JPH0357794A - Wing structure for airplane - Google Patents

Abstract

PURPOSE:To eliminate the dispersion of the dimension of each wing module and shape the wing sectional form with high precision by shaping each article of the wing module. CONSTITUTION:A plurality of wing modules 12 which are molded to a wing sectional form from resin material are arranged in parallel along the longitudinal direction of a wing. Then, the contiguous wing modules 12 are connected by the girders 30 which penetrate through the wing modules 12, and a desired wing structure (main wing) 10 of an airplane is formed.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a wing structure for a lightweight aircraft such as a human-powered airplane.

[Prior Art] In conventional human-powered airplanes, it is known that the main wings are molded from a lightweight resin material whose base material is expanded polystyrene.

This main wing has a structure in which a plurality of small bones having an airfoil cross section are connected with spars to form a lattice-like frame, and an outer plate is attached to this frame.

[Problems to be Solved by the Invention] In order to fully utilize the aerodynamic characteristics of the main wing, it is necessary to set the dimensions of each part of the main wing with high precision, including the cross-sectional shape of the main wing.

However, in conventional human-powered airplanes, all of the parts that make up the main wing, such as the small bones, spars, and outer panels, were handmade, so special manufacturing techniques were required to obtain the theoretical wing shape. there were. For this reason, it takes a great deal of time and effort to manufacture each of the above-mentioned parts, and since they are handmade, there is a natural limit in terms of dimensional accuracy, and there is still room for improvement in this respect.

The present invention was made based on these circumstances, and
The purpose of the present invention is to provide an aircraft wing structure capable of forming a lightweight yet strong wing with high precision without requiring special techniques.

[Means for Solving the Problems] Therefore, the present invention includes a plurality of wing modules molded from a resin material into a cross-sectional airfoil shape and arranged side by side along the longitudinal direction of the wing, and there is a gap between these wing modules. It is characterized by passing through a spar and connecting adjacent wing modules to each other with this spar.

[Operation] According to this configuration, the plurality of wing modules that form the wing are
Since each piece is molded, not only is there no variation in dimensions, but a highly accurate blade cross-sectional shape can be obtained.

In addition, since the plurality of wing modules are connected to each other by passing through the spars along the direction in which they are juxtaposed, in combination with the fact that the wing modules are molded, it is necessary to use a special jig to form the wing modules. It is possible to connect accurately without any problems. Therefore, the connection work can be performed simply and easily, and no complicated special manufacturing techniques are required.

Furthermore, since the spars that penetrate between the wing modules function as cross members, the wings can be made of resin to reduce weight while ensuring sufficient strength.

[Embodiment] An embodiment of the present invention will be described below based on drawings in which the present invention is applied to a human-powered airplane.

The fuselage, indicated by the reference numeral 1 in FIGS. 1 and 10, includes a cockpit 2 in which a passenger gets into the vehicle. A rearwardly extending tail boom 3 is provided at the rear of the fuselage 1, and the tail boom 3 is provided with a vertical stabilizer 4 and a horizontal stabilizer 5.

A propeller pod 7 is supported at the upper part of the fuselage t via an upwardly extending pylon B, and a propeller 8 is provided at the rear of the propeller pod 7, which is driven by the leg force of the occupant.

Furthermore, a main glO extending in the left-right direction is fixed to the upper part of the body 1. The main wing 10 of this embodiment has three wing units lla. llb, lie, and these wing units lla. 1lb, l
Each lc is constructed by arranging a plurality of wing modules 12 in parallel in the longitudinal direction of the main wing 10.

These wing modules 12 all have a common configuration, and the details of the wing modules 12 will be explained below by representing one wing module.

That is, as shown in FIGS. 3 and 4, the wing module l2 has a square shape in plan view and an airfoil shape in cross section, and the leading edge reinforcement is applied in order from the leading edge side along the longitudinal direction of the main wing lO. Material 13, I-shaped cross-section spar holder 1
4 and a trailing edge reinforcement l5. These leading edge reinforcing material 13, suber holder l4, and trailing edge reinforcing material 15 are as follows:
Each of them is a styrofoam molded product, and they are arranged parallel to each other with an interval in the front-rear direction of the main GLO.

A through hole 1B is provided inside the leading edge reinforcing material l3 and the trailing edge reinforcing material 15 along the longitudinal direction, and
The spar holder l4 is divided into front and rear parts, and recesses L8a and 18b are formed over the entire length of the mating surfaces of these divided pieces 17a and 17b, respectively. These recesses 1
8a, 18b are split beads 17a. When stacking l7b, a girder insertion hole t9 with an I-shaped cross section is formed,
This spar insertion hole 19 is opened at both left and right end surfaces of the wing module 12.

A plate-shaped small rib 2o is provided between the leading edge reinforcing member l3 and the stub holder l4, between the shaving holder 14 and the trailing edge reinforcing member 5, and on the rear surface of the trailing edge reinforcing member i5. These small bones 20 are also molded or shaped products of styrofoam,
They are arranged on both left and right end surfaces of the wing unit 10 and at three locations between these end surfaces, spaced apart in the left and right direction, and
The ossicles 2o that are adjacent to each other in the front and back with the spar holder l4 and the rear edge reinforcing member 15 sandwiched therebetween are located on the same straight line.

