KR102004227B1 - VERTICAL TAKE OFF AND LANDING AIRCRAFT USING HYBRID-ELECTRIC PROPULSION SYSTEM and THE CONTROL METHOD - Google Patents

Abstract

According to one embodiment of the present invention, a vertical takeoff and landing aircraft using a hybrid electric propulsion system and a control method thereof are possible to control a flight vehicle (1) so that power is provided to a motor (80) form a generator (20), an electricity managing device (40) and a battery managing system (60) at the same time when the flight vehicle (1) vertically takes off and lands and are possible to control the flight vehicle (1) so that thrust of a second propeller (820) is increased and remaining electricity generated in the generator (20) is charged in a batter (62) of the battery managing system (60) when the flight vehicle (1) cruise-flies or transition-flies.

Description

TECHNICAL FIELD [0001] The present invention relates to a vertical takeoff and landing aircraft using a hybrid electric propulsion system, and a control method thereof. [0002]

The present invention relates to a vertical takeoff and landing aircraft using a hybrid electric propulsion system.

A vertical takeoff and landing aircraft based on a rotating wing such as a helicopter is advantageous in that it does not require a separate takeoff and landing facility or equipment, but has lower performance than a fixed wing aircraft in high speed flight, long flight and high altitude performance.

Compared to fixed-wing aircraft, which can select a variety of propulsion systems from electric motors to jet engines, vertical takeoff and landing aircraft, which depend on the engine's axial horsepower, have limited propulsion systems as the weight of the aircraft decreases.

In particular, the reciprocating engine widely used for small aircraft with a maximum take-off weight (MTOW) of about 10 to 300 kg has a very low output-to-weight ratio of about 2. In order to supply the necessary power for vertical take-off and landing, the volume and weight of the engine becomes very large compared to the fixed wing gas of the same class, and the weight of the propulsion system to the aircraft's empty weight is excessively large, ) And an endurance time are difficult to secure.

Therefore, although a propulsion system using a battery and an electric motor is widely used for a small aircraft, current battery technology having a low energy density can not provide sufficient time required for a mission.

In order to construct a long-term space, energy sources with high specific energy and power units capable of converting them are required. However, for vertical takeoff and landing, energy sources with high specific power and devices capable of converting them are required .

However, since there is no energy source and no power source for both non-energy and non-power sources, an energy source and a power generator with high specific energy are usually mounted on the aircraft for long-term storage.

The vertical take-off and landing of the aircraft requires a lot of energy, and the propulsion system including the power generating device must be designed to supply sufficient power to the vertical take-off and landing, so that the weight of the entire propulsion system is much heavier than the weight required for flight Aircraft weight and propulsion system inefficiency.

In recent years, efforts have been made to reduce the weight of the propulsion system, increase the efficiency, and provide a longer running time by simultaneously using an energy source with high energy and a source with high power.

KR 10-2011-0112402 A KR 10-1667330 B1 KR 10-1615486 B1 KR 10-1638964 B1

SUMMARY OF THE INVENTION Accordingly, it is an object of the present invention to provide a vertical takeoff and landing aircraft using a hybrid electric propulsion system capable of efficiently utilizing available energy by solving a large difference in thrust between vertical takeoff and landing flights and a control method thereof .

According to an aspect of the present invention, there is provided a vertical take-off airplane using a hybrid electric propulsion system, comprising: a flight body having a fixed blade; An engine (10) installed in the air vehicle (1) for burning fuel to produce power; A generator (20) connected to the engine (10) to produce electric power; A power management device (40) for managing the power; A battery management system 60 in which the power provided from the power management device 40 is charged; A motor 80 installed in the fixed wing 4 and operated by receiving power from the battery management system 60; A first propeller 81 operated by the motor 80; A second propeller 82 operating as the engine 10; And a control unit (50) for controlling operation of the engine (10), the generator (20), the motor (80) and the second propeller (82)

The control unit 50 controls the motor 80 to supply power from the generator 20, the power management unit 40 and the battery management system 60 to the motor 80 at the same time when the air vehicle 1 takes off and land vertically. 80 to provide the control signals.

