KR100811084B1 - Small-sized rotating aircraft using an auto rotation - Google Patents

Abstract

The present invention relates to a model rotorcraft, and more particularly, in the model rotorcraft, a thrust motor connected to a propeller is mounted to generate thrust after a forward slide or takeoff to the model rotorcraft, and lift and direction change of the model rotorcraft. Rotor hubs equipped with two or more rotary blades are hingedly coupled to each other, and a servo link is connected to the rotor hub one by one symmetrically with respect to the center of the model rotorcraft fuselage. The servo link is symmetrically with respect to the center of the rotorcraft fuselage on horizontal wing blades installed on both sides of the vertical tail blades mounted on the rear end of the rotorcraft. One by one connection operation, the horizontal direction of the hinged horizontal tail blade relative to the forward direction It relates to a rotary-wing model using the automatic rotation adjustment made to use.

The present invention is a simple control device, it is possible to easily switch the direction of the model rotorcraft, thereby reducing the weight of the model rotorcraft, it is possible to stably obtain the lightweight load required for flight, thereby reducing costs After takeoff, it is to provide a model rotorcraft that can fly smoothly to the required place by the control adjustment of the rotary blades or horizontal tail blades.

Automatic rotation, model, rotorcraft

Description

Small-sized rotating aircraft using an auto rotation}

1 is a perspective view showing a model rotorcraft according to the present invention.

2 is a schematic view showing a model rotorcraft according to the present invention.

Figure 3 is a schematic diagram showing a first embodiment of the direction adjustment of the rotary blades of the model rotorcraft according to the present invention.

Figure 4 is a schematic view showing a second embodiment of the direction adjustment of the rotary blades of the model rotorcraft according to the present invention.

Figure 5 is a schematic diagram showing a third embodiment of the direction adjustment of the rotary blades of the model rotorcraft according to the present invention.

Figure 6 is a schematic view showing a fourth embodiment of the direction adjustment of the rotary blades of the model rotorcraft according to the present invention.

Figure 7 is a schematic diagram showing a first embodiment of the direction adjustment of the horizontal tail blades of the model rotorcraft according to the present invention.

8 is a schematic view showing a second embodiment of the direction adjustment of the horizontal tail blades of the model rotorcraft according to the present invention.

Figure 9 is a schematic diagram showing a third embodiment of the direction adjustment of the horizontal tail blades of the model rotorcraft according to the present invention.

10 is a schematic view showing a fourth embodiment of the direction adjustment of the horizontal tail blades of the model rotorcraft according to the present invention.

11 is a perspective view showing a model rotorcraft of another embodiment according to the present invention.

[Explanation of symbols on the main parts of the drawings]

1: thrust electric motor 2: servo motor

3: servo link 4: rotary wing

5 ': Hinge for front and rear mirrors 5 ": Hinge for side mirrors

6: vertical stand 7: wheel

8: Horizontal fuselage 9: Propeller

10: Tail Boom

11: vertical tail wing 12: horizontal tail wing

13: rotor hub

The present invention relates to a model rotorcraft, and more particularly, in the model rotorcraft, a thrust motor connected to a propeller is mounted to generate thrust after a forward slide or takeoff to the model rotorcraft, and lift and direction change of the model rotorcraft. Rotor hubs equipped with two or more rotary blades are hingedly coupled to each other, and a servo link is connected to the rotor hub one by one symmetrically with respect to the center of the model rotorcraft fuselage. The servo link is symmetrically with respect to the center of the rotorcraft fuselage on horizontal wing blades installed on both sides of the vertical tail blades mounted on the rear end of the rotorcraft. One by one connection operation, the horizontal direction of the hinged horizontal tail blade relative to the forward direction It relates to a rotary-wing model using the automatic rotation adjustment made to use.

In general, model airplanes that can be used for play or learning can be classified into no-power, rubber power, and electric power, depending on the power source. No-powered model airplanes fly with natural wind without power generators. They are convenient because they do not use power, but to fly without power, you have to throw a model airplane from an ascending hill and fly a lot of falls. There are drawbacks that accompany it.

In addition, rubber power is to fly a model plane by rotating the propeller using a rubber band, but generally has a disadvantage that can not fly far.

The electric model rotorcraft using electric power has a fuselage, a blade, an electric motor coupled to the fuselage, a propeller coupled to the electric motor, and a battery for supplying power to the electric motor. In order to reduce the capacity of the electric motor that should be used in general, the fuselage and wings are mainly made of wood or synthetic resin lighter than metal materials, and the battery uses a nickel-cadmium-based battery as a secondary rechargeable battery. Such an electric model rotor blade can be manufactured in a smaller weight and size than other model rotorcrafts, and has the advantage of easy resupply of power after landing.

