公开(公告)号：US20210064720A1

公开(公告)日：2021-03-04

申请号：US16551126

申请日：2019-08-26

Applicant: The Boeing Company

Inventor： Forouzan Behzadpour ,  Patrick Bickford Stickler

IPC: G06F17/50 ,  B64D47/00

Abstract: A method, apparatus, and system for managing a composite part. An acceptable level of a warpage is identified for the composite part. The warpage for the composite part is a change in the composite part as manufactured that deviates from design specifications for the composite part. Orientations in a stacking sequence for plies in the composite part are selected that result in the composite part having the acceptable level of the warpage and a desired strength to form selected orientations. The composite part is manufactured using the selected orientations.

公开(公告)号：US20200282692A1

公开(公告)日：2020-09-10

申请号：US16296687

申请日：2019-03-08

Applicant: The Boeing Company

Inventor： Forouzan Behzadpour

IPC: B32B3/26 ,  B32B7/12 ,  B32B37/12

Abstract: An interleaved layer construction of a composite panel and a composite plank constructed of three sub-planks that are adhered together and secured to the panel stiffen and strengthen the panel.

公开(公告)号：US10723436B2

公开(公告)日：2020-07-28

申请号：US15676047

申请日：2017-08-14

Applicant: The Boeing Company

Inventor： Jiangtian Cheng ,  Forouzan Behzadpour

IPC: B64C3/18 ,  B64F5/10 ,  B29C43/24 ,  B29C70/44 ,  B29C43/00 ,  B29C48/00 ,  B29D99/00 ,  B29K105/12 ,  B29K501/12 ,  B29L31/30

Abstract: Methods and apparatus to increase strength and toughness of aircraft structural components are disclosed. An example apparatus includes a composite structure of an aircraft, a stringer coupled to the composite structure of the aircraft, where the stringer and the composite structure form a stringer radius gap. A gap filler is disposed in the stringer radius gap, which includes chopped fibers randomly distributed throughout an entire volume of the gap filler.

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：US20190047677A1

公开(公告)日：2019-02-14

申请号：US15676047

申请日：2017-08-14

Applicant: The Boeing Company

Inventor： Jiangtian Cheng ,  Forouzan Behzadpour

IPC: B64C3/18 ,  B64F5/10 ,  B29C47/00 ,  B29C43/24 ,  B29C43/00 ,  B29C70/44

CPC classification number: B64C3/182 ,  B29C43/003 ,  B29C43/24 ,  B29C48/022 ,  B29C70/443 ,  B29D99/0003 ,  B29K2105/12 ,  B29K2501/12 ,  B29L2031/3082 ,  B29L2031/3085 ,  B64F5/10

Abstract: Methods and apparatus to increase strength and toughness of aircraft structural components are disclosed. An example apparatus includes a composite structure of an aircraft, a stringer coupled to the composite structure of the aircraft, where the stringer and the composite structure form a stringer radius gap. A gap filler is disposed in the stringer radius gap, which includes chopped fibers randomly distributed throughout an entire volume of the gap filler.

公开(公告)号：US20190047676A1

公开(公告)日：2019-02-14

申请号：US15913488

申请日：2018-03-06

Applicant: The Boeing Company

Inventor： Forouzan Behzadpour ,  Jiangtian Cheng

IPC: B64C1/06 ,  B64C3/18 ,  B64F5/10

CPC classification number: B64C1/064 ,  B64C1/12 ,  B64C3/182 ,  B64C3/26 ,  B64C2001/0072 ,  B64F5/10

Abstract: Stringer stiffened composite panels having improved pull-off strength are disclosed. An example stringer includes a first surface, a second surface, an edge, and a chamfer. The second surface is located opposite the first surface and is to be coupled to a composite structure of an aircraft. The edge extends from the second surface toward the first surface. The chamfer extends from the first surface to the edge at an angle between twelve and eighteen degrees relative to the first surface.