JPS62214946A - Manufacture of honeycomb panel structure - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

Detailed Description of the Invention (Field of Industrial Application) The present invention relates to a method for manufacturing a honeycomb panel structure, which is generally called the so-called expansion method, and particularly relates to a method for manufacturing a honeycomb panel structure by applying a large compressive load to a high-load portion of the honeycomb panel structure. This relates to products whose strength is partially increased so that they can sufficiently withstand

(Prior Technology) Conventionally, so-called honeycomb panel structures with a sand-inch structure, which is a honeycomb core material with many honeycomb-shaped spaces formed inside and integrated with face plates on both sides, are lightweight and resistant to bending and compressive stress. Vehicle body materials, due to their strong resistance to
It is widely used in various industrial fields as an aircraft body material or building material. And in general,
The honeycomb core material used in this honeycomb panel structure is formed by partitioning a substantially regular hexagonal honeycomb-like space with the same shape using a large number of strip-shaped core sheets, and the honeycomb-like space has the above-mentioned characteristics. It is something that can be done.

However, on the other hand, the honeycomb core material has a drawback in that its strength against local compressive loads is extremely low. For this reason, for example, when attaching various parts etc. to a honeycomb panel structure by tightening bolts, the compressive load due to bolt tightening is locally concentrated at the attachment point of the honeycomb panel structure, so the honeycomb core material There is a problem in that buckling is likely to occur in a portion corresponding to the above-mentioned attachment location, and this buckling causes the core material in that portion to collapse, resulting in a partial decrease in its strength.

Therefore, in order to solve this problem, conventionally, a separate honeycomb-like space with a small size (high core density) was installed in advance in the high-load area corresponding to the above-mentioned installation location of the honeycomb core material. After inserting the core material or joining face plates to both sides of the honeycomb core material, holes are made in the areas corresponding to high load areas on one face plate and the honeycomb-shaped space is filled with synthetic resin. There is a generally known method for making the bolts resistant to compressive loads due to bolt tightening.

(Problem to be Solved by the Invention) However, in the former conventional method, before joining the face plates to both sides of the honeycomb core material, a portion of the honeycomb core material that will be a high load portion is cut out or It is necessary to prepare another core material to fit into the cutout. In addition, in the latter method, it is necessary to perform drilling work and resin filling work in the face plate, and in both cases, there is a problem that these setup work is time-consuming and troublesome.

In particular, the former method is difficult to perform once the honeycomb core material has been made into a finished product (honeycomb panel structure) with face plates joined to both sides; therefore, the core material is cut out in the semi-finished state, and then the face plates are joined. This is not desirable from a work standpoint.

The present invention has been made in view of these points, and its purpose is to increase the core density of the high-load portion of the core material during a predetermined process of forming honeycomb-shaped spaces in the honeycomb core material. By taking measures, there is no need to partially fit a separately prepared core material with high core density into the expanded core material, or to reinforce it by filling it with synthetic resin, etc., and this setup work can be done easily. The object of the present invention is to easily obtain a honeycomb panel structure in which the strength of the high-load portion of the core material is increased without carrying out the above steps.

(Means for Solving the Problems) In order to achieve the above object, the solving means of the present invention first consists of a large number of core sheets coated with an adhesive at predetermined intervals, each of which is coated with an adhesive. A laminate is prepared by laminating and adhering the layers so that they are positioned with a certain regularity. and,
A honeycomb core material having honeycomb-shaped spaces between core sheets is formed by partially restricting the laminate using a restriction jig so that the expansion ratio of the high-load portion is smaller than that of other portions. Next, face plates are bonded to both sides of this core material to obtain a honeycomb panel structure.

(Function) With the above configuration, in the present invention, when a laminate formed by laminating and bonding a large number of core sheets is stretched and stretched from both sides in the sheet lamination direction, the laminate is subjected to a high load during the stretching process. Because the expansion is partially regulated by a regulating jig so that the expansion rate of the part that becomes the part is small,
In the honeycomb-shaped space formed after expansion, the core density of the expansion restriction portion (portion that becomes a high load portion) is higher than that of other portions. This makes it possible to increase the strength of the high-load portions simply by controlling the expansion rate during the expansion process of the laminate.