However, in the conventional electric model rotorcraft, when the air current of 6m per second or more is present, it is difficult to fly itself, and flight trajectory and performance are greatly influenced by the launching position at the beginning of takeoff, and the power is stopped. Afterwards, there was a problem that the air current is easily lost by continuing to fly without descending.

In addition, due to the low capacity of the battery, the flight speed is low, and in order to fly, the weight of the fuselage and the wing had to be minimized, so there was a problem in that it was structurally weak and easily damaged.

Furthermore, very smooth control devices are attached for smooth redirection or flight of the rotorcraft, resulting in structural problems due to excessive weight.

The present invention has been made to solve this problem, having a minimum thrust motor for takeoff, and after takeoff stops the operation of the thrust motor as needed, pure lifting force by the rotation of the rotor blades It can fly in the air, by changing the direction of the rotor blades or horizontal tail blades by a simple control operation, to fly the model rotorcraft to the desired place, and do not be largely affected by the launching attitude and weather conditions at the beginning of takeoff It has excellent flight stability and provides a model rotorcraft that can significantly reduce the risk of loss compared to the conventional electric model rotorcraft, and provides a model rotorcraft using automatic rotation that can have high flight speed and sufficient structural strength. It is.

In the present invention, the model rotorcraft, more specifically, in the model rotorcraft is equipped with a thrust motor (1) connected to the propeller (9), generating a thrust after the forward slide or take-off to the model rotorcraft,

The rotor hub 13, which is equipped with two or more rotary blades 4 at the top end, is hinged for lifting and direction change of the model rotorcraft, and the servo link 3 is connected to the rotor hub 13. It is connected to each one symmetrically with respect to the center of the fuselage, and relates to a model rotorcraft using an automatic rotation that is configured to incline the direction of the hinged rotary blade 4 with respect to the forward direction or 90 ° direction of the forward direction.

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  In another embodiment

In order to change the lift and direction of the rotorcraft, two or more rotary blades 4 are mounted at the top end, and fixed in a predetermined direction.

The servo link 3 is connected to the horizontal tail blades 12 installed on both sides of the vertical tail blades 11 mounted on the rear surface of the model rotary blades symmetrically with respect to the center of the model rotor blade body, and is operated by hinge coupling. It relates to a model rotary wing using an automatic rotation made to incline the horizontal direction of the horizontal tail blades 12 with respect to the forward direction.

Hereinafter, the present invention will be described in detail with reference to the accompanying drawings.

1 is a perspective view showing a model rotorcraft according to the present invention, Figure 2 is a schematic view showing a model rotorcraft according to the present invention, it will be described in detail as follows.

The overall shape of the model rotorcraft according to the present invention is equipped with a plurality of wheels 7 at the bottom of the horizontal fuselage 8, so that the model rotorcraft slides on the ground, and maintains safety in the vertical direction and the left and right directions when taking off. The tail boom 10 and the vertical tail wing 11 and the horizontal tail wing 12 are formed to be bonded to the rear end surface of the horizontal body 8 is attached to the end.

A vertical stand 6 is mounted on one side of the horizontal body 8 of the model rotorcraft, and a thrust motor 1 connected to a propeller 9 is mounted on one side rear face of the vertical stand 6, To generate forward thrust on the rotorcraft.

The propeller 9 connected to the thrust electric motor 1 generates thrust in the forward direction with respect to the model rotorcraft, and this thrust is lifted by the rotary vanes automatically rotating due to the flow of air when the model rotorcraft slides on the ground. To generate the thrust in the forward direction, even when flying in the sky, and to function to fly to the desired place.

The rotary blades 4 are mounted in plural number on the model rotor blades, and are rotated by the wind with no power, thereby generating lift force, so that the model rotor blades are raised and lowered in the expanse.

To this end, the rotary blade 4 of the airfoil shape is formed to be mounted with the rotor hub 13, the rotor hub 13 is the front and rear inclination hinge (5 ') at the upper end of the vertical stand (6). And mutually hinged. Because of this, the rotary blade 4 is to adjust the hinge inclination to be inclined with respect to the forward direction of the model rotorcraft.

In order to smoothly change the direction in the expanse of the model rotorcraft, the side warp hinge 5 "is formed to be spaced apart from the front and rear warp hinge 5 'by a predetermined distance, and is positioned at 90 ° with respect to the front and rear inclination hinge direction. It is formed to be hinged relative to.

The rotor hub 13 with the rotary blade 4 mounted to the side warp hinge 5 "is hinged to each other, and the rotor hub 13 mounted to the side warp hinge 5" if necessary. Is adjusted so as to be inclined with respect to the 90 ° direction of the horizontal body 8 of the model rotorcraft, so that the direction of the model rotorcraft is switched.

The operating principle for changing the direction of the rotary blade 4 of the rotorcraft is as follows.

