公开(公告)号：US10696373B2

公开(公告)日：2020-06-30

申请号：US15264209

申请日：2016-09-13

Applicant: The Boeing Company

Inventor： Steven P. Walker ,  Forouzan Behzadpour ,  Gary D. Oakes ,  Ian E. Schroeder ,  Patrick B. Stickler ,  Jason H. Inouye

IPC: B64C3/18 ,  B64C1/26 ,  B64C3/26 ,  B64C1/00 ,  B64C1/06

Abstract: Aircraft wings and aircraft including such aircraft wings are disclosed. An example apparatus includes an aircraft wing having a first panel; a second panel; ribs coupled between the first and second panels; and stiffeners coupled between the ribs in a spanwise direction and to the first panel, the coupling between the stiffeners and the first panel to deter axial loads from being received by the stiffeners, the stiffeners to increase a compressional stability of the first panel, wherein the coupling between the stiffeners and the first panel are indirect couplings formed via clips, the couplings formed via the clips deter the axial loads from being received by the stiffeners while increasing the compressional stability of the first panel.

公开(公告)号：US20180346093A1

公开(公告)日：2018-12-06

申请号：US15610598

申请日：2017-05-31

Applicant: The Boeing Company

Inventor： David Wesley Trop ,  Patrick B. Stickler ,  William John Koch, IV ,  Benjamin Joseph Palmer

IPC: B64C3/18 ,  B64C3/26

Abstract: Aircraft, aircraft wings and associated shear ties are disclosed. An example apparatus includes a first panel coupled to a second panel to define a wing box; a rib disposed chordwise within the wing box; and a stringer disposed spanwise within the wing box immediately adjacent at least one of the first panel or the second panel, the rib including a shear tie including first and second legs extending in opposite directions, the first and second legs to be coupled to at least one of the first panel, the second panel, or the stringer.

公开(公告)号：US20180281923A1

公开(公告)日：2018-10-04

申请号：US15471422

申请日：2017-03-28

Applicant: The Boeing Company

Inventor： Steven P. Walker ,  Gregory M. Santini ,  Gary D. Oakes ,  Patrick B. Stickler

IPC: B64C3/26 ,  B64C1/12

Abstract: A skin panel configured for attachment to an aircraft structure is constructed of a composite material and has a continuous, smooth outer surface; a continuous, smooth inner surface that is configured for attachment to an aircraft structure; a peripheral edge that extends entirely around the skin panel and has a continuous, smooth surface and a plurality of cavities inside the material of the skin panel. The cavities reduce the weight of the skin panel without significantly detracting from the compression strength and tensile strength of the skin panel.