JP2012232692A - Fastener, aircraft assembly, method for manufacturing aircraft assembly, and jig - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a fastener that sufficiently secures explosion-proof performance even though being inexpensive, an aircraft assembly, a method for manufacturing the aircraft assembly, and a jig used for the manufacturing.SOLUTION: The fastener 1 fastens at least two members 11, 12 constituting an aircraft fuselage to each other. The fastener has: a fastener body 15; a fastening member 17 attached to the tip 15B of the fastener body 15; an insulating cap 20 that is a molding formed of a sealant material and has an opening 21 including the tip 15B of the fastener body 15 and the fastening member 17; and a sealant material 30 filled in the opening 21 of the cap 20. The cap 20 is formed with a leg 25 formed by expanding the outer diameter at a position facing the member 12 to the outer peripheral side.

Description

  The present invention relates to a fastener for fastening members constituting an aircraft body, an aircraft assembly, a method for manufacturing an aircraft assembly, and a jig used for manufacturing.

A wing constituting an aircraft body generally has a hollow structure, and a wing surface panel forming a wing surface is fixed to a structural member inside the wing by a fastener member (fastener).
In addition to this, structural members other than the wing surface panel and members for fixing equipment are also fastened and fixed by fastener members inside the wing and in the body.
In these cases, the fastener member is inserted into the pin-shaped fastener main body so as to penetrate both of the through holes formed in both of the members fixed to each other, and the distal end portion thereof is fixed by the fastening member (collar). Then, both members are fastened.
In addition, the wing surface panel or member to be fixed is not limited to two.

  By the way, in an aircraft, it is necessary to take all possible measures against lightning for explosion protection. When lightning occurs in an aircraft and a large current flows through a wing surface panel such as a main wing or a structural member, a part or all of the current flows in a fastening portion formed by the fastener body and the fastening member. When the current value exceeds the limit value of the allowable passage current at each fastening portion, a discharge called an electric arc (or thermal spark) is generated (hereinafter referred to as an arc in this specification). This is a phenomenon in which a rapid temperature rise occurs at the local part of the fastening interface of the member mainly composed of a conductive member that constitutes the fastening part due to the current passing through the fastening part, and a discharge is generated in the atmosphere in the vicinity. In this case, the molten material, which is called hot particles, is scattered from the melted portion. In general, the inner space of the wing also serves as a fuel tank. During this lightning strike, the generation of an arc and the hot particles that scatter from the arc are suppressed by suppressing the arc generation or sealing the arc. It is necessary to prevent explosions and prevent explosions by avoiding contact with combustible fuel vapor. Here, the part where the flammable fuel vapor may exist is a surge tank (such as a vent scoop or a burst disk) installed in the fuel tank, generally on the wing tip side of the fuel tank, inside the wing and the fuselage. Inside the tank) and inside the fuel system equipment.

  As one of the above-mentioned explosion-proof measures, the arc that may occur at the fastening interface is sealed with an insulating cap such as PS (polyphenylene sulfide resin), polyimide, PEEK (polyether-ether-ketone resin), or nylon resin. Can be considered. As such a cap, a type made of resin and screwed into the fastener body has been developed (Patent Document 1).

JP 2010-254287 A

In an aircraft body, fasteners are provided in a very large number of locations, and if the fasteners can be reduced in cost, a large cost reduction can be expected as a whole.
The present invention has been made based on such a technical problem, and provides a fastener, an aircraft assembly, a method for manufacturing an aircraft assembly, and a jig used for manufacturing that can ensure explosion-proof performance at a low cost. The purpose is to do.

  By the way, the aircraft body has a region where a large current easily flows when an arc of the same condition occurs, and a region where a large current hardly flows and a relatively low current flows. In a region where a relatively low current flows, explosion-proof performance can be sufficiently ensured even if the breakdown voltage against the outside inside the cap is lower than the breakdown voltage of a region where a large current flows.

