公开(公告)号：WO2006130454A3

公开(公告)日：2007-08-09

申请号：PCT/US2006020377

申请日：2006-05-26

Applicant: BELL HELICOPTER TEXTRON INC ,  OLDROYD PAUL K

Inventor： OLDROYD PAUL K

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

CPC classification number: B64D15/12 ,  B32B5/024 ,  B32B5/12 ,  B32B5/26 ,  B32B2250/03 ,  B32B2250/20 ,  B32B2250/40 ,  B32B2255/02 ,  B32B2255/205 ,  B32B2260/023 ,  B32B2260/046 ,  B32B2262/101 ,  B32B2262/106 ,  B32B2307/54 ,  B32B2603/00 ,  G06F1/1628 ,  G06F1/1632 ,  H05B3/347 ,  H05B2203/007 ,  H05B2203/014 ,  H05B2203/017

Abstract: A rotor blade of a helicopter is presented. In an embodiment, the rotor blade (100) includes a body (105) ; and a heating mat (301) arranged in the body (105) and configured to supply heat to said body. The heating mat (301) includes a first (505) plurality of fibers (400) and a second (510) plurality of fibers (400) 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.

Abstract translation: 呈现直升机的转子叶片。 在一个实施例中，转子叶片（100）包括主体（105）; 以及布置在所述主体（105）中并且被配置为向所述主体供应热量的加热垫（301）。 加热垫（301）包括电连接到第一多根纤维的第一（505）多个纤维（400）和第二（510）多个纤维（400）。 所述第一多根纤维相对于垂直于所述主体的纵向方向的第一方向限定小于约+ 45°的正角度。 第二多根纤维相对于第一方向限定大于约-45°的负角度。

公开(公告)号：CA2972528C

公开(公告)日：2019-07-09

申请号：CA2972528

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: In some embodiments, an aircraft includes a flying frame having an airframe, a propulsion system attached to the airframe and a flight control system operably associated with the propulsion system wherein, the flying frame has a vertical takeoff and landing mode and a forward flight mode. A pod assembly is selectively attachable to the flying frame such that the flying frame is rotatable about the pod assembly wherein, the pod assembly remains in a generally horizontal attitude during vertical takeoff and landing, forward flight and transitions there between.

公开(公告)号：CA2967974A1

公开(公告)日：2017-11-21

申请号：CA2967974

申请日：2017-05-18

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： FOSKEY CHRISTOPHER ,  BURNETT MICHAEL ,  BOSWORTH JEFFREY ,  PAULSON JARED ,  MCINTYRE JOEL ,  OLDROYD PAUL K

IPC: B64C27/28 ,  B64C11/26 ,  B64C27/473

Abstract: A tiltrotor aircraft includes a fuselage, a wing member extending from the fuselage, an engine disposed relative to the wing member and a proprotor mechanically coupled to the engine. The proprotor includes a plurality of proprotor blade assemblies each including a spar and a sheath extending spanwise along the spar forming the leading edge of the proprotor blade assembly. The spar has a root section, a main section and a tip section. The spar has a generally oval cross section at radial stations along the main section and a first edge having a structural bias relative to a generally oppositely disposed second edge at the radial stations along the main section.

公开(公告)号：CA2843930C

公开(公告)日：2017-06-20

申请号：CA2843930

申请日：2014-02-21

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： OLDROYD PAUL K ,  HETHCOCK JAMES D JR ,  MCNEILL DAVID B

IPC: B29C53/60

Abstract: A method of making a composite core can include configuring a plurality of mandrels to have a desired thermal expansion characteristic, placing a composite material around each mandrel, placing the plurality of mandrels in a tool, the tool being configured to constrain the plurality of mandrels as the mandrels experience a thermal expansion, heating the mandrels so that the mandrels thermally expand, thereby applying a pressure to the composite material during a cure cycle, and then cooling and separating the mandrels from the composite core. The mandrel is configured as an internal form for making a tube member of a composite core.

公开(公告)号：CA2844020A1

公开(公告)日：2014-09-01

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：CA2609119C

公开(公告)日：2014-02-11

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 (100) includes a body (105) ; and a heating mat (301) arranged in the body (105) and configured to supply heat to said body. The heating mat (301) includes a first (505) plurality of fibers (400) and a second (510) plurality of fibers (400) 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：DE08728622T1

公开(公告)日：2011-04-21

申请号：DE08728622

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

公开(公告)号：CA2967974C

公开(公告)日：2019-06-04

申请号：CA2967974

申请日：2017-05-18

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： FOSKEY CHRISTOPHER ,  BURNETT MICHAEL ,  BOSWORTH JEFFREY ,  PAULSON JARED ,  MCINTYRE JOEL ,  OLDROYD PAUL K

IPC: B64C27/28 ,  B64C11/26 ,  B64C27/473

Abstract: A tiltrotor aircraft includes a fuselage, a wing member extending from the fuselage, an engine disposed relative to the wing member and a proprotor mechanically coupled to the engine. The proprotor includes a plurality of proprotor blade assemblies each including a spar and a sheath extending spanwise along the spar forming the leading edge of the proprotor blade assembly. The spar has a root section, a main section and a tip section. The spar has a generally oval cross section at radial stations along the main section and a first edge having a structural bias relative to a generally oppositely disposed second edge at the radial stations along the main section.

公开(公告)号：CA3042471A1

公开(公告)日：2018-01-01

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: An aircraft (10) includes a flying frame (12) having an airframe (26), a propulsion system (34) attached to the airframe (26) and a flight control system (68) operably associated with the propulsion system (34) wherein, the flying frame (12) has a vertical takeoff and landing mode and a forward flight mode. A pod assembly (70) is selectively attachable to the flying frame (12) such that the flying frame (12) is rotatable about the pod assembly (70) wherein, the pod assembly (70) remains in a generally horizontal attitude during vertical takeoff and landing, forward flight and transitions therebetween.

公开(公告)号：CA2844136C

公开(公告)日：2017-09-05

申请号：CA2844136

申请日：2014-02-26

Applicant: BELL HELICOPTER TEXTRON INC

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

IPC: B29C70/30 ,  B29C63/12

Abstract: A method of manufacturing a composite core can include: wrapping a mandrel in a mandrel wrapping process by securing a mandrel with a winding jig; orienting the composite material at a wrap angle to the mandrel; and depositing the composite material around a circumference of the mandrel. The method can further include assembling the wrapped mandrels in a tool and applying a pressure to the composite material during a curing cycle.