Therefore, these leading edge reinforcement l3, suba holder l
4. The rear edge reinforcing material 15 and the small bones 20 constitute a frame body 2l framed in a lattice shape as shown in FIG.

By covering the periphery of this frame body 2l with an outer skin 22 made of polystyrene, for example, the wing module l
2, and since the frame body 21 has a lattice shape inside the wing module 12, the portions corresponding to the eyes of this lattice are spaces 23.

Note that a lightening hole 24 is opened in the small bones 20 and the spar holder l4 for weight reduction.

Such a wing module i2 is produced by setting the frame body 21 coated with a fusion promoter and the outer skin 22 in a mold (not shown), and sealing the frame body 2 in the mold with the outer skin 22 surrounding it. , heat-forming is carried out by heating this mold.

That is, when the mold is heated, the leading edge reinforcing material l3, the spar holder 14, and the trailing edge reinforcing material 15 that constitute the frame body 21 are heated.
The contact portions of the small bones 20 are fused together and joined together, and the contact portions between the frame body 2l and the outer skin 22 are also fused and integrated. Moreover, these framework bodies 2
Since the inside of the mold containing the mold and outer skin 22 is sealed, the internal pressure of the mold is increased by the expansion of air as the temperature rises, and the outer skin 22 is tightly attached to the inner surface of the mold without any gaps, resulting in the above-mentioned condition. A shaped wing module l2 is molded.

After that, the wing module 12 is taken out from the mold, and if necessary, finish processing is performed on both the left and right end surfaces of the adjacent wing module 12, that is, the mating surface 12a with the adjacent wing module 12, using the spar insertion hole l9 as a reference. The work to apply is carried out.

Note that this finishing process is performed to prevent molding distortion and improve the accuracy of the mating surface 12a, and usually a method is used in which the mating surface 12a of the wing module 12 is wire-cut using a nichrome wire that generates heat. .

By the way, the main spar 30 having an I-shaped cross section is inserted into the spar insertion hole 19 of the wing module 12 molded in this way. The main girder 30 is made of carbon fiber reinforced thermosetting plastic (CFRP), and in the case of this embodiment, the main girder 3
0 continuously passes through eight wing modules 12 arranged in parallel in the longitudinal direction of the main wing IO.

In addition, a front spar 31 and a rear spar 32 made of CFRP pipes are inserted into the through holes 16 of the leading edge reinforcing member L8 and the trailing edge reinforcing member 15, which constitute the wing module l2, respectively. Similarly to the main spar 30, the sections 31 and 32 continuously pass through the eight wing modules 12.

In this case, adhesive is applied to the entire surface of the main spar 30, front spar 31, and rear spar 32, and to the joint surface of the wing module 12, respectively, and as shown in FIG. 31 and the rear spar 32 are passed through the eight wing modules in a skewered manner, and the wing modules l2 are brought into close contact with each other, thereby forming the wing units Ha, llb. It can be assembled as Lie.

In addition, in the case of this embodiment, the mating surface 12a of the wing module 12
As shown in FIG. 1, it extends in a direction perpendicular to the longitudinal direction of the main wing 10, but as shown by the imaginary line in FIG. You can let me.

On the other hand, the left and right wing units 11a. 11c and the central wing unit llb are connected to each other using the main spar 30 and the front spar 3l.

That is, as shown in FIGS. 5 and 6, the front spar 3l
Both ends of the wing unit lla, 1lb. It protrudes from the end face of l1c, and both ends thereof are connected to each other via a fitting 33.

In addition, the main girder 30 of the wing units lla and llc on both the left and right sides
A connecting fitting 34 is attached to the. Connecting metal fittings 3
4 is a pair of plates 35 that are provided at two places above and below the end of the main girder 30, and sandwich the main girder 30 from both the front and back sides, respectively.
a. 35b. The plates 35a, 35b are fastened to the main girder 30 via bolts 36 and nuts 37, and these plates 35a. 35b protrudes from the end surfaces of the wing units lla and lie. Both ends of the main spar 30 of the central wing unit Ilb protrude from the end face of this wing unit Ilb, and the main spar 30
Both ends of are inserted between the plates 35a and 35b and fixed via bolts 38 and nuts 39.

For this reason, the left and right wing units 11a. A gap 40 corresponding to the amount of protrusion of the main spar 30 is formed between the wing unit 11c and the central wing unit llb.
A sheet 41 made of bolystyrene is placed across the ends of the blade units l1a. llb
, by pasting it on the .lie, it is covered and hidden from the outside.

Further, tapered wing tip members 42 are connected to both ends of the left and right wing units lla, lie, and these three wing units lla, llb, lie and the wing tip members 42
The main wing 10 is constituted by the following.

The main wing 10 configured in this manner is connected to the fuselage 1 at the center of the central wing unit Ilb that intersects with the fuselage 1.

