JPH094712A - Aircraft pressure vessel and its manufacture - Google Patents

Abstract

PURPOSE: To provide a aircraft pressure vessel and its manufacture whereby such a labor to wind additional reinforcing fiber on the reinforced part of a vessel main body and cut or joint honeycomb cores is eliminated and the same reinforced effect as before can be obtained. CONSTITUTION: For the reinforced fibers 10a and 10b of helical filament winding, a bundle of 3000 filaments (f) is used and, for the reinforced fibers 11a and 11b of hoop filament winding, a thick filament winding formed with a bundle of 12,000 filaments (f) is used. Also, for a reinforced part X at the mounted part of a strap, the filament winding is wound at a fine winding pitch and, for the other general parts Y excluding the reinforced part X, it is wound at a coarse winding pitch.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a pressure vessel for an aircraft and a method for manufacturing the same, and more particularly to a reinforcing structure for a pressure vessel such as a drinking water tank for an aircraft having a mounting structure for the inside of an aircraft body. It is a thing.

[0002]

2. Description of the Related Art Generally, as a mounting structure of an aircraft pressure vessel, for example, a drinking water tank for an aircraft, as shown in FIG. 3, a cylindrical container body 1 is attached to two body structures. It was placed on the bases 2a and 2b, and was clamped and fixed via two straps 3a and 3b.

By the way, in the case of such a mounting structure for the container body 1, the straps 3a and 3b of the container body 1 and the base 2 are caused by a sudden ascent and descent of the body, and further a sudden turn.
A high stress is generated in the portion A that contacts a and 2b. Therefore, as shown in FIG. 4, the strap 3 of the container body 1
It is necessary to reinforce the portions A that come into contact with the a and 3b and the bases 2a and 2b.

[0004]

As a conventional reinforcing structure of the container body 1, as shown in FIG. 5, a thin film inner layer material 4 (liner) formed in a hollow shape is formed on the outer peripheral surface of FIG. Hoop winding 5a and helical winding 5b of reinforcing fiber 5 of filament winding having a cross section width of 1.6 mm and a thickness of 0.12 mm, which is obtained by bundling 3000 filaments f as shown in a).
And wrapping the honeycomb core 6 on the reinforcing fiber 5 by winding 3000 filaments of the same filament f, and winding the reinforcing fiber 7 by the helical winding 7b and the hoop winding 7a. Reinforcement portion A of the container body 1 having the structure
In addition, the reinforcing fiber 8 is reinforced by hoop winding.

However, the reinforcing method as described above is easy to process, but since the laminated structure has an asymmetric structure above and below the honeycomb core 6, the moment of inertia of section and the section modulus increase only slightly. However, there is a problem that the reinforcing effect is low. Further, as a reinforcing structure for solving such a problem, as shown in FIG. 6, the thickness of the honeycomb core 6a of the reinforcing portion A of the container body 1 is reduced to reduce the honeycomb core 6a.
A structure has been proposed in which 3,000 filaments f are bundled on the upper and lower surfaces and reinforcing fibers 9a and 9b of filament winding are reinforced by hoop winding.

This reinforcing structure has a laminated structure in which the reinforcing portion A is symmetrical and has a good reinforcing effect, but since the honeycomb cores 6 and 6a having different thicknesses are used, there are the following problems. That is, if there are two reinforcing portions A, the honeycomb core 6,
6a needs to be prepared by dividing it into five pieces, so that the labor for cutting the honeycomb cores 6, 6a increases.

Further, since the divided honeycomb cores 6, 6a are used, it takes time and effort to connect the honeycomb cores 6, 6a, resulting in extremely poor productivity. The present invention has been devised in view of such conventional problems, and the reinforcing portion of the container body is further wound with reinforcing fibers, the honeycomb core is cut, and the time and effort of joining and using are omitted. It is an object of the present invention to provide a pressure vessel for an aircraft and a method for manufacturing the same, which is capable of achieving the same reinforcing effect as in the past.

[0008]

In order to achieve the above object, the present invention forms a general portion of a reinforcing layer and a reinforcing portion of a strap attaching portion by using a bundle of thick filament winding fibers, and The reinforcing part is made to have a dense fiber winding pitch, and the fiber winding pitch of the other general parts is made sparse.

[0009]

According to the present invention, the reinforcing fiber of the filament winding is wound around the outer peripheral surface of the hollow thin film inner layer material by the hoop winding and the helical winding, and is formed on the reinforcing fiber. In a state in which honeycomb cores are laminated, a reinforcing body for filament winding is wound by helical winding and hoop winding to form a container body, and the container body is integrally molded by heating and pressurizing. In the manufacturing method, the fiber of the filament winding for hoop winding is used with a thick fiber bundle, and the reinforcing portion of the strap attachment portion that is attached to the straight body portion of the container body is wound with a tight winding pitch. Other parts except the reinforcing part are wound with a narrow winding pitch.

The container body thus formed is integrally molded by heating and pressurizing the container body so that reinforcing fibers can be further wound around the reinforcing portion of the container body.
Further, it is possible to omit the trouble of cutting the honeycomb core and using it for joining, and it is possible to obtain the same reinforcing effect by using the same amount of fibers as the conventional one.

[0011]

Embodiments of the present invention will be described below with reference to the accompanying drawings. The same components as those in the conventional example are denoted by the same reference numerals, and description thereof will be omitted. FIG. 1 is a partially enlarged cross-sectional view of a reinforcing portion X of a container body 1 of a pressure vessel for an aircraft embodying the present invention, and 4 is a thin-film inner layer material (liner) formed in a hollow shape. The outer peripheral surface of the thin film inner layer material 4 is divided into a reinforcing portion X for attaching the straps 3a and 3b and another general portion Y, and the honeycomb core 6 is sandwiched between the reinforcing fibers 10a for filament winding. 10b and 11a, 11b are wound by hoop winding and helical winding to form the container body 1.

