公开(公告)号：US20180362145A1

公开(公告)日：2018-12-20

申请号：US15843039

申请日：2017-12-15

Applicant: Bell Helicopter Textron Inc.

Inventor： Christopher E. Foskey ,  Brendan P. Lanigan

IPC: B64C11/18 ,  B64C11/24

Abstract: In a first aspect, there is a method for improving a lift to drag ratio of a rotor blade, including providing a blade member having a leading edge and a trailing edge; providing a leading edge extension member; and coupling the leading edge extension member to a portion of the leading edge of the blade member to form the rotor blade. In a second aspect, there is a rotor blade including a blade member having a leading edge, and a trailing edge; and a leading edge extension member disposed on the leading edge of the blade member, wherein the leading edge extension member is configured to extend the chord length of at least a portion of the rotor blade. In a third aspect, there is a leading edge extension member for a rotor blade including a convex exterior surface configured to extend at least a portion of the chord length of the rotor blade.

公开(公告)号：US20180072409A1

公开(公告)日：2018-03-15

申请号：US15815482

申请日：2017-11-16

Applicant: Bell Helicopter Textron Inc.

Inventor： Christopher E. Foskey ,  Michael J. Southerland

IPC: B64C27/35 ,  B64C29/00 ,  B64C11/04 ,  B64C27/00 ,  F16F1/38

CPC classification number: B64C27/35 ,  B64C11/04 ,  B64C27/001 ,  B64C29/0033 ,  F16F1/38

Abstract: In some embodiments, a rotorcraft may include a yoke, a blade, a spindle associated with the yoke, and an elastomeric bearing assembly. The center length of the spindle may define a center axis that passes through a center of the elastomeric bearing assembly. The elastomeric bearing assembly may contain a housing coupled to the blade and disposed around the center axis that is configured to rotate in relation to the center axis. The elastomeric bearing assembly may contain an elastomeric shear bearing that has an interior portion coupled to the spindle and an exterior portion coupled to the housing. The elastomeric bearing assembly may contain an elastomeric centrifugal force bearing pressed against the housing. The shear bearing may be configured to counteract a torsional force, and the centrifugal force bearing may be configured to counteract a compression force.

公开(公告)号：US09873507B2

公开(公告)日：2018-01-23

申请号：US14630382

申请日：2015-02-24

Applicant: Bell Helicopter Textron Inc.

Inventor： Christopher E. Foskey ,  Michael J. Southerland

IPC: B64C27/35 ,  B64C11/04 ,  B64C29/00 ,  B64C27/00 ,  F16F1/38

CPC classification number: B64C27/35 ,  B64C11/04 ,  B64C27/001 ,  B64C29/0033 ,  F16F1/38

Abstract: In some embodiments, a rotorcraft may include a yoke, a blade, a spindle associated with the yoke, and an elastomeric bearing assembly. The center length of the spindle may define a center axis that passes through a center of the elastomeric bearing assembly. The elastomeric bearing assembly may contain a housing coupled to the blade and disposed around the center axis that is configured to rotate in relation to the center axis. The elastomeric bearing assembly may contain an elastomeric shear bearing that has an interior portion coupled to the spindle and an exterior portion coupled to the housing. The elastomeric bearing assembly may contain an elastomeric centrifugal force bearing pressed against the housing. The shear bearing may be configured to counteract a torsional force, and the centrifugal force bearing may be configured to counteract a compression force.

公开(公告)号：US09476312B2

公开(公告)日：2016-10-25

申请号：US13841390

申请日：2013-03-15

Applicant: Bell Helicopter Textron Inc.

Inventor： Christopher E. Foskey ,  Frank B. Stamps

IPC: B63H1/06 ,  F01D7/00 ,  B64C27/605 ,  B64C27/72

CPC classification number: F01D7/00 ,  B64C27/605 ,  B64C27/72 ,  B64C2027/7216 ,  Y02T50/34 ,  Y10T29/49316

Abstract: An apparatus comprising a hub configured to couple to a mast, a grip configured to couple to the hub and a rotor blade, a pitch actuator coupled to the grip and configured to change a pitch of the rotor blade relative to the mast, and a delta-3 restraint coupled to the pitch actuator, wherein the delta-3 restraint is fixed relative to the mast. An apparatus comprising a hub configured to couple to a mast, a grip configured to couple to the hub and a rotor blade, a pitch actuator coupled to the grip and configured to change a pitch of the rotor blade relative to the mast, and a delta-3 restraint coupled to the pitch actuator, wherein the delta-3 restraint is configured to control the pitch of the blade relative to the mast when the pitch actuator fails, and wherein the delta-3 restraint provides an instantaneous blade pitch-flap coupling response.

Abstract translation: 一种装置，包括被配置成联接到桅杆的毂，配置成联接到轮毂和转子叶片的把手，连接到把手并被配置为相对于桅杆改变转子叶片的桨距的俯仰致动器，以及三角形 -3约束，其耦合到桨距致动器，其中，Δ-3约束相对于桅杆固定。 一种装置，包括被配置成联接到桅杆的毂，配置成联接到轮毂和转子叶片的把手，连接到把手并被配置为相对于桅杆改变转子叶片的桨距的俯仰致动器，以及三角形 -3限制器，其耦合到所述桨距致动器，其中所述Δ-3约束被配置为当所述桨距致动器故障时控制所述叶片相对于所述桅杆的桨距，并且其中所述Δ-3约束提供瞬时桨叶桨距翼片联接响应 。

公开(公告)号：US20150239555A1

公开(公告)日：2015-08-27

申请号：US14630382

申请日：2015-02-24

Applicant: Bell Helicopter Textron Inc.

Inventor： Christopher E. Foskey ,  Michael J. Southerland

IPC: B64C27/35 ,  B64C27/46

CPC classification number: B64C27/35 ,  B64C11/04 ,  B64C27/001 ,  B64C29/0033 ,  F16F1/38

Abstract: In some embodiments, a rotorcraft may include a yoke, a blade, a spindle associated with the yoke, and an elastomeric bearing assembly. The center length of the spindle may define a center axis that passes through a center of the elastomeric bearing assembly. The elastomeric bearing assembly may contain a housing coupled to the blade and disposed around the center axis that is configured to rotate in relation to the center axis. The elastomeric bearing assembly may contain an elastomeric shear bearing that has an interior portion coupled to the spindle and an exterior portion coupled to the housing. The elastomeric bearing assembly may contain an elastomeric centrifugal force bearing pressed against the housing. The shear bearing may be configured to counteract a torsional force, and the centrifugal force bearing may be configured to counteract a compression force.

Abstract translation: 在一些实施例中，旋翼航空器可以包括轭，叶片，与轭架相关的心轴和弹性轴承组件。 主轴的中心长度可以限定穿过弹性体轴承组件的中心的中心轴线。 弹性体轴承组件可以包含联接到叶片并且围绕中心轴线设置的壳体，该壳体构造成相对于中心轴线旋转。 弹性体轴承组件可以包含弹性体剪切轴承，其具有联接到心轴的内部部分和联接到壳体的外部部分。 弹性体轴承组件可以包含压靠壳体的弹性体离心力轴承。 剪切轴承可以构造成抵抗扭转力，并且离心力轴承可被构造成抵消压缩力。