KR19980045670A - Skin for wing of aircraft and manufacturing method thereof - Google Patents

Abstract

The present invention is a front skin made of a composite material that is hollow inside and forms the leading edge, a rear skin of a composite material arranged to partially overlap with the front skin and filled with a very dense material to form a trailing edge, and a front skin and a rear skin. Provides a skin for the auxiliary wing consisting of a metal mesh to prevent damage caused by lightning strikes covering the outer surface of the vehicle.

In addition, the present invention is a step of laminating the adhesive, the lower metal mesh, the bottom plate of the rear skin in turn on the reference plate, the step of laminating the front skin on the laminated jig and positioned on the reference plate, the inside of the trailing edge and on the bottom plate of the rear skin Skin preparation of an aircraft auxiliary wing comprising the steps of positioning the ultra-density material, laminating the upper plate of the rear skin, the upper metal mesh, and the adhesive, and molding at high temperature and high pressure using a pressure plate in the autoclave Provide a method. Laminating the ultra-density material consists of laminating the LOHAC foam with the adhesive on the trailing edge and then placing the honeycomb core with the adhesive foam on the bottom plate of the rear skin.

Description

Skin for wing of aircraft and manufacturing method thereof

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a skin for an aircraft auxiliary wing and a method for manufacturing the same, and more particularly to a skin for an aircraft auxiliary wing composed of a composite material and a method for manufacturing the same.

In general, the auxiliary wing 10 (FIG. 1) of the aircraft maintains weight balance with respect to the leading edge 1 connected to the main wing, the trailing edge 2 forming a sharp edge, and the driving hinge axis 3. It consists of a mass balancer (4) for the purpose, the front and rear support parts (5, 6) disposed between the upper and lower plates forming the front and rear edges (1, 2), and the trim tab (7) arranged on the trailing edge It is located on the left and right rear edges of the aircraft and is used for the aircraft's horizontal control.

As shown in FIG. 2, the skin 20 of the conventional auxiliary blade includes a top plate 21, a bottom plate 22, a rear support 23 supporting the top plate 21, and a bottom plate 22. It consists of a trailing edge 26 into which wedges 25 are inserted to form sharp edges. The auxiliary wing skin 20 is made of a metal material, and the upper and lower plates 21 and 22 and the rear support part 23 and the upper and lower plates 21 and 22 and the wedge 25 of the trailing edge part 26 are coupled to each other. At (24,27) with a binder such as fastener. However, the auxiliary wing skin of such a structure has a disadvantage that the assembly time is long because the upper and lower plates 21 and 22 and the rear support portion 23, the upper and lower plates 21 and 22 and the wedge 25 must be combined with a fastener one by one. There was this.

In addition, the wedge 25, which increases the weight on the trailing edge 26 side, arranges an additional mass balancer on the leading edge to satisfy the weight balance condition for the driving hinge axis of the leading edge required for the control surface such as the auxiliary wing. This caused a problem of increasing the weight of the aircraft.

In order to reduce the weight of the mass balancer, it is possible to think of a method of constructing the skin of the auxiliary wing with a durable, light and durable composite material, but in order to realize this, there is a problem of requiring an additional device to prevent damage caused by lightning strikes. there was.

An object of the present invention is to reduce the weight of the balance device for balancing the weight of the driving hinge axis of the leading edge by using a composite material, and to reduce the assembly time by eliminating the fastening process between the upper and lower plates and the support and the upper and lower plates and wedges The present invention provides a skin for an aircraft auxiliary wing and a method of manufacturing the same to reduce production costs.

It is still another object of the present invention to provide an auxiliary wing skin for an aircraft having a device capable of preventing damage due to lightning and a method of manufacturing the same.

In order to achieve the above object, the present invention consists of a front skin consisting of a composite material that is empty inside and forms the leading edge, and a composite material that is arranged to partially overlap with the front skin and is filled with a very dense material to form the trailing edge. Provided is a skin of an aircraft auxiliary wing composed of a rear skin and a metal mesh for preventing damage caused by lightning strikes covering the outer skin of the front skin and the rear skin.

The rear skin includes an upper and lower plates disposed to partially overlap the front skin, a trailing edge portion disposed in the trailing edge of the upper and lower plates, a first ultra-density material layer filled in the space in the trailing edge, and between the front skin and the first ultra-density layer. It is composed of a second ultra-density layer filled in the space in the upper and lower plates located at. Adhesive foam is disposed between the first microdensity layer and the second microdensity layer and between the second microdensity layer and the trailing edge of the front skin. An adhesive layer is disposed between the trailing edge part and the first ultra-low density material layer, between the upper and lower plates and the second ultra-low density material layer, and between the metal net and the front skin and the upper and lower plate. The first microdensity layer is composed of a Roha cell foam, and the second microdensity layer is composed of a honeycomb core.

In addition, the present invention is a step of laminating the adhesive, the lower metal mesh, the bottom plate of the rear skin in turn on the reference plate, the step of laminating the front skin on the laminated jig and positioned on the reference plate, on the inside of the trailing edge and the bottom of the rear skin Manufacturing the skin of the auxiliary wing of an aircraft consisting of positioning the ultra-density material, laminating the upper plate of the rear skin, the upper metal mesh, and the adhesive, and then molding at high temperature and high pressure using a pressure plate in the autoclave. Provide a method. The step of laminating the ultra-density material consists of laminating the LOHACELL foam with the adhesive on the trailing edge, and then placing the honeycomb core together with the adhesive foam on the lower plate of the rear skin.