The control unit 50 of the vertical take-off airplane using the hybrid electric propulsion system according to the embodiment of the present invention is configured such that when the airplane 1 vertically takes off and land, the thrust of the second propeller 82 is transmitted to the airplane 1, So as not to affect the flight of the vehicle at all.

The control unit 50 of the vertical take-off airplane using the hybrid electric propulsion system according to the embodiment of the present invention may be configured such that when the airplane 1 vertically takes off and land, the engine 10 and the second propeller 82 It is possible to control to shut off the power connection.

The control unit 50 of the vertical takeoff and landing aircraft using the hybrid electric propulsion system according to the embodiment of the present invention increases the thrust of the second propeller 82 when the airplane 1 is cruising or transiting The battery 62 of the battery management system 60 can be controlled so that the spare power produced by the generator 20 is charged.

According to an aspect of the present invention, there is provided a control method for a vertical takeoff and landing aircraft using a hybrid electric propulsion system, the method including: a first step of generating power; A second step of operating the generator (20) with the power to produce electric power; A third step of distributing power to each configuration of the air vehicle 1 by the power management device 40; A fourth step in which a part of the electric power is charged in the battery 62 of the battery management system 60; And a fifth step of operating the first propeller (81) with the motor (80)

Controlling power supplied from the generator 20, the power management device 40 and the battery 62 to the motor 80 at the same time when the air vehicle 1 is vertically raised or lowered; .

The control method of the vertical take-off airplane using the hybrid electric propulsion system according to the embodiment of the present invention is such that when the airplane 1 vertically takes off and land, the thrust of the second propeller 82 for cruising is transmitted to the airplane 1, Lt; RTI ID = 0.0 > and / or < / RTI >

The control method of the vertical take-off airplane using the hybrid electric propulsion system according to the embodiment of the present invention is characterized in that when the airplane 1 vertically takes off and land, the power connection between the engine 10 and the second propeller 82 Controlled so as to be able to intercept.

The control method of the vertical takeoff and landing aircraft using the hybrid electric propulsion system according to the embodiment of the present invention is to control the vertical takeoff and landing aircraft to increase the thrust of the second propeller 82 when the airplane 1 is cruising or transiting, And controlling the battery 62 of the battery management system 60 to be charged with the spare power produced by the battery 20.

The details of other embodiments are included in the detailed description and drawings.

The vertical takeoff and landing aircraft and the control method thereof using the hybrid electric propulsion system according to the present invention as described above are capable of maintaining the feathering state even when the power generated in the engine is transmitted to the second propeller, And the angle of attack of the second propeller can be adjusted by controlling the angle of attack of the second propeller when the transition flight is performed, and the angular attack of the second propeller can be adjusted So that the required thrust can be generated.

Further, the vertical takeoff and landing aircraft using the hybrid electric propulsion system according to the embodiment of the present invention and the control method thereof may include a clutch device when the angularly fixed propeller is adopted, so that the power transmission from the engine to the second propeller And it is possible to reduce the power loss by controlling the engine control device and to transmit the power from the transition flight altitude to the second propeller by the clutch device when the transition flight is performed and to adjust the engine output by controlling the engine control device, The first propeller for delivering power to the propeller and for vertical takeoff and vertical landing can efficiently distribute and utilize energy consistent with the direction of travel of the aircraft.

Meanwhile, the vertical takeoff and landing aircraft and the control method thereof using the hybrid electric propulsion system according to the embodiment of the present invention can use a first propeller when vertically ascending or descending for takeoff and landing, And the power output from the power generator and the power management device can be used simultaneously to reduce the capacity of the battery, thereby reducing the weight of the battery and reducing the weight of the aircraft as much as the battery reduction.

