KR101895366B1 - the improved hybrid drone - Google Patents

Abstract

The present invention provides an improved hybrid drone, comprising: a body (100) installed in the main axis direction; main wings (200) coupled to the body (100) in the perpendicular axis direction thereto and having auxiliary wings (210) and flaps (230) installed thereon; two motor tube frames (800) respectively installed at the left side and the right side of the main wings (200) in the main axis direction; a horizontal stabilizer plate (300) coupled to the two motor tube frames (800) by connecting the same at the rear portion thereof and having an elevator (310) installed thereon; and vertical stabilizer plates (400) coupled to the upper portions of the motor tube frames (800) at the rear portions thereof and having rudders (410) installed thereon, wherein a main propeller (700) is installed at the rear end of the body (100) so as to be driven by an engine and front propellers (500) and rear propellers (600) are installed at the front ends and the rear ends of the motor tube frames (800) so as to be driven by motors respectively.

Description

Improved hybrid drone {the improved hybrid drone}

The present invention combines only the advantages of an engine and a motor, uses a motor as a main power source during flight and uses a motor as an auxiliary power source for landing and landing, and combines the number of propellers connected to the engine, To an improved hybrid drones capable of taking off and landing, hovering and flying.

In recent years, electric motor-driven multi-copter drones have become popular.

Conventional drones are convenient to control with the support of electronic equipment, and are convenient for expanding functions because they fly by battery and electric motor power.

Especially, when the vertical landing and takeoff is required, it is required to cope with almost all the energy output for the gas flight, so that the battery is consumed fast and the life of the motor and the propeller is shortened.

In the case of a gas driven by an engine, noise and vibration are large and precise control is difficult compared to a motor.

For example:

Comparing the thrust / weight ratio (TWR), the thrust weight ratio of the vertical takeoff / landing should theoretically exceed at least 1.0 to float in the air. That is, there must be a larger thrust (output conversion) than the weight of the gas.

For example, an aircraft such as a passenger plane that does not have a vertical takeoff and landing function and a long runway is guaranteed to be able to operate efficiently with a small thrust weight ratio of 0.15 to 0.35.

On the other hand, a longer runway is needed because the wing can get lifts that exceed the take-off weight as long as there is enough speed to get the lift required for the flight.

For some fighters or acrobatics that require a lot of maneuvering, they have a thrust weight ratio of about 0.8 to 1.4, because performance is more important than efficiency.

Accordingly, the present inventors have combined the merits of an engine and a motor to use the engine as a main power source in flight and use a motor as an auxiliary power source in takeoff and landing, and combine the number of propellers connected to the motor, And to develop an improved hybrid drones capable of stable landing, hovering and flight.

[Patent Document 1] Korean Patent No. 10-1812679 'Balance Control Method of Drones', December 20, 2017 [Patent Document 2] Korea Patent No. 10-1788411 entitled " Drone Operating Method and System for Responding to Industrial Accidents ", October 13, 2017

SUMMARY OF THE INVENTION The present invention has been made in order to solve the above-mentioned problems of the related art. The purpose of this system is to combine the merits of the engine and the motor, to use the engine as the main power source in flight and to use the motor as the auxiliary power source for the takeoff and landing. The number of propellers connected to the engine and the motor, To provide an improved hybrid drones that can take off and land, hover and fly.

According to an aspect of the present invention, there is provided a portable terminal comprising: a body;

A wing 200 coupled to the body 100 in a direction perpendicular to the axial direction and having an auxiliary vane 210 and a flap 230;

Two motor tube frames 800 provided on the left and right sides of the wing 200 respectively in the direction of the main axis;

A horizontal stabilizer 300 coupled to the two motor tube frames 800 at the rear and connected to the elevator 310;

A vertical stabilizer 400 coupled to a rear upper portion of the motor tube frame 800 and provided with a rudder 410;

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A main propeller 700 driven by an engine is installed at a rear end of the body 100,

A front propeller 500 and a rear propeller 600 driven by a motor are installed on the front and rear ends of the motor tube frame 800, respectively.

According to the present invention, by combining only the merits of an engine and a motor, a main power source is an engine, and a motor is used as an auxiliary power source for landing and landing. A combination of the number of propellers connected to the engine, It provides an improved hybrid drones that can perform stable landing, hovering and flying.

