Method for manufacturing the trailing edge ribs and the bearing ribs of trailing edges of aircraft lifting surfaces

Abstract

A method for manufacturing the trailing edge ribs and the bearing ribs of trailing edges of aircraft lifting surfaces, in which the trailing edge ribs and the bearing ribs are made by joining simple C-shaped parts and/or simple L-shaped parts so as to obtain the final trailing edge ribs and bearing ribs. The manufacturing of the simple C-shaped parts uses the same tooling both for the trailing edge ribs and the bearing ribs, and the manufacturing of the simple L-shaped parts uses the same tooling both for the trailing edge ribs and the bearing ribs.

Claims

1. A method for manufacturing stability trailing edge ribs and bearing ribs of trailing edges of aircraft lifting surfaces with control surfaces, the bearing ribs configured to hold a hinge line of a control surface, comprising the steps: making the stability trailing edge ribs and the bearing ribs by joining C-shaped cross-section parts and/or L-shaped cross-section parts so as to obtain the final stability trailing edge ribs and the bearing ribs, manufacturing the C-shaped cross-section parts using the same tooling both for the stability trailing edge ribs and the bearing ribs, and/or manufacturing the L-shaped cross-section parts using the same tooling both for the stability trailing edge ribs and the bearing ribs, wherein the joining of C-shaped cross-section parts and/or L-shaped cross-section parts results in an I-shaped cross-section profile for the final stability trailing edge ribs and bearing ribs, comprising a central web, lower and upper flanges and a rear projection, wherein the joining of C-shaped cross-section parts and/or L-shaped cross-section parts results in final stability trailing edge ribs and bearing ribs in which the width of the upper flanges and the lower flanges is greater in the front than in the rear, wherein all the bearing ribs and the stability trailing edge ribs are made of the same material, wherein the material is thermoplastic resin reinforced with continuous carbon fiber, and the C-shaped cross-section parts and/or the L-shaped cross-section parts are joined by welding, wherein the joining of C-shaped cross-section parts and/or L-shaped cross-section parts results in final stability trailing edge ribs and bearing ribs in which a first lower flange of the lower flanges comprises a straight front section and an inclined section ascending toward the rear, and wherein the joining of C-shaped cross-section parts and/or L-shaped cross-section parts results in final stability trailing edge ribs and bearing ribs which additionally comprise a second lower flange of the lower flanges placed under the inclined section of the first lower flange that comprises a straight front section and an inclined section ascending toward the rear.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) FIG. 1 is a perspective view of an aircraft with its fuselage.

(2) FIG. 2 is a view of a known prior art HTP.

(3) FIG. 3 is a view of the general overview of a trailing edge of an HTP.

(4) FIG. 4 is a view of a prior art trailing edge showing the trailing edge ribs (TERs) and the bearing ribs (BRs).

(5) FIG. 5 is a schematic view of a trailing edge of the invention showing the positions for the trailing edge ribs (TERs) and the bearing ribs (BERs).

(6) FIGS. 6a to 6e show several views of a configuration of a preform for TERs/BRs of a trailing edge of the invention.

(7) FIGS. 7a to 7e show several views of a configuration of another preform for TERs/BRs of a trailing edge of the invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

(8) FIG. 1 shows an aircraft with its aircraft fuselage and the empennage which may embody the present invention. FIG. 2 shows a prior art horizontal tail plane of an aircraft showing the torsion boxes, the leading edges and the trailing edges with control surfaces. FIG. 3 is a general overview of a trailing edge 3 of an HTP; as it can be seen, the trailing edge 3 is the transition between the torsion box and the control surfaces. FIG. 4 is a detail of FIG. 3 (Detail A) showing a view of a portion of a prior art trailing edge 3 showing several trailing edge ribs (TERs) 1 and bearing ribs (BRs) 2 with different configurations.

(9) FIG. 5 is a schematic view of a trailing edge 3 showing the positions for the trailing edge ribs (TERs) 1 and the bearing edge ribs (BRs) 2, manufactured according to the method of the invention.

(10) FIGS. 6a to 6e and 7a to 7e show two configurations of TERs/BRs 1, 2 of a trailing edge 3, manufactured according to the method of the invention.

(11) In the method for manufacturing the TERs 1 and the BRs 2 of trailing edges 3 of aircraft lifting surfaces of the invention, the TERs 1 and the BRs 2 are made by joining simple C-shaped parts and/or simple L-shaped parts so as to obtain the final TERs 1 and BRs 2. The manufacturing of the simple C-shaped parts uses the same tooling both for the TERs 1 and the BRs 2, and the manufacturing of the simple L-shaped parts uses the same tooling both for the TERs 1 and the BRs 2.

(12) Both BRs 2 and TERs 1 are manufactured by joining parts with C-shape or L-shape. Accordingly, the invention comprises the manufacturing of those parts for all BRs 2 and TERs 1 using the same tooling, such that then they are joined to get a final part (BR 2 or TER 1) with the specific size and geometry needed.

(13) The bearing ribs 2 hold the hinge line attached to the rear spars of the torsion box, while the trailing edge ribs 1 provide stability to the structure of the trailing edge 3.

(14) The bearing ribs 2 and the trailing edge ribs 1 can have an “I” profile, comprising a central web 5, lower and upper flanges 6, 7 and a front projection 8.

(15) The width of the upper flanges 7 and the lower flanges 6 of the bearing ribs 2 and the trailing edge ribs 1 can be greater in the back than in the front, and one of the lower flanges 6 can comprise a straight back section 9 and an inclined section 10 ascending toward the front.

(16) The bearing ribs 2 and the trailing edge ribs 1 additionally may comprise a lower flange 6′ placed under the inclined section 10 of the lower flange 6 that comprises a straight back section 9 and an inclined section 10 ascending toward the front (FIGS. 7a to 7e).

(17) All the bearing ribs 2 and the trailing edge ribs 1 can be made of the same material.

(18) Materials used can be metal or any CFRP with thermoset or thermoplastic resin. Depending on the material selected, the joining technology could be one or more of the following: fastening, bonding, secondary bonding or thermoplastic welding.

(19) The preferred material is thermoplastic resin reinforced with continuous carbon fiber. This allows the following: forming in a modular tool the parts to be joined welding in between parts to form final BR 2 or TER 1 thermoplastics does not need an autoclave thermoplastics are recyclable.

(20) Although the present invention has been fully described in connection with preferred embodiments, it is evident that modifications may be introduced within the scope thereof, not considering this as limited by these embodiments, but by the contents of the following claims.

(21) While at least one exemplary embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms “comprise” or “comprising” do not exclude other elements or steps, the terms “a” or “one” do not exclude a plural number, and the term “or” means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.