JPH04321488A - Asymmetrical rigid wing of airplane - Google Patents

Abstract

PURPOSE:To enhance the flutter characteristic of an airplane wing by arranging it so that the rigidity of its mounting part is asymmetrical about the airplane axis. CONSTITUTION:To mount a main wing on a fuselage 1, a shock mount 5 made of rubber, etc., to exert spring action in the axial direction of a bolt is interposed between the mounting seat 3 at the front right and the main wing 2. Between the mounting seat 4 at the rear right and each eye piece 2a constituting the mounting part of main wing 2, shock mounts 6 are interposed made of the same material as the first named shock mount 5 while pinching the eye piece 2a. Thus shock mounts 5, 6 are installed on only one side at the front and rear of the main wing 2 about the airplane axis, which should provide a symmetrical rigidity to lead to enhancement of the flutter characteristic according to the form of object loaded such that the flutter velocity lowers extremely in the counter-symmetrical mode.

Description

[Detailed description of the invention]

0001

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a wing with improved flutter characteristics for an aircraft, and more particularly to a wing in which the rigidity of the mounting portion is asymmetrically combined.

0002

2. Description of the Related Art In a conventional aircraft, as shown in FIG. 4, the main wings 2 and the fuselage 1 are joined in a symmetrical manner using the same mounting method. That is, directly to the mounting seats 3 and 4 with bolts, etc.
It was installed. In addition, (a) of a figure is a figure seen in the up-and-down direction of a principal part, (b) is a perspective view seen diagonally backward, and (c) is a perspective view seen diagonally forward.

[0003] In the case of this conventional configuration, the mode shapes of symmetrical or antisymmetrical vibration are the same for the left and right wings.

0004

SUMMARY OF THE INVENTION The conventional aircraft wing-body coupling means described above has the following problems to be solved.

That is, in the case of the conventional mounting method where the left and right sides are the same,
For models with various payload patterns, there may be a payload configuration in which the flutter speed is extremely low in antisymmetric mode.

[0006] If such a configuration exists among the derived configurations of the mounting configuration, there is a problem in that all the configurations on the upstream side are limited by the flutter characteristics (flutter speed) of this configuration.

SUMMARY OF THE INVENTION In order to solve the above-mentioned problems, it is an object of the present invention to provide an asymmetrically rigid wing for an aircraft in which flutter characteristics are improved by making the mounting rigidity of the wing asymmetric between the left and right sides.

[0008]

[Means for Solving the Problems] As a means for solving the above problems, the present invention provides a wing attached to the fuselage of an aircraft.
An object of the present invention is to provide an asymmetrically rigid wing for an aircraft, characterized in that the rigidity of the attachment portion of the wing is asymmetrical with respect to the aircraft axis.

[0009]

[Operations] Since the present invention is constructed as described above, it has the following functions.

That is, by making the mounting rigidity of the aircraft wing asymmetric on the left and right sides, the basic vibration characteristics of the aircraft can be made symmetrical and
It is no longer an antisymmetric mode and becomes asymmetric.

[0011] This makes it possible to realize asymmetrical vibration characteristics even in a configuration with a bilaterally symmetrical mounted object, and improves flutter characteristics.

FIG. 3 shows an example (b) in which the outboard cargo of an aircraft is mounted symmetrically on the wings of a normal aircraft, that is, an aircraft whose wing mounting rigidity is symmetrical, and an example in which the cargo is mounted asymmetrically (b). The relationship between the frequency and damping rate with respect to the aircraft speed in a), that is,
This is a diagram showing flutter characteristics, and shows that the left-right asymmetric case (a) does not fall into the unstable region even at high speeds and has excellent flutter characteristics.

[0013]

[Embodiment] An embodiment of the present invention will be explained with reference to FIG. Note that the same reference numerals are given to the same components as in the conventional example,
The explanation will be omitted.

