JPH05178293A - Flapping airplane - Google Patents

Abstract

PURPOSE:To allow a flapping airplane larger than any conventional one to fly in the air by obtaining thrust only by flapping its main wing. CONSTITUTION:Flapping wings are constructed in such a way as to attach driving strings 2 on the wing tip sides of spars 3 that elastically deform, pull the driving strings 2 by a reel that is rotated by an electric motor to bring down the wings, then lift off the wings by repulsive force possessed by the spars 3 that elastically deform, and this flapping airplane is constructed in such a way as to open/close the circuit of the electric motor with the driving strings 2 so as to flap the wings continuously, thereby the flapping wings become the main wings of the flapping airplane.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a flapping airplane using flapping wings having elastically deformable spars.

[0002]

2. Description of the Related Art The wing root side is pivotally supported with respect to the body of an airplane,
Conventionally, an airplane having flapping wings that obtain thrust by applying an external force to the action point on the blade root side and vertically vibrating the blade tip side around a pivot point has been provided. Generally, in this conventional airplane, the wing root side comrades of both wings are pinned, and this pinning portion is often used as a point of action.

[0003]

The conventional airplane of this type has a large dimensional ratio between the pivot point and the working point and between the pivot point and the wing tip, so that the thrust force required for the airplane is obtained. In order to obtain the vertical movement of the blade tip, the external force applied to the point of action must be increased.

For example, an electric motor may be used as a power source, but when high torque is to be obtained,
Since the reduction ratio of the electric motor is large, it is necessary to directly connect a reduction gear having a gear to the output shaft of the electric motor. However, since the speed reducer in which gears are combined increases the weight of the airplane, the electric motor is not actually used, but relies on rubber power.

When rubber power is used, there is a limit to the power, so it is not possible to expect an increase in the size of the airplane, and there is a strong demand for an increase in the size of the airplane by using an electric motor. Therefore, it is an object of the present invention to propose an airplane having a large flapping wing using an electric motor.

[0006]

SUMMARY OF THE INVENTION In order to solve the above-mentioned problems, the present invention basically arranges elastically deformable spars at the leading edges of the blades, and decelerates them with a spool on both sides of the blades. It employs a means to add the output from the electric motor and to lower the spar.

More specifically, according to the present invention, a spar made of an elastic material extending in the span direction of a fuselage front portion having a tail and a spar having a center fixed to the fuselage are stretched on the spar. A flapping wing comprising a wing surface film supported on a body; an electric motor supported on a front portion of the body; a spool wound on an output shaft of the electric motor; wound on the spool and each end of the spar. A fluttering airplane having a drive thread respectively supported on each wing tip side; and a device for operating the electric motor so as to elastically deform the spar by the drive thread in a direction in which the spar is lowered.

Preferably, the axial center of the bobbin is located at the center of the body and below the spar.
Also, the blade tip side of the spar is warped rearward by the blade surface film.

More preferably, the movement of the spar in the launching direction is performed by the elastic force of the spar, the intermittent frequency of the motor is synchronized with the natural frequency of the spar, and the spool is positioned in front of the spar. Further, the tail fin is vibrated in the vertical direction so as to suppress pitching of the body.

[0010]

Operation: The electric motor is turned on, and its output is decelerated by bobbin winding. This decelerated output is transmitted to the wing spar via the drive thread wound around the bobbin, and the spar is lowered. When the down state of the spar is detected, the electric motor is turned off, and the spar is launched up by the elastic force of the spar itself. When the launching state of the spar is detected, the electric motor is turned on again, and the spar is downed as described above. By repeating this operation, the wings are flapping and the thrust required for flight is obtained, causing the plane to fly.

When the on / off of the electric motor is synchronized with the natural frequency of the spar, the energy required to vibrate the blade mass is saved, efficiency is increased, and thrust is increased.

Positioning the center of the bobbin at the center of the fuselage and below the spar counteracts the lateral forces that occur when pulling the wing and reduces the forces on the fuselage and wing root.

In the blade configured so that the blade tip side of the spar is warped backward by the blade surface film, the tension in the lateral direction of the blade trailing edge is increased to maintain the attack angle of the blade against the flow of air. The work becomes stronger and more thrust is generated.

When the bobbin is positioned in front of the spar and the drive thread is pulled forward, the function of maintaining the attack angle of the blade against the flow of air is strengthened and more thrust is generated.

By vibrating the tail fin in the longitudinal direction centering on the joint axis with the fuselage in synchronization with the flapping of the wing to suppress the pitching of the fuselage, the energy consumed for the vibration of the pitching of the fuselage is saved, and the thrust force is reduced. To increase.

[0016]

EXAMPLES Examples will be described with reference to the drawings.
Upper part of frame (1) of fuselage (11) with tail (12)
The front edge spar (3) is fixed to 1c), and the wing surface membrane (4) sewn into a bag shape as shown in FIG. 6 is attached to the spar (3), and the spool (5) is attached to the front part of the body (11). The electric motor (6) and the pulley (7) are arranged as shown in FIGS. 4 and 5.

The body 11 is a front frame (11b) in which a lightweight and high-strength rod material such as carbon fiber is trapezoidally assembled.
And a portion (11a) extending rearward from the lower portion thereof, and a lower frame (11a) extending rearward from the portion (11a).
d), at least an upper frame (11c) extending rearward from an upper part of the front frame (11b). A first plate (13) is fixed between the front frames (11b) of the pair and another second plate (14) is fixed between the parts (11a) of the pair. In addition, the front frame (11
The third plate (15) is fixed to the upper part of the pair of reinforcing frames (11e) located outside of b) and connecting the pair of parts (11a) and the front frame (11b).

