KR20200073948A - A Drone Aircraft - Google Patents

Abstract

The present invention relates to a vertical takeoff and landing aircraft with a drone function, which can perform vertical takeoff and landing by generating lift force by moving movable airfoil in the direction opposite to wind while transmitting wind to a fixed and installed airfoil with power of a power generator using a refrigeration cycle, weakens the density of the atmosphere by transmitting a radio wave for dissociating positive ions of the atmosphere to a proceeding direction, and flies by an engine for propulsion. According to the present invention, a general drone or vertical takeoff and landing aircraft sprays wind or pressure to the ground and thus, is difficult to be used around people due to scattering of dust or the like, and a small aircraft is difficult to be used since a runway cannot be secured. Accordingly, according to the present invention, air is blown to a fixed blade by a centrifugal compression device with a power generator using a refrigeration cycle and energy of the same, a rotating blade is moved to the direction opposite to wind to generate strong lift force so as to perform vertical takeoff and landing, and a device for weakening the density of the atmosphere by transmitting electrons is invented to fuse a drone function and a function of an aircraft with high speed such that a drone aircraft is provided. Therefore, the vertical takeoff and landing aircraft with a drone function of the present invention is positively necessary.

Description

Drone Aircraft}

The present invention sends wind to an airfoil fixedly installed by the power of a power generation device using a refrigeration cycle, and simultaneously moves a moving airfoil in the opposite direction of the wind to generate lift and take off and land vertically, dissociating the positive ions in the air toward the direction to proceed. It is a drone that transmits a radio wave to weaken the density of the atmosphere and thrusts it. It relates to a vertical takeoff and landing aircraft that functions as a drone flying by an engine.

Vertical take-off and landing aircraft based on rotorcraft, such as helicopters and drones, have the advantage of not requiring separate take-off and landing facilities, but are inferior to fixed-class aircraft in their class for high-speed flight, long-term airborne, and high altitude performance.

In general, aircraft and drones that take off and land vertically take advantage of nozzles that take off from the ground by rotating the propellers of the main aircraft of the British main force, the fighter plane of the British Air Force that takes off vertically from the ground by spraying with a nozzle. There is a method of generating lift by transferring wind from the center of the drone's circular airfoil to the outside.

The former has a difficulty in using at home due to the generation of dust on the ground, and the latter has the disadvantage of slow flight speed.

Compared to fixed-wing aircraft that can select a variety of propulsion systems from electric motors to jet engines, the vertical takeoff and landing aircraft that rely only on the engine's axial horsepower has a smaller choice of propulsion system.

In particular, in the case of a reciprocating engine widely used in small aircraft with a maximum take-off weight (MTOW) of about 10 to 300 kg, the output-to-weight ratio is very small, about 2 or more.

Therefore, in order to supply the power required for vertical takeoff and landing, the engine's volume and weight become very large compared to that of a fixed-wing aircraft of the same class, and the weight of the propulsion system compared to the empty weight of the aircraft is excessive, so the required payload for the mission ( It is difficult to secure payload and endurance time.

Therefore, although a propulsion system using a battery and an electric motor is widely used in a small aircraft, due to limitations of current battery technology having a low energy density, sufficient flight time required for a mission cannot be provided.

An energy source with a high specific energy and a power device capable of converting it are required for long-term flight, but an energy source with a high specific power and a device capable of converting it are required for vertical take-off and landing. .

However, since there is no energy source and a power generating device having both high specific energy and non-power, efforts to provide a longer flight time are continuing.

On the other hand, the most frequently used aviation engines have a centrifugal compressor in the first half and burn compressed air; The turbine is driven by the combusted mixed gas to generate power, and the combustion gas is injected at a strong pressure to form a negative pressure in the first half of the plane and spray the strong pressure to the rear of the plane to transfer it to its driving force.

However, conventional internal combustion engines and aviation engines are operated using fossil fuels, and thus have a great problem of polluting the environment.

Therefore, the object of the present invention is to blow the fixed blade by a centrifugal compression device using a power generation device using the refrigeration cycle and its energy as a power source, and move the rotor blade in the opposite direction of the wind to generate strong lift, allowing vertical takeoff and landing. It is to provide a drone aircraft by integrating the functions of a drone function and a high-speed aircraft by making a device that reduces the density of the atmosphere by transmitting electrons.

Another object of the present invention is to provide a drone aircraft capable of flying at high speed by transmitting radio waves in a desired direction to cationize the atmosphere and reducing the density of the atmosphere to reduce air friction.

