JPH02224937A - Assembly of box type adhesion structure - Google Patents

Abstract

PURPOSE:To perform hardening while heating and to improve the positional accuracy of an internal member by inserting an elastic body into the gap formed between a slit and connection piece, fixing the connection piece to an adhesion face fixing device, and providing an adhesive on the joining part located between the outer plate provided on the adhesion face support face and the connection piece. CONSTITUTION:A connection piece 3 is located just above a slit 6 of an adhesive face fixing device 7, the elastic body 20 of a round bar consisting of a heat resistant rubber is arranged at one side of the connection piece 3 and by descending the connection piece 3 in an arrow mark direction the connection piece 3 and elastic body 20 are inserted into the slit 6 and the connection piece 3 is fitted at a specific position. In this case, the elastic body 20 located in a gap 21 presses the connection piece 3 to a wall face 7a by the elastic force caused by its deformation, positioning it at specific position. Then, after the connection piece 3 being coated with an adhesive, an outer plate 2 is joined, a pack 22 is arranged so as to surround the whole body and after keeping this internal part space in a vacuum state, a heat hardening treatment is received and the outer plate 2 and connection piece 3 are fixed.

Description

Detailed Description of the Invention (Field of Industrial Application) The present invention is most suitable for assembling a composite structure for making a box-shaped composite structure to be incorporated into an aircraft, and is also applicable to other adhesive assemblies. This invention relates to a method for assembling a box-shaped adhesive structure.

(Prior Art) As shown in FIG. 3, a composite material structure 1 to be incorporated into an aircraft has a box-shaped structure in which a pair of outer panels 2.2 are connected by a connecting piece 3 and an opening 4 is limited. However, as shown in FIG. 4, this type of composite material structure 1 is provided with a composite material fixing device 7 having composite material support surfaces 5.5 on both sides and a slit 6 extending in the vertical direction. The connecting piece 3 is inserted into the slit 6 of the composite material fixing device 7, an adhesive is provided between the composite material 2 provided on the composite material support surface 5 and the connecting piece 3, and the adhesive is heated and cured to connect the composite material 2. The connecting piece 3 of the assembled composite material structure 1 has a fixing piece 8 and a fixture 9 as shown in FIG.
is attached by normal means (-1), but this attachment requires a high degree of precision in dimensions.

(Problems to be Solved by the Invention) In the box-shaped structure made by the method for assembling a composite material structure described above, when the connecting piece 3 is inserted into the slit 6 of the composite phase fixing device 7 as shown in FIG. In addition, because the width of the slit 6 is set wider than the width of the connecting piece for convenience of assembly work, there is a gap, and the connecting piece 3 inserted into the slit 6 moves during the curing cycle when the adhesive exhibits fluidity. ,
It will be in a state that is inclined to the - side, and if it is joined in this state,
When attaching the fixing piece 8 and fixture 9, misalignment of the fastener hole positions may occur.

On the other hand, in the fastener joint assembly of aircraft manufacturing, the seventh
As shown in the figure, the link mechanism 1 is attached to the rod portion 11 of the main body 10.
A backup tool in which abutment strips 14.14 are provided symmetrically through 3.13, and these abutment strips 14 are used to position and fix the composite material structure is disclosed in Japanese Patent Application Laid-Open No. 63-745.
As is known from Japanese Patent No. 38, in this case, when assembling a composite material structure, if a backup tool is mechanically fixed together with a set of internal members, after the composite phase and internal parts are heated and hardened, The backup tool cannot be removed because there is no opening to put your hand in to operate the instrument, and if the backup tool is mechanically operated remotely from the outside before or after curing, the seal inside the bag will be incomplete. This will cause a decline in the quality of the molded product, and if the structure is small, there will be a lack of internal storage space, so a link mechanism cannot be used to provide a backup tool.

The present invention has been made in view of the above-mentioned points, and is a method for assembling a composite material structure that improves the positional accuracy of internal members when assembling the structure by bonding, and also enables easy removal work after assembly. The purpose is to provide

(Means for Solving the Problems) The method for assembling an adhesive structure of the present invention includes providing an adhesive surface fixing device having composite phase support surfaces on both sides and forming slits extending in the vertical direction, Insert the connecting piece into the slit, insert an elastic body into the gap formed between the slit and the connecting piece, and fix the connecting piece to the adhesive surface fixing device.
Next, an adhesive is applied to the joint between the outer panel and the connecting piece provided on the adhesive surface support surface, and the adhesive is heated and cured to fix the composite material and the connecting piece.