The spar (3) arranged at the front edge of the blade is made of a lightweight, high-strength, high-modulus rod material such as carbon fiber, and one or a central portion thereof is joined. Secure the spar (3) to the third plate (15) in a dihedral fashion. Of course, it may be fixed to the upper frame (11c).

As shown in FIG. 3, the spar (3) is passed through the front edge bag-like portion (16) of the blade film (4) made of a material such as cloth or spin cloth cut into a flat surface, and the spar (3) is rearwardly moved. Warp to the wing tip, especially to the wing tip side. Body (1
The side edge of the wing surface film (4) is sewn by the upper frame (11c) of 1). Thus, the lateral tension on the trailing edge of the blade can be increased and the attack angle of the blade can be maintained. The wing composed of the spar (3) and the wing surface film (4) can be flapping by the down stroke and the up stroke of the front edge spar (3).

Please refer to FIG. 4 and FIG. The electric motor (6) is arranged on the center of the body (11) on the second plate (14), and the spool (5) is connected to its output shaft.
The end of the spool (5) below the spar (3) is rotatably supported by the first plate (13). Bobbin (5)
The ends of the drive yarns (2) wound around are fixed to the wing tips of the spar (3). Thus, when the drive thread (2) is wound around the spool (5), the drive thread (2) hits down the spar (3). Since the downed spar (3) has a strong restoring force, in this example, the launch of the spar (3) is
It is assumed to be due to its own elastic force. For this reason spurs (3)
When is downed, the electric motor (6) is turned off, and the spar (3) can be launched by its own elastic force.

A pulley (7) is rotatably supported on a shaft (17) between the first plate (13) and a member on the electric motor (6) side. One end of the driving yarn (2) from the yarn winding (5) is wound around the pulley (7), for example, once to fix the end portion to the spar (3). The pin (8) fixed to the side surface of the pulley (7) is opposed to the switch (9) for connecting and disconnecting the electric current to the electric motor (6), and the pin (8) is moved in accordance with the movement of the pulley (7) at a constant rotation angle. 8) enables the switch (9) to be turned on and off. That is, when the down movement of the spar (3) by the drive thread (2) is completed, the pin (8) turns off the switch (9), stops the electric motor (6), and allows the spar (3) to be launched. . When the launch of the spar (3) is completed, the pin (8)
Turns on the switch (9), and restarts the down stroke of the spar (3) by the electric motor (6). Repeating this work will cause the wings to flap continuously.

The electric motor (6) may be turned on / off (interrupted) so as to synchronize the down and up of the spar (3) with the natural frequency of the spar (3) as described above.

At a constant frequency, the bobbin winder (5) is intermittently rotated using an electronic circuit that opens and closes the circuit connecting the electric motor (6) and the battery, and while the circuit is closed, the drive thread (2) ) To lower the spar (3), and while the circuit is open, the spar (3) can be launched by the elastic force of the spar (3) so that the wing flaps at a constant frequency.

[0024]

By reducing the diameter of the bobbin,
It is possible to reduce the pulling amount of the driving yarn per one rotation, and the flapping mechanism that pulls the elastically deforming spar by the bobbin to flaps the spinner of the electric motor while satisfying the conditions of being lightweight and highly efficient. The fluttering frequency can be reduced with a large reduction ratio of several tens to one hundredth.

Pull both wings with the drive thread from one spool,
By performing the operation symmetrically around the bobbin, it is possible to cancel the force applied to the machine body and suppress an increase in weight.

By vibrating the tail wings up and down according to the flapping frequency, it is possible to suppress the vibration of the machine body, save the energy lost by the vibration of the machine body, and improve the thrust efficiency.

[Brief description of drawings]

FIG. 1 is a perspective view of an example of a flapping airplane of the present invention.

FIG. 2 is a front view of an example of a flapping airplane of the present invention.

FIG. 3 is a plan view showing one wing.

FIG. 4 is a side view showing a wound portion.

FIG. 5 is a front view showing a wound portion.

FIG. 6 is a cross-sectional view of a spar and a blade film.

[Explanation of symbols]

2 Drive thread 3 Spur 4 Wing surface film 5 Thread winding 6 Electric motor 7 Pulley 8 Pin 9 Switch 11 Body 11a, 11b, 11c, 11d, 11e Frame constituting the body 12 Tail blade 13 First plate 14 Second plate 15 Third Plate 16 Blade front edge bag 17 Shaft

Claims (6)

[Claims] 1. A spar made of an elastic material extending in the span direction of a fuselage front portion having a tail, and a wing surface film stretched on the spar whose center is fixed to the fuselage and supported by the fuselage. Flapping wing; an electric motor supported on the front of the fuselage; a bobbin connected to the output shaft of the electric motor; each end wound on the bobbin and supported at each wing end side of the spar. A fluttering aircraft having a drive thread that is operated; and a device that operates the electric motor so as to elastically deform the spar by the drive thread in a direction in which the spar is lowered. 2. The airplane according to claim 1, wherein an axial center of the bobbin is located at a center of the body and below the spar. 3. The aircraft according to claim 2, wherein the wing tip side of the spar is warped rearward by the wing surface film. 4. The aircraft according to claim 3, wherein the movement of the spar in the launching direction is made by the elastic force of the spar, and the intermittent frequency of the motor is synchronized with the natural frequency of the spar. 5. The aircraft according to claim 3, wherein the bobbin is located in front of the spar. 6. The aircraft according to claim 4, wherein the tail fin is vertically vibrated so as to suppress pitching of the fuselage.