CN114368469A - A kind of aircraft wing surface composite material wingtip structure and manufacturing method - Google Patents

Abstract

An aircraft wing surface composite material wing tip structure and a manufacturing method, the wing tip structure is connected with an aircraft wing surface box segment, the wing tip structure includes a skin, a foam core, an end partition, and a tail edge, and the The foam core is a variable-section machine-added structure that matches the shape of the wingtip. One side of the foam core is connected to the end baffle, and the other side of the foam core is connected to the tail strip. The end baffle and the tail strip are In the composite material pre-product, the foam core, the end baffle and the tail edge are bonded to form an integral wing tip core structure, and the skin is a resin skin covering the outer layer of the wing tip core structure.

Description

A kind of aircraft wing surface composite material wingtip structure and manufacturing method

technical field

The present application relates to the technical field of aircraft design and manufacture, and further relates to an aircraft wing-like wing-like composite wingtip structure and a manufacturing method.

Background technique

Aircraft wings can be divided into wing box section, fixed leading edge, fixed trailing edge, wingtip, nacelle suspension, flaps, ailerons, spoilers and other structures according to their parts.

In the prior art, in order to improve the stiffness of the skin and maintain the aerodynamic shape, the wingtip structure of the aircraft airfoil is generally a metal structure, and skeletons such as beams and baffles are arranged inside the skin. This structure has a large number of parts and connectors, which greatly increases the weight of the structure. For airfoils with complex shapes, such as hyperboloids, this structure greatly increases the difficulty of forming the skin and the skeleton structure and reduces the structure. Maintainability and interchangeability requirements affect the performance of the aircraft to a certain extent and reduce the service life of the aircraft. Now, composite materials have been widely used in important parts such as fuselage and wings. Compared with metal structures, composite material structures can greatly reduce the structural weight while meeting the performance of aircraft. At present, the wing tip structure of aircraft wing surface is mainly made of composite material skin and metal skeleton mechanically connected. Maintainability and reliability, and greatly increase the structural weight.

SUMMARY OF THE INVENTION

In view of the shortcomings of the prior art, the purpose of the present application is to provide an aircraft wing-like wing-like composite wingtip structure and a manufacturing method.

An aircraft wing surface composite material wing tip structure, the wing tip structure is connected with the aircraft wing surface box segment, and the wing tip structure includes a skin, a foam core, an end partition, and a tail edge, and is characterized in that the The foam core is a variable-section machine-added structure that matches the shape of the wingtip. One side of the foam core is connected to the end baffle, the other side of the foam core is connected to the tail strip, and the end baffle and the tail strip are connected. It is a composite material pre-product, and the foam core, end baffles and tail strips are bonded to form an integral wing tip core structure, and the skin is a resin skin covering the outer layer of the wing tip core structure.

The foam core can be a composite structure spliced with butt surfaces, one or more blind lightening holes are arranged on the butting surface of the foam core, and there is a ventilation hole communicating with the blind lightening hole, and the ventilation hole is connected to the On the surface of the foam core, the end partitions are provided with corresponding ventilation holes, and the ventilation holes communicate with the lightening blind holes of the foam core through the ventilation holes of the foam core.

The present application also proposes a manufacturing method of the above-mentioned aircraft wing surface composite wingtip structure, which is characterized by comprising the following contents: 1) According to the design digital model of the wingtip structure, firstly, the molding end is pre-cured by means of resin paving. baffles and tail strips; 2) processing the foam core structure by machining; 3) bonding the foam core structure with the end baffles and tail strips to form an integral wing tip core structure; 4) using an integral wing The tip core structure is a mold, and the outer side of the wing tip core structure is covered with a resin skin, and the overall co-bonding molding of the wing tip structure is performed.

When the foam core is a composite structure with butt surfaces spliced together, when machining the foam core structure by machining, firstly, two foam core components are processed by machining, and then the butting surfaces of the foam core components are processed. Blind holes and ventilation holes are reduced; the two foam core components are joined together to form an integral foam core structure of the wingtip structure; ventilation holes corresponding to the ventilation holes are also processed on the end baffle; the integral foam core structure The wing tip core structure is bonded to the end baffle and the tail strip as a whole, so that the ventilation holes on the end baffle plate are connected with the ventilation holes of the foam core and the blind holes. The outer side of the wing tip core structure is covered with a resin skin, and the overall co-bonding molding of the wing tip structure is performed.