Therefore, the present inventors have focused on the sealant material that has been filled in the interior of the resin cap, and have come up with the idea of molding the cap with the sealant material. The sealant material is less expensive than the resin material, but the pressure resistance is not as high as that of the resin material. Therefore, a sealant cap can be suitably used in a region where a relatively low current flows in the aircraft body.
However, as a result of repeated studies, since the cap made of sealant is flexible, the edge of the cap tends to buckle when the cap is abutted against the member. For this reason, it hit the problem that it is difficult to make a cap adhere to a member. In order to ensure the explosion-proof performance, the cap needs to be in close contact with the member, and the arc must be reliably sealed between the cap and the member.

  For this purpose, a fastener for fastening at least two members constituting an aircraft fuselage is provided with a fastener body penetrating a hole formed in all the members, and a tip portion protruding from the fastener body member. A fastening member to be mounted; an insulating cap having a molded body formed of a sealant material; an insulating cap having an opening that encloses the distal end portion of the fastener body and the fastening member; and a sealant material filled inside the opening of the cap; It is equipped with. The cap is formed with a leg portion formed by expanding the outer diameter toward the outer peripheral side at a position facing the member.

  According to the present invention, the outer diameter at the position facing the member is increased toward the outer peripheral side, so that the position facing the member in the cap is formed to be thicker than other portions. ing. Since the strength of the edge of the cap is increased by the thickening due to the formation of the leg portion, even if the other portion of the cap is flexible, it does not buckle when it is abutted against the member. Since the contact area between the cap and the member is enlarged due to this and the formation of the leg portion, the cap can be easily adhered along the surface of the member. Therefore, it is possible to ensure explosion-proof performance by sealing the arc between the cap and the member while reducing the cost by using an inexpensive sealant cap.

In the present invention, it is preferable that at least the outermost peripheral portion of the leg portion is covered with a sealant material.
According to this invention, between the outermost peripheral part of a leg part and a member is sealed, the contact | adhesion power of the cap to a member can be strengthened.
Also, if the cap and the sealant material that covers at least the outermost peripheral part of the leg are made of the same kind of sealant material having an approximate coefficient of thermal expansion, they can be prevented from peeling when the temperature changes. Adhesion can be maintained.

The sealant material that covers at least the outermost periphery of the leg part is the sealant material filled inside the cap opening that protrudes outside the cap opening when the cap covers the tip of the fastener body and the fastening member. Preferably there is.
According to this invention, since the cap is fixed to the member by using a part of the sealant material filled in the cap as a bonding material, separate members such as an adhesive and a screw member used only for fixing the cap are unnecessary. Can be. In addition, since the sealant is protruded from the opening of the cap when the fastener body and the fastening member are covered with the cap, the fixing of the cap is completed. Separately, the step of fixing the cap to the member can be eliminated. That is, the number of processes is reduced and the cost of a separate member is not required compared to a configuration that requires an adhesive or screw tightening, so that the cost can be further reduced.

  Furthermore, it is preferable that the leg portion is held on the member by the protruding sealant material. That is, the sealant material that protrudes from the opening of the cap slightly wraps around the outer peripheral surface of the leg portion, and the leg portion is held between the protruded sealant material and the member. Thereby, the adhesive force to the member of a cap can be strengthened.

Then, it is preferable that the leg portion and the protruding sealant material are integrally formed when the cap covers the front end portion of the fastener body and the fastening member.
By using a jig or the like, the protruding sealant material can be fastened to the periphery of the leg portion, and the leg portion can be more securely adhered to the member by the sealant material.

  An aircraft assembly is configured by fastening the members constituting the aircraft body with the above-described fasteners. Also in this aircraft assembly, the explosion-proof performance can be secured while reducing the cost, as described above.

  The method of manufacturing an aircraft assembly according to the present invention includes a fastening member mounting step of mounting a fastening member on a front end portion protruding from a member of the fastener main body, and a front end portion of the fastener main body by a cap filled with a sealant material inside the opening. And a cap mounting step of covering the fastening member and abutting the leg portion against the member.

  According to the present invention, the cap can be easily adhered along the surface of the aircraft member, similarly to the description of the fastener described above. Therefore, the explosion-proof performance can be ensured while reducing the cost by using an inexpensive sealant cap.

  In the manufacturing method described above, a jig having a recess having an enlarged diameter portion formed on the periphery thereof is used, the cap filled with the sealant material is accommodated in the recess, and the leg portion of the cap is accommodated in the enlarged diameter portion. It is preferable to form the sealant material that protrudes from the opening of the cap and accumulates in the enlarged diameter portion by setting the state and abutting the cap against the member with a jig.