1 is a plan view of an improved hybrid drones of the present invention.
2 is a side view of an improved hybrid drones of the present invention.
3 shows the tilting function of the propeller in the improved hybrid drones of the present invention.
FIGS. 4 and 5 show operation concepts of the engine starting, the gas rising, the hovering mode, the low-speed flight, the high-speed flight and the gas descent in the improved hybrid drones of the present invention from the left side, the front side and the rear side.
FIG. 6 is a conceptual view of the operation in horizontal direction yawing in the hovering mode in the improved hybrid drones of the present invention on the left side, the front side, and the rear side.
Fig. 7 is a plan view of Fig. 6. Fig.
FIG. 8 shows the concept of operating the engine in the release mode when the engine stops operating during flight in the hybrid hybrid drones of the present invention.
Figure 9 is the final state of Figure 8.
FIG. 10 conceptually illustrates signal transmission paths and program mixing of a main board, a receiver, and a transmitter in the improved hybrid drones of the present invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings.

Fig. 1 is a plan view of an improved hybrid drones of the present invention, and Fig. 2 is a side view of an improved hybrid drones of the present invention.

For reference, 'RF', 'LF', 'RR', and 'LR' signify 'front right', 'left front', 'right rear', 'left rear' Is a line passing through the body from left to right in FIG. 1, and the 'right angle axis' is a line perpendicular to the main axis in FIG.

The improved hybrid drones of the present invention include a moving body 100 installed in the direction of the main axis;

A wing 200 coupled to the body 100 in a direction perpendicular to the axial direction and having an auxiliary vane 210 and a flap 230;

Two motor tube frames 800 provided on the left and right sides of the wing 200 respectively in the direction of the main axis;

A horizontal stabilizer 300 coupled to the two motor tube frames 800 at the rear and connected to the elevator 310;

A vertical stabilizer 400 coupled to a rear upper portion of the motor tube frame 800 and provided with a rudder 410;

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A main propeller 700 driven by an engine is installed at a rear end of the body 100,

A front propeller 500 and a rear propeller 600 driven by a motor are installed at the front and rear ends of the motor tube frame 800, respectively.

The front end of the motor tube frame 800 includes a pair of motors whose output is higher than the rear end of the motor tube frame 800 considering the center of gravity of the whole body of the gas in front of the engine according to the position of the engine, And includes a pair of motors.

3 shows the tilting function of the propeller in the improved hybrid drones of the present invention.

As shown in FIGS. 2 and 3, a tilting function is given from the side,

The main propeller 700 rotates about the tilt axis between the rear and the bottom and the front propeller 500 rotates about the motor tilting axis between the upper side and the front side, And the rear propeller 600 is rotatably moved between a rear side and a lower side with respect to a motor tilting axis.

More specifically, the rear propeller 600 includes:

And has two rotating shafts that rotate between the rear and lower sides about the motor tilting axis and rotate in the left and right directions about the motor tube frame 800. [

In addition, the main propeller 700 is a push type, and the wing is fixed in an extended state,

The front propeller 500 is of a pull type,

The rear propeller 600 is a push type, and is characterized in that the wing is extended when it is rotated.

That is, the front propeller 500 and the rear propeller 600 are automatically extended when a lift is generated in the wing using a hinge or a spring, and folding is automatically performed when the lift decreases. Of course, it is possible to impart the folding function by mechanically or electrically driving and controlling the driving means.

In addition,

The present invention is composed of an engine, which is a main power source located at a central portion, and two pairs of motors and propellers having different outputs on the front and rear sides.

Considering that the center of gravity of the gas is located on the wing 200 in FIG. 1, it is preferable for the motor to use a motor having a higher output than the motor on the rear side in takeoff and landing.

The present invention is a structure in which an engine airplane and a multi-copter are mixed. A push propeller is mounted on an engine as a main power source, and a hinge is attached to a bracket of a fuselage so that an engine mount can be tilted downward and backward. And can be forced out.

As mentioned above, the motor and the propeller consist of a high-output motor and propeller part at the front and a low-output motor and propeller part at the rear,

The front group is a full-type propeller consisting of a larger-diameter propeller in combination with a higher output motor than the rear.

