公开(公告)号：US09919791B2

公开(公告)日：2018-03-20

申请号：US14687022

申请日：2015-04-15

Applicant: Gulfstream Aerospace Corporation

Inventor： Brenden Autry ,  Bryan Williams ,  Travis Cope ,  Susan Daggett ,  John McGuire ,  Michael McKee ,  Charles Aitken

IPC: B64C1/00 ,  B64C3/18 ,  B32B37/10 ,  B29C70/00 ,  B29C70/34 ,  B29D99/00

CPC classification number: B64C3/187 ,  B29C70/00 ,  B29C70/342 ,  B29D99/0014 ,  B32B37/1018 ,  B64C3/18 ,  B64C3/20 ,  Y02T50/43

Abstract: Stiffening structures, wing structures and methods for manufacturing stiffening structures are provided. In accordance with an exemplary embodiment, a stiffening structure includes a first longitudinal member, a second longitudinal member, and a first rib that extends from the first longitudinal member to the second longitudinal member and is integral with the first longitudinal member and the second longitudinal member. The first longitudinal member has a first wall, a second wall and a joining wall that joins the first wall and second wall. The first wall, the second wall and the joining wall form a space having a trapezoidal shape.

公开(公告)号：US20170043859A1

公开(公告)日：2017-02-16

申请号：US14824273

申请日：2015-08-12

Applicant: Gulfstream Aerospace Corporation

Inventor： Brenden Autry ,  Bryan Williams ,  Travis Cope ,  Susan Daggett ,  Mike McKee ,  Francis Russo ,  Charles Aitken

IPC: B64C3/28 ,  B64C23/06 ,  B64C9/00 ,  B64C3/26

CPC classification number: B64C3/28 ,  B32B1/00 ,  B32B3/263 ,  B32B5/024 ,  B32B5/06 ,  B32B5/26 ,  B32B7/12 ,  B32B2250/44 ,  B32B2260/021 ,  B32B2260/023 ,  B32B2260/046 ,  B32B2262/101 ,  B32B2262/106 ,  B32B2605/18 ,  B64C3/20 ,  B64C3/26 ,  B64C9/00 ,  B64C23/069 ,  Y02T50/164

Abstract: Trailing edge components of aircraft structures, aircraft structures comprising such trialing edge components, and methods of manufacturing such trailing edge components are provided. In an exemplary embodiment, a trailing edge component includes a first skin comprising a first plurality of plies of carbon fiber reinforced polymer material and having a first mating region. The first plurality of plies includes a first ply with a first drop-off edge in the first mating region. A second skin includes a second plurality of plies of carbon fiber reinforced polymer material and having a second mating region affixed to the first mating region.

Abstract translation: 提供了飞机结构的后缘部件，包括这种修剪边缘部件的飞行器结构以及制造这种后缘部件的方法。 在示例性实施例中，后缘部件包括第一皮肤，其包括第一多个碳纤维增强聚合物材料层并具有第一配合区域。 第一多个层包括在第一配合区域中具有第一下落边缘的第一层。 第二皮肤包括第二多个碳纤维增强聚合物材料层，并且具有固定到第一配合区域的第二配合区域。

公开(公告)号：US20160304187A1

公开(公告)日：2016-10-20

申请号：US14687022

申请日：2015-04-15

Applicant: Gulfstream Aerospace Corporation

Inventor： Brenden Autry ,  Bryan Williams ,  Travis Cope ,  Susan Daggett ,  John McGuire ,  Michael McKee ,  Charles Aitken

IPC: B64C3/18 ,  B32B37/10

CPC classification number: B64C3/187 ,  B29C70/00 ,  B29C70/342 ,  B29D99/0014 ,  B32B37/1018 ,  B64C3/18 ,  B64C3/20 ,  Y02T50/43

Abstract: Stiffening structures, wing structures and methods for manufacturing stiffening structures are provided. In accordance with an exemplary embodiment, a stiffening structure includes a first longitudinal member, a second longitudinal member, and a first rib that extends from the first longitudinal member to the second longitudinal member and is integral with the first longitudinal member and the second longitudinal member. The first longitudinal member has a first wall, a second wall and a joining wall that joins the first wall and second wall. The first wall, the second wall and the joining wall form a space having a trapezoidal shape.

Abstract translation: 提供了加强结构，翼结构和制造加强结构的方法。 根据示例性实施例，加强结构包括第一纵向构件，第二纵向构件和从第一纵向构件延伸到第二纵向构件的第一肋，并且与第一纵向构件和第二纵向构件 。 第一纵向构件具有连接第一壁和第二壁的第一壁，第二壁和接合壁。 第一壁，第二壁和连接壁形成具有梯形形状的空间。