In order to achieve the above object, the present invention is the first to generate electricity using a thermo-electric power generating element to generate the difference in the pressure of the refrigeration cycle using a turbine, fuse electrons with air heat, and move electrons generated between the hot and cold parts. A power unit; A second power unit configured to power a rotational force of the magnet; A power generation unit driven by receiving electric energy generated by the first power unit; A lifting portion for generating lift by sending wind to the fixed and rotating wings with the rotational force of the motor; A driving unit for strongly rotating the rotor blade; It is a basic feature of the technical configuration by installing a radio wave generating transmission part that generates and transmits a predetermined frequency, and a centrifugal compression thrust device that thrusts air in the directions of up, down, left, and right through high-speed compression.

In addition, when the aircraft is not running, it serves to cool and heat the inside of the aircraft with the second power unit, and charges the battery with excess electricity, so that the battery and the second power unit provide energy for starting and initial operation of the airplane. When the first power unit starts normal operation after a predetermined time, the first power unit is installed to take charge of all the power, and a reverse propulsion jet is installed on the other side to take off and land, and to stop the flight. It was installed for use.

As described above, the drone aircraft of the present invention produces the following effects.

The drone aircraft of the present invention,

1. Since it is not a method of spraying pressure or wind to the ground, it can be conveniently used regardless of home or place.

2. After takeoff, the flight speed is fast, it can be rotated in place, and it can be used as a drone and aviation function.

3. It can fly for a long time without supply of fuel with the air-heat generator, and it can also sail in the sea as a function of aircraft and ships.

4. It can function as a house and a camper.

5. By transmitting radio waves in the direction of travel, dissociation of cations reduces the density of the atmosphere to reduce the friction of the atmosphere so that it can fly faster.

)와 일반 화살표는 유체 흐름과 날개, 항공기 이동방향임.
표시 없는 사각은 공간과 같은 목적의 부품임.1: Front view of the drone aircraft structure of the present invention.
2: Draft aircraft structural description plan view of the present invention.
Figure 3: Front view of the drone aircraft of the present invention.
4: Plan for explaining the takeoff situation of the drone aircraft of the present invention.
5: Another structural description front view of the drone aircraft of the present invention.
6 is a plan view showing another structure of the drone aircraft of the present invention.
7: Frontal view explaining another takeoff situation of the drone aircraft of the present invention.
8: A plan view illustrating another takeoff situation of the drone aircraft of the present invention.
9: Front view of the rotation of the drone aircraft of the present invention in place.
10: Description of the rotation of the drone aircraft of the present invention.
11: A front view explaining the thrust situation of the drone aircraft of the present invention.
Figure 12: A plan view illustrating the thrust situation of the drone aircraft of the present invention.
13: Front view of thrust explanation according to the radio wave transmission of the drone aircraft of the present invention.
14 is a plan view illustrating thrust according to radio wave transmission of a drone aircraft of the present invention.
* Description of main symbols in drawings
01) Fixed wing 03) Blower 11) Other fixed wing
13) Other blowers 22) Lift propeller 23) Rotor blade
25) Rotary support roller 33) Main propulsion device 34) Left rotation thrust device
35) Right thrust device 36) Rear thrust device 37) Auxiliary thrust device
38) Help thrust device 55) Intake power generator 66) Vertical thrust device
77) Air flow pipe 83) Stair lifting device 84) Turning plate
85) Hydraulic leg 86) Drive gear 87) Separation wall plate
88) Cockpit 89) Upper part 90) Lower part
91) Fuel tank 92) Ladder 93) Elevator
96) Sliding door 97) Frequency generator 98) Battery
99) Transmitter 100) Radio
* arrow(

) And the general arrows indicate the direction of fluid flow, wing and aircraft movement.
Squares without markings are intended for space purposes.

The configuration state of the present invention will be described in detail based on the drawings presented from FIGS. 1 to 14 as follows.

In our daily life, without this landing runway, a small private aircraft cannot be used.

Therefore, the drone aircraft of the present invention, as a device for enabling the landing function, the fixed wing (01) and the other fixed wing 11 between the separation wall plate 87 of the body is installed; Before and after the fixed wing 01 and the other fixed wing 11, the blowing device 03 and the other blowing device 13 are installed.

At this time, depending on the purpose can be installed so that the other air blowing device 13 to send air in the same direction or a different direction from the air blowing device 03, which is the purpose of generating lift of the lift propeller 22 and the rotor blade 23 Depending on the installation.

