JPS5881896A - Aircraft plane made of composite material - 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 The present invention relates to an aircraft wing made of fiber-reinforced composite material suitable for the aerodynamic characteristics of an aircraft.

Currently, there are two types of composite materials used in aircraft, which are called high-strength type composite materials due to their different properties.
There is something called a high elasticity type composite material.

These in 0FRP are mainly obtained by changing the type of carbon fiber. Table 1 shows the properties of OFI'LP using carbon fibers extracted from the pamphlet provided by Company A. Materials using the elastic modulus E are called high elasticity type composite materials.

Conventionally, when manufacturing aerodynamic wing surfaces of aircraft using bonding materials, the unidirectional composite material used for the outer skin is a bonding material that is particularly strong and has excellent properties (hereinafter referred to as high-strength type composite material).
Alternatively, only one type of composite material with particularly excellent elastic properties (for example, one that satisfies properties such as a high modulus of elasticity and is hereinafter referred to as a high-strength type composite material) is unified.
No efforts have been made to use two or more composite materials with different strength and elastic properties.

Therefore, for example, when using a high-strength composite material for the entire wing, the strength is determined at the wing root.

The number of pole layers may be determined so as to satisfy the strength requirements. However, even if the strength of the outer wing is increased, it tends to be rigid due to the requirements for aeroelastic properties, and if high-strength composite paulownia wood is used in this part to meet the rigidity requirements, a structure with a large surplus in terms of strength will result. In addition, compared to using a high-elasticity type composite material in the outer wing section, the weight is increased, and the aeroelastic properties are 8%, which is disadvantageous for flutter, etc. Therefore, there is a need to further increase the number of laminated layers and increase the rigidity. The flap had the disadvantage of being wasteful in terms of cost.

In addition, similarly high elasticity composite material is used for the entire wing.
If the strength is satisfied at the blade root, where the strength is oriented, the blade root becomes a structure with a large surplus in terms of rigidity.

There were some problems that resulted in waste in terms of weight and cost.

Therefore, in order to improve these defects and shortcomings,
Conventionally, there is a method known as tailoring technology that optimizes composite materials by changing the lamination direction and number of layers, but this method requires a special computer program and has some disadvantages. .

The present invention eliminates the waste of weight and cost, and improves strength and
The objective is to provide an aircraft wing that effectively satisfies rigidity requirements and can be easily optimized.
If used in conjunction with the puller rolling technique described in nlj, it is possible to produce even more efficient rolls.

The aircraft fiber made of the composite material of the present invention has a high-strength type composite material laminate at the wing root, which serves as a strength standard.

It is characterized by the fact that the outer wing sections, which provide rigidity, are made of elastic composite material laminates.

The present invention will be explained in detail below with reference to one drawing.

FIG. 1 is a schematic diagram of a wing cross section showing the lamination of two composite material aircraft wings as an embodiment of the present invention.

FIG. 2 is an enlarged view of section A showing details of the composite material 4+ stacked state in FIG. 1. Figures 3, 4, 5, and 6 are
FIG. 2 is a schematic true plan view showing the arrangement of fibers constituting the composite material in the laminated state of the composite material in FIG. 2. What is the 00 direction here?

is the direction from the wing root 7 to the outer wing 8 at the chord of the wing,
Regarding the angle, the front of the wing is positive and the rear edge of the wing is negative. Figures 3 and 4 show high-strength type 3 in which the fiber direction is 0°. This shows a composite material laminate from High Elasticity Quiz 4, with bending applied to the wing.

This is to maintain the continuity of the fibers in the middle of the wing so that it can resist the tensile and compressive stress (axial force) that occurs across the entire surface of the wing.

Figure 5 shows a laminate 5 made of a composite material with a fiber direction of +α0, in which the high-strength tie-blade composite material 1 is applied to the blade root part 7, which has two strength orientations, and the high-strength tie-bu composite material 1 is applied to the outer blade part 8, which has rigidity orientation. An elastic type composite material 2 is arranged. Similarly, in Figure 6, the fiber direction is -
This shows the composite material Hanto laminate 6 with α0, and the blade root 7
High-strength type composite material 1 is applied to the outer wing, and high-elasticity quiz is applied to the outer wing.
Composite material 2 is arranged.

The laminated plates 3, 4, and 5°6 of each composite material are laminated as shown in FIG. 2 (75).

