公开(公告)号：CA2609119A1

公开(公告)日：2006-12-07

申请号：CA2609119

申请日：2006-05-26

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： OLDROYD PAUL K

IPC: B64D15/12 ,  B32B5/12 ,  H05B3/20 ,  H05B3/34

Abstract: A rotor blade of a helicopter is presented. In an embodiment, the rotor blade includes a body; and a heating mat arranged in the body and configured to supply heat to said body. The heating mat includes a first plurality of fibers and a second plurality of fibers electrically connected to the first plurality of fibers. The first plurality of fibers define a positive angle smaller than about +45° relative to a first direction perpendicular to a longitudinal direction of the body. The second plurality of fibers define a negative angle greater than about -45° relative to the first direction.

公开(公告)号：CA2972527C

公开(公告)日：2019-09-17

申请号：CA2972527

申请日：2017-06-30

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： OLDROYD PAUL K ,  MCCULLOUGH JOHN RICHARD

IPC: B64C29/02 ,  B64C27/08 ,  B64C27/26 ,  B64C39/00 ,  B64D27/40

Abstract: An aircraft haying a vertical takeoff and landing fight mode and a forward flight mode. The aircraft includes an airframe and a versatile propulsion system attached to the airframe. The versatile propulsion system includes a plurality of propulsion assemblies. A flight control system is operable to independently control the propulsion assemblies. The propulsion assemblies are interchangeably attachable to the airframe such that the aircraft has a liquid fuel flight mode and an electric flight mode. In the liquid fuel flight mode, energy is provided to each of the propulsion assemblies from a liquid fuel. In the electric flight mode, energy is provided to each of the propulsion assemblies from an electric power source.

公开(公告)号：CA3050137A1

公开(公告)日：2018-01-01

申请号：CA3050137

申请日：2017-06-30

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： OLDROYD PAUL K ,  MCCULLOUGH JOHN RICHARD

IPC: B64C29/02 ,  B64C27/08 ,  B64C27/26 ,  B64C39/00 ,  B64D27/40

Abstract: An aircraft (10) having a vertical takeoff and landing fight mode and a forward flight mode. The aircraft (10) includes an airframe (12) and a versatile propulsion system attached to the airframe (12). The versatile propulsion system includes a plurality of propulsion assemblies (26a-d). A flight control system (40) is operable to independently control the propulsion assemblies (26a-d). The propulsion assemblies (26a-d) are interchangeably attachable to the airframe (12) such that the aircraft (10) has a liquid fuel flight mode and an electric flight mode. In the liquid fuel flight mode, energy is provided to each of the propulsion assemblies (26a-d) from a liquid fuel. In the electric flight mode, energy is provided to each of the propulsion assemblies (26a-d) from an electric power source.

公开(公告)号：CA2972527A1

公开(公告)日：2018-01-01

申请号：CA2972527

申请日：2017-06-30

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： OLDROYD PAUL K ,  MCCULLOUGH JOHN RICHARD

IPC: B64C29/02 ,  B64C27/08 ,  B64C27/26 ,  B64C39/00 ,  B64D27/40

Abstract: An aircraft haying a vertical takeoff and landing fight mode and a forward flight mode. The aircraft includes an airframe and a versatile propulsion system attached to the airframe. The versatile propulsion system includes a plurality of propulsion assemblies. A flight control system is operable to independently control the propulsion assemblies. The propulsion assemblies are interchangeably attachable to the airframe such that the aircraft has a liquid fuel flight mode and an electric flight mode. In the liquid fuel flight mode, energy is provided to each of the propulsion assemblies from a liquid fuel. In the electric flight mode, energy is provided to each of the propulsion assemblies from an electric power source.

公开(公告)号：CA2844020C

公开(公告)日：2017-03-28

申请号：CA2844020

申请日：2014-02-25

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： KENDRICK PHILLIP A ,  OLDROYD PAUL K ,  ARMSTRONG LEVI H ,  OBERLE ELIZABETH

IPC: B29C70/30 ,  B29C70/08 ,  B32B3/12 ,  C08J5/12

Abstract: A method of manufacturing a composite core including wrapping each of a plurality of mandrels with a composite material and stacking the plurality of mandrels wrapped with the composite material in a tool. A heated fluid may be moved through an interior of the plurality of mandrels to controllably heat the composite material in a curing process. A pressure may be controllably applied to the tool with a bladder during a curing process. A tooling system for manufacturing a composite core is also discussed.