FIG. 1 is a view showing the main part of this embodiment, that is, the joint between the fuselage 1 and the main wing 2. (a) is a view of the main part seen in the vertical direction, and (b) is a view diagonally rearward. (c) is a view seen diagonally forward. In the figure, between the mounting seat 3 on the front right side and the main wing 2, a shock mount 5 made of rubber or the like has a spring action in the direction of the axial force of a bolt (not shown).
is interposed therebetween, and the main wing 2 and the mounting seat 3 are fastened together. Furthermore, shock mounts 6 made of the same material as the shock mount 5 are interposed between the rear right mounting seat 4 and the eye fitting 2a forming the attachment part of the main wing 2 on both sides of the eye fitting 2a, and are fastened together. ing. In other words, shock mounts 5 and 6 are mounted only on one side of the main wing 2, both on the front and rear sides with respect to the aircraft axis.
are interposed, and the main wing 2 is attached so that its rigidity is asymmetric.

Next, the operation of the above structure will be explained. As described above, by asymmetrically coupling the left and right wings 2, the degrees of freedom for attaching the left and right wings 2 are different, and therefore the vibration mode shapes are different between the left and right wings.

Due to the effect of this different mode shape, as shown in FIG. 2, in the symmetrical mounting, that is, in the conventional mounting method shown in FIG. 2(b), an unstable region appeared from a considerably low speed. On the other hand, asymmetrical mounting, i.e., Fig. 2(a)
It is clear that with the mounting system according to the embodiment, almost no unstable region appears.

That is, as shown in FIG. 3, this embodiment achieves the effect of improving flutter characteristics, which is known when outboard payloads are mounted asymmetrically on the wing, regardless of the asymmetry of the payloads.
This is achieved by making the mounting rigidity of the wing itself asymmetric,
This greatly expands the loading restriction area.

[0018] In this embodiment, the shock mount 5,
Although a rubber product is used in 6, the material is not limited to rubber; other elastic bodies, such as a spring, specifically a spring washer, can be used so that it can swing both ways without being completely fastened. , appropriate means may be chosen. Further, the shock mount is not limited to the right side, and may be attached only to the left side. Further, the means for changing the rigidity between the left and right sides is not limited to the means of using a washer-like cushioning material on a bolt or the like.

As described above, according to this embodiment, the main wing 2 and the fuselage 1 are connected by interposing the shock mounts 5 and 6 only at the mounting portion on one side with respect to the aircraft axis. The rigidity of the mounting portion is asymmetrical, and the vibration characteristics are accordingly asymmetrical, so there is an advantage that flutter characteristics are significantly improved.

[0020]

Effects of the Invention Since the present invention is constructed as described above, it has the following effects.

In other words, by asymmetrically coupling the main wing and the fuselage, the main wing vibration characteristics become asymmetric, which has caused problems in conventional aircraft, such as extremely decreasing flutter speed in the antisymmetric mode. It is possible to improve the flutter characteristics of the mounted object.

[0022] This makes it possible to significantly increase the speed limit imposed by the flutter characteristic.

[Brief explanation of drawings]

FIG. 1 is a diagram of an embodiment of the present invention, in which (a) is a view seen in the vertical direction, (b) is a perspective view seen diagonally backward, and (c) is a perspective view seen diagonally forward. .

[Fig. 2] Comparative explanatory drawings of the effects of the above embodiments, (a) is a schematic diagram of the aircraft in which the mounting method according to the embodiment is viewed in the longitudinal direction and its flap characteristic diagram, and (b) corresponds to (a). FIG.

FIG. 3 is a flutter characteristic diagram of an example (a) in which outboard cargo is mounted asymmetrically on a normal aircraft, and (b) an example in which it is mounted symmetrically.

4A and 4B are views of main parts of a conventional example, in which (a) is a view seen in the vertical direction, (b) is a perspective view seen diagonally backward, and (c) is a perspective view seen diagonally forward.

[Explanation of symbols]

1 Torso 2 Main wing 2a Eye fitting 3,4 Mounting seat 5, 6 Shock mount

Claims (1)

[Claims] 1. An asymmetrically rigid wing for an aircraft, characterized in that, in the wing attached to the fuselage of the aircraft, the rigidity of the attachment portion of the wing is asymmetric with respect to the aircraft axis.