1 is a view for explaining a pitch control propeller mounting type in a vertical takeoff and landing aircraft using a hybrid electric propulsion system according to an embodiment of the present invention.
2 is a view for explaining a clutch device mounting type in a vertical takeoff and landing aircraft using a hybrid electric propulsion system according to an embodiment of the present invention.
3 is a diagram for explaining a schematic diagram of a vertical takeoff and landing aircraft using a hybrid electric propulsion system according to an embodiment of the present invention.
4 and 5 are views for explaining an example of a vertical takeoff and landing aircraft using a hybrid electric propulsion system according to an embodiment of the present invention.
6 and 7 are views for explaining another example of a vertical takeoff and landing aircraft using a hybrid electric propulsion system according to an embodiment of the present invention.
FIGS. 8 and 9 are views for explaining another example of a vertical takeoff and landing aircraft using a hybrid electric propulsion system according to an embodiment of the present invention.

BRIEF DESCRIPTION OF THE DRAWINGS The advantages and features of the present invention, and how to accomplish them, will become apparent by reference to the embodiments described in detail below with reference to the accompanying drawings.

Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings. It is to be understood that the embodiments described below are provided for illustrative purposes only, and that the present invention may be embodied with various modifications and alterations. In the following description, well-known functions or constructions are not described in detail since they would obscure the invention in unnecessary detail. In addition, the attached drawings are not drawn to scale in order to facilitate understanding of the invention, but the sizes of some components may be exaggerated.

On the other hand, the terms first, second, etc. may be used to describe various elements, but the elements should not be limited by the terms. The terms are used only for the purpose of distinguishing one component from another. For example, without departing from the scope of the present invention, the first component may be referred to as a second component, and similarly, the second component may also be referred to as a first component.

It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory and are intended to provide further explanation of the invention as claimed.

Like reference numerals refer to like elements throughout the specification.

Hereinafter, a vertical takeoff and landing aircraft using a hybrid electric propulsion system according to an embodiment of the present invention and a control method thereof will be described with reference to FIGS. 1 to 5. FIG. 1 is a view for explaining a pitch control propeller mounting type in a vertical takeoff and landing aircraft using a hybrid electric propulsion system according to an embodiment of the present invention.

The vertical takeoff and landing aircraft using the hybrid electric propulsion system according to the embodiment of the present invention includes a flight object 1, an engine 10, a generator 20, a power management device 40, a battery management system 60, a motor 80 , First and second propellers 81 and 82, and a control unit 50. [

The air vehicle 1 may have a structure in which the fixed body 4 is provided on the body 2 as shown in Figs.

The engine 10 can be installed in the air vehicle 1, more specifically, in the fixed wing 4, and can generate power by burning fuel.

The integrated starter generator (ISG) 20 may be connected to the engine 10 and may operate as an engine output to produce electric power.

The generator 20 can also function as a starter so that the engine 10 can be started by supplying power to the generator 20 when the engine 10 is started.

The power management unit (PMU) 40 can manage the power, and more specifically, can manage generated power, surplus power, and battery charging power.

The battery management system 60 may include a first battery 62 and power supplied from the power management device 40 may be charged to the first battery 62. [

The motor 80 may be installed in the fixed wing 4 or the body 2 and may be powered by the battery management system 60.

The first propeller 81 may be operated by the motor 80. Meanwhile, the first propeller 81 may be installed in a vertical direction, and may be installed to be inclined at an appropriate slope according to the flying purpose of the air vehicle 1.

The second propeller 82 may operate as the engine 10. [

1, the second propeller 82 may be equipped with the pitch control device 100 and may control the angle of attack of the second propeller 82 with the pitch control device 100 .

2, a clutch device 102 may be provided between the engine 10 and the second propeller 82 and the clutch device 102 may be provided between the engine 10 and the second propeller 82 The power transmitted to the power source 82 can be disconnected or connected.