The beneficial effects of the present application are as follows: 1) The integrated structure is beneficial to the application of composite materials, and the skin, end baffles, foam cores, and tail strips are co-bonded and integrally formed, which reduces the difficulty of the process and reduces the number of parts and solid parts. 2) The skin is filled with foam core, and there are blind holes for lightening, which improves the rigidity of the skin and strengthens the structural stability. At the same time, due to the low density of the foam core, the weight of the structure is greatly reduced. 3) There are ventilation holes on the foam core, which are connected with the ventilation holes on the end partitions. When co-bonding is formed by high-temperature curing, the gas in the blind hole can be reduced to the outside of the wingtip, so as to avoid the expansion of high-temperature gas, and improve the performance of the foam. The overall performance of the foam core improves the overall performance of the wingtip. 4) The design of the "C" shape of the end partition ensures that it has sufficient bonding strength with the inner surface of the skin and the foam core, which improves the bearing capacity. 5) The wingtip structure is a fully glued structure, which does not need to make holes on the composite material components, which reduces the damage to the performance of the composite materials, reduces the stress concentration on the structural components, and greatly improves the fatigue performance of the aircraft.

The present application will be described in detail below with reference to the accompanying drawings.

Description of drawings

Fig. 1 is the schematic diagram of the wingtip structure of the aircraft wing surface composite material of the present application

FIG. 2 is a schematic sectional view of the wingtip structure of an aircraft wing surface composite material of the present application

Figure 3 is a schematic diagram of the bonding of the foam core, the tail edge and the skin.

Number description in the figure: 1 wingtip structure, 2 skin, 3 end bulkheads, 4 tail edge, 5 foam core, 6 butt surface, 7 lightening blind holes, 8 ventilation holes, 9 ventilation holes.

specific embodiment

Referring to the drawings, the aircraft wing surface composite material wing tip structure of the present application, the wing tip structure 1 is connected with the aircraft wing box section, and the wing tip structure 1 contains a skin 2, a foam core 5, and an end partition 3 , tail strip 4, in practice, the foam core 5 is a variable-section machined structure that matches the shape of the wingtip. The foam core 5 is filled in the skin 2, covered by the skin 2, and one side of the foam core 5 is Connect the end partition 3, the other side of the foam core 5 is connected to the tail edge 4, the end partition 3 and the tail edge 4 are composite material prefabricated products, the foam core 5, the end partition 3 and the tail edge 4 The integral wing tip core structure is formed by bonding, and the skin 1 is a resin skin covering the outer layer of the wing tip core structure.

In practice, in order to reduce the structural weight to the greatest extent, the foam core 5 is a composite structure that is spliced with butt surfaces 6, and one or more lightening blind holes 7 are also provided on the butt surfaces of the foam core 6. A vent hole 8 communicated with the lightening blind hole 7 is communicated to the surface of the foam core 5, and the end baffle 4 is provided with a corresponding vent hole 9, and the vent hole 9 passes through the vent hole 8 of the foam core and the lightening of the foam core. The blind holes 7 are connected. There are ventilation holes 8 on the foam core, which are connected with the ventilation holes 9 on the end partitions. During high temperature curing and co-adhesion molding, the gas in the blind hole 7 can be reduced to the outside of the wing tip, so as to prevent the expansion of high temperature gas from affecting the wing The shape of the tip structure improves the overall performance of the foam core, thereby improving the overall performance of the wingtip.

The diameter of the ventilation holes on the end partition is larger than the diameter of the ventilation holes on the foam core. In the embodiment, the diameter of the ventilation holes 9 on the end partition is 4 mm to 5 mm larger than the diameter of the ventilation holes 8 on the foam core.