公开(公告)号：CA2820004A1

公开(公告)日：2012-07-05

申请号：CA2820004

申请日：2010-12-28

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： MCCULLOUGH JOHN R ,  CARLSON DAVID GORDON ,  HETHCOCK JAMES DONN ,  OLDROYD PAUL K ,  MAY CARL A

IPC: B64C3/18

Abstract: A structural joint includes a first member having a first base portion and a first leg portion. The structural joint further includes a second member having a second base portion and a second base portion. The first base portion and the second base portion are coupled together at an overlapping portion. The first leg portion and the second leg portion form a cavity for structurally coupling to a structural member.

公开(公告)号：CA2712638A1

公开(公告)日：2009-08-06

申请号：CA2712638

申请日：2008-01-31

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： HIROS TRICIA ,  STAMPS FRANK BRADLEY ,  TISDALE PAT ,  MEASOM RON ,  BRASWELL JIM ,  CAMPBELL TOM ,  OLDROYD PAUL K ,  BARBOUR RICHARD

IPC: B64C27/00

Abstract: A method of making a rotor yoke includes preparing a cured composite rotor yoke preform on a single-sided curing tool and machining at least one portion of the cured rotor yoke preform to form a rotor yoke. In one embodiment, preparing the cured composite rotor yoke is accomplished by applying successive layers of uncured polymeric composite material to a single-sided tool in a configuration to produce an uncured rotor yoke preform; disposing a semi-rigid caul to an untooled side of the uncured rotor yoke preform; enclosing the uncured rotor yoke preform and the semi-rigid caul by substantially hermetically sealing a vacuum bag to the tool; substantially evacuating a volume defined by the vacuum bag and the tool of air; and heating the uncured rotor yoke preform, sometimes under pressure, to form the cured composite rotor yoke preform.

公开(公告)号：AU2006252729A1

公开(公告)日：2006-12-07

申请号：AU2006252729

申请日：2006-05-26

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： OLDROYD PAUL K

IPC: B64D15/12 ,  B32B5/12 ,  H05B3/20 ,  H05B3/34

Abstract: A rotor blade of a helicopter is presented. In an embodiment, the rotor blade includes a body; and a heating mat arranged in the body and configured to supply heat to said body. The heating mat includes a first plurality of fibers and a second plurality of fibers electrically connected to the first plurality of fibers. The first plurality of fibers define a positive angle smaller than about +45° relative to a first direction perpendicular to a longitudinal direction of the body. The second plurality of fibers define a negative angle greater than about -45° relative to the first direction.

公开(公告)号：CA3042471C

公开(公告)日：2021-11-16

申请号：CA3042471

申请日：2017-06-30

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： MCCULLOUGH JOHN RICHARD ,  OLDROYD PAUL K

IPC: B64C29/02 ,  B64C27/08 ,  B64C27/26 ,  B64C27/30 ,  B64C39/00 ,  B64D1/22 ,  B64D5/00

Abstract: A transportation services method comprises receiving a request for transportation of a pod assembly. Characterized in the steps of coupling the pod assembly (70, 170) to a flying frame (12); rotating the flying frame including the at least two propulsion assemblies (36, 38, 40, 42, 44, 46, 48, 50, 136, 138, 140, 142, 144, 146, 148, 150) directly coupled to each wing (14, 16, 114, 116) relative to the pod assembly to transition the flying frame between a vertical takeoff and landing mode wherein the first wing is forward of the pod assembly and the second wing is aft of the pod assembly and a forward flight mode wherein the first wing is below the pod assembly and the second wing is above the pod assembly; and decoupling the pod assembly at the destination. The rotation to the forward flight mode allowing the slipstream from the propellers to strike the wing on its smallest dimension, thus improving vertical thrust efficiency as compared to tiltrotor aircraft.

公开(公告)号：CA2957557C

公开(公告)日：2019-04-02

申请号：CA2957557

申请日：2017-02-08

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： CARLSON DAVID G ,  MCCULLOUGH JOHN R ,  OLDROYD PAUL K ,  MAY CARL A ,  KOOIMAN JAMES E

IPC: B64C3/18 ,  B64C1/06 ,  B64F5/10

Abstract: A rib assembly for an aircraft wing including a rib web having a top and a bottom, the rib web includes a first laminate, a second laminate, and a honeycomb panel having an array of large cells disposed between the first laminate and the second laminate, each cell having a width of at least 1 cm; and a plurality of skin flanges for fixedly attaching the rib web to a skin of the wing, each skin flange has a base member having a first portion and a second portion and a vertical member extending from the base member. The rib assembly overcomes problems associated with conventional rib assemblies that require a large number of fasteners and support components, which limits fuel space in the wing.