To further explain this connection structure, as shown in FIGS. 7 to 9, a pair of left and right front connection fittings 44 are attached to the main spar 30 of the wing unit flb via a spacer 43. The front connecting fitting 44 includes a support portion 45 that sandwiches the main girder 30 from the front and rear, and the support portion 45 is tightened and fixed to the main girder 30 and the spacer 43 via bolts 46 and nuts 47. Support part 45
A bracket portion 48 that protrudes downward is integrally provided. The bracket part 48 penetrates the outer skin z2 of the wing unit Llb and is led out downward, and the lower end of this bracket part 48 is connected to the mounting seat 4 located at the upper front end of the fuselage l.
9 via a bottle 50.

Further, a rear connecting fitting 5l is also attached to the rear spar 32 of the wing unit llb. The rear connecting fitting 5l is the outer skin 2
The lower end of this rear connecting fitting 51 is connected to another mounting seat 52 located at the upper part of the fuselage 1 via a pin 53.

According to such a structure, each wing unit 11 of the main wing 10
a. 1lb. Since the wing module l2 that forms the wing module 11c is individually heat-molded or shaped, there is no variation in the dimensions of each wing module 12, and the cross-sectional shape of the wing can be formed with high accuracy, making it possible to replace the conventional handmade one. In comparison, the dimensional accuracy of the main wing 10 is significantly improved.

In addition, since the plurality of wing modules l2 are connected to each other by passing the main spar 30, front spar 31, and rear spar 32 between these wing modules l2, the work of connecting the wing modules l2 is simple and easy. It can be carried out.

In particular, the wing module 12 has a spar insertion hole 19 and a through hole 16 precisely formed by molding for passing the main spar 30, the front spar 3l, and the rear spar 32, so that the connection of the wing module 12 is exceptional. Each hole 1 described above can be
B. The wing module 12 can be accurately connected by simply passing the main spar 30, front spar 3l, and rear spar 32 through the main spar 19.

Therefore, there is an advantage that no complicated special manufacturing technology is required for molding the main wing 10.

Moreover, three spars 3 penetrating the plurality of wing modules l2
0, 31, and 32 function as cross members, the wing units 11a. Llb. 11c can also be sufficiently ensured.

In addition, in the case of this embodiment, the wing module l2 includes a lattice-like frame body 21 and an outer skin 2 that covers this frame body 2l.
2, and most of the inside is a space 23, so together with the fact that the frame body 2l is made of styrofoam, the weight of the wing module 12 alone can be significantly reduced, making the main wing to even lighter. can do.

In the above embodiment, the wing module is constructed of a frame body and an outer skin, but the present invention is not limited to this. For example, the entire wing module may be molded into a solid shape from Styrofoam.

In addition, this wing module is not limited to being made of styrofoam.
It may also be made of other thermoplastic resin materials.

Further, the main girder does not necessarily have to pass through the inside of the spar holder, and may be inserted and disposed at a position outside the spar holder, for example, as shown by the imaginary line in FIG.

At the same time, the wing module is not limited to one that constitutes the main wing, and may constitute, for example, a horizontal stabilizer.

Further, the aircraft according to the present invention is not limited to a human-powered airplane powered by human power, but can be implemented similarly even if it is a light aircraft whose propeller is driven by an engine.

[Effects of the Invention] According to the present invention described in detail above, the wing modules that form the wing are molded or shaped individually, so variations in dimensions between wing modules are eliminated, and the cross-sectional shape of the wing can be formed with high precision. This greatly improves the dimensional accuracy of the blade compared to conventional hand-made ones.

Furthermore, since the plurality of wing modules are connected to each other by passing the spars through these wing modules,
These wing modules can be connected without using special jigs.
The wing modules can be connected accurately by simply passing the girder through. Therefore, there is no need for any special manufacturing techniques that are troublesome to form the blades.

Furthermore, since the spars that pass through the plurality of wing modules function as cross members, there is an advantage that the wing can be made lightweight while ensuring sufficient strength.

[Brief explanation of drawings]

The drawings show one embodiment of the present invention, and FIG. 1 is a plan view of a human-powered airplane, FIG. 2 is a perspective view showing a state in which the wing modules are connected, FIG. 3 is a partially sectional plan view of the wing module, and FIG. Figure 4 is a side view of the wing module, Figure 5 is a partially sectional plan view of the connection part of the wing unit, Figure 6 is a view taken from the direction of the arrow in Figure 5, and Figure 7 is a view of the main wing and FIG. 8 is a sectional view of the connecting portion between the main wing and the fuselage, FIG. 9 is an exploded perspective view of the connecting portion between the main wing and the fuselage, and FIG. 10 is a side view of the human-powered airplane. 10... Main wing, 12... Wing module, 30, 31
．． 32...digit (main digit, front digit, rear digit)

Claims (1)

[Claims] A plurality of wing modules molded from a resin material into a cross-sectional airfoil shape and arranged side by side along the longitudinal direction of the wing, and a spar that penetrates these wing modules and connects adjacent wing modules. An aircraft wing structure characterized by comprising: