KR100254259B1 - Method of making tail wing - Google Patents

Abstract

PURPOSE: Manufacturing method of a tail wing is provided to increase coupling strength as well as to set a proper fitting position by riveting and adhesive with an adherent film during combination of components. CONSTITUTION: A tail wing of a light airplane comprises a rudder and an elevator which consists of a pair of skins(31) composing an external form, combined mutually and plural first ribs(33) forming a structure frame inside the skins. A spur connected across a front face of the skins and plural second ribs fixed to support leading edges are included therein. The first ribs are bonded and a rib angle(34) is bonded to a specific position of other skin. At a normal temperature, a second rib is bonded to the leading edge. At a combining location of spur and skins, and joining spot of leading edge and skin, plural combining slots are formed and an adherent film is bonded on each combining position for linking mutually the pair of skins, spurs and leading edges. In the combining slots, rivets are fitted and the components are hardened under high pressure and under high temperature.

Description

How to make a tail for light aircraft

FIG. 1 is a perspective view schematically showing a part of a tail for a general light aircraft. FIG.

FIG. 2 is a schematic perspective view of a portion of an elevator and a rudder of a conventional light aircraft; FIG.

FIG. 3 is a partial cross-sectional view of a light aircraft for a conventional aircraft according to one embodiment of the present invention; FIG.

FIG. 4 is a partial cross-sectional view of a light aircraft for another embodiment of the present invention. FIG.

FIGS. 5 to 9 are schematic diagrams for explaining a manufacturing process of a rudder for a light aircraft according to the present invention.

DESCRIPTION OF THE REFERENCE NUMERALS

11, 21, 25, 31: first skin 12, 22, 26, 32:

13, 33: first rib 34: rib angle

5,35: Spa 17,37: Leading Edge

8, 38:

BACKGROUND OF THE INVENTION 1. Field of the Invention [0002] The present invention relates to a method for manufacturing a light aircraft, and more particularly, to a method for manufacturing a light aircraft using a lightweight high strength composite material. As shown in FIG. 1, the fuselage for a light aircraft generally comprises a horizontal fin 1 and a vertical fin 3, and is rotatably coupled to the rear ends of the horizontal fist 1 and the vertical fist 3, An elevator 2 for adjusting the direction of travel of the airplane, and a rudder 4.

Each of the rudder and elevator of a typical light aircraft fuselage has a structure as shown in FIG. As shown in the figure, the rudder and the elevator each include a pair of first skins 11 and second skins 12 which are mutually combined to form an outer shape, and a pair of first skins 11 and second skins 12, A leading edge 17 provided on the front surface of the skins 11 and 12 and a plurality of second ribs 18 coupled to the leading edge 17 to support the leading edge 17, do.

The first and second skins 11 and 12 are made of a composite material and are coupled to each other by the first ribs 13. The two skins 11 and 12 are made of a NOMEX honeycomb core. Here, NOMEX is the abbreviation of NONMETALLIC. That is, the NOMEX honeycomb core refers to a honeycomb-like structure made of a non-metal polyamide (POLYAMIDE).

The leading edge 17 is rounded to facilitate reciprocating rotation.

Conventional methods for assembling the two skins of each of the rudder for the light aircraft and the elevator as mentioned above are as follows.

FIG. 3 is a partially enlarged cross-sectional view for explaining a rudder of a light aircraft and a method of manufacturing a first skin and a second skin of each elevator according to a conventional example.

As shown in the figure, the first skin 21 made of Nomex honeycomb core and the second skin 22, The ribs 23 are prepared. The rib 23 includes a rib 231 for maintaining a gap between the two skins 21 and 22 and a rib 231 formed at both ends of the rib 231 and connected to the two skins 21 and 22, And a coupling band 232 to be coupled. The coupling between the coupling base 232 and the two skins 21 and 22 was made of an epoxy resin. In this case, there is a problem that strength and durability are lowered by bonding using a room temperature resin.

FIG. 4 is a partially enlarged cross-sectional view for explaining a rudder of a light aircraft according to another conventional mode and a method of manufacturing a first skin and a second skin of the elevator, respectively.

As shown, the ribs 27 and the rib angles 28 are prepared to mutually join the first and second skins 25 and 26 made of Nomex honeycomb cores. The rib angles 28 are bent in a "┐" shape as a thin plate. A pair of rib angles 28 are attached to predetermined positions of the first and second skins 25 and 26 so as to be spaced apart from each other by a predetermined distance so that the ribs 27 can be fitted. Epoxy resin or the like is used for adhesion between the two skins 25 and 26 and the rib angle 28. Then, the ribs 27 are bonded between the rib angles 28 to bond the first and second skins 25 and 26 to each other. At this time, an adhesive is applied to the bonding surface of the two skins 25 (26) and the rib angle 28, which are in contact with the ribs 27, and is cured at a high temperature of about 121 캜.

As described above, when the two skins 25 and 26 are combined, the cost of the tool is excessive when the ribs 28 are joined to the ribs 27. Further, when the ribs 27 are joined, there is a risk that the adhesive adhered between the rib angles 28 and the two skins 25, 26 may melt and flow down.

SUMMARY OF THE INVENTION Accordingly, the present invention has been made to overcome the above-described problems in the conventional method for manufacturing a light aircraft fin, and it is an object of the present invention to provide a high-temperature composite material having improved strength and durability The object of the present invention is to provide a method for manufacturing an airplane tail.