The control unit 50 may control the operation of the engine 10, the generator 20, the motor 80, and the second propeller 82.

The control unit 50 may be implemented by an engine control unit 30, a power management unit 40, a master control unit, an air control system 90, a flight control computer (FCC) .

The engine control device 30 can control the rotation speed of the engine 10 and more specifically can control the output of the engine 10 by opening and closing the throttle server 12.

The master control unit can collectively control the air vehicle 1 and the air control system 90 and the flight control device can control the operation of the air vehicle 1 and can control the operation of the air vehicle 1, It can be used to control speed, pressure, communication, flight attitude, and so on.

The controller 50 controls the motor 80 to supply power from the generator 20, the power management unit 40 and the battery management system 60 to the motor 80 at the same time when the air vehicle 1 takes off and land vertically. As shown in Fig.

The vertical takeoff and landing aircraft using the hybrid electric propulsion system according to the embodiment of the present invention can use the first propeller 81 when the airplane 1 vertically ascends or descends for takeoff and landing, The capacity of the battery can be reduced by simultaneously using the engine 10, the generator 20, and the power output from the power management device 40 for the operation of the one propeller 81. [

 Thus, the vertical takeoff and landing aircraft using the hybrid electric propulsion system according to the embodiment of the present invention can reduce the weight of the battery and reduce the weight of the aircraft as much as the battery reduction.

An electronic control example of the control unit 50 will be described below with reference to Fig.

The vertical takeoff and landing aircraft using the hybrid electric propulsion system according to the embodiment of the present invention uses the first propeller 81 when vertically taking off and landing. First, the engine 10 receives fuel from the fuel system 14 under the control of the engine control device 30 and outputs power.

The generator 20 can be controlled by the control unit 50, and can operate with the power to produce electricity.

The power generated by the generator 20 can be managed by the power management device 40, for example, it can be distributed to require power, and if excessive power is produced by monitoring whether excess power is produced, It is possible to control the output of the engine 10 through the device 30 to be reduced.

The power management device 40 may provide power to the battery management system 60 and the battery management system 60 may charge some of the power to the first battery 62 and some of the other power to the motor 80 .

Meanwhile, the vertical takeoff and landing aircraft using the hybrid electric propulsion system according to the embodiment of the present invention may include a plurality of motors 80, and an electric speed control device 70 may be provided for each motor 80.

Each of the electronic speed control devices 70 can receive power from the battery management system 60 and each of the electronic speed control devices 70 can be powered by the control unit 50 or the air control system 90 The speed of each motor 80 can be individually controlled, thereby stabilizing the attitude of the air vehicle 1.

The pitch control device 100 controls the angle of attack of the second propeller 82 to maintain the feathering state even if the second propeller 82 is connected to the engine 10 to operate the second propeller 82, The power loss generated in the engine 10 can be reduced even if the propeller 82 is operated.

The control unit 50 controls the pitch control device 100 so that the thrust of the second propeller 82 does not affect the flight of the airplane 1 at all when the airplane 1 takes off and land vertically, . More specifically, the angle of attack of the second propeller 82 can be controlled so as to approach zero degrees, whereby the thrust by the second propeller 82 becomes a value of " 0 & .

On the other hand, the vertical takeoff and landing aircraft using the hybrid electric propulsion system according to the embodiment of the present invention can use the second propeller 82 for the transition flight or the cruise flight.

The vertical takeoff and landing aircraft using the hybrid electric propulsion system according to the embodiment of the present invention can control the desired thrust by adjusting the angle of attack of the second propeller 82 at the transition flight altitude when the transition is flying.

Similarly, the vertical takeoff and landing aircraft using the hybrid electric propulsion system according to the embodiment of the present invention can generate necessary thrust by controlling the angle of attack of the second propeller 82 when cruising.

