US 2014/0151506 A1 · HIGHLY INTEGRATED STRUCTURE INCLUDING LEADING AND TRAILING EDGE RIBS FOR AN AIRCRAFT LIFTING SURFACE

Abstract

The invention provides an aircraft lifting surface with a monolithic main supporting structure (14) of a composite material comprising an upper skin (21) including at least a part of the upper aerodynamic profile of the leading edge (11) and/or of the trailing edge (15), a lower skin, a front spar (18), a rear spar (20), a plurality of leading edge ribs and/or a plurality of trailing edge ribs. This main supporting structure allows a weight and cost reduction of aircraft lifting surfaces. The invention also provides a manufacturing method of said monolithic main supporting structure (14).

Claims12

Dependent claims

Aircraft lifting surface comprising a main supporting structure (14) and leading and trailing edges (11, 15);

the main supporting structure (14) comprising an upper skin (21), a lower skin (23), a front spar (18) and a rear spar (20) of a composite material, characterized in that:
the main supporting structure (14) also comprises a plurality of leading edge ribs and/or a plurality of trailing edge ribs of a composite material;
the upper skin (21) includes at least a part of the upper aerodynamic profile of the leading edge (11) and/or of the trailing edge (15);
the main supporting structure (14) is a monolithic structure.

1 more element

Method of manufacturing a main supporting structure (14) of an aircraft lifting surface comprising an upper skin (21), a lower skin (23), a front spar (18), a rear spar (20), a plurality of leading edge ribs and/or a plurality of trailing edge ribs;

the upper skin (21) including part of the aerodynamic profile of the leading edge (11) and/or of the trailing edge (15);
the method comprising the following steps:
a) providing a set of laminated preforms of a composite material for forming said main supporting structure (14), each laminated preform being configured to form a part of it;
b) arranging said laminated preforms in a curing assembly (40) comprising a first set of tools for forming the closed part of the main supporting structure (14) and a second set of tools for forming the open part of the main supporting structure (14);
c) subjecting the curing assembly (40) to an autoclave cycle to co-cure said laminated preforms;
d) demoulding the first set of tools in a spanwise direction and the second set of tools in a chordwise direction.

3 more elements

Dependencies are inferred from the claim text.

Facts

Application

14/086,424Filed 21 Nov 2013

Priority

EP 12382459.122 Nov 2012

Published

5 Jun 2014

Term ends

Not estimatedThe source records don’t support an estimate.

Classification15 codes

B29C 70/302
Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould,…:…
B29C 35/0238
Using pressure vessels, e.g. autoclaves, vulcanising pans: presses provided with pressure vessels, e.g. steam chambers
B29D 99/0014
Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings: provided with ridges or ribs, e.g. joined ribs
B64C 3/182
Spars; Ribs; Stringers: stringers, longerons

Highly integrated structure including leading and trailing edge ribs for an aircraft lifting surface

Life of this patent

Highly integrated structure including leading and trailing edge ribs for an aircraft lifting surface

Life of this patent

Abstract

Claims12