JPH1120031A - Material for aircraft - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a material for an aircraft formed of an assembly structure having a plurality of branches in a lengthwise direction integrally manufactured by braiding. SOLUTION: A plurality of assembly units 1 for forming a branch by braiding by using a braider and assembling a plurality of filaments via a mandrel are manufactured. A main tube 1a of these units 1 is, for example, coupled by a coupling mandrel 3, and an assembly aggregate is formed. The aggregate is integrally braided to manufacture the material for an aircraft.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention is made by performing braiding using a braider and assembling a plurality of yarns or fiber bundles (hereinafter referred to as "yarns") via a mandrel. It relates to aircraft materials.

[0002]

2. Description of the Related Art There has been known a molded product formed by forming a braid around a mandrel by performing braiding using a braider and then molding and curing the braid with a resin. Such molded articles are extremely lightweight and have high strength, and thus are widely used as various parts of aircraft.

[0003] In this case, a straight braid or a braid forming a branch portion can be easily manufactured, but the main pipes of the braid forming the branch portion are connected to each other due to structural limitations of the blader. A braided structure having a plurality of branch portions in the length direction, which is formed by joining together, is difficult to integrally produce by braiding, and therefore, a molded article having a plurality of branch portions in the length direction. It was difficult to produce by integral molding.

[0004] For this reason, for example, when fabricating an aircraft material having a plurality of branches in the longitudinal direction, such as a skid of a helicopter, according to the conventional braiding technology, the material is formed from a braid forming the branches. The aircraft material has been assembled by bonding the molded product unit and the molded product unit made from the linear assembly to each other with an adhesive or the like or connecting them with bolts.

However, such an assembling operation involves a number of steps, so that there is a problem that the assembling cost is high and the strength of the joint portion of each molded product unit is not sufficient.

[0006]

SUMMARY OF THE INVENTION Accordingly, an object of the present invention is to provide an object which is integrally manufactured by braiding.
An object of the present invention is to solve the above problem by providing an aircraft material including a braided structure having a plurality of branch portions in a length direction.

[0007]

According to the present invention, in order to solve the above-mentioned problems, a branching portion is formed by performing braiding using a blader and assembling a plurality of yarns via a mandrel. A plurality of braided units were produced, the main pipes of these braided units were connected to form a braided combined body, and the braided body was integrally braided to be fabricated. The aircraft material is characterized by the following.

[0008] In this configuration, preferably, after the braided unit is manufactured, the mandrel is extracted from each main pipe of the braided unit, and the connecting mandrel is passed through the main pipe of the braided unit. It is formed by connecting the main pipes of the braided unit.

[0009] More preferably, a liner is mounted between a predetermined portion of the connecting mandrel in the braid assembly and the yarn assembled thereon.

[0010]

Preferred embodiments of the present invention will be described below with reference to the accompanying drawings. FIG. 1 is a front view of one example of a blader suitable for performing the method according to the present invention, and FIG. 2 is a side view of the blader shown in FIG.

In FIG. 1 and FIG.
Is composed of a blader body Bb and a mandrel device Bm. The blader body Bb is provided with a curved upper plate U having a radius of curvature R disposed in a substantially cylindrical machine base Fb having a horizontal axis and an opening e on one side, and is provided in a circumferential direction of the upper plate U. A bobbin carrier C that travels along the trajectory, a driving device D that causes the bobbin carrier C to travel along the trajectory, and a yarn guiding device G.

Then, the yarn Y pulled out from the bobbin mounted on the bobbin carrier C in the axial direction of the bobbin gathers substantially at the center of the upper plate U, and the position of the mandrel m attached to the mandrel device Bm is , The assembly point P of the assembly formed on the mandrel m is located at the center of the upper plate U. The mandrel device Bm can control the position of the mandrel m one-dimensionally, two-dimensionally, or three-dimensionally.