Subsequently, the lifting vanes including the fixed wing 01, the other fixed wing 11, the blowing device 03, and the other blowing device 13 are installed in two stages, upper and lower, and separated upper and lower separation wall plates 87 ), the lift propeller 22 or the rotor blade 23 is installed.

At this time, the lift propeller 22 is installed together with the drive motor, the rotor 23 is fixed to a plurality of firmly installed on one rotating plate 84 installed in the center; The rotating plate 84 is provided with an internal gear in the central portion; A drive gear 86 is connected to the inward gear by a gear joint.

At this time, the rotating plate 84 is supported by the rotating support roller 25, and other detailed installation is omitted because it is a conventional technique implemented by kinematics.

Subsequently, the sliding door 96 is installed along the outer circumferential surface of the part belonging to the upper and lower edges of the partition wall plate 87; A frequency generating device 97 and a battery 98 are installed in the form of a circle on the outside of the edge separation wall plate 87; On the outer side of the frequency generator 97 and the battery 98, an air flow pipe 77 installed by forming a circular pipe in a circular ring shape is installed; The air flow pipe 77 is provided with a main propulsion device 33 on one side of the central X-axis and a rear thrust device 36 on the other side; A left thrust thruster 34 and a right thrust thruster 35 are installed symmetrically on both sides of the X axis of the main thruster 33, and symmetrically opposite to each other of the rear thruster 36 to assist the thruster ( 37) and the help thrust device 38 are installed through the air flow pipe 77 and the pipe joint.

At this time, the thrust devices may be installed in space to be replaced with an ion engine and an EM drive (an electromagnetic wave engine used in space).

On the other hand, a plurality of transmitters 99 are installed in a circular band shape, and all transmitters 99 on either side of the plane are installed to transmit in the same direction in the X-axis direction, and on the other side The transmitter 99 is installed in the same manner with the transmission direction reversed 180 degrees.

This is to dissociate positive ions in the forward atmosphere in the forward direction while the drone aircraft of the present invention transmits the radio wave 100 in the forward direction when the drone aircraft moves forward and backward.

On the other hand, a plurality of vertical thrust devices 66 are distributed and installed at predetermined positions along the outer circumferential surface of the drone aircraft, but a door that is automatically opened and closed must be installed above and below.

Subsequently, the installation of the drone aircraft of the present invention is completed by installing the stair lift device 83, the hydraulic meal leg 85, and the boarding ladder 92 below the drone aircraft body and installing the elevator 93 indoors.

Subsequently, the operation state of the present invention will be described in detail with reference to the drawings presented in FIGS. 1 to 14 as follows.

The characteristic of the drone aircraft is how efficient the vertical takeoff and landing device is equipped with, and the present invention is to create a flow of air and rotate the airfoil to reverse the flow to generate strong lift force.

If the fixed wing (01) and the other fixed wing (11) are installed between the separation wall plates (87) in the first way so that the lift is generated in the passage where the wind blows, the opposite shape is installed opposite, so the wind blows in reverse. , The lift propeller 22 rotates through the gaps of the partition wall plate 87 composed of the upper and lower two stages, is propelled and rotated in the opposite direction of the wind, and rotates, and the relative speed of the wind acting on the airfoil Is doubled, and theoretically, the lift is 8 times.

This is because lift is a function of the cube of the wind speed.

That is, lift (F) = 1/2ρAV ³ , ρ = air density, A = airfoil area, V = air velocity, and (2V) ³ = 8V ³ .

In the second method, the wind blowing between the separating wall plates 87 has two passages in the same direction, and the rotor 23 rotates in the opposite direction to the direction of the wind. It is 8 times the speed, and lift is generated.

On the other hand, since the propagation of the radio wave length of 80.1 MM generated by the transmitter 99 dissociates the cations of the atmosphere, it has recently been proven that the cations of the cations move to the atmosphere where the anions dissociate toward the dissociated atmosphere. When the cation dissociates by analogy, the atmosphere from which the cation dissociates moves toward the atmosphere of the anion, and the atmosphere splits up, down, or left, and right, so when the radio waves are transmitted in the direction of the drone aircraft, the atmosphere propagates. The drones that fly toward the atmosphere with less friction can be made to fly faster by splitting the outside of the transmitter's transmission part to weaken the density.