(Example) Embodiments of the present invention will be described below based on the drawings.

FIG. 1 shows the manufacturing process in the method for manufacturing a honeycomb panel structure according to an embodiment of the present invention. First, the core sheet laminate shown in FIG. Prepare 2.

This laminate 2 is usually formed as follows.

That is, for example, adhesive is applied in lines at predetermined intervals to a large number of aluminum thin plates (not shown), and the adhesive is applied to the large number of thin plates so that each part of the thin plates is positioned with a certain regularity. After adhering them to each other by pressure in a laminated arrangement state, the core sheets are cut into a predetermined size in the arrangement direction of the adhesive-applied parts, thereby forming a large number of strip-shaped core sheets 3°3, . . . as shown in Fig. 7. - Thus, a prismatic laminate 2 is formed. In the figure, 4,4. . . . indicate the adhesive application portions of each core sheet 3, and the adhesive application portions 4 are divided into areas A, A, . Formed every third in...
In the core sheets 3, 3 which are in surface contact with each other, one sheet 3
Each adhesive application part 4 is arranged so as to correspond to a region located between adjacent adhesive application parts 4, 4 of the other sheet 3.

The laminate 2 thus formed is moved in the sheet stacking direction (
Pull it in the left-right direction in Figure 1 (a>) and pre-expand it as shown in Figure 1 (b). In this state, the laminate 2 has honeycomb-shaped spaces 6, 6, .
... is formed, but at this stage, the expansion ratio of the laminate 2 is small, so each of the honeycomb-shaped spaces 6 is formed into a hexagonal shape elongated in the longitudinal direction of the core sheet 3.

Next, with respect to the laminate 2 in the pre-expanded state, as shown in FIG. 1(C) and FIG. Partially restricted with jig 7.7. in particular,
Each of the regulating jigs 7 includes an elongated plate-shaped jig main body 8 extending in the longitudinal direction of the core sheet 3, and the jig main body 8 is provided with a plurality of pairs (three pairs in FIG. 2) of regulating pins 9, 9.9 are arranged opposite to each other in the width direction so as to form two rows in the longitudinal direction, and each of the regulating pins 9 is formed in the longitudinal direction on the lower surface of the jig main body 8, as shown in enlarged detail in FIGS. 3 and 4. The proximal end 9 is attached to two dovetail grooves 10, 10 (only one groove is shown in the figure) extending in the direction.
They are fitted to be slidably movable via bearings 11, 11, . . .

Each of the above-mentioned regulating jigs 7 is arranged above the high-load portion of the honeycomb panel structure 1 in the laminate 2, and each regulating pin 9 is placed in the honeycomb-shaped space 6 with a small expansion ratio. By inserting it, the subsequent expansion of the high-load portion is restricted.

Thereafter, the laminate 2 is roughly stretched from both sides in the sheet lamination direction to form a honeycomb core material 5 as shown in FIG. 1(d). Due to this rough stretching process, the parts of the laminate 2 other than the stretch regulating parts (high load parts) by the above-mentioned two regulating jigs 7, 7 are further stretched, and as shown in FIG. The honeycomb-shaped space 6 is expanded and formed into a substantially regular hexagonal shape. Note that the width of the core material 5 corresponding to this expanded portion becomes narrower depending on the expansion rate.

On the other hand, the two regulating jigs 7 restrict the influence of the further expanding operation on both the expanding regulating portions, and the expanding rate at the time of the preliminary expanding is maintained. As a result, the honeycomb core material 5 has two parts with a small expansion rate and a high load area with a predetermined distance apart, and the width of both parts is wider than other parts with a high expansion rate on the outside. It becomes a state of protrusion.

During this stretching, each of the regulating pins 9 of the regulating jigs 7.7 slightly slides in the longitudinal direction of the jig main body 8, thereby forming a boundary between the stretching regulating portion of the laminate 2 and other parts. Deformation of the honeycomb-shaped space 6 in the portion is prevented as much as possible.

After forming regions with partially different elongation rates in this way, face plates 12.1 are placed on both sides of the core material 5 as shown in FIG.
2 to core sheet 3, 3. ...honeycomb-shaped space 6 between
6. ... are joined in a sealed manner, and then both ends are cut by a predetermined length in the longitudinal direction (so-called ear cuts) to remove the protruding parts of the high-load parts. 5 is integrated into a sandwich structure with face plates 12, 12 to obtain a rectangular honeycomb panel structure 1.