In this way, the bobbin carrier C is caused to travel along the track by the driving device D, and the position of the mandrel m is controlled by the mandrel device Bm. As a result, a large number of yarns Y intersect, and Correspondingly, the middle thread y from the bobbin carrier C disposed substantially horizontally on the frame Fb 'of the machine base Fb is entangled with the thread Y that is unwound and assembled from the bobbin carrier C traveling along the track. As a result, braiding is performed, and braids are assembled on mandrels m of various shapes.

After the braiding is completed by braiding, the yarns Y and y are cut by a suitable cutting device, and the mandrel m with the completed braid is removed from the mandrel device.

Using the above-mentioned braider BR composed of the braider body Bb and the mandrel device Bm,
An aircraft material according to the invention is made. Hereinafter, a case where a skid of a helicopter, particularly, a leg of the skid is manufactured as an example of the aircraft material will be described.

First, as shown in FIG. 3, a braider is used to form a braid 1 which forms a T-shaped branch of a skid leg on a T-shaped mandrel 2a, 2b by braiding. You. In this case, an assembly 1 is formed which forms two T-shaped branches for each of the pair of legs of the skid.

Next, the mandrel 2a of the main pipe portion of the T-shaped mandrel is extracted from the inside of each of the braids 1 thus manufactured. Then, as shown in FIG. 4, a linear connecting mandrel 3 is disposed so as to penetrate the main pipe portion 1 a of each of the braids 1, and the mandrel 2 b of the branch pipe portion 1 b of each of the braids 1
Are fixed to the linear mandrel 3. In this way, the main pipes 1a of the two braids 1 are connected by the connecting mandrel 3 at a distance from each other.

Further, as shown in FIG. 5, a curved mandrel 4 forming the tip of the leg of the skid is fixed to the front end of the connecting mandrel 3 to form a braided combination. A liner 5 having a thickness corresponding to the thickness of the peripheral wall of the braid 1 is provided on a region of the connecting mandrel 3 which is not covered by the braid 1 and on the outer periphery of the curved mandrel 4.
Is attached. The liner 5 prevents a step from being formed in a boundary region between each of the braids 1 and the connecting mandrel 3 when braiding is integrally performed on the braid assembly as described later.

Then, the mandrel of the braided assembly is mounted on the mandrel device, and is appropriately swirled to move along the curved mandrel 4, the connecting mandrel 3, and the axial direction of the main pipe 1a of the braid 1. Thus, the braiding is integrally performed on the braid assembly. At this time, the assembled yarn 6 does not catch on the branch pipe portion 1b of the braid 1 due to the swiveling motion of the mandrel of the braid assembly. In this way, the braided structure forming the legs of the skid, ie the aircraft material, is formed.

Further, as shown in FIG. 6, the braid 7 is used to separately manufacture the braids 7 forming the connecting portions for connecting the pair of legs of the skid to each other.

A braided structure forming each leg of the individually manufactured skid and a braided structure 7 forming a connecting portion
Is then molded. In this case, as a molding method, any method such as external pressure or internal pressure molding using an RTM, an autoclave or the like may be adopted. In the case of the internal pressure molding, an internal pressure tube is used in place of the mandrel in the resin molding step.

Next, the legs and connecting portions of the molded skid are joined together. FIG. 7 shows the connection between the leg of the skid and the connecting part in detail. As shown in FIG. 7, the branch pipe portion 1b of the leg 12 has a reinforcing portion 8 formed so as to be thicker in the distal end region than in other regions. A through hole 9 for passing a bolt is formed in the peripheral wall.

The reinforcing portion 8 is formed by assembling the braid 1 by reciprocating the thread many times at the time of fabricating the braid 1 described with reference to FIG. At the time of manufacture, a pin corresponding to the through hole 9 is inserted into the outer peripheral surface of the mandrel 2b of the branch pipe portion 1b, and the thread is made to escape at that portion.
Further, the inner cavity of the reinforcing portion 8 is formed so as to be tapered toward the back by post-processing after molding.