On the other hand, the drone aircraft of the present invention uses the above-described lift generating device and the vertical thrust device 66, the main thrust device 33, the left thrust device 34, and the right thrust device 35 at the same time to watch It can rotate in a clockwise and counterclockwise direction and move up and down; While flying in the opposite direction described above, the rear thrust device 36, the right rotation thrust device 35, and the left rotation thrust device 37 are simultaneously used to rotate in place, clockwise and counterclockwise, and straight forward and backward. It is possible to proceed quickly.

Therefore, the drone aircraft of the present invention will be able to fly at a speed of Mach 8, which is impossible on the earth because it is possible to land, regardless of location, and has less friction, and is safer than conventional aircraft even in emergency landing. It is advantageous to have a device, and it is possible to safely make an emergency landing even with the wind resistance of the rotor blade 23 and the vertical thrust device 66.

In addition, the drone aircraft of the present invention can also be used as a mobile home, and can be used as a camper.

What has been described above is only one embodiment for carrying out the present invention of a drone aircraft, and the present invention is not limited to the above-described embodiments and without departing from the gist of the present invention claimed in the following claims. Anyone with ordinary knowledge in the field to which they belong will be able to implement various changes.

Claims (12)

Fixed wing lift installed with a blower device (03) and another blower device (13) before and after the fixed wing (01) and the other fixed wing (11) in a passage divided into two upper and lower two stages by a partition wall plate (87). Boo,
The lift propeller 22 or the rotor blade 23 is installed between the upper and lower two-stage partition wall plates 87, and is rotated in the opposite direction to the direction of the wind blowing in the passage, resulting in twice the relative speed. A rotary wing lifting portion that causes lift,
An intake power generation device 55, a main propulsion device 33, a left rotation thrust device 34, and a right rotation thrust device 35 are installed in the air flow pipe 77 [rear thrust device for propelling the vehicle as described above. (36), the auxiliary thrust device (37), the assist thrust device is installed oppositely], two or more vertical thrust devices (66) are distributed and installed along the outer peripheral surface of the main body,
Drone aircraft characterized in that the body portion of the hydraulic leg (85) and ladder (92) is installed along the outer periphery of the body of the drone aircraft, the radio wave transmission unit (100) transmitter 99 is installed, and the lower body body. The method of claim 1, wherein the fixed wall (01) and the other fixed wing (11) are installed in the same direction in the passage of the partition wall plate (87), and the blowing device (03) and the other blowing device (13) are installed in the same direction, Drone aircraft characterized in that the rotor 23 to rotate in the opposite direction of the wind. The method of claim 1, wherein the fixed wall (01) and the other fixed wing (11) are installed in the opposite direction to the passage of the partition wall plate (87), and the blowing device (03) and the other blowing device (13) are installed in opposite directions, Drone aircraft characterized in that the wing rotation of the lift propeller (22) rotates in the opposite direction to the progress of the wind on both sides of the passage. The drone aircraft according to claim 1, characterized in that the radio wave of the transmitter (99) transmits at a size of 70 to 90 mm in length of the radio wave dissociating the positive ions of the atmosphere. The drone aircraft according to claim 1, wherein the intake power generator (55) is replaced with a power generator using air heat and a refrigeration cycle. The drone aircraft according to claim 1, wherein the hydraulic leg (85) is installed by replacing it with a pneumatic shock absorber. The drone aircraft according to claim 1, wherein the lifting propeller (22) or the rotor blade (23) is replaced with carbon fiber or graphene. According to claim 1, In the installation of the rotor blade 23 and the separating wall plate 87, a ferromagnetic body and a magnet are installed at the ends of the rotor blade (23); A drone aircraft characterized in that electromagnets are installed on upper and lower adjacent partition wall plates (87) on the rotational orbit of the rotor blades (23). The drone aircraft according to claim 4, characterized in that in the transmitter (99) transmitting the radio wave (100), a helical antenna is installed and the circular polarized wave is transmitted. The feature of claim 1, wherein a generator is attached to the vertical thrust device (66), and an airbag operated with power generated in an emergency is installed in all of the interior spaces of the cockpit (88), the upper interior (89), and the lower interior (90). Drone aircraft. According to claim 1, The main thrust device (33), left thrust device (34), right thrust device (35), rear thrust device (36), auxiliary thrust device (37), energy source of help thrust device (38) Drone aircraft characterized by installing a combustion heat injection engine, a power generation device for a refrigeration cycle using air heat, and a rotating device using a magnet. According to claim 1, The main thrust device (33), left thrust device (34), right thrust device (35), rear thrust device (36), auxiliary thrust device (37), energy source of help thrust device (38) It is a drone aircraft characterized by being installed as an engine of an ion engine or an EM drive.

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