One servo link 3 is connected to one side of the rotor hub 13 symmetrically with respect to the center of the model rotorcraft body, and is rotated by each of the servo motors 2 to which the servo link 3 is connected. By operating the servo link (3), it is made to adjust the inclination of the hinged rotor hub 13 relative to the forward direction or 90 ° direction of the forward direction.

Another embodiment for changing the direction of the model rotorcraft is to use a horizontal tail wing, the configuration according to it is as follows.

Two servo motors 2 are added to one side of the upper surface of the horizontal body 8, and one side point of each of the horizontal tail blades 12 provided on both sides of the servo motor 2 and the vertical tail blades 11 is provided. Connected by the servo link (3), by operating the respective servo link (3) by the rotational movement of the servo motor (2) to which the servo link (3) is connected, the horizontal of the hinged horizontal tail (12) The direction is made to be adjusted independently of each other with respect to the forward direction.

It is the lift on the wing that supports the load of the plane so that it can fly in the air. When the airplane advances in the air at a constant speed, the same wind (air flow) as that speed flows in contact with the wing. The flow of air is faster when passing through the upper surface of the large curved blade, and the lower velocity is lower on the lower curved surface. Therefore, the upper flow of the air flows relatively fast to the state of low pressure, the lower surface of the air flow is relatively slow, the state of high pressure.

The pressure difference between the top and the bottom of the wing causes the plane to lift and fly. Therefore, in manufacturing a rotating wing (main wing) of a general model airplane, the upper surface of the wing is given a large curvature and the lower surface is formed of an airfoil shape that is smaller than the curved portion of the upper surface.

The present invention is to provide a model rotorcraft to adjust the direction of the rotation of the rotary blade of the airfoil very easily, the present invention is to install a vertical stand (6) on one side of the horizontal body (8), A thrust generating motor 1 for thrust generation for taking off the model rotorcraft is mounted on one side of 6), and the model rotorcraft is rotated by the rotational movement of the propeller 9 connected to the thrust motor 1. Thrust is generated, and even after takeoff, it is continuously or intermittently rotated for the thrust of the model rotorcraft if necessary.

At the upper end of the vertical stand 6, a plurality of rotary blades 4 are mounted on the rotor hub 13 hinged to one side, and the rotary blades 4 generate lift due to the rotational movement on the model rotary blades. And, it is formed to fly the expanse, it is adjusted to tilt the hinged rotor hub 13 to the front and rear or left and right about the hinge point for the necessary direction change.

The rotary blade 4 is mounted to the rotor hub 13 which is hinged to the front and rear inclination hinge 5 'of the upper end of the vertical stand 6, the rotor hub 13 is a servo link ( 3), due to the operation of the servo link (3), the hinge is rotated, the direction of the rotary blade (4) of the airfoil shape is changed. One side of the servo link (3) is bent a number of times, always maintain a constant tension, the servo link (3) is operated by the rotation of the servo motor 2, the rotor hub (13) connected thereto is hinged The direction of the rotary blade 4 is adjusted.

The operation principle for adjusting the direction of the rotary blade 4 will be described in detail as follows with reference to FIGS.

Figure 3 is a schematic view showing a first embodiment of the direction adjustment of the rotary blades of the model rotorcraft according to the present invention, which is a symmetrical mounted on the upper surface of one side of the horizontal fuselage (8) each of the two servo motors 2 It shows the case where all the rotation in the inclined direction with respect to the center of rotation, by rotating in the lower inclination direction, the servo link (3) respectively connected to the rotation point is moved in the lower direction, and thus the front and rear inclination hinge ( The rotor hub 13 hinged to 5 'is inclined downward with respect to the forward direction, so that the position of the front face of the rotary blade 4 rises relatively.

4 is a schematic view showing a second embodiment of the direction adjustment of the rotary blades of the model rotorcraft according to the present invention, and shows the case where the servomotor 2 rotates in the upper tilt direction with respect to each rotation center, By rotating in the upward inclination direction, the servo links 3 respectively connected to the rotation points are moved upwards, which causes the rotor hub 13 hinged to the front and rear inclination hinges 5 'to the forward direction. The inclined movement upward, the position of the front end surface of the rotary blade 4 is relatively low.

Figure 5 is a schematic diagram showing a third embodiment of the direction of the rotation of the rotary blades of the model rotorcraft according to the present invention, Figure 6 is a schematic diagram showing a fourth embodiment of the direction adjustment of the rotary blades of the model rotorcraft according to the present invention. This is a case where the servo motor 2 rotates in different directions with respect to each center of rotation, in which one motor rotates in the upper tilt direction and the other motor rotates in the lower tilt direction.

In this case, the rotor hub 13 is tilted with respect to the 90 ° direction of the forward direction, and the plurality of rotary blades 4 mounted on the rotor hub 13 are tilted with respect to the 90 ° direction of the forward direction as a whole. It is made possible.