And the rear group is a push type propeller composed of a propeller with a smaller diameter in combination with a motor with lower output than the front part.

The front propeller is tilted from forward to upward, the rear propeller from downward to backward and from left to right, and a folding propeller is preferably applied to reduce air resistance.

FIGS. 4 and 5 show operation concepts of the engine starting, the gas rising, the hovering mode, the low-speed flight, the high-speed flight and the gas descent in the improved hybrid drones of the present invention from the left side, the front side and the rear side.

Motor A. The motor B, and the engine are power sources for driving the front propeller 500, the rear propeller 600, and the main propeller 700, respectively.

And the angles and outputs of the power shafts and the like are all indicative of preferred embodiments and are not necessarily limited to the numerical values described.

4 and 5, the explanation will be omitted and only the main features will be described as follows.

In vertical take off or landing flight mode, the propeller axes are aligned with engine-down, front-up, rear-down, and all generate lift downward.

If the propeller shaft is set to be inclined during vertical takeoff or stopping flight, the aircraft will slowly fly horizontally. At this time, the output rate of the motor will decrease according to the inclination of the propeller shaft, The motor is stopped and only the engine is started.

If the propeller shaft is tilted in reverse order in a stop mode or a vertical landing mode in flight mode, low-speed flight is possible,

Vertically aligning completely results in vertical takeoff and landing mode.

In addition,

In the hovering mode, which involves raising or lowering the gas,

The main propeller 700 is positioned downward to generate a downward force,

The front propeller 500 is positioned upward and generates a downward force,

The rear propeller 600 is positioned downward and generates a lift force downward.

At this time, the throttle of the motor is mixed with the throttle of the engine through the spare channel, and the mixing volume thereof is mixed with the downward angle of the flap so that the flap is pulled down when hovering, It is the mode that can maximize the output during vertical take-off, landing and hovering.

When flying at low speed,

The main propeller 700 is inclined from the lower side to the rear side to generate an upward force inclined from the lower side to the rear side,

The front propeller 500 is inclined forward from the upper side to generate a lift force inclined downward to backward,

The rear propeller 600 is positioned to be inclined rearwardly from below, and generates a lift force such that it is inclined rearwardly from below.

At this time, the throttle of the motor is mixed with the throttle of the engine through the spare channel, and its mixing volume is mixed so that it is adjusted to the downward angle of the flap, so that the throttle of the main engine and the motor It becomes a mode in which only a part is tuned (for example, 50%).

Therefore, in all the cost modes, the throttle of the motor and the engine is mixed through the spare channel or the like, and the inclination angle of the main propeller 700, the front propeller 500, the rear propeller 600, One gas control is possible.

When flying at high speed,

The main propeller 700 is positioned rearward to generate a lift force in the rear direction,

The front propeller 500 and the rear propeller 600 are not driven.

At this time, the throttle of the motor is mixed with the throttle of the main engine through the spare channel, and the mixing volume is mixed with the downward angle of the flap so that the flap is at 0 degree in the normal flight state. The tuning rate becomes 0% and the power is shut off.

In addition, the front propeller 500 and the rear propeller 600 may be positioned forward and rearward, respectively, and may not be driven in a folded state.

FIG. 6 is a view showing the concept of operating in the horizontal direction yawing in the hovering mode in the improved hybrid drones of the present invention on the left side, the front side and the rear side,

Fig. 7 is a plan view of Fig. 6. Fig.

The improved hybrid drones of the present invention, when viewed from the front in horizontal direction yawing,

The rear propeller 600 is inclined from the lower side to the left or the right side so that a lift is generated so as to be inclined leftward or rightward.

Specifically, in order to prevent rotation of the gas by generating an anti torque corresponding to a counter torque of the gas generated by the torque of the main propeller 700 in the hovering and low-speed flight mode, ,

The rear propeller 600 is characterized in that the motor tube frame 800 is inclined downward to the left or right from the lower side to generate an upward inclination toward the left or right side.

For reference purposes,
(1) Torque is the force (physics) that rotates the propeller of the engine and the motor,
(2) Counter torque is a force that rotates in the opposite direction when the propeller of the engine and the motor rotates in the opposite direction. The torque is the same in magnitude but opposite in direction (physical: reaction)
(3) Anti torque refers to the force against counter torque (the direction of the torque and the anti-torque must be the same for the straight flight without the gas rotating).

