公开(公告)号：WO2008036618A3

公开(公告)日：2008-06-26

申请号：PCT/US2007078703

申请日：2007-09-18

Applicant: BELL HELICOPTER TEXTRON INC ,  BUILTA KENNETH E

Inventor： BUILTA KENNETH E

IPC: G05D1/08

CPC classification number: G05D1/0202

Abstract: One embodiment of the present invention is a method for automatically reducing the effect of a component of an external force that is laterally incident on a rotorcraft. A signal of the rotorcraft indicative of and proportional to the component is monitored. An absolute value of the signal and a preset high limit are compared. If the absolute value is greater than the preset high limit, manual heading control of the rotorcraft is disabled and the heading of the rotorcraft is adjusted with respect to the external force so as to decrease the lateral component of the external force experienced by the rotorcraft.

Abstract translation: 本发明的一个实施例是用于自动降低横向入射在旋翼飞行器上的外力分量的影响的方法。 监测旋翼机指示并与部件成比例的信号。 比较信号的绝对值和预设的上限。 如果绝对值大于预设上限，则旋翼航空器的手动航向控制被禁用，并且相对于外力调整旋翼航空器的航向，以便减小旋翼航空器所经历的外力的横向分量。

公开(公告)号：WO2008085558A3

公开(公告)日：2010-03-11

申请号：PCT/US2007078396

申请日：2007-09-13

Applicant: BELL HELICOPTER TEXTRON INC ,  BUILTA KENNETH E ,  SCHULTE KYNN J ,  HARRIS JAMES E ,  GORE BILLY K

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

IPC: G05D1/06 ,  B64C29/00

CPC classification number: B64C29/0033 ,  G05D1/0858

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.

Abstract translation: 本发明的一个实施例是一种用于自动控制倾斜旋翼飞机的转换的方法。 接收到倾斜旋翼飞机的空速命令。 空速命令转换为挂架位置。 计算空速指令与测量空速之差。 空速指令和测量空速之间的差异转换为动态塔架位置。 从塔架位置和动力塔架位置计算总塔架位置。 倾斜旋翼飞机的塔架移动到总塔架位置。 本发明的另一实施例是一种用于基于空速命令来计算倾斜旋翼飞机的塔架的位置的系统。 该系统包括空速指令模块，塔架装饰位置模块，动力塔位置模块和挂架位置模块。

公开(公告)号：WO2008111952A3

公开(公告)日：2009-01-15

申请号：PCT/US2007017702

申请日：2007-08-09

Applicant: BELL HELICOPTER TEXTRON INC ,  BUILTA KENNETH E

Inventor： BUILTA KENNETH E

IPC: B64C29/00

CPC classification number: B64C29/0033

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.

Abstract translation: 倾斜旋翼飞机的第一塔架的第一位置（110）与飞机的第二塔架的第二位置（120）之间的差异被防止变得太大。 从第一座架的第一位置（110）和第一座架的指令的第一位置（150）之间的差计算第一座架的致动器位置误差（140）。 根据第二位置（120）和第二塔的命令的第二位置（170）之间的差计算第二塔的致动器位置误差（160）。 将第一塔的致动器位置误差的绝对值（165）与预设极限（130）进行比较（135）。 如果第一吊架的执行器位置误差的绝对值大于或等于预设极限，则由第一位置和第二位置之间的差计算第二托架的执行器位置误差。

公开(公告)号：CA2660997A1

公开(公告)日：2008-09-18

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 tiltr otor 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 t he first pylon is calculated from a difference between the first position (1 10) and a commanded first position (150) of the first pylon. An actuator pos ition error (160) for the second pylon is calculated from a difference betwe en the second position (120) and a commanded second position (170) of the se cond pylon. An absolute value (165) of the actuator position error for the f irst pylon is compared (135) to the preset limit (130). If the absolute valu e of the actuator position error for the first pylon is greater than or equa l to a preset limit, the actuator position error for the second pylon is cal culated from the difference between the first position and the second positi on.

公开(公告)号：AU2007348983A1

公开(公告)日：2008-09-18

申请号：AU2007348983

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 of a first pylon of a tiltrotor aircraft and a second position of a second pylon of the aircraft is prevented from becoming too large. An actuator position error for the first pylon is calculated from a difference between the first position and a commanded first position of the first pylon. An actuator position error for the second pylon is calculated from a difference between the second position and a commanded second position of the second pylon. An absolute value of the actuator position error for the first pylon is compared to the preset limit. 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.

公开(公告)号：CA2664103A1

公开(公告)日：2008-03-27

申请号：CA2664103

申请日：2007-09-18

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： BUILTA KENNETH E

IPC: G05D1/08

Abstract: One embodiment of the present invention is a method for automatically red ucing the effect of a component of an external force that is laterally incid ent on a rotorcraft. A signal of the rotorcraft indicative of and proportion al to the component is monitored. An absolute value of the signal and a pres et high limit are compared. If the absolute value is greater than the preset high limit, manual heading control of the rotorcraft is disabled and the he ading of the rotorcraft is adjusted with respect to the external force so as to decrease the lateral component of the external force experienced by the rotorcraft.

公开(公告)号：BRPI0418602A

公开(公告)日：2007-05-02

申请号：BRPI0418602

申请日：2004-03-25

Applicant: BELL HELICOPTER TEXTRON INC

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

IPC: G06F17/00 ,  B64C13/20 ,  B64C39/02 ,  G05D1/02

Abstract: A system for controlling flight of an aircraft has sensors, a receiver, and a digital control system, all of which are carried aboard the aircraft. The sensors determine the position of the aircraft relative to the earth and the inertial movement of the aircraft. The receiver receives transmitted data communicating the position and movement of a reference vehicle relative to the earth. The control system calculates the position and velocity of the aircraft relative to the reference vehicle using the data from the sensors and the receiver and then commands flight control devices 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：CA2587835A1

公开(公告)日：2007-03-22

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：CA2773702A1

公开(公告)日：2005-11-03

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：CA2664103C

公开(公告)日：2014-11-04

申请号：CA2664103

申请日：2007-09-18

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： BUILTA KENNETH E

IPC: G05D1/08

Abstract: One embodiment of the present invention is a method for automatically reducing the effect of a component of an external force that is laterally incident on a rotorcraft. A signal of the rotorcraft indicative of and proportional to the component is monitored. An absolute value of the signal and a preset high limit are. compared. If the absolute value is greater than the preset high limit, manual heading control of the rotorcraft is disabled and the heading of the rotorcraft is adjusted with respect to the external force so as to decrease the lateral component of the external force experience by the rotorcraft.