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公开(公告)号：US11014656B2
公开(公告)日：2021-05-25
申请号：US15627819
申请日：2017-06-20
Applicant: Bell Helicopter Textron Inc.
Inventor： Jared Mark Paulson , Bryan Marshall , Christopher E. Foskey
Abstract: The present invention includes a balancing system that includes a weight box, mounted substantially within the rotor-blade spar, flush with a rotor-blade spar outer surface, operably accessible from a rotor-blade tip, and retained within the rotor-blade spar by a weight-box retention pin, one or more weight-box contact surfaces bonded to a rotor-blade-spar inner surface, or a weight-box lip providing a bearing contact with an edge of a spar rotor-blade spar cutout; and a weight package attached to the weight box, the weight package including a weight-box cover, two or more weight guide-rods attached to the weight-box cover, wherein one of the two or more weight guide-rods is positioned forward of a pitch change axis or center of twist and wherein one of the two weight guide-rods is positioned aft of the pitch change axis or center of twist, and one or more balance weights mounted on the weight guide-rods.
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公开(公告)号：US20200223532A1
公开(公告)日：2020-07-16
申请号：US16247736
申请日：2019-01-15
Applicant: Bell Helicopter Textron Inc.
Inventor： Jared Mark Paulson
Abstract: A spar assembly has a spar having a tip comprising a most outboard portion of the spar, a root comprising a most inboard portion of the spar, a main section disposed inboard relative to the tip, and a middle section disposed inboard relative to the main section. The spar also has a transition section disposed between the main section and the middle section and the transition section has an outboard interface cross-sectional shape and an inboard cross-sectional shape that is different than the outboard interface cross-sectional shape.
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3.发明申请公开(公告)号：US20190185141A1
公开(公告)日：2019-06-20
申请号：US15845928
申请日：2017-12-18
Applicant: Bell Helicopter Textron Inc.
Inventor： Jared Mark Paulson , Tyler Wayne Baldwin , Kyle Thomas Cravener
Abstract: A folding rotor blade assembly for a tiltrotor aircraft comprising a rotor blade pivotally connected to a yoke with dual concentric blade bolts having a common central axis providing a pivotal axis inboard of an outboard shear bearing. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.
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公开(公告)号：US10239604B2
公开(公告)日：2019-03-26
申请号：US15161215
申请日：2016-05-21
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher Foskey , Michael Burnett , Jeffrey Bosworth , Jared Mark Paulson , Joel McIntyre , Paul K. Oldroyd
IPC: B64C11/26 , B64C29/00 , B64C11/24 , 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.
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公开(公告)号：US20190071185A1
公开(公告)日：2019-03-07
申请号：US15694666
申请日：2017-09-01
Applicant: Bell Helicopter Textron Inc.
Inventor： Jared Mark Paulson , Jeffrey Paul Nissen
Abstract: An ice protection system is configured for a rotor blade having a leading edge along at least a portion of a spanwise length extending between a root portion and a tip portion. The system has an electric spanwise anti-ice heater configured for placement on the leading edge of the blade and a first electric spanwise de-ice heater adjacent the anti-ice heater and having varying chordwise dimensions. The de-ice heater is configured for placement on an upper surface of the blade or a lower surface of the blade. Electrical connectors for each heater are configured for connection near the root portion of the blade to a source of electrical power.
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Patent Agency Ranking
公开(公告)号：US20200039633A1
公开(公告)日：2020-02-06
申请号：US16055121
申请日：2018-08-05
Applicant: Bell Helicopter Textron Inc.
Inventor： Kyle Thomas Cravener , Tyler Wayne Baldwin , Jared Mark Paulson
Abstract: A rotor blade locking assembly for locking a rotor blade in a deployed position. The rotor blade locking assembly comprises a locking mechanism configured to be coupled to a blade grip. The locking mechanism comprises a latch and an actuator configured to cause the latch to move between an unlocked position and a locked position. The assembly comprises a locking plate configured to be coupled to the rotor blade. The locking plate comprises a bearing surface configured to bear against a contact surface of the latch, when the latch is in the locked position.
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公开(公告)号：US20200031086A1
公开(公告)日：2020-01-30
申请号：US16048869
申请日：2018-07-30
Applicant: Bell Helicopter Textron Inc.
Inventor： Jared Mark Paulson , Mark Mays , Michael Christopher Burnett
IPC: B32B1/08 , B64C27/473 , B64C3/18 , B32B27/08
Abstract: Embodiments are directed to systems and methods for two or more cured composite assemblies that are bonded together to form a tubular composite structure, wherein each of the cured composite assemblies do not have a tubular shape. The tubular composite structure may form a spar for an aerodynamic component, for example. The two or more cured composite assemblies may comprise carbon or fiberglass composite materials or a combination of materials. Each of the cured composite assemblies may further comprise axial edges that are configured to be bonded to another of the cured composite assemblies, wherein the axial edges have a sloped shape. An adhesive agent may be applied on the axial edges for bonding two cured composite assemblies. Alternatively, or additionally, one or more fasteners may be used to attach the axial edges of at least two cured composite assemblies.
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公开(公告)号：US20190389569A1
公开(公告)日：2019-12-26
申请号：US16016280
申请日：2018-06-22
Applicant: Bell Helicopter Textron Inc.
Inventor： Jared Mark Paulson , Ken Shundo
Abstract: A folding rotor blade assembly includes a blade fold support and a blade-fold actuator system coupled to the blade fold support. The blade-fold actuator system includes a motor, a tab configured to selectively prevent rotation of a blade tang of a rotor blade, and a cam connected to the blade fold support and coupled to the motor, the cam configured to move the tab between a locked position that prevents rotation of the blade tang and an unlocked position that permits rotation of the blade tang.
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公开(公告)号：US20190185142A1
公开(公告)日：2019-06-20
申请号：US15845967
申请日：2017-12-18
Applicant: Bell Helicopter Textron Inc.
Inventor： Jared Mark Paulson , Tyler Wayne Baldwin , Kyle Thomas Cravener
Abstract: A folding rotor blade assembly for a tiltrotor aircraft comprising a rotor blade pivotally connected to a grip with dual concentric blade bolts having a common central axis providing a pivotal axis inboard of an outboard bearing. A folding spindle connects the outboard bearing to an outboard tip of a yoke. The outboard bearing and the spindle fold with the rotor blade relative to the yoke. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.
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公开(公告)号：US20170334548A1
公开(公告)日：2017-11-23
申请号：US15161215
申请日：2016-05-21
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher Foskey , Michael Burnett , Jeffrey Bosworth , Jared Mark Paulson , Joel McIntyre , Paul K. Oldroyd
CPC classification number: B64C11/26 , B64C11/24 , B64C27/473 , B64C29/0033 , B64C2027/4736
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.
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