The above-mentioned aircraft wing surface composite material wingtip structure includes the following contents in the manufacturing process: firstly, according to the design digital model of the wingtip structure, firstly, the end baffle and the tail edge strip are pre-cured and formed by resin laying; the end baffle The upper and lower ends of 3 are used to support the skin, and one side is used to bond the foam core to seal the end structure of the foam core, and its cross-section is "C"-shaped. It should be emphasized that the section of the partition can also be in other forms, such as "I" shape, "Z" shape, and the tail strip is also used to support the skin and seal the tail structure of the foam core. It should be emphasized that the tail edge is formed by resin paving and curing, but it is not limited to this composite material form, and can also be in the form of other non-metallic materials, such as cloth bakelite.

The foam core is processed by machining. When the foam core is a composite structure with the butt surface 6 spliced together, when the foam core structure is processed by machining, the two foam core components are first processed by machining. , and process the lightening blind hole 7 and the ventilation hole 8 on the butting surface 6 of the foam core assembly; then connect the two foam core assemblies to form an integral foam core structure of the wing tip structure; A vent hole 9 corresponding to the vent hole 8 is processed, and the vent hole can be reserved when the end frame is prefabricated. The integral foam core 3 structure is bonded to the end baffle 3 and the tail strip 4 into an integral wingtip core structure, so that the ventilation holes 9 on the end baffle 3 are communicated with the ventilation holes 8 of the foam core 3 and the lightening blind holes 7 Finally, using the integral wing tip core structure as a mold, the outer side of the wing tip core structure is covered with a resin skin, and the overall co-bonding molding of the wing tip structure is performed.

The structure reduces the number of connecting parts, reduces material damage and stress concentration caused by hole making on the composite material component, improves the fatigue performance of the aircraft, and further improves the structural efficiency and use quality of the aircraft.

Claims (5)

1. an aircraft wing surface composite material wing tip structure, this wing tip structure is connected with the aircraft wing surface box section, and the described wing tip structure contains skin, foam core, end clapboard, tail edge, it is characterized in that , the foam core is a variable-section machine-added structure that matches the shape of the wingtip, one side of the foam core is connected to the end baffle, the other side of the foam core is connected to the tail strip, the end baffle and the tail The edge strip is a composite material pre-product, the foam core, the end baffle and the tail edge strip are bonded to form an integral wing tip core structure, and the skin is a resin skin covering the outer layer of the wing tip core structure. 2 . The composite wingtip structure of aircraft airfoil as claimed in claim 1 , wherein the foam core is a composite structure spliced with butt surfaces, and one or more There are two lightening blind holes, and another ventilation hole communicating with the lightening blind hole is connected to the surface of the foam core. The end partition is provided with corresponding ventilation holes, and the ventilation holes pass through the ventilation holes of the foam core and the lightening of the foam core. Blind vias are connected. 3 . The composite wingtip structure of aircraft airfoils according to claim 2 , wherein the diameter of the ventilation holes on the end baffle is larger than the diameter of the ventilation holes on the foam core. 4 . 4. a manufacturing method of aircraft wing surface composite material wingtip structure as claimed in claim 1, is characterized in that comprising the following content: 1) according to the design digital model of wingtip structure, at first adopt the mode of resin paving in advance Curing and forming end baffles and tail strips; 2) processing the foam core structure by machining; 3) bonding the foam core structure with the end baffles and tail strips to form an integral wingtip core structure; 4) with The overall wing tip core structure is a mold, and the outer side of the wing tip core structure is covered with a resin skin, and the overall co-bonding molding of the wing tip structure is performed. 5. a manufacturing method of aircraft wing surface composite material wing tip structure as claimed in claim 2, is characterized in that comprising the following content: 1) according to the design digital model of wing tip structure, at first adopt the mode of resin paving in advance Cure and form the end baffles and tail strips; 2) Process the two foam core components by machining, and process the lightening blind holes and ventilation holes on the butt surfaces of the foam core components; 3) Combine the two foam core components The components are butted together to form an integral foam core structure of the wing tip structure; 4) The ventilation holes corresponding to the ventilation holes are machined on the end clapboard; 5) The integral foam core structure is bonded to the end clapboard and the tail strip as a whole 6) Using the integral wing tip core structure as a mold, covering the outer side of the wing tip core structure with a resin skin to carry out the overall co-bonding molding of the wing tip structure.

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