  According to the present invention, by using the jig, the protruding sealant material can be collected around the leg portion, and the leg portion can be securely adhered to the member by the sealant material. Further, by using the jig, the pressing force to the cap member is constant, and the amount of the sealant material protruding is also constant, so that the size and shape of the protruding sealant material can be controlled. Furthermore, since the pressing force to the cap member is constant in the circumferential direction of the cap, the size and shape of the protruding sealant material are uniform over the entire circumference of the cap, so the adhesion to the cap member is enhanced. it can.

The jig of the present invention has a recess for accommodating the cap. A diameter-expanded portion is formed on the periphery of the recess to store a part protruding from the opening of the sealant material filled in the opening of the cap.
By using such a jig, the protruding sealant material can be collected around the leg portion, and the leg portion can be securely adhered to the member by the sealant material. In addition, since the pressing force to the cap member is constant and the amount of the sealant material protruding is also constant, variations in the size and shape of the protruding sealant material can be prevented. Furthermore, since the size and shape of the protruding sealant material are uniform over the entire circumference of the cap, the adhesion between the leg portion and the member can be increased.
In addition, since the cap is fixed to the member only by abutting the cap against the member with the jig, the number of steps and the member cost can be reduced, and the cost can be reduced.

  According to the present invention, explosion-proof performance can be sufficiently ensured at a low cost by ensuring adhesion of an inexpensive sealant cap to a member.

It is sectional drawing of the fastener which concerns on embodiment of this invention. It is a top view of the cap of a fastener. It is the elements on larger scale of FIG. It is sectional drawing of the jig | tool used for shaping | molding of a sealant material. It is a figure which shows the cap mounting | wearing process using a jig | tool.

Hereinafter, the present invention will be described in detail based on embodiments shown in the accompanying drawings.
As shown in FIG. 1, the members 11 and 12 constituting the aircraft body are fastened at a number of locations by a number of fasteners 1. The member 11 is, for example, a wing surface panel, and the member 12 is, for example, a structural member inside the wing. Note that the number of members fastened by the fastener 1 is not limited, and three or more members may be fastened by the fastener 1.

  The fastener 1 includes a fastener main body 15 that passes through holes 11A and 12A formed in the members 11 and 12, a fastening member (collar) 17 that is attached to the fastener main body 15, an end of the fastener main body 15, and a fastening member 17. The insulating cap 20 having an opening 21 that encloses the inside of the opening 21 and a filling sealant material 30 filled inside the opening 21 are provided.

The fastener body 15 has a head portion 15 </ b> A exposed on the surface of the member 11 and a tip portion 15 </ b> B protruding from the member 12. When the fastening member 17 is screwed into the distal end portion 15 </ b> B, the members 11 and 12 are fastened between the head portion 15 </ b> A and the fastening member 17.
The distal end portion 15 </ b> B and the fastening member 17 are covered with the filling sealant material 30 and the cap 20. As a result, the arc generated at the fastening interface 157 between the tip portion 15B and the fastening member 17 is sealed in the cap 20.

  A washer 18 and a spacer 19 are interposed between the end surface of the fastening member 17 and the member 12. The diameter of each of the washer 18 and the spacer 19 is slightly smaller than the diameter of the opening periphery 21 </ b> A of the cap 20, and the cap 20 is positioned along the periphery of the washer 18 or the spacer 19.

  As shown in FIGS. 1 and 2, the cap 20 is a molded body made of a sealant material, and PS (polyphenylene sulfide resin), polyimide, PEEK (polyether ether ketone resin), nylon, which have been conventionally used for caps. Higher flexibility than resin materials such as resin. The cap 20 is formed continuously from a disc-shaped bottom surface portion 22 facing the tip portion 15B of the fastener main body 15 and an outer peripheral portion of the bottom surface portion 22, and a side surface portion 23 substantially along the axial direction of the fastener main body 15. And have. In order to prevent the side surface portions 23 of the caps 20 of the adjacent fasteners 1 from interfering with each other, the side surface portion 23 rises substantially vertically from the bottom surface portion 22 without substantially expanding.

