阅读说明：本技术 制造飞机升力面后缘的后缘肋和支承肋的方法 (Method for producing trailing edge ribs and supporting ribs for the trailing edge of an aircraft lifting surface ) 是由 弗朗西斯科·哈维尔·霍诺拉托·鲁伊斯 杰西·哈维尔·瓦兹奎兹·卡斯特罗 恩立克·季纳尔多·弗纳恩 于 2019-07-05 设计创作，主要内容包括：制造飞机升力面后缘(3)的后缘肋(1)和支承肋(2)的方法,其中后缘肋(1)和支承肋(2)通过连接简单C形部件和/或简单L形部件制成,以获得最终的后缘肋(1)和支承肋(2),使得简单C形部件的制造使用用于后缘肋(1)和支承肋(2)的相同的工具,并且简单L形部件的制造使用用于后缘肋(1)和支承肋(2)的相同的工具。(Method for manufacturing a trailing edge rib (1) and a support rib (2) of an aircraft lifting surface trailing edge (3), wherein the trailing edge rib (1) and the support rib (2) are made by joining a simple C-shaped component and/or a simple L-shaped component to obtain the final trailing edge rib (1) and support rib (2), such that the manufacture of the simple C-shaped component uses the same tools for the trailing edge rib (1) and the support rib (2) and the manufacture of the simple L-shaped component uses the same tools for the trailing edge rib (1) and the support rib (2).)

1. Method for manufacturing a trailing edge rib (1) and a support rib (2) of an aircraft lifting surface trailing edge (3), characterized in that the trailing edge rib (1) and the support rib (2) are made by joining a simple C-shaped part and/or a simple L-shaped part to obtain the final trailing edge rib (1) and the support rib (2), so that the manufacture of the simple C-shaped part uses the same tools for the trailing edge rib (1) and the support rib (2) and the manufacture of the simple L-shaped part uses the same tools for the trailing edge rib (1) and the support rib (2).

2. Method for manufacturing a trailing edge rib (1) and a support rib (2) for an aircraft lifting surface trailing edge (3) according to claim 1, wherein all the support ribs (2) and the trailing edge rib (1) are made of the same material.

3. Method for manufacturing a trailing edge rib (1) and a support rib (2) for an aircraft lifting surface trailing edge (3) according to claim 1 or 2, wherein the simple C-shaped component and/or the simple L-shaped component are connected by fastening, gluing, secondary gluing or welding.

4. Method for manufacturing a trailing edge rib (1) and a support rib (2) for an aircraft lifting surface trailing edge (3) according to claim 2, wherein the material is a thermoplastic resin reinforced with continuous carbon fibres and the simple C-shaped part and/or the simple L-shaped part are connected by welding.

5. Method of manufacturing a trailing edge rib (1) and a support rib (2) of an aircraft lifting surface trailing edge (3) according to any of the preceding claims, wherein said connection of simple C-shaped parts and/or simple L-shaped parts results in an "I" profile of the final trailing edge rib (1) and support rib (2), comprising a central web (5), lower and upper flanges (6,7) and a front protrusion (8).

6. Method for manufacturing a trailing edge rib (1) and a support rib (2) for an aircraft lifting surface trailing edge (3) according to claim 5, wherein the connection of a simple C-shaped part and/or a simple L-shaped part results in a final trailing edge rib (1) and support rib (2), wherein the width of the upper flange (7) and the lower flange (6) is larger at the rear than at the front.

7. Method of manufacturing a trailing edge rib (1) and a support rib (2) of an aircraft lifting surface trailing edge (3) according to claim 6, wherein the connection of a simple C-shaped part and/or a simple L-shaped part results in a final trailing edge rib (1) and support rib (2), wherein one of the lower flanges (6) comprises a straight rear portion (9) and an inclined portion (10) rising towards the front.

8. Method of manufacturing a trailing edge rib (1) and a support rib (2) for an aircraft lifting surface trailing edge (3) according to claim 7, wherein said connection of a simple C-shaped part and/or a simple L-shaped part results in a final trailing edge rib (1) and support rib (2) which additionally comprises a lower flange (6') below said inclined portion (10) of said lower flange (6), which lower flange (6) comprises a straight rear portion (9) and an inclined portion (10) rising towards the front.

Technical Field

The invention relates to a method for producing trailing edge ribs and supporting ribs for the trailing edge of an aircraft lifting surface, using a modular production concept.