FIG. 8 illustrates the concept of operating the engine in the engine release mode when the engine is stopped during flight in the hybrid hybrid drones of the present invention,

Figure 9 is the final state of Figure 8.

The improved hybrid drones of the present invention, when the engine stops operating during flight,

The motor is driven so that the front propeller 500 is forwardly positioned and generates lift force in the rear direction, and the rear propeller 600 is positioned rearward to generate lift force in the rear direction,

The main propeller 700 may be detached from the engine and separated.

1 and 2, a description of the present invention will be given.

1. Fuselage, wing, Horizontal, vertical tail wing (stabilizer) , Landing gear, main engine propulsion, etc. Fixed wing  The default configuration.

- The motor consists of a pair of high-output motor parts on the front and a pair of low-output motor parts on the rear part.

- A pair of motor parts on the rear part are linked with the rudder of the vertical tail wing (stabilizer) when the yawing is started, so that it can be turned to the right and left tilting in the vertical direction and to cancel the anti torque of the propeller due to the rotation of the vertical axis of the main engine

2. The motor tube which is the frame of the tail wing Frame frame  It extends to protrude from the front of the wing. ① ② It acts as a supporting shaft of the motor mount.

-①② The tilting of the motor mount is mixed with the flap so that when the flap is in the normal state, it runs in all directions and when the flap is operated 100% (about 45˚), the motor shaft works upwards.

3. Motor tube which is the frame of the tail wing Frame frame  Tail wing (stabilizer) extended to protrude to the rear side, ③ ④ serves as a rotating shaft support of the motor mount.

-③④ The tilting of the motor mount is mixed with the flap so that when the flap is in the normal state, it runs backward and when the flap is operated 100% (about 45˚), the motor shaft works in the downward direction,

The tilting of the motor tube frame 800 is also performed by interlocking with the auxiliary tilting and tilting rudder 410 of the vertical stabilizer 400.

4. Engine + Propeller is mounted on the body Backward ~ Rotate downward ( Tilting ) Engine mount  .

- The tilting of the engine mount is mixed with the flap so that when the flap is in the normal state, it moves in the backward direction. When the flap is operated 100% (about 45˚), the motor shaft works in the downward direction.

5. Operation of engine and motor The mode is  There are three main categories.

(1) Hovering mode :

Engine and rear motor parts are downward pitch pitch propeller (PUSHtype). The front motor part is an upward positive pitch propeller (PULLtype), the flap is fully down (100% of the total angle)

At this time,

a. Throttle up-down: hovering up / down operation by engine + motor output control (engine and motor throttle tuning ratio 100%)

b. Elevator up-down: tilting the front of the body posture, tilting to the rear (forward and backward movement in hovering state), controlling the motor output of the front and rear motor parts to be opposite, the engine is not affected. Interlocking up and down of the horizontal wing (horizontal stabilizer) elevator

c. Aileron left - right: tilt of the body posture. (Bank angle - left and right movement in hovering state). Control the motor output of the left and right motor parts in the same way before and after. The engine has no effect. Left and right movement of wing secondary wing (Aileron).

d. Rudder Left-Right: The horizontal direction of the rider is changed from the vertical axis to the fuselage. (The axis of the motor B is vertically downward, and the motor tube frame is tilted right and left by the shaft and the auxiliary wing (rudder) of the vertical tail wing (stabilizer) is interlocked)

(2) Low-speed flight mode :

In hovering mode, engine and rear motor parts (reverse pitch propeller) are partially tilted from down to back. The front motor part (Pull type) is tilted forward and tilting the engine and motor shaft in conjunction with partial tilting, flap mixing and flap operation (20 ~ 50% of total descending angle). The flaps are partially lowered (20 to 50% of the total lowering angle)

 At this time,

a. Throttle up-down: hovering up and down by engine + motor output control

b. Elevator up-down: tilt to the front and back of the fuselage. (Forward and backward movement in hovering state). Control the motor output of the front motor part and the rear motor part to be opposite. The engine has no effect. The elevator up-down linkage of the horizontal tail wing (horizontal stabilizer).

c. Aileron Left-Right: Tilt of the fuselage. Change the direction to the left or right (Bank turn). Control the motor output of the left and right motor parts in the same way before and after. The engine has no effect. Left and right movement of wing secondary wing (Aileron).

d. Rudder Left-right: Yawing of the nose in the horizontal direction with respect to the vertical axis. When the axis of motor B is vertical Tilting rearward (interlocked with flap lifting angle), tilting motor tube frame to the left and right along the axis and interlocking with the rudder of the vertical tail wing (stabilizer).

