公开(公告)号：CA2773702C

公开(公告)日：2014-07-22

申请号：CA2773702

申请日：2004-03-25

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： BUILTA KENNETH E ,  HARRIS JAMES E ,  HONZA BRYAN P ,  EPP JEFFREY W ,  SCHULTE KYNN J

IPC: B64C19/00 ,  G01C23/00 ,  G05D1/00

Abstract: A system for controlling flight of an aircraft has sensors (37, 43), a receiver (45), and a digital control system (57), all of which are carried aboard the aircraft. The sensors (37, 43) determine the position of the aircraft relative to the earth and the inertial movement of the aircraft. The receiver (45) receives transmitted data (51, 55) communicating the position and movement of a reference vehicle relative to the earth. The control system (57) calculates the position and velocity of the aircraft relative to the reference vehicle using the data from the sensors (37, 43) and the receiver (45) and then commands flight control devices (33) on the aircraft for maneuvering the aircraft in a manner that maintains a selected position and/or velocity relative to the reference vehicle. The system allows use of a graphical or tactile user interfaces.

公开(公告)号：CA2788512C

公开(公告)日：2014-05-20

申请号：CA2788512

申请日：2004-03-25

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： BUILTA KENNETH E ,  HARRIS JAMES E ,  HONZA BRYAN P ,  EPP JEFFREY W ,  SCHULTE KYNN J

IPC: B64C19/00 ,  B64D43/00

Abstract: A system for controlling flight of an aircraft has sensors (37, 43), a receiver (45), and a digital control system (57), all of which are carried aboard the aircraft. The sensors (37, 43) determine the position of the aircraft relative to the earth and the inertial movement of the aircraft. The receiver (45) receives transmitted data (51, 55) communicating the position and movement of a reference vehicle relative to the earth. The control system (57) calculates the position and velocity of the aircraft relative to the reference vehicle using the data from the sensors (37, 43) and the receiver (45) and then commands flight control devices (33) on the aircraft for maneuvering the aircraft in a manner that maintains a selected position and/or velocity relative to the reference vehicle. The system allows use of a graphical or tactile user interfaces.

公开(公告)号：CA2571372C

公开(公告)日：2010-09-28

申请号：CA2571372

申请日：2004-07-29

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： BUILTA KENNETH E

IPC: B64C27/52

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.

公开(公告)号：CA2591713C

公开(公告)日：2013-07-16

申请号：CA2591713

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.

公开(公告)号：CA2587835C

公开(公告)日：2010-02-16

申请号：CA2587835

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.

公开(公告)号：MX2009001863A

公开(公告)日：2009-04-15

申请号：MX2009001863

申请日：2007-08-09

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： BUILTA KENNETH E

IPC: B64C19/02

Abstract: La diferencia entre una primera posición (110) de una primera bancada del motor de una aeronave de rotor oscilante y una segunda posición (120) de una segunda bancada del motor de la aeronave se previene que llegue a ser demasiado grande. Un error (140) de la posición del accionador para la primera bancada del motor es calculado a partir de una diferencia entre la primera posición (110) y una primera posición comandada (150) de la primera bancada del motor. Un error (160) de la posición del accionador para la segunda bancada del motor es calculado a partir de una diferencia entre la segunda posición (120) y una segunda posición comandada (170) de la segunda bancada del motor. Un valor absoluto (165) del error en la posición del accionador para la primera bancada del motor es comparado (135) con el límite preajustado (130). Si el valor absoluto del error en la posición del accionador para la primera bancada del motor es mayor que o igual a un límite preajustado, el error en la posición del accioandor para la segunda bancada del motor es calculado a partir de la diferencia entre la primera posición y la segunda posición.

公开(公告)号：CA2664195A1

公开(公告)日：2008-07-17

申请号：CA2664195

申请日：2007-09-13

Applicant: BELL HELICOPTER TEXTRON INC

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

IPC: B64C29/00

Abstract: One embodiment of the present invention is a method for automatically con trolling the conversion of a tiltrotor aircraft. An airspeed command for the tiltrotor aircraft is received. The airspeed command is converted to a pylo n position. A difference between the airspeed command and a measured airspee d 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 embo diment 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 inclu des an airspeed command module, a pylon trim position module, a dynamic pylo n position module, and a pylon position module.

公开(公告)号：AU2005338333A1

公开(公告)日：2007-05-24

申请号：AU2005338333

申请日：2005-11-15

Applicant: BELL HELICOPTER TEXTRON INC

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

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.

公开(公告)号：CA2571372A1

公开(公告)日：2006-03-02

申请号：CA2571372

申请日：2004-07-29

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： BUILTA KENNETH E

IPC: B64C27/52

公开(公告)号：CA2788512A1

公开(公告)日：2005-11-03

申请号：CA2788512

申请日：2004-03-25

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： BUILTA KENNETH E ,  HARRIS JAMES E ,  HONZA BRYAN P ,  EPP JEFFREY W ,  SCHULTE KYNN J

IPC: B64C19/00 ,  B64D43/00

Abstract: A system for controlling flight of an aircraft has sensors (37, 43), a receiver (45), and a digital control system (57), all of which are carried aboard the aircraft. The sensors (37, 43) determine the position of the aircraft relative to the earth and the inertial movement of the aircraft. The receiver (45) receives transmitted data (51, 55) communicating the position and movement of a reference vehicle relative to the earth. The control system (57) calculates the position and velocity of the aircraft relative to the reference vehicle using the data from the sensors (37, 43) and the receiver (45) and then commands flight control devices (33) on the aircraft for maneuvering the aircraft in a manner that maintains a selected position and/or velocity relative to the reference vehicle. The system allows use of a graphical or tactile user interfaces.