  The bottom surface portion 22 is flat, and thereby the height of the cap 20 is suppressed. For this reason, it is possible to prevent the cap 20 from interfering with surrounding members, and to reduce the weight of the cap 20 as compared with a cap having an expanded bottom surface.

  A marking 24 (FIG. 2) indicating the size and type of the fastener 1 is displayed on the bottom surface portion 22. The marking 24 is displayed by engraving or printing when the cap 20 is formed, and the marking 24 is easy to apply because the bottom surface portion 22 is flat. By using the marking 24, it becomes easy to select a cap 20 that is compatible with various fastener bodies 15 of different sizes and types, so that it is possible to prevent an erroneous mounting of the cap 20.

  On the outer periphery of the opening peripheral edge 21 </ b> A facing the member 12 in the side surface portion 23, an annular leg portion 25 whose outer diameter is expanded so as to protrude radially outward over the entire periphery of the opening peripheral edge 21 </ b> A is formed. The leg portion 25 is formed thicker than other portions of the cap 20. The thickness of the leg portion 25 is determined so that buckling of the opening peripheral edge 21A when the cap 20 is attached can be avoided and it does not interfere with the cap 20 of the adjacent fastener 1. When the thickness of the leg portion 25 is t1, and the thickness of the side surface portion 23 and the bottom surface portion 22 other than the leg portion 25 is t2, t1 is preferably 1.2 to 1.4 times t2.

  The leg portion 25 may be formed so as to protrude toward the inner peripheral side of the opening peripheral edge 21 </ b> A in the sense of thickening in the vicinity of the opening peripheral edge 21 </ b> A of the cap 20. However, in order to reduce the weight by avoiding an increase in the size of the cap 20, and from the viewpoint of making the clearance between the inner wall of the cap 20 and the washer 18 and the spacer 19 small for positioning the cap 20 as described above, the opening. It is preferably formed so as to protrude to the outer peripheral side of the peripheral edge 21A.

  FIG. 3 is an enlarged view showing the vicinity of the leg portion 25. A part of the filling sealant material 30 filled inside the opening 21 (filling sealant material 30A) protrudes outside the opening 21 of the cap 20 and covers a portion including the outermost peripheral portion 25A of the leg portion 25. Further, the leg portion 25 is held by the member 12 by the filling sealant material 30A. In addition, the filling sealant material 30 </ b> A may be interposed at the interface between the member 12 and the leg portion 25.

  The member 11 and the member 12 are fastened by the fastener 1 as described above, whereby the aircraft assembly 100 (FIG. 1) is configured. This aircraft assembly 100 is an assembly of, for example, a wing surface panel and a structural member inside the wing.

  Here, the fastener 1 including the sealant cap 20 described above can be suitably used in the aircraft assembly 100 in a region where a relatively low current flows during lightning. The cap 20 made of sealant has a lower withstand pressure than a cap made of resin such as PS, polyimide, PEEK, and nylon resin. However, even such a cap 20 made of a sealant exhibits a sufficient sealing effect against an arc generated by a relatively low current.

  That is, in the aircraft assembly 100, another fastener having a resin cap having a high pressure resistance such as PS, polyimide, PEEK, nylon resin or the like can be suitably used in a region where a large current easily flows, and is relatively low. The fastener 1 described above can be suitably used in a region where current flows. Since the cap 20 made of sealant can be manufactured at a lower cost than the cap made of resin, the cost can be reduced by using the fastener 1 for a suitable part of an aircraft member.

  Next, a method for manufacturing the aircraft assembly 100 will be described. FIG. 4 shows a jig 40 used for mounting the cap 20. The jig 40 is formed with a recess 41 for accommodating the cap 20. On the periphery of the recess 41, an enlarged diameter portion 41A having an opening diameter that is gradually increased is formed. The enlarged diameter portion 41A is formed with an inner diameter larger than the outer diameter of the leg portion 25 so that a predetermined space can be secured on the outer peripheral side of the leg portion 25 in a state where the cap 20 is accommodated in the recess 41.