In the low-speed flight mode, the rotation axis of the motor linked to the flap of the wing is tilted according to the operation angle of the flap,

Because of the program mixing of the flap and the main board, the output of the motor decreases in inverse proportion to the flap downward angle. Therefore, the control effect is lowered, but the aileron, elevator, and rudder in the horizontal stabilizer, And it compensates the insufficient control function of the motor.

(3) Flight mode

- In low-speed flight mode, the engine part is completely tilted from the downward to the backward direction, and the propulsive force of the reverse-pitch propeller (push type) is generated.

- The rear motor part is completely tilted from the downward to the rear, the motor is stopped by the flap + throttle program mixing, and the reverse pitch propeller is folded.

- The front motor part is fully forward tilting forward pitch propeller (Pull type), flap operation 0% (flight mode)

At this time,

a. Throttle up-down: When the flap angle is 0 ° due to the program mixing of the flap and motor throttle, the power of the motor is cut off and the rotation of the propeller stops. Throttle up-down controls the speed of the airframe by adjusting the number of revolutions of the engine in the horizontal axis.

b. Elevator up-down: front tilt of body posture, tilt to rear. The motors of the front motor part and the rear motor part stop rotating and are folded and have no control function. Up-down control of the airplane body with the aid of a horizontal tail wing (horizontal stabilizer).

c. Aileron Left-Right: Tilt of the fuselage. Left / right movement in bank turn or hovering. The motor of the right and left motor parts stops rotating and is folded and has no control function. Left and right motion of the wing secondary wing (Aileron) to control the tilt of the gas (bank angle).

d. Rudder Left-right: The horizontal direction of the rider is changed with the fuselage as the vertical axis. Axis of the motor tube frame of motor B The tilting of the motor and the tilting of the vertical tail wing (stabilizer) are tilted. However, the motor is stopped by the flap and program mixing, and the control is not affected. It is controlled only by the auxiliary wing (rudder) of the vertical tail wing (stabilizer).

(4) Motor On thrust  by Flight mode

- In case of emergency, the engine part is moved to one step and the motor is driven horizontally to generate thrust

- When the spare channel 2 of the controller is turned OFF, the hinge bracket fixed to the body is opened. When the rotation axis of the main engine mount is released, the engine is separated from the gas, and the throttle mixing of the flap and the motor is turned off. Throttle is activated even in the flight mode.

- The rear motor part is fully tilted backwards and the flap + throttle program mixing (preliminary channel ~ mixing volume of the motor throttle) is shut off, so the main engine throttle and tuning ratio are maintained at 100% Throttle activation of motor, reverse pitch propeller (push type) rotation propulsion.

- Front motor part fully tilts forward, flap + throttle program mixing (preliminary channel ~ mixing volume of motor throttle) is shut off, so main engine throttle and tuning ratio are kept 100% Throttle activation of the motor, constant pitch propeller (Pull type) rotation propulsion.

At this time,

a. Throttle up-down: Energize the motor even if the flap angle is 0 ° due to the programmed mixing of the flap and motor throttle. Propeller rotation generates propulsion. Throttle up-down controls the speed of the airframe by adjusting the number of revolutions of the engine in the horizontal axis.

b. Elevator up-down: front tilt of body posture, tilt to rear. The motors of the front motor part and the rear motor part maintain the opposite RPM, but the effect on the flight attitude is insignificant. Up-down control of the airplane body with the aid of a horizontal tail wing (horizontal stabilizer).

c. Aileron Left-Right: Tilt of the fuselage. Left / right movement in bank turn or hovering. It is effective in Yawing phenomenon and Bank turn operation because it reacts with opposite RPM of motor of left and right motor part. Left and right motion of the wing secondary wing (Aileron) to control the tilt of the gas (bank angle).

d. Rudder Left-right: The horizontal direction of the rider is changed with the fuselage as the vertical axis. Tilting left and right in the vertical axis of the motor B is a tilting in the backward and horizontal direction and tilting right and left with the motor tube frame as an axis. However, since the power of the motor is cut off and it is the same axis (motor tube frame) Does not affect flight position. Controlled only by the auxiliary wing (rudder) of the vertical tail wing (stabilizer).