In the embodiment of the present invention, the reinforcing fibers 11a, 11 of the filament winding of the above helical winding.
b is a cross-sectional width of 1.6 mm and a thickness of 0.12 mm obtained by bundling 3000 filaments f as shown in FIG.
The reinforcing fibers 10a and 10b of the hoop-wound filament winding have a cross sectional width of 3.2 mm and a thickness of 0.24 mm in which 12,000 filaments f are bundled as shown in FIG. 2 (b). It uses thick filament winding.

The reinforcing fibers 10a, 10b of the thick hoop-wound filament winding are wound with a dense winding pitch of the filament winding in the reinforcing portion X of the strap attachment portion attached to the straight body portion of the container body 1. Attached, general portion Y excluding the reinforcing portion X
Is wound with a narrow winding pitch for filament winding.

By thus dividing the winding pitch into the reinforcing portion X and the general portion Y and applying the hoop winding, the yarn amount of the reinforcing fibers 10a and 10b becomes equivalent to that of the conventional one, and the same. It is possible to obtain a strong reinforcing effect. Next, a method of manufacturing a pressure vessel for aircraft will be described. First, on the outer peripheral surface of the hollow thin film inner layer material, the reinforcing fiber 10a of the thick filament winding in which 12,000 filaments f are bundled is provided in the general portion Y. For, the winding pitch is made sparse, and the reinforcing portion X of the strap mounting portion is wound by hoop winding with a tight winding pitch.

Next, 3 filaments f are provided on the outer peripheral surface of the filament.
000 bundles of the filament winding reinforcing fibers 11a are wound by helical winding, the honeycomb core 6 is laminated thereon, and then the filaments f are 3,000 again.
Reinforcing fiber 11b of the bundled filament winding
Is wound by helical winding, and the reinforcing fiber 10a of thick filament winding in which 12,000 filaments f are bundled is further wound on the general portion Y with a narrow winding pitch, and on the reinforcing portion X of the strap attachment portion. Is wound by hoop winding with a tight winding pitch.

The container body 1 thus formed is placed in an oven or the like, heated and pressed to be integrally molded, so that reinforcing fibers are further added to the reinforcing portion X of the container body 1 as in the conventional case. The work of winding, cutting the honeycomb core, and joining the honeycomb cores can be omitted, and a similar reinforcing effect can be obtained by using the same amount of yarn as the conventional one.

[0017]

As described above, according to the present invention, the general portion of the reinforcing layer and the reinforcing portion of the strap attaching portion are formed by using a bundle of thick filament winding fibers, and the reinforcing portion of the strap attaching portion is a fiber winding. By making the attachment pitch dense and making the fiber winding pitch of other general parts sparse, it is possible to further wind the reinforcing fiber around the reinforcing portion of the container body and cut the honeycomb core as in the conventional case. As a result of eliminating the trouble of jointing and using, there is an effect that productivity can be improved and a similar reinforcing effect can be obtained with the same fiber weight as the conventional one.

[Brief description of drawings]

FIG. 1 is a partially enlarged sectional view of a reinforcing portion of a container body embodying the present invention.

FIG. 2 (a) is a cross-sectional explanatory view of a reinforcing fiber of filament winding wound by helical winding, (b).
[FIG. 3] is a cross-sectional explanatory view of reinforcing fibers of filament winding wound by hoop winding.

FIG. 3 is a perspective view showing a mounted state of a conventional aircraft pressure vessel (drinking water tank).

FIG. 4 is a side view of a conventional aircraft pressure vessel (drinking water tank).

FIG. 5 is a partially enlarged sectional view of a reinforcing portion of a conventional aircraft pressure vessel.

FIG. 6 is a partially enlarged sectional view of a reinforcing portion of another conventional aircraft pressure vessel.

[Explanation of symbols]

DESCRIPTION OF SYMBOLS 1 Container body 4 Thin film inner layer material (liner) 6 Honeycomb core 10a, 10b Reinforcing fiber of filament winding of hoop winding 11a, 11b Reinforcing fiber of filament winding of helical winding X Reinforcing portion of container body Y General portion of container body

──────────────────────────────────────────────────続 き Continued on the front page (51) Int.Cl. ⁶ Identification code Agency reference number FI Technical indication // B29L 22:00

Claims (2)

[Claims] 1. An aircraft formed by integrally forming a container body by forming a reinforcing layer by filament winding with a honeycomb core interposed on a hollow thin film inner layer material, and attaching a mouthpiece to both ends. In the pressure vessel for use, the general portion of the reinforcing layer and the reinforcing portion of the strap attaching portion are formed by using a bundle of thick filament winding fibers, and the reinforcing portion of the strap attaching portion makes the fiber winding pitch dense, The air-vessel pressure vessel characterized in that the fiber winding pitch in the general part of is made sparse. 2. A filament wound reinforcing fiber is wound around the outer peripheral surface of a hollow thin film inner layer material by hoop winding and helical winding, and a honeycomb core is laminated on the reinforcing fiber. A method for manufacturing an aircraft pressure vessel, comprising winding a reinforcing fiber for winding by helical winding and hoop winding to form a container body, and integrally molding the container body by heating and pressurizing the container body. The thick part of the bundle is used to attach to the straight body part of the container body. The reinforcement part of the strap attachment part is wound tightly, and the other part except the reinforcement part is wrapped with the pitch. It is special to form the container body integrally by heating and pressing the container body formed in this way. A method of manufacturing a pressure vessel for an aircraft.