A laminate plate 3 made of a high-strength type bales material in the fiber direction O0 is placed in the center layer of the stack, and each laminate plate 3, 4, 5, and 6 is stacked 17 in mirror symmetry around this laminate plate. The number of times of lamination is 10-20 times in thin places and 50-6 times in thick places.
Required 0 times.

In this way, when the wing surface is made, the blade root of the strength locating part is made of a high-strength quiz composite material, and the outer wing part of the rigidity locating part is made of a high-modulus composite material. Many laminates are used, each with a strong [1! In order to meet the demands and rigidity requirements, the surplus in strength or rigidity can be reduced by one.

In other words, since many high-strength composite material laminates are used in the blade root, which has one strength orientation, the strength can be increased while eliminating wasted rigidity, and the number of laminated layers can be reduced. Furthermore, since a large number of high-modulus composite material laminates are used in the outer wing section, which is used to determine the rigidity, waste in terms of strength can be eliminated, rigidity can be increased, and the number of unnecessary laminated layers can be eliminated. In particular, since a high-elasticity composite material laminate is used for the ±αO layer, torsional rigidity is increased, and aeroelastic properties such as flutter and quizzence can be improved.

In addition, in the aircraft wing made of a gold-receiving material according to the present invention, it is not necessarily necessary to change the composite material in the middle of a single laminated plate.

A second embodiment of the present invention shown in FIGS. 7, 8, 9, 10, and 11 will be described below.

Figures 7, 8, 9, and 10 are true plane diagrams of laminates made of composite materials of one type, and 9 is a laminate of high-strength type composite materials with a fiber direction of +α0. The board, 10 is a laminate of a high-strength type composite material with a fiber direction of 1αO, 11 is a laminate of a high-elasticity type composite material with a fiber direction of +α0, and 12 is a high-elasticity type laminate with a fiber direction of −α0. A composite laminate is shown. Figure 11 is.

This is a schematic cross-sectional view of a composite material wing according to a second embodiment of the present invention when cut in the 00 direction. High elasticity composite material laminates 4, 11, 12 are used in large numbers in the portion near the center layer of the laminated layer, where the layers continue for a long time up to the blade tip of the outer wing portion 8.

Even if a large number of high-strength type composite material laminates 3, 9, and 10 are used in the surface layer of the composite material, which is only necessary up to the middle of the wing, the same effect can be obtained as a result.

By using the aircraft wing made of composite material of the present invention, strength requirements and rigidity requirements for aeroelastic properties such as flutter and divergence can be easily satisfied; In addition to the surface,
It can also be applied to leisure and sporting goods that use composite materials as strong and rigid members.

Table 1 Characteristics of Company A carbon fiber unidirectionally reinforced composite material

[Brief explanation of drawings]

Fig. 1 is a schematic longitudinal cross-sectional view in the chord direction of an aircraft wing surface made of composite material, Fig. 2 is an enlarged cross-sectional view of the wing of Fig. 1 showing the laminated state of composite materials of the first embodiment of the present invention, and Fig. 3 Figures 4, 5, 6, and 7. Figures 8, 9, and 10 are schematic plan views of a wing laminate material showing the fiber direction and type of fiber of the fiber reinforced composite material constituting the wing of the embodiment of the present invention, and Figure 11 is a plan view of the wing laminate material of the present invention. FIG. 3 is a schematic vertical cross-sectional view in the spanwise direction showing the laminated state of composite materials on the blade surface of the second embodiment of the present invention. l: High-strength type composite material laminate (partial). 2: High elasticity type composite material laminate (partial). 3: Laminated board of high strength type composite material with fiber direction 00,
4: Laminated board of high elasticity type composite material with fiber direction 00,
5: Composite material laminate with a fiber direction of +α0 and a combination of high elasticity type and high strength type. 6: Fiber direction is -α0, high elasticity type and high strength. Composite material laminate using both types, 7: Blade root. 8: Outer wing part, 9: Laminate of high-strength type composite material with fiber direction +α0, 10: Laminate of high-strength type composite material with fiber direction -α0, 11: High elasticity type composite with fiber direction +α0 Material laminate. 12: Laminated board of high elasticity type composite material with fiber direction -a0. Man 3 Figure 84 Sen Man 5 Figure Man 6 Close Man 7 Prisoner Gen 8 Sen

Claims (1)

[Claims] In the aircraft wing structure, the wing root, which is one strength location, is made of a high-strength composite material laminate, and the outer wing, which is a rigidity location, is made of a high-modulus composite material laminate. A composite material aircraft wing featuring