FIG. 10 conceptually illustrates signal transmission paths and program mixing of a main board, a receiver, and a transmitter in the improved hybrid drones of the present invention.

10 is as follows.

- Manipulator: Manipulator for controlling the gas (Remote controler)

- receiver (reciever): Receive the radio signal of the transmitter and transmit it to the servo motor and transmission by wire.

- Main board: A processing device that automatically controls the attitude of the improved hybrid drones of the present invention by processing a signal similar to a receiver or a signal of a controller and data such as a three-axis gyro, an acceleration sensor, and a GPS

- Motor + Transmission + Tilting Servomotor: Receive signals from the receiver or main board to control the rotation speed of the motor and operate the servomotor in the transmission.

- Main Engine Servo Motor Throttle + Tilting Servo Motor: The servomotor receiving the signal from the receiver or main board executes the operation such as throttle cable, tilting.

The mixing of the program is as follows.

Assign pilot 1, 2 preliminary channel

① Controller (Throttle + spare channel -1) Program Mixing → Receiver Spare Channel -1 → Mainboard Throttle Port → Motor Transmission Steering Throttle → Receiver Throttle → Engine Throttle Servo

② Operator Elevator → Receiver Elevator → Horizontal tail wing Elevator Servo → Receiver Elevator → Mainboard Elevator Port → Motor Transmission

③ Controller Rudder → Receiver Rudder → Vertical tail wing Rudder Servo → Receiver Rudder → Motor B (Rear side) Tilting Servo

④ Aileron → Aileron → Aileron → Aileron → Aileron → Aileron → Aileron → Aileron → Aileron → Aileron → Aileron → Aileron → Aileron → Aileron → Aileron → Aileron → Aileron → Aileron → Aileron → Aileron → Aileron → Aileron → Aileron → Aileron → Aileron → Aileron →

⑤ Manipulator Landing gear → Receiver Landing gear → Landing gear Servo

⑥ Control Flap → Receiver Flap → Flap → Flap Servo Controller Flap + Spare Channel -1 Program Mixing → Receiver Spare Channel -1 → Mainboard Throttle * Throttle Port → Motor Transmission

⑦ Manipulator (preliminary channel -2 + (flap ~ spare channel 1 mixing)) ON, OFF switch mixing

Further, according to the structure and feature of the present invention,

(1) According to the present invention, there is provided an air conditioner comprising: a base (an aileron, an elevator, a rudder, a flap, etc.) equipped with a push-type engine + propeller set mounted to be tiltable from a downward to a rearward direction;

Connected to both sides of the wing in the direction of the gas, fixed frame, the end of the frame protruding forward of the wing is mounted on the left and right of the front motor A part of the multi-

The frame extending to the rear side of the wing is connected to the tail wing (vertical and horizontal stabilizer) and extends to the tail wing tail, and the rear end motor B part is attached to the left and right sides respectively.

(2) The front mounted motor A part has a higher output than the rear motor B part and is mounted to be able to tilt from forward to upward with a combination of large constant pitch propellers (Pull type)

The rear motor B part can be tilted from downward to backward by a combination of low output and small reverse pitch propeller (Pusher type)

During hovering, the nose can be tilted from left to right in a downward direction to horizontally rotate left and right.

(3) It also has a receiver for control using the other side (auxiliary wing) of the body, and a main board connected to the receiver to adjust the rotation speed of the motor, so that the program is mixed and controlled.

(4) The horizontal direction switching (Yawing start) of the gas is not controlled, and it is controlled by the auxiliary wing (rudder) of the vertical tail wing (vertical stabilizer) of the gas during flight. In the hovering or low-speed flight mode, the rear motor B part is controlled to tilt from left to right in a vertically downward state.