According to an aspect of the present invention,

A pair of skins which are mutually coupled and form an outer shape; A plurality of first ribs joined to the inside of the skin to form a skeleton; A spa coupled across the bottom of the skin; A leading edge provided on a front surface of the skin; And a plurality of second ribs coupled to the leading edge to support the leading edge, the method comprising the steps of:

Joining the first rib to the inside of the one skin; Joining the rib angles to predetermined internal positions of the other skins to which the first ribs are to be joined; Wherein a plurality of engagement holes are formed at a joint position of the spar and the skin and at a joint position of the leading edge and the skin, and the adhesive film is bonded to each engagement position to form a pair of skins, ; And a step of fastening the rivet to each of the plurality of engagement holes and curing the rivet in a high-pressure and high-temperature atmosphere.

Hereinafter, a method for manufacturing a light aircraft according to the present invention will be described in detail with reference to the accompanying drawings.

The fuselage for the light aircraft is fundamentally structured as shown in FIG.

And, the rudder and the elevators constituting a part of the tail are as shown in Fig. 2 in the structure thereof. That is, the first and second skins 31 and 32, which form an outer shape by being superposed on each other, a plurality of first ribs 33 that are joined to the inside of the two skins 31 and 32 to form a skeleton, A spear 35 coupled across the front of the two skins 31 and 32, a leading edge 37 provided on the front of the two skins 31 and 32, And a plurality of second ribs 38 coupled thereto. And a plurality of rib angles 34 for supporting the first ribs 33 when the first and second skins 31 and 32 are coupled with the first ribs 33.

It is preferable to select the material used for the main members of each of the rudder for the light aircraft and the elevator according to the present invention as shown in Table 1. [

[Table 1]

The rudder of the light aircraft having such a structure and the manufacturing method according to the present invention of each of the elevators will be described with reference to FIGS. 5 to 9. First, as shown in FIG. 4 and FIG. 5, a plurality of first ribs 33 are joined to the inside of the first skin 31. At this time, the rib angles 34 are aligned with the joining surfaces of the first ribs 33 and the first skins 31, and joined at a high temperature using a graphite prepreg (PREPREG).

7 and 8, each of the plurality of rib angles 34 is joined to an inner position at which the first ribs 33 of the second skin 32 are to be joined. At this time, a graphite prepreg is used at high temperature to join.

As shown in FIG. 9, the second rib 38 is joined to the leading edge 37. In this case, bonding is carried out at room temperature using a bonding resin for room temperature. Here, a plurality of the leading edges 37 are provided and are attached to the front surface of the skins 31 and 32 with a predetermined distance therebetween. Here, in the case of a rudder, a fastening device (not shown) for connecting the rudder and the vertical tail wing is provided in the spaced space between the leading edges 37. On the other hand, in the case of an elevator, a fastening device (not shown) for connecting the horizontal tail wing and the elevator to the spaced space between the leading edges 37 is provided.

It is preferable to correct the incomplete forming by attaching or polishing the composite material after matching the partially joined parts in this manner in advance. Thereafter, the fabrication process is not shown.

The combining position of the spa 35 and the skin 21 to prevent the position of the single product from changing due to the flow of the adhesive when the product is cured at a high temperature for joining the products, 31) 32 are formed at the coupling positions of the first and second coupling members 31, 32, respectively.

Then, the adhesive film is adhered to each engagement position to bond the first and second skins 31 and 32, the spar 38 and the leading edge 37 to each other. Then, a rivet (not shown) is fastened and fixed to each of the plurality of engagement holes. The temporarily bonded parts are cured under a high temperature and high pressure atmosphere. The maintenance of high pressure uses the vacuum unit which can control the pressure of the combined parts. At this time, the pressure inside the vacuum chamber is regulated within a range in which the skins 31 and 32 do not sink. Preferably, the cure is maintained at a curing temperature of about 250 +/- 10 [deg.] F for about 90 minutes.

As described above, according to the rudder of the airplane for the light aircraft and the method of manufacturing each of the elevators according to the present invention, by using the adhesive film to fasten the rivet together with the joining film, , There is an advantage that the bonding strength can be increased. While the present invention has been particularly shown and described with reference to exemplary embodiments thereof, it will be understood by those of ordinary skill in the art that various changes in form and details may be made therein without departing from the scope of the present invention.

Accordingly, the true scope of protection of the present invention should be determined by the technical idea of the claims.

Claims (4)

A pair of skins which are mutually coupled and form an outer shape; A plurality of first ribs joined to the inside of the skin to form a skeleton; A spa coupled across the front of the skin; A leading edge provided on a front surface of the skin; A plurality of second ribs coupled to the inside thereof to support the leading edge; A method for manufacturing a fuselage for a light aircraft including a rudder and an elevator, the method comprising: joining the first rib to the inside of the one skin; Joining the rib angles to a predetermined position at which the first ribs inside the other skins are to be joined; Bonding the second rib to the leading edge at room temperature; Forming a plurality of coupling holes at a coupling position of the spar and the skin and a coupling position of the leading edge and the skin and bonding the adhesive film to the coupling positions to couple the pair of skins and the spar and the leading edge to each other; ; And a step of fastening a rivet to each of the engaging holes and curing the rivet in a high-pressure and high-temperature atmosphere, and a step of manufacturing the rudder and the elevator. The method of claim 1, wherein the joining of the first rib and the rib angle to the skin uses a graphite prepreg at a high temperature. 2. The method of claim 1, further comprising the step of correcting the incomplete forming by attaching or polishing the composite material after matching the individual parts before the bonding step of the adhesive film Way. 2. The method of claim 1, wherein the curing step is performed for 90 minutes at a high temperature of 250 10 F within a vacuum chamber capable of controlling the pressure.