The honeycomb panel structure 1 obtained in this way has a small expansion ratio in the high-load portion as described above and can sufficiently withstand a large compressive load.
As illustrated in the figure, holes 14, 14 are formed facing each other in locations corresponding to high-load portions of the face plate 12.12, and bolts 15 are passed through both holes 14, 14 and tightened By attaching them, parts and the like can be fixed to the honeycomb panel structure 1 via the mounting fittings 16.

As described above, in this embodiment, the regulating pins 9, 9, . ... into this honeycomb-shaped space 6, 6. Since the subsequent expansion of ... is restricted, the trouble of separately adopting reinforcing means such as inserting core materials with different core densities or filling with synthetic resin is eliminated, and it becomes a high-load part. A honeycomb panel structure 1 whose parts are strengthened can be easily obtained.

Furthermore, by preparing several types of jigs with different pin spacing in the sheet expansion direction of the regulating jig 7, it is possible to freely set the area of the high load portion of the honeycomb panel structure 1, and also By shifting the timing of use of the regulating jig 7, the core density and therefore the compressive strength can be easily changed.

In the above embodiment, the regulating pins 9, 9 . Using a regulating jig 7 having..., each regulating pin 9 is inserted into the honeycomb-shaped space 6 to regulate the stretching of the 2 parts of the laminate between the regulating pins 9 and 9 arranged in parallel in the sheet stretching direction. However, the present invention is not limited to this, and for example, it is also possible to employ a regulating jig that clamps a portion that becomes a high load portion from both the upper and lower surfaces of the laminate 2 during the stretching process to restrict the stretching of the portion. be.

In addition, the core sheet 3.3 constituting the honeycomb core material 5.
. . . is not limited to aluminum, but may also be made of plastic, paper, or other suitable materials depending on the application.

(Effects of the Invention) As explained above, according to the present invention, in the process of stretching the laminate of the honeycomb core material to form the honeycomb-shaped space, the expansion of the portion of the core material that becomes a high load portion is regulated by the regulating jig. Therefore, the core density can be partially increased without extra work such as separately inserting core materials with different core densities or filling with synthetic resin after expansion, and this results in high-load parts of the core material. A honeycomb panel structure whose parts are strengthened can be easily obtained.

[Brief explanation of drawings]

The drawings show an embodiment of the present invention, and Fig. 1 is a process diagram showing the manufacturing process, Fig. 2 is a perspective view of a honeycomb core material in which expansion regulation parts are partially formed using a regulation jig, and Fig. 3 is a regulation diagram. Figure 4 is a cross-sectional view of the jig taken along line ■-m in Figure 2, Figure 4 is a cross-sectional view of the regulating jig taken along line IV-IV in Figure 2, and Figure 5 is an enlarged plan view showing the honeycomb core material after expansion. , Fig. 6 is a longitudinal sectional front view showing a state in which the mounting brackets are fixed by bolting in order to attach various parts etc. to the honeycomb panel structure, and Fig. 7 is a perspective view for explaining the formation process of the laminate. be. DESCRIPTION OF SYMBOLS 1... Honeycomb panel structure, 2... Laminate, 3...
... Core sheet, 4 ... Adhesive application part, 5 ... Honeycomb core material, 6 ... Honeycomb-shaped space, 7 ... Regulating jig, 12 ... Face plate. Patent applicant Mazda Motor Corporation 1. - 111th generation Masato 1) Hiroshi [・ □,・
Dan-ku 1 Fig. 7 Fig. 5

Claims (1)

[Claims] (1) A laminate made by laminating and bonding a large number of core sheets coated with adhesive at predetermined intervals such that each adhesive coated area is positioned with a certain regularity is used as a high-load area. Forming a honeycomb core material having a honeycomb-shaped space between core sheets by expanding it while partially regulating it with a regulating jig so that the expansion rate of the part is smaller than that of other parts,
A method for manufacturing a honeycomb panel structure, comprising: thereafter bonding face plates to both sides of the core material to obtain a honeycomb panel structure.