(5) The throttle of the manipulator is interlocked with the throttle of the receiver, the throttle of the manipulator and the program mixing of the preliminary channel-1 of the manipulator, connecting the spare channel-1 of the manipulator and the receiver to the throttle port of the main board,

The flap of the manipulator is a flap of the receiver, and the manipulator flap is a program mixer that controls the throttling of the manipulator and the mixing volume of the pre-

Even if the throttle is controlled by the controller, the RPM of all the motors is controlled in the same manner as the engine when the flap is down,

When the flap is in the normal state, the flap angle is 0 even if the throttle of the pilot is controlled, so that the mixing volume of the throttle and the preliminary channel-1 is "0", and the program mixing is performed in a double manner so as not to react with the pilot throttle.

(6) The preliminary channel-2 mixes the program so as to have a switch function of turning on and off the mixing of the manipulator throttle and the preliminary channel-1,

The spare channel-2 of the transmitter is connected to the receiver grip channel servo-motor mounted on the engine mount hinge bracket,

When the pilot channel 2 is turned OFF, the throttle control of the motor is canceled, and the engine throttle and the transmission of the motor operate in synchronization with the engine.

Also, the engine can be forcibly released by releasing the grip of the engine mount rotary shaft of the main engine.

(7) In hovering and vertical takeoff and landing, all output control of engine and motor can be operated in conjunction with each other to maximize vertical takeoff weight.

In the low-speed flight mode, when the flap is partially lowered, the forward motor A part is switched from upward to forward, and the rotation axis of the engine and rear motor B part is changed from the downward direction to the rearward direction. Since the wing and tail wing influences the gas posture control with low speed flight, the posture of the gas can be safely controlled by the transmission control of the other side of the gas and the motor.

(8) In the flight mode, the power of the motor is shut off, the front motor A part is in the forward direction, the rear motor B part is in the rear direction, and the propeller is in the folded state,

Depending on the propulsion of the engine, you can fly and adjust the flight time according to the fuel load.

When the engine stops in flight, if the pilot channel 2 is changed to an emergency condition, the throttle of the motor releases the program mixing with the flap, so that the transmission of the motor is activated so that the rotation axis of the motor rotates in the horizontal direction And a function of returning to the flight by the motor drive which is activated in the state where the axis is maintained and the driving force is obtained,

By installing GPS on the aircraft and programming the route, it is possible to extend the application field of practical use by installing the automatic flight function in a certain area or route.

To explain the features and advantages of the present invention,

In conventional drones, the take-off weight is also indicative of the flight capability of the airplane, and it consumes 70 to 90% of the normal output during vertical takeoffs, which consumes fuel or batteries.

In order to solve this problem, the present invention increases the take-off weight by increasing the take-off weight and increases the output in the vertical takeoff and landing flight mode. Depending on the propulsion power of the engine, the output is driven to the minimum level of the engine, so that it is possible to increase the fuel efficiency and to fly for a long time depending on the capacity of the fuel tank.

Since the engine or the motor also becomes large when the gas is large, it is possible to secure the electric power of the motor necessary for the take-off or landing flight by installing the solar module in the wing or the body, or installing the auxiliary generator in the engine and charging the battery. In addition to vertical takeoff and landing during flight, it is also possible to stop or slow flight as needed.

In addition, it is possible to design the airframe to be able to carry out for a long time, and to increase the size of the fuel tank, it is possible to fly for a long time (several hours to several hours).

In addition, depending on the situation, the entire output of the gas can be operated at a time to allow the stationary flight for the purpose of lifting heavy objects or for precise observation.

An advantage of the present invention is that the take-off weight of the vertical take-off and landing aircraft can be improved and the flight time can be extremely extended.

In vertical takeoff and landing mode, all the power of the engine and the motor can be activated to maximize the take-off weight.

During long-haul or long-haul flights, the engine only operates and the battery of the motor is charged by charging the auxiliary generator during flight, so that it is capable of repeatedly performing vertical take-off and landing flights

In the emergency stop mode, the engine mount shaft and engine mount are separated one step, and the main engine is forcedly released. At the same time, the mixing of the motor and flap is canceled to synchronize the engine throttle and the transmission of the motor. It is equipped with the ability to fly and return with the power of the motor.

 This allows emergency landings to take place in a flight mode that reduces the weight of the aircraft by releasing the engine to the required mode when the engine is in a stop or out of control state and depends on the propulsive force of the motor, and allows vertical landing when the battery capacity is secured.