  When fastening the members 11 and 12 by the fastener 1, first, the fastener body 15 is passed through the holes 11 </ b> A and 12 </ b> A (FIG. 1) formed in the members 11 and 12, and the distal end portion 15 </ b> B of the fastener body 15 protruding from the member 12. After passing the washer 18 and the spacer 19, the fastening member 17 is attached to the tip 15B.

  Next, as shown in FIG. 5A, the molded cap 20 before curing is placed in the recess 41 of the jig 40, and the filling sealant material 30 is filled into the opening 21 of the cap 20. Then, as shown in FIG. 5B, the cap 20 is abutted against the member 12 by the jig 40, and the cap 20 is mounted by covering the tip portion 15 </ b> B and the fastening member 17 with the cap 20. Since the cap 20 is flexible, the cap 20 is easily abutted against the member 12 by using the jig 40. Further, it is easy to remove the cap 20 from the jig 40.

  When the cap 20 is mounted, the filled sealant material 30A that protrudes outside the opening 21 as shown in FIG. 3 is collected in the enlarged diameter portion 41A of the jig 40, and the filled sealant material 30A follows the shape of the enlarged diameter portion 41A. By being molded, the leg portion 25 comes into close contact with the member 12. The cap 20 is fixed to the member 12 by the adhesion between the leg portion 25 and the member 12. The fastening interface 157 between the fastener body 15 and the fastening member 17 is sealed between the cap 20 and the member 12.

Here, since the strength of the edge of the cap 20 is increased by increasing the thickness due to the formation of the leg portion 25, the cap 20 does not buckle when it is abutted against the member 12. Moreover, since the opposing surface to the member 12 of the leg part 25 is wide, the cap 20 and the member 12 contact in a wide area. From these things, the adhesive force to the member 12 of the cap 20 can be enlarged.
Furthermore, since the space between the outermost peripheral portion 25A (FIG. 3) of the leg portion 25 and the member 12 is sealed by the filling sealant material 30A, the adhesion of the cap 20 to the member 12 can be enhanced.
In addition, since the leg portion 25 is held on the member 12 by the filling sealant material 30 </ b> A, the adhesion force of the cap 20 to the member 12 can be further strengthened.

  As described above, the adhesion of the cap 20 to the member 12 is strengthened by the leg portion 25, and the insulation withstand voltage by the cap 20 can be increased, so that the explosion-proof performance can be stably obtained. Moreover, the yield improves because the contact | adhesion power to the member 12 of the cap 20 is strengthened.

  The aircraft assembly 100 is manufactured by the two processes of attaching the fastening member 17 to the fastener body 15 and attaching the cap 20 described above. Here, the mounting of the cap 20 is completed by putting the cap 20 on the fastener main body 15 and the fastening member 17 to protrude the filling sealant material 30A, so that the cap 20 is mounted using an adhesive or the like. Thus, the number of processes can be reduced, and the member cost can be reduced in that a separate member is not required.

  Further, by using the jig 40, it is possible to prevent variations in the molding dimension and shape of the filled sealant material 30A. Furthermore, since the filled sealant material 30 </ b> A (molded portion) has a uniform size and shape over the entire circumference of the cap 20, the adhesion of the cap 20 to the member 12 can be further strengthened.

And in order to ensure the contact | adhesion power to the member 12 of the cap 20, since only the leg part 25 should just be thick, parts other than the leg part 25 of the cap 20 can be thinned. That is, the cap 20 can be made thin as a whole while using the inexpensive but flexible cap 20, so that the weight of the cap 20 can be reduced without impairing the adhesion to the member 12.
As described above, according to the fastener 1 of the present embodiment, the adhesion of the cap 20 to the aircraft member 12 can be ensured at a low cost, so that the explosion-proof performance and the weight reduction of the aircraft can be realized.

In addition, the said embodiment is only an illustration and can be changed suitably.
For example, even when the leg portion 25 is not formed on the cap 20 and the entire cap 20 is formed thin, the edge of the cap 20 is held by the member by the filling sealant material 30A protruding from the opening of the cap 20. It only has to be. The jig 40 described above can also be used to fix a cap that does not have such a leg portion 25. That is, the cap without the leg portion 25 is accommodated in the concave portion 41 of the jig 40, and the cap 40 is abutted against the member 12 by the jig 40, whereby the filled sealant material 30A protruding from the opening of the cap is collected in the enlarged diameter portion 41A. The sealant material 30A is formed integrally with the edge of the cap. The cap is fixed to the member 12 when the edge of the cap is in close contact with the member 12 by the protruding sealant material 30A.