(Function) In the method for assembling a box-shaped adhesive structure of the present invention, the connecting piece inserted into the slit of the adhesive surface fixing device is connected to the elastic body inserted into the gap formed between the slit and the connecting piece. The fixed connecting piece is fixed to the adhesive surface fixing device by adhesive, and the fixed connecting piece and the outer plate provided on the supporting surface are bonded via adhesive, and the outer plate and the connecting piece are fixed by heating and curing to form a structure. To improve the positioning accuracy of internal members during adhesive assembly and to simplify the removal of an adhesive surface fixing device after assembly.

(Example) An embodiment of the present invention will be described below with reference to the drawings.

In FIG. 1, the same members as in FIG. 4 are given the same reference numerals.

Figures 1 (a), (b), and (c) are diagrams showing the order of steps in the method of assembling a box-shaped composite structure of the present invention. First, as shown in Figure 1 (a), the adhesive surface is A connecting piece 3 is positioned directly above the slit 6 of the spacing device 7, and an elastic body 20 made of a round bar made of heat-resistant rubber is placed on one side of the connecting piece 3, and the connecting piece 3 is indicated by an arrow. By lowering the connecting piece 3 and the elastic body 20 into the slit 6, the connecting piece 3 is inserted into the slit 6 as shown in FIG. Insert into position.

In this embodiment, since the outer panel and the connecting material are made of composite material, the adhesive surface fixing device is made of composite material in consideration of thermal expansion. In this case, the elastic body 20 located in the gap 21 formed between the slit 6 and the connecting piece 3 presses the connecting piece 3 against the wall surface 7a forming the slit 6 of the adhesive surface fixing device 7 by the elastic force generated by its deformation. , the connecting piece 3 has its wall surface 7a
is pressed into position and positioned at a predetermined position. Further, a heat-resistant tube filled with a predetermined amount of gas may be used to press the elastic body 20 as necessary depending on the force and vacuum pressure. In this case, if the gas is inserted into the slit before filling it with gas, the insertion becomes easy and the gas can be applied to a case where the gap 21 changes. After the connecting piece 3 fixed to the composite material fixing device 7 is coated with adhesive as shown in FIG. , pack 2 via a vacuum device (not shown)
After maintaining the internal space of the outer panel 2 in a vacuum state, the outer panel 2 and the connecting piece 3 are fixed by being heated and hardened in an autoclave device.

2(a) and 2(b) show another modified example of the present invention. In this modified example, the elastic body 30 exhibits a linear shape as shown in FIG. 2(a) at room temperature, and a second ( b) One made of a shape memory alloy exhibiting a coil shape as shown in the figure is used. In this case, an elastic body 30 is loosely fixed and disposed in the gap 21 formed between the slit 6 and the connecting piece 3 with adhesive tape or the like.
maintains a flat shape in an environment at room temperature and can be easily inserted into and removed from the slit 6, and the elastic force generated by the deformation of the elastic body 30 due to high temperatures allows the connecting piece 3 to be inserted into the slit 6 of the adhesive surface fixing device 7. Since it is pressed against the wall surface 7a to be formed, the connecting piece 3 is pressed against the wall surface 7a and positioned at a predetermined position.

(Effects of the Invention) As described above, according to the present invention, the positional accuracy of internal members in bonding and assembling a structure is improved, and the work of setting the internal members and removing them after curing is simplified.

[Brief explanation of the drawing]

Figures 1 (a), (b), and (c) are diagrams showing the process order of the method for assembling a composite material structure of the present invention, and Figures 2 (a) and (b).
) is a diagram showing another modification of the present invention, FIG. 3 is a perspective view showing an example of a composite material structure for an aircraft, and FIG. 4 is a diagram showing a conventional adhesive assembly method of the composite material structure for an aircraft. Figure, 5th
The figure shows the attachment of a fixing member to the same aircraft composite structure, Figure 6 is an explanatory diagram showing the drawbacks of the conventional adhesive assembly method for composite structures, and Figure 7 shows how to assemble an aircraft fastener. It is a figure showing the apparatus used. 6...Slit, 7...Composite phase fixing device, 20...
- Elastic body, 21... gap. Applicant's representative: Sato - Male (b) Bird 2 Figure 4 Trap 5 Island 7 Figure

Claims (1)

[Claims] An adhesive surface fixing device is provided with supporting surfaces on both sides and slits extending vertically, a connecting piece is inserted into the slit of the adhesive surface fixing device, and an elastic body is inserted into the gap formed between the slit and the connecting piece. is inserted to fix the connecting piece to the composite material fixing device, and then an adhesive is applied between the outer panel material provided on the supporting surface and the connecting piece, and the adhesive is heated and cured to fix the outer panel material and the connecting piece. A method for assembling a box-shaped bonded structure.