It is effective for a long period of time with automatic flight in a wide area. It is effective for maritime search or illegal fishing, such as normal drone, forest monitoring activity or situation information collection. It patrols the scheduled route such as highway by automatic flight. Etc.).

And it is possible to supply rescue equipment to the victims,

As described above, in order to extend the flight time, it is possible to land on a certain place (such as a ship) and resume flying after refueling.

In addition, it has a large take-off weight and can be loaded in large quantities, can increase the speed of flight, and is also effective in spreading pesticides in forest areas and large cultivated areas.

In slow flight mode, engine + motor and wing lift are added, which is efficient.

While the present invention has been particularly shown and described with reference to exemplary embodiments thereof, it is to be understood that the invention is not limited to the disclosed embodiments, but, on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the invention.

It is therefore intended that the appended claims cover such modifications and variations as fall within the true scope of the invention.

100:
200: main wing
210: aileron
230: flap
300: horizontal stabilizer
310: elevator
400: Vertical stabilizer
410: rudder
500: forward propeller
600: rear propeller
700: Main propeller
800: motor frame tube

Claims (10)

A body 100 installed in the direction of the main axis;
A wing 200 coupled to the body 100 in a direction perpendicular to the axial direction and having an auxiliary vane 210 and a flap 230;
Two motor tube frames 800 provided on the left and right sides of the wing 200 respectively in the direction of the main axis;
A horizontal stabilizer 300 coupled to the two motor tube frames 800 at the rear and connected to the elevator 310;
A vertical stabilizer 400 coupled to a rear upper portion of the motor tube frame 800 and provided with a rudder 410;
, ≪ / RTI >
A main propeller 700 driven by an engine is installed at a rear end of the body 100,
A front propeller 500 and a rear propeller 600 driven by a motor are installed at the front and rear ends of the motor tube frame 800,
From the side,
The main propeller 700 rotates about the engine tilting axis about the motor tilting axis, and the front propeller 500 rotates between the upper and the front about the motor tilting axis, And is rotatably moved between a rear side and a lower side about a tilting axis,
In the hovering mode, which involves raising or lowering the gas,
The main propeller (700) is positioned downward to generate lift, the front propeller (500) is positioned upward and generates lift, and the rear propeller (600) is positioned downward to generate lift and,
When flying at low speed,
The main propeller (700) is inclined rearward to generate a lift force, and the front propeller (500) is inclined forward from above to generate a lift force, and the rear propeller (600) So that an upward lift is generated,
In order to prevent the rotation of the body by generating an anti torque corresponding to the counter torque of the gas generated by the torque of the main propeller 700 in the hovering mode or the low speed flight mode, The rear propeller 600 is rotated downward to the left or right side of the motor tube frame 800 to generate a lift force inclined leftward or rightward.
In the hovering mode, the throttle of the motor is mixed with the throttle of the engine through the spare channel and the mixing volume is adjusted to be adjusted to the downward angle of the flap, so that the flap is pulled down when hovering, Synchronized,
In the low-speed flight mode, the throttle of the motor is mixed with the throttle of the engine through the spare channel, and the mixing volume thereof is mixed so as to adjust the downward angle of the flap so that the throttle of the main engine and the motor is partially synchronized Therefore,
In the hovering mode or the low-speed flight mode,
The throttle of the motor and the engine is mixed through the spare channel and the inclination angle of the main propeller 700, the front propeller 500, the rear propeller 600 and the angle of the flap are automatically controlled, The hybrid drones.
delete The method of claim 1,
The main propeller 700 is a push type and is fixed in a wing-extended state,
The front propeller 500 is of a pull type,
Wherein the rear propeller (600) is a push type, and when the rotor (600) is rotated, a wing is extended.
delete delete delete delete The method of claim 1,
When viewed from the front during horizontal yawing,
The rear propeller (600) is inclined from the lower side to the left or the right side so that an upward lift is generated in an inclined manner to the left or right.
The method of claim 1,
If the engine stops operating during flight,
Wherein the motor is driven such that the front propeller is positioned forward and generates lift, and the rear propeller is positioned rearward to generate lift.
The method of claim 9,
Wherein the main propeller (700) is detached from the engine and separated.

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