1 is a plan view of a secondary aircraft auxiliary wing to which the present invention is applied.

FIG. 2 is a cross-sectional view of a skin of a conventional auxiliary aircraft wing shown along the plane A-A of FIG.

3 is a cross-sectional view of the skin of the auxiliary wing for an aircraft of the present invention.

Explanation of symbols for main parts of drawings>

10: auxiliary wing 20,30: skin

23: rear support 25: wedge

31: Front skin 32: Rear skin

35: metal mesh 39: trailing edge

39: honeycomb core part 41: lowha cell foam part

42: adhesive foam

Skin and manufacturing method of the auxiliary wing for the aircraft of the present invention will be described in detail with reference to the drawings.

Referring to FIG. 3, the skin 30 of the auxiliary wing of the aircraft of the present invention is disposed so as to partially overlap with the front skin 31 and the front skin 31, which are made of a composite material which is empty inside and forms the leading edge. It consists of a rear skin 32 composed of a composite material forming a, and a metal mesh 35 for preventing damage caused by lightning strikes covering the outer surfaces of the front skin 31 and the rear skin 32. The metal mesh 35 is preferably made of copper.

The rear skin 32 includes upper and lower plates 33 and 34 arranged to partially overlap the front skin 31, a trailing edge portion 38 disposed in the trailing edge portion of the upper and lower plates 33 and 34, and a trailing edge portion ( 38) to the honeycomb core part 39 filled in the space in the lower plate 33 and 34, which is located between the front skin 31 and the lower plate 33 and 34 located between the front skin 31 and the lower cell form 41. It is composed. The adhesive foam 42 is disposed between the lower cell foam portion 41 and the honeycomb core portion 39 and between the honeycomb core portion 39 and the rear end portion of the front skin 31.

Between the trailing edge portion 38 and the lower shell form portion 41, between the upper and lower plates 33 and 34 and the honeycomb core portion 39, and the metal mesh 35 and the front skin 31 and the upper and lower plates 33 and 34 The adhesive layer 40 is disposed between the layers.

Referring to Figure 3 manufacturing method of the present invention configured as described above are as follows.

First, the adhesive plate 40, the lower metal mesh 36, and the lower plate 33 of the rear skin 32 are sequentially stacked on the reference plate 43.

Next, the front skin 31 is laminated on the laminated jig 45 and positioned on the reference plate 43. Next, the LOHACELL foam 41 is laminated with the adhesive 40 on the trailing edge 38 and the honeycomb core 39 is disposed on the lower plate 33 of the rear skin 32 together with the adhesive foam 42. do.

Next, the upper plate 34, the upper metal mesh 37, and the adhesive 40 of the rear skin 32 are laminated in this order, and are compressed at high pressure using a pressure plate 44 in an autoclave (not shown). Molding completes the manufacture of the skin for the aircraft auxiliary wing of the present invention.

As described above, the device of the present invention uses a composite material to reduce the weight of the balancer for the balance of weight on the driving hinge axis of the leading edge, eliminating the fastening process between the upper and lower plates and the support and the upper and lower plates and wedges Therefore, it can be seen that the present invention provides a method for manufacturing an auxiliary wing skin and a method of manufacturing the same, which reduces the number of parts and shortens the assembly time to reduce the production cost.

Claims (8)

In the auxiliary wing of an aircraft composed of composite materials, The front skin is empty and forms the leading edge Partly overlapped with the front skin and the inside is made of very dense material A rear skin that is filled to form a trailing edge, Skin for an aircraft auxiliary wing comprising a metal mesh to prevent damage caused by lightning strikes covering the outer surface of the front skin and the rear skin. 2. The rear skin according to claim 1, wherein the rear skin comprises: an upper and lower plates arranged to partially overlap the front skin, a trailing edge disposed in the trailing end of the upper and lower plates, a first ultra-low density layer filled in the space in the trailing edge, and the front skin. Skin of an auxiliary wing for an aircraft, characterized in that the second ultra-density material layer is filled in the space in the upper and lower plates located between the first ultra-low density material layer. 3. The skin of an aircraft auxiliary wing according to claim 2, wherein an adhesive foam is disposed between the first microdensity layer and the second microdensity layer and between the second microdensity layer and the rear end of the front skin. The auxiliary wing for an aircraft according to claim 3, wherein an adhesive layer is disposed between the trailing edge part and the first ultra-low density material layer, between the upper and lower plate and the second ultra-low density material layer, and between the copper net and the front skin and the upper and lower plate. Skins. The auxiliary wing skin according to claim 4, wherein the first microdensity layer is made of Rohacell Foam, and the second microdensity layer is made of Honeycomb Core. 5. The skin of an auxiliary wing for an aircraft according to claim 4, wherein the metal mesh is made of copper. Laminating the adhesive on the reference plate, the lower metal mesh, and the lower plate of the rear skin in sequence; Stacking the front skin on the laminated jig and placing it on the reference plate; Placing a very dense material inside the trailing edge and on the lower plate of the rear skin, laminating the upper plate of the rear skin, the upper metal mesh, and the adhesive in this order; Skin manufacturing method of the auxiliary wing for an aircraft, characterized in that the step of forming a high temperature and high pressure using a pressure plate in the autoclave. The method of claim 7, wherein the step of laminating the ultra-density material consists of laminating the Lohacel foam with the adhesive on the trailing edge and then placing the honeycomb core with the adhesive foam on the bottom plate of the rear skin. Skin manufacturing method for auxiliary wing.