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公开(公告)号：CA2789269C
公开(公告)日：2015-12-29
申请号：CA2789269
申请日：2011-02-07
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： SCHULTE KYNN J , FORTENBAUGH ROBERT L , BUILTA KENNETH E
Abstract: A method for operating an aircraft to prevent/recover from a stall condition includes the steps of detecting an actual vertical velocity of the aircraft, calculating vertical velocity error of the aircraft, the vertical velocity error being based upon a comparison between the actual vertical velocity of the aircraft and a commanded vertical velocity of the aircraft, and determining if the aircraft is in one of a near stalled condition and a stalled condition based upon at least the detected vertical velocity error and the polarity of the vertical velocity error. The method further includes the steps of taking control of the aircraft from an operator of the aircraft, reducing a bank angle of the aircraft, pitching the aircraft downward, and increasing the airspeed of the aircraft if the aircraft's airspeed is outside an airspeed window if the aircraft is in one of the near stalled condition and the stalled condition.
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公开(公告)号：CA2664195C
公开(公告)日：2015-02-03
申请号：CA2664195
申请日：2007-09-13
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： BUILTA KENNETH E , SCHULTE KYNN J , 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.
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公开(公告)号：CA2789269A1
公开(公告)日：2011-08-18
申请号：CA2789269
申请日：2011-02-07
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： SCHULTE KYNN J , FORTENBAUGH ROBERT L , BUILTA KENNETH E
IPC: G05D1/08
Abstract: A method for operating an aircraft to prevent/recover from a stall condition includes the steps of detecting an actual vertical velocity of the aircraft, calculating vertical velocity error of the aircraft, the vertical velocity error being based upon a comparison between the actual vertical velocity of the aircraft and a commanded vertical velocity of the aircraft, and determining if the aircraft is in one of a near stalled condition and a stalled condition based upon at least the detected vertical velocity error and the polarity of the vertical velocity error. The method further includes the steps of taking control of the aircraft from an operator of the aircraft, reducing a bank angle of the aircraft, pitching the aircraft downward, and increasing the airspeed of the aircraft if the aircraft's airspeed is outside an airspeed window if the aircraft is in one of the near stalled condition and the stalled condition.
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公开(公告)号：MX2009003068A
公开(公告)日：2009-04-02
申请号：MX2009003068
申请日：2007-09-13
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： BUILTA KENNETH E , SCHULTE KYNN J , HARRIS JAMES E , GORE BILLY K
IPC: B64C29/00
Abstract: Una modalidad de la presente invención es un método para controlar automáticamente la conversión de una aeronave de rotor inclinable. Un comando de velocidad aerodinámica para la aeronave de rotor inclinable es recibido. El comando de velocidad aerodinámica es convertido a una posición de mástil. Es calculada una diferencia entre el comando de velocidad aerodinámica y una velocidad aerodinámica medida. La diferencia entre el comando de velocidad aerodinámica y una velocidad aerodinámica medida es convertida a una posición dinámica de mástil. Es calculada una posición total de mástil a partir de la posición de mástil y la posición dinámica de mástil. Un mástil de la aeronave de rotor inclinable es movido a la posición total de mástil. Otra modalidad de la presente invención es un sistema para calcular una posición de un mástil de una aeronave de rotor inclinable, con base en un comando de velocidad aerodinámica. El sistema incluye un módulo de comando de velocidad aerodinámica, un módulo de posición de compensación de mástil, un módulo de posición dinámica de mástil y un módulo de posición de mástil.
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公开(公告)号：BRPI0418962A
公开(公告)日：2007-12-04
申请号：BRPI0418962
申请日：2004-07-29
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： BUILTA KENNETH E
IPC: B64C27/52
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Patent Agency Ranking
公开(公告)号：CA2591713A1
公开(公告)日：2007-05-24
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.
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公开(公告)号：CA2555836A1
公开(公告)日：2005-11-03
申请号：CA2555836
申请日：2004-03-25
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： BUILTA KENNETH E , HARRIS JAMES E , HONZA BRYAN P , SCHULTE KYNN J , EPP JEFFREY W
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. Th e receiver (45) receives transmitted data (51, 55) communicating the position and movement of a reference vehicle relative to the earth. The control syste m (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.
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公开(公告)号：CA2660997C
公开(公告)日：2015-09-29
申请号：CA2660997
申请日：2007-08-09
Applicant: BELL HELICOPTER TEXTRON INC
Inventor： BUILTA KENNETH E
IPC: B64C29/00
Abstract: The difference between a first position (110) of a first pylon of a tiltrotor aircraft and a second position (120) of a second pylon of the aircraft is prevented from becoming too large. An actuator position error (140) for the first pylon is calculated from a difference between the first position (110) and a commanded first position (150) of the first pylon. An actuator position error (160) for the second pylon is calculated from a difference between the second position (120) and a commanded second position (170) of the second pylon. An absolute value (165) of the actuator position error for the first pylon is compared (135) to the preset limit (130). If the absolute value of the actuator position error for the first pylon is greater than or equal to a preset limit, the actuator position error for the second pylon is calculated from the difference between the first position and the second position.
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公开(公告)号：CA2555836C
公开(公告)日：2013-05-28
申请号：CA2555836
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
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.
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公开(公告)号：DE05858317T1
公开(公告)日：2009-04-30
申请号：DE05858317
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.
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