This is a control device that is operated to turn left and right of the model rotorcraft.

11 is a perspective view showing a model rotorcraft of another embodiment according to the present invention,

As the present invention is a control device by a horizontal tail wing, the description thereof is as follows.

The rotary blades 4 are fixed, and two servomotors 2 are mounted on one side of the upper surface of the horizontal body 8, and each horizontal is installed on both sides of the servomotor 2 and the vertical tail blades 11. One side of the tail wing 12 is connected by the servo link 3, and the servo link 3 is pulled or released by the rotational movement of the servo motor 2 to which the servo link 3 is connected. The hinged horizontal tail wings 12 are made to be inclined independently of each other with respect to the advancing direction.

7 is a schematic view showing a first embodiment of the direction adjustment of the horizontal tail blades of the model rotorcraft according to the present invention, in which two servomotors 2 are each symmetrically mounted on the upper surface of one side of the horizontal fuselage 8. The rotational direction of the rotation in the direction of the lower inclination, as shown in the case, by rotating in the lower inclination direction, each of the servo link (3) connected to the hinge point is moved to the lower direction, whereby one side is hinged Of the horizontal tail blade 12 is inclined to move downward with respect to the forward direction, the position of the front end surface of the horizontal tail blade 12 is relatively raised.

8 is a schematic view showing a second embodiment of the direction adjustment of the horizontal tail blades of the model rotorcraft according to the present invention, in which the two servomotors 2 are all rotated in the upper tilt direction with respect to their respective rotation centers. As shown, by rotating in the upward inclination direction, the servo links 3 respectively connected to the hinge points are moved upwards, so that the one-sided hinged horizontal tail blades 12 are moved upward in the forward direction. It is moved inclined so that the position of the front end surface of the horizontal tail wing 12 is relatively low.

9 is a schematic view showing a third embodiment of the adjustment of the horizontal tail blades of the model rotorcraft according to the present invention, Figure 10 is a fourth embodiment of the adjustment of the direction of the horizontal tail blades of the model rotorcraft according to the present invention As a schematic diagram shown, this is a case where the servomotor 2 rotates in different directions with respect to each center of rotation, in which one motor rotates in the upper tilt direction and the other motor rotates in the lower tilt direction.

In this case, the horizontal tail blades 12 are inclined in different directions with respect to the forward direction.

The driving of the thrust electric motor 1 and the thermomotor 2 for this operation is to be controlled by remote control.

As described above, the present invention, as a simple control device, can easily switch the direction of the model rotorcraft, thereby making it possible to reduce the weight of the model rotorcraft, thereby stably obtaining the light weight necessary for flight, The cost can be reduced, and the plane will be able to fly stably.

After takeoff, it provides a model rotorcraft that can easily fly to the desired place by driving the rotor blades and the horizontal tail wings, and if necessary, to provide a model rotorcraft that continuously or intermittently drives the rotation of the thrust propeller. will be.

Claims (5)

In model rotary wing, A plurality of wheels 7 are mounted at the bottom of the horizontal fuselage 8 to allow the model rotorcraft to slide on the ground, and the vertical tail blades 11 and the horizontal tails formed to maintain safety in the vertical direction and the left and right directions during takeoff. Tail boom 10 attached to the end of the wing 12 is bonded to the rear end surface of the horizontal fuselage 8, A vertical stand 6 is mounted on an upper surface of one side of the horizontal fuselage 8, and a thrust motor 1 connected to a propeller 9 is mounted on one side rear surface of the vertical stand 6, and forward thrust to the model rotorcraft. Causes The upper part of the vertical stand 6 has a side warp hinge 5 "and a side warp hinge 5" having a yaw angle of 90 ° with respect to the length of the horizontal body 8 of the model rotorcraft. A front and rear inclination hinge 5 'having a roll angle of 90 ° with respect to the length direction of the horizontal body 8 of the model rotorcraft is provided on the vertically spaced vertical stand 6, and the front and rear inclination hinge ( 5 ') is provided with a rotor hub 13 having an airfoil-shaped rotary blade 4 mounted thereon, and two servomotors 2 mounted on one side surface of the horizontal body 8 to model rotorcraft. To lift and reorient, The servo link 3 is connected to both sides of the rotor hub 13 and the two servomotors 2 with respect to the fuselage center of the model rotorcraft 13 so that the direction of the rotary blade 4 is the forward direction of the model rotorcraft or Model rotorcraft using automatic rotation, characterized in that the inclined adjustment with respect to the 90 ° direction of the forward direction. The method of claim 1, The drive of the thrust electric motor (1) and the servo motor (2) is a model rotorcraft using automatic rotation, characterized in that controlled by remote control. delete delete delete

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