The connecting portion 7 also has a reinforcing portion 10 formed so as to be thicker in the distal end region than in other regions, and the peripheral wall of the reinforcing portion 10 has
A through hole 11 for passing a bolt is formed corresponding to the through hole 9 of the reinforcing portion 8 of the branch pipe portion of the leg 12. The method of forming the reinforcing portion 10 and the through hole 11 of the connecting portion 7 is as follows.
This is the same as the case of the branch pipe portion 1b of the leg 12. Further, the outer peripheral surface of the reinforcing portion 10 of the connecting portion 7 is formed so as to taper toward the distal end in accordance with the shape of the lumen of the branch tube portion 1b of the leg 12.

The reinforcing portion 10 of the connecting portion 7 is
Is inserted into the lumen of the reinforcing portion 8 of the branch pipe portion 1b, and the connecting portion 7 and the leg 12 are connected by an adhesive and a bolt, thereby completing the skid 13 as shown in FIG.

Thus, according to the present invention, a skid for a helicopter can be manufactured in a smaller number of steps than in the past. In addition, the strength of the joint between the branch portion and the linear portion of the skid leg can be significantly improved. In this embodiment, the case where a skid of a helicopter is manufactured has been described. However, the present invention is not limited to this embodiment, and according to the present invention, there is provided a group having a plurality of branch portions. The aircraft material composed of the object structure can be integrally manufactured by braiding. In this case, a braid forming a branch portion other than the T-shape can be used, or the braids can be connected to each other by using a curved connecting mandrel to form a braid assembly.

[0027]

As described above, according to the present invention, an aircraft material consisting of a braided structure having a plurality of branches in the longitudinal direction can be integrally manufactured by braiding. The cost of assembling the material for aircraft can be reduced, and the strength of aircraft parts formed from the material for aircraft can be significantly improved.

[Brief description of the drawings]

FIG. 1 is a front view of one example of a braider suitable for performing the method according to the invention.

FIG. 2 is a side view of the blader shown in FIG.

FIG. 3 is a side sectional view illustrating a case where a skid of a helicopter is manufactured as an example of the aircraft material according to the present invention.

FIG. 4 is a side sectional view illustrating a case where a helicopter skid is manufactured as an example of the aircraft material according to the present invention.

FIG. 5 is a side sectional view illustrating a case where a helicopter skid is manufactured as an example of the aircraft material according to the present invention.

FIG. 6 is a side sectional view illustrating a case where a skid of a helicopter is manufactured as an example of the aircraft material according to the present invention.

FIG. 7 is a view showing a connecting portion between a leg of a skid of a helicopter and a connecting portion.

FIG. 8 is a perspective view of one leg side of the completed helicopter skid.

[Explanation of symbols]

 Reference Signs List 1 Braid forming T-shaped branch of skid leg 1a Main pipe 1b Branch pipe 2a Main pipe mandrel 2b Branch pipe mandrel 3 Straight connection mandrel 4 Curved mandrel 5 Liner 6 Assembled Thread 7 Braid forming connection part 8 Reinforcement part 9 Through hole 10 Reinforcement part 11 Through hole 12 Skid leg 13 Skid

──────────────────────────────────────────────────続 き Continued on the front page (51) Int.Cl. ⁶ Identification code FI // B29K 105: 08

Claims (3)

[Claims] 1. A plurality of braided units which form a branch by producing a plurality of yarns through a mandrel by performing braiding using a braider, and a main pipe of these braided units. An aircraft material produced by connecting parts to form a braided combination and integrally braiding the braided combination. 2. The braid assembly, after producing the braid unit, pulls out a mandrel from each main pipe part of the braid unit, and penetrates a connecting mandrel through the main pipe part of the braid unit. The aircraft material according to claim 1, wherein the material is formed by connecting main pipes of the braided unit. 3. The aircraft according to claim 2, wherein a liner is mounted between a predetermined portion of the connection mandrel in the braided assembly and a thread assembled thereon. Materials.