. Another embodiment of the present invention is a system for calculating a position of a pylon of a tiltrotor aircraft based on an airspeed command. The system includes an airspeed command module, a pylon trim position module, a dynamic pylon position module, and a pylon position module.

    Automatic velocity control system for aircraft
    37.
    发明专利
    Automatic velocity control system for aircraft 未知

    公开(公告)号：AU2005336430A1

    公开(公告)日：2007-03-22

    申请号：AU2005336430

    申请日：2005-09-12

    Applicant: BELL HELICOPTER TEXTRON INC

    Inventor： SCHULTE KYNN J ,  BUILTA KENNETH E

    IPC: B64C19/00

    Abstract: A flight control system for an aircraft receives a selected value of a first parameter, which is either the airspeed or inertial velocity of the aircraft. A primary feedback loop generates a primary error signal that is proportional to the difference between the selected value and a measured value of the first parameter. A secondary feedback loop generates a secondary error signal that is proportional to the difference between the selected value of the first parameter and a measured value of a second flight parameter, which is the other of the airspeed and inertial velocity. The primary and secondary error signals are summed to produce a velocity error signal, and the velocity error signal and an integrated value of the primary error signal are summed to produce an actuator command signal. The actuator command signal is then used for operating aircraft devices to control the first parameter to minimize the primary error signal.

    METHOD AND APPARATUS FOR FLIGHT CONTROL OF TILTROTOR AIRCRAFT
    40.
    发明公开
    METHOD AND APPARATUS FOR FLIGHT CONTROL OF TILTROTOR AIRCRAFT 有权
    方法和装置飞行控制倾转旋翼飞机

    公开(公告)号：EP1773658A4

    公开(公告)日：2009-10-28

    申请号：EP04786134

    申请日：2004-07-29

    Applicant: BELL HELICOPTER TEXTRON INC

    Inventor： BUILTA KENNETH E

    IPC: B64C27/52 ,  B64C29/00 ,  G05D1/08

    CPC classification number: G05D1/0858 ,  B64C27/52 ,  B64C29/0033

    Abstract: A method and apparatus provide for automatically controlling the flight of a tiltrotor aircraft while the aircraft is in flight that is at least partially rotor-borne. The method and apparatus provide for automatically tilting nacelles in response to a longitudinal-velocity control signal so as to produce a longitudinal thrust-vector component for controlling longitudinal velocity of the aircraft. Simultaneously, cyclic swashplate controls are automatically actuated so as to maintain the fuselage in a desired pitch attitude. The method and apparatus also provide for automatically actuating the cyclic swashplate controls for each rotor in response to a lateral-velocity control signal so as to produce a lateral thrust-vector component for controlling lateral velocity of the aircraft. Simultaneously, collective swashplate controls for each rotor are automatically actuated so as to maintain the fuselage in a desired roll attitude. The method and apparatus provide for yaw control through differential longitudinal thrust produced by tilting the nacelles.

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