Background

Aircraft lifting surfaces, such as wings, Horizontal Tail Planes (HTPs) or Vertical Tail Planes (VTPs), typically include a torsion box as the primary support structure, leading and trailing edges with control surfaces (flaps, ailerons, elevators, rudders, etc.). An example of a known prior art HTP can be seen in fig. 2.

The trailing edge of the aircraft lifting surface is a critical element because it is the transition between the torque box and the control surface.

The trailing edge typically comprises an upper cover (placed on the upper side of the aircraft lifting surface) and a lower cover (placed on the lower side of the aircraft lifting surface), both of which are formed by a set of plates.

The set of plates corresponding to the lower cover, or at least a part of the set of plates, is typically connected to the aircraft lifting surface by a hinge, so that the plates constituting the lower cover can be opened to gain access to maintenance tasks for elements such as systems, actuators, fittings, etc.

The standard construction of the trailing edge comprises the two sets of plates already mentioned and a set of ribs extending between the upper and lower covers, which are connected to the torsion box at the points of coincidence with the torsion box ribs (for a multi-ribbed torsion box), although the number of ribs placed at the trailing edge is significantly smaller.

These ribs can be of two types, so-called Bearing Ribs (BR) and Trailing Edge Ribs (TER). Bearing ribs (also called hinge arms) support the hinge lines of the control surfaces, while trailing edge ribs are used to provide stability to the trailing edge structure.

Some prior art documents disclose aircraft lifting surfaces having trailing edges comprising ribs.

EP 2738086 a1 provides an aircraft lifting surface having a main supporting structure comprising upper and lower surfaces defining its aerodynamic profile, front and rear surfaces oriented towards the leading and trailing edges respectively, a first set of transverse ribs extending from the front surface to the rear surface and a second set of transverse ribs passing through the front and/or rear surface. The integration of the front and rear edge ribs in the main support structure allows the weight and cost of the aircraft lifting surface in this invention to be reduced. The invention also provides a manufacturing method of the main supporting structure.

EP 2735504 a1 provides an aircraft lifting surface with an integral main support structure of composite material comprising an upper skin comprising at least a part of the upper aerodynamic profile of the leading and/or trailing edge, a lower skin, a front spar, a rear spar, a plurality of leading edge ribs and/or a plurality of trailing edge ribs. The invention also provides a manufacturing method of the integral main supporting structure.

EP 2878435 a1 relates to an integral composite trailing edge and a method of manufacturing the same. The trailing edge includes an integrated main structure including an upper cover, a lower flange, and a set of ribs extending between the upper cover and the lower flange, and a set of sandwich-type lower plates connectable to the lower flange of the integrated main structure. The method comprises the following steps: a set of prepreg laminate preforms is provided on a set of tool modules having a hollow core such that each laminate constitutes a double C-shaped laminate preform having an upper part with a recess, the upper part forming in part an upper cover, two main flange parts forming in part ribs, and two second flanges forming lower flanges.

The Trailing Edge Rib (TER) and the support rib (BR) used in HTPs and VTPs are typically different in shape (i.e., the shape of TER is different from the shape of BR). For example, in an airbus a320 airplane, there are 9 TER and 6 BR on each side of the HTP, with the shape of the BR being different from the shape of the TER.

The Trailing Edge Ribs (TER) and support ribs (BR) in the HTP and VTP are also typically different from component to component (e.g., TER in HTP assumes a different configuration than TER in VTP), as are the size of the supported loads and design space.

One of the key top-level requirements in terms of potential cost savings in designing an aircraft empennage is versatility. It is therefore desirable to have a tail wing with improved versatility in its components.

Disclosure of Invention

It is therefore an object of the present invention to provide a method of manufacturing a trailing edge rib and a support rib for a trailing edge of an aircraft lifting surface, which solves the above-mentioned disadvantages and increases the versatility.

The invention provides a method for manufacturing a trailing edge rib and a support rib for a trailing edge of an aircraft lifting surface, wherein the trailing edge rib and the support rib are manufactured by joining simple C-shaped parts and/or simple L-shaped parts to obtain the final trailing edge rib and support rib, such that the manufacture of the simple C-shaped parts uses the same tools for the trailing edge rib and the support rib, and the manufacture of the simple L-shaped parts uses the same tools for the trailing edge rib and the support rib.

