公开(公告)号：US20250002135A1

公开(公告)日：2025-01-02

申请号：US18344033

申请日：2023-06-29

Applicant: The Boeing Company

Inventor： Paul W. Dees ,  William M. Sampedro-Thompson ,  Bret Alan Bowers ,  Robert E. Grip ,  Neal A. Harrison ,  Alan C. Simonini ,  Theodore K. Rothaupt

IPC: B64C1/26

Abstract: Apparatus and articles of manufacture are disclosed of an aircraft comprising: a brace to support a wing of the aircraft, the brace including a first end coupled to the wing and a second end coupled to a fuselage of the aircraft, the brace including: a strut extending between the first end and the second end; and an airfoil having a cavity containing the strut.

公开(公告)号：US10040537B2

公开(公告)日：2018-08-07

申请号：US14598002

申请日：2015-01-15

Applicant: The Boeing Company

Inventor： Jordan Charles ,  William M. Sampedro-Thompson ,  Jessica L. Watkins ,  Ryan Christopher Roache ,  Michael John Gamble ,  Tyler W. Downey ,  Wendell C. K. Choy ,  Gregory M. Santini

IPC: B24C1/06 ,  B64C3/18 ,  B64C1/06 ,  B64C1/12 ,  B64C3/20 ,  B64C3/26

Abstract: A wing may include a wing skin, a laminate composite first stringer, a rib, and at least one fastener. A majority of the first stringer may be characterized by a stacked plurality of generally planar plies of reinforcement material structurally joined as a stack to an interior surface of the wing skin and extending generally parallel to the interior surface and a span-wise direction of the wing along a substantial portion of the interior surface. The first stringer may have a generally solid trapezoidal cross section when viewed in a plane that is generally perpendicular to the span-wise direction. The rib may be positioned adjacent the interior surface, and may extend generally perpendicular to the span-wise direction. The trapezoidal cross section may be interfaced with the rib flange. The fastener may extend through the wing skin, the trapezoidal cross section, and the rib flange.

公开(公告)号：US20160207607A1

公开(公告)日：2016-07-21

申请号：US14598002

申请日：2015-01-15

Applicant: The Boeing Company

Inventor： Jordan Charles ,  William M. Sampedro-Thompson ,  Jessica L. Watkins ,  Ryan Christopher Roache ,  Michael John Gamble ,  Tyler W. Downey ,  Wendell C.K. Choy ,  Gregory M. Santini

IPC: B64C3/18 ,  B64C3/26

CPC classification number: B64C3/187 ,  B64C1/064 ,  B64C1/12 ,  B64C3/182 ,  B64C3/20 ,  B64C3/26 ,  Y02T50/43

Abstract: A wing may include a wing skin, a laminate composite first stringer, a rib, and at least one fastener. A majority of the first stringer may be characterized by a stacked plurality of generally planar plies of reinforcement material structurally joined as a stack to an interior surface of the wing skin and extending generally parallel to the interior surface and a span-wise direction of the wing along a substantial portion of the interior surface. The first stringer may have a generally solid trapezoidal cross section when viewed in a plane that is generally perpendicular to the span-wise direction. The rib may be positioned adjacent the interior surface, and may extend generally perpendicular to the span-wise direction. The trapezoidal cross section may be interfaced with the rib flange. The fastener may extend through the wing skin, the trapezoidal cross section, and the rib flange.

Abstract translation: 翼可以包括机翼皮肤，层压复合材料第一纵梁，肋和至少一个紧固件。 大多数第一纵梁的特征可以是堆叠的多个大体平坦的增强材料层，其作为堆叠结构地结合到翼面的内表面，并且大致平行于内表面延伸并且翼的跨度方向 沿着内表面的大部分。 当在大致垂直于跨度方向的平面中观察时，第一纵梁可以具有通常为实心的梯形横截面。 肋可以邻近内表面定位，并且可以大致垂直于跨度方向延伸。 梯形横截面可以与肋凸缘接合。 紧固件可以延伸穿过机翼皮肤，梯形横截面和肋凸缘。

公开(公告)号：US20240140610A1

公开(公告)日：2024-05-02

申请号：US17979060

申请日：2022-11-02

Applicant: THE BOEING COMPANY

Inventor： Druh Palma ,  Donald T. Powell ,  William M. Sampedro-Thompson

IPC: B64D27/26

CPC classification number: B64D27/26 ,  B64D2027/264

Abstract: A coupling system is configured to secure one or more struts to a wing of an aircraft. The coupling system includes one or more splice straps that secure the one or more struts to the wing. A method for securing one or more struts to a wing of an aircraft includes securing, by one or more splice straps, the one or more struts to the wing.

公开(公告)号：US20160159453A1

公开(公告)日：2016-06-09

申请号：US14560533

申请日：2014-12-04

Applicant: The Boeing Company

Inventor： Brian H. Korenaga ,  Robert G. Albers ,  Ian C. Burtord ,  William M. Sampedro-Thompson ,  David W. Evans

IPC: B64C1/06 ,  B32B37/18 ,  B64D45/00 ,  B32B37/12

CPC classification number: B64C1/064 ,  B29C67/0007 ,  B29C70/08 ,  B29D99/0003 ,  B29D99/0007 ,  B32B3/04 ,  B32B5/26 ,  B32B7/12 ,  B32B37/12 ,  B32B37/18 ,  B32B2260/021 ,  B32B2260/023 ,  B32B2262/101 ,  B32B2262/106 ,  B32B2556/00 ,  B32B2571/00 ,  B32B2603/00 ,  B32B2605/18 ,  B64C2001/0072 ,  B64D45/00 ,  B64F5/60 ,  Y02T50/43

Abstract: Systems and methods provide for edge protection and visual damage indication for a composite blade stringer. According to one aspect, an edge protection and visual indication system may be an edge treatment provided over an outer edge of a web of a composite blade stringer. The edge treatment may include a number of material layers encompassing the outer edge of the web and extending from a first surface of the web to a second surface of the web. The material layers may include a color contrasting layer and fiberglass layers. The material layers may alternatively include two overlapping, pre-cured angles.

Abstract translation: 系统和方法为复合叶片纵梁提供边缘保护和视觉损伤指示。 根据一个方面，边缘保护和视觉指示系统可以是在复合叶片纵梁的腹板的外边缘上提供的边缘处理。 边缘处理可以包括多个材料层，其包围幅材的外边缘并从幅材的第一表面延伸到幅材的第二表面。 材料层可以包括颜色对比层和玻璃纤维层。 材料层可以备选地包括两个重叠的预固化角度。