Further, the present invention includes a case where the cap is attached without using the jig 40.
Further, the filling sealant material 30 </ b> A that protrudes from the opening of the cap 20 may be provided only in the gap at the interface between the leg portion 25 and the member 12. Also in this case, the leg portion 25 is held in close contact with the member 12 by the protruding sealant material 30A.
In short, a fastener, an aircraft assembly, a manufacturing method thereof, and a jig 40 used for manufacturing the fastener used for fixing the cap 20 without wiping off the filling sealant material 30A intentionally protruding from the opening 21 of the cap 20 are Included in the invention.

  Other than this, as long as the gist of the present invention is not deviated, the configuration described in the above embodiment can be selected or changed to another configuration as appropriate.

1 fasteners 11 and 12 members (members constituting an aircraft)
11A, 12A Hole 15 Fastener body 15A Head 15B Tip 17 Fastening member 18 Washer 19 Spacer 20 Cap 21 Opening 21A Opening peripheral edge 22 Bottom face 23 Side face 24 Marking 25 Leg 25A Outermost circumference 30 Filling sealant material (sealant material)
30A Filling sealant material (protruded part)
40 Jig 41 Recess 41A Expanding portion 100 Aircraft assembly 157 Fastening interface

Claims (10)

A fastener for fastening at least two members constituting an aircraft fuselage,
A fastener body passing through holes formed in all the members;
A fastening member mounted on a tip portion protruding from the member of the fastener body;
An insulating cap comprising a molded body formed of a sealant material, and having an opening that encloses the tip portion of the fastener body and the fastening member;
A sealant material filled inside the opening of the cap, and
The fastener is characterized in that the cap is formed with a leg portion formed by expanding the outer diameter at the position facing the member toward the outer peripheral side.   The fastener according to claim 1, wherein at least an outermost peripheral portion of the leg portion is covered with a sealant material.   The sealant material that covers at least the outermost peripheral portion of the leg portion has an opening of the cap when the sealant material filled inside the opening of the cap covers the front end portion of the fastener body and the fastening member with the cap. The fastener according to claim 2, wherein the fastener protrudes from the outside.   The fastener according to claim 3, wherein the leg portion is held by the member by the protruding sealant material.   The fastener according to claim 3 or 4, wherein the leg portion and the protruding sealant material are integrally formed when the cap covers the tip portion of the fastener body and the fastening member. At least two members constituting the aircraft body;
An aircraft assembly comprising: the fastener according to any one of claims 1 to 5 that fastens the at least two members. A method of manufacturing an aircraft assembly according to claim 6,
A fastening member mounting step of mounting the fastening member on a tip portion protruding from the member of the fastener body;
A cap mounting step of covering the front end portion of the fastener main body and the fastening member with the cap filled with the sealant material inside the opening, and abutting the leg portion against the member. A method for manufacturing an aircraft assembly.   In the cap mounting step, when the leg portion is abutted against the member, the sealant material protrudes outside the opening of the cap, and at least the outermost peripheral portion of the leg portion is covered with the sealant material. The method for manufacturing an aircraft assembly according to claim 7. Using a jig having a recess with an enlarged diameter portion formed on its periphery,
The cap filled with the sealant material is housed in the recess, and the cap is pressed against the member by the jig, so that the cap protrudes from the opening of the cap and accumulates in the enlarged diameter portion. The method of manufacturing an aircraft assembly according to claim 8, wherein the sealant material is formed. A jig used for manufacturing an aircraft assembly including at least two members constituting an aircraft fuselage and a fastener for fastening these members,
From the fastener main body which the said fastener has penetrated the hole formed in all the said members, the fastening member with which the front-end | tip part protruded from the said member of the said fastener main body, and the molded object formed from sealant material And an insulating cap having an opening that encloses the front end portion of the fastener main body and the fastening member, and
A recess for accommodating the cap;
A jig having a diameter-enlarged portion for storing a part of the sealant material filled in the opening of the cap that protrudes from the opening is formed on the periphery of the recess.

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