The present invention provides several advantages over the prior art:

all ribs (whether they are supporting edge ribs or trailing edge ribs) that allow one tool to make the trailing edge of the HTP and VTP.

Allowing significant cost reduction by using a common rib concept for both HTPs and VTPs.

The invention offers advantages for those sectors dealing with operability and service operations, based on a similar approach to the supporting and trailing edge ribs of the HTP/VTP.

The concept of a multifunctional rib is proposed for the trailing edge, which performs two structural functions (BR: connecting the elevator hinge lines; TER: supporting the trailing edge plate).

Other features and advantages of the present invention will become apparent from the following detailed description of several embodiments, which illustrate the object associated with the drawings.

Drawings

Fig. 1 is a perspective view of an aircraft having a fuselage.

Fig. 2 is a view of a known prior art HTP.

FIG. 3 is an overall view of the HTP trailing edge.

FIG. 4 is a view of a prior art trailing edge showing the Trailing Edge Rib (TER) and the support rib (BR).

FIG. 5 is a schematic of the trailing edge of the present invention showing the location of the Trailing Edge Rib (TER) and the support rib (BER).

Fig. 6A to 6E show several views of the construction of the preform of the TER/BR of the trailing edge of the present invention.

Fig. 7A to 7E show several views of the construction of another preform for TER/BR of the trailing edge of the present invention.

Detailed Description

Fig. 1 shows an aircraft with an aircraft fuselage and a tail. Fig. 2 shows a horizontal tail plane of a prior art aircraft, showing a torque box, a leading edge and a trailing edge with control surfaces. FIG. 3 is a general overview of the trailing edge 3 of the HTP; it can be seen that the trailing edge 3 is the transition between the torque box and the control surface. 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 (TER)1 and support ribs (BR)2 having different configurations.

Fig. 5 is a schematic view of the trailing edge 3, showing the positions of the Trailing Edge Rib (TER)1 and the supporting edge rib (BR)2 manufactured according to the method of the present invention.

Fig. 6A to 6E and 7A to 7E show two configurations of TER/BR 1, 2 of the trailing edge 3 manufactured according to the method of the invention.

In the method of the invention for manufacturing TER 1 and BR 2 of the trailing edge 3 of an aircraft lifting surface, TER 1 and BR 2 are manufactured by joining simple C-shaped parts and/or simple L-shaped parts to obtain the final TER 1 and BR 2. The manufacture of simple C-shaped parts uses the same tools for TER 1 and BR 2, and the manufacture of simple L-shaped parts uses the same tools for TER 1 and BR 2.

BR 2 and TER 1 are made by joining C-shaped or L-shaped parts. Thus, the invention includes using the same tooling to make those parts for all BR 2 and TER 1 so that they are connected to obtain the final part (BR 2 or TER 1) with the particular size and geometry required.

The support ribs 2 support the hinge lines connected to the rear spar of the torque box, while the rear edge ribs 1 provide stability to the structure of the rear edge 3.

The support rib 2 and the trailing edge rib 1 may have an "I" shaped profile comprising a central web 5, a lower flange 6, an upper flange 7 and a forward projection 8.

The upper and lower flanges 7, 6 of the support rib 2 and the rear edge rib 1 have a width greater at the rear than at the front, and one of the lower flanges 6 may include a straight rear portion 9 and an inclined portion 10 rising toward the front.

The support rib 2 and the rear edge rib 1 may additionally include a lower flange 6' located below the inclined portion 10 of the lower flange 6, the lower flange 6 including a straight rear portion 9 and an inclined portion 10 rising toward the front (fig. 7A to 7E).

All the support ribs 2 and the trailing edge rib 1 may be made of the same material.

The material used may be metal or any CFRP with thermosetting or thermoplastic resins. Depending on the materials selected, the joining technique may be one or more of the following: fastening, bonding, secondary bonding or thermoplastic welding.

A preferred material is a thermoplastic resin reinforced with continuous carbon fibers. This allows the following:

-forming parts to be connected in a modular tool

Welding between the parts to form the final BR 2 or TER 1

Thermoplastics without the need for autoclaves

The thermoplastic is recyclable.

While the invention has been fully described in connection with the preferred embodiments, it is apparent that modifications can be introduced within the scope thereof, and these embodiments should not be construed as limiting the scope of the invention but as being defined by the contents of the appended claims.