Assuming that the flying ratio is 10 when the air vehicle 1 is flying, the thrust required for cruising can be one tenth of the vertical lift or vertical lift, and approximately 5 minutes when accelerating or dashing Lt; / RTI >

That is, when the airplane 1 is vertically rising or falling vertically, a lot of energy is required. However, when the airplane 1 is flying or cruising, the energy consumption may be relatively small, and surplus energy may be generated. The surplus energy can be electrical energy, and this surplus power can be charged to the first battery 62. [

The control unit 50 can increase the thrust of the second propeller 82 when the air vehicle 1 is cruising or transiting and the spare power produced by the generator 20 is supplied to the battery management system 60, The first battery 62 of the first embodiment can be charged. The first battery 62 is charged, thereby further increasing the braking time of the air vehicle 1.

On the other hand, the vertical take-off airplane using the hybrid electric propulsion system according to the embodiment of the present invention can use both the first propeller 81 and the second propeller 82 when the transition is flying, The ratio of the electrical energy to be supplied to the first propeller 81 to the mechanical energy to be supplied to the second propeller 82 may be controlled by the controller 50 according to the flight mode.

In addition, the vertical takeoff and landing aircraft using the hybrid electric propulsion system according to the embodiment of the present invention can add the clutch device 102 when the propeller having fixed angle of attack is adopted, which will be described with reference to FIG. 2 is a view for explaining a clutch device mounting type in a vertical takeoff and landing aircraft using a hybrid electric propulsion system according to an embodiment of the present invention.

The control unit 50 may control to shut off the power connection between the engine 10 and the second propeller 82 when the air vehicle 1 takes off and land vertically.

The vertical takeoff and landing aircraft using the hybrid electric propulsion system according to the embodiment of the present invention operates the clutch device 102 when the air vehicle 1 takes off and land vertically to transmit power from the engine 10 to the second propeller 82 Thereby reducing power loss. The control unit 50 may control the operation of the clutch device 102. [

All of the mechanical energy produced by the engine 10 can be supplied to the generator 20 to increase the electric production, thereby enabling a large-capacity and stable power supply to the motor 80. Furthermore, the stable operation of the motor 80 allows the first propeller 81 to operate satisfactorily, so that the vertical rise or the vertical fall of the air vehicle 1 can be realized more smoothly.

On the other hand, an electronic speed control device 70 may be provided for each motor 80.

Each of the electronic speed control devices 70 can receive power from the battery management system 60 and each of the electronic speed control devices 70 can be powered by the control unit 50 or the air control system 90 The speed of each motor 80 can be individually controlled, thereby stabilizing the attitude of the air vehicle 1.

On the other hand, when the transition is flying, the clutch device 102 is operated at the transition flight altitude to connect the engine 10 and the second propeller 82 so that the second propeller 82 can increase the thrust. The engine 10 can control the engine output by controlling the engine control device 30 and can transmit the power of the engine 10 to the second propeller 82 by the clutch device 102 when cruising.

On the other hand, the vertical takeoff and landing aircraft using the hybrid electric propulsion system according to the embodiment of the present invention can be inclined such that the first propeller 81 coincides with the traveling direction of the aircraft when cruising, And can be used.

3 is a diagram for explaining a schematic diagram of a vertical takeoff and landing aircraft using a hybrid electric propulsion system according to an embodiment of the present invention. The description of the technical description described above is not repeated.

The engine 10 may be equipped with the pitch control device 100 or the clutch device 102.

The pitch control device 100 may control the angle of attack of the second propeller 82 and the clutch device 102 may disconnect the power transmitted from the engine 10 to the second propeller 82 Or connect.

Generator 20 may be further equipped with sensor 22 and sensor 22 may be coupled with power management device 40. [ The sensor 22 can monitor the generator 20 and based on the detected first detected value the controller 50 can determine whether the current power generation is appropriate or not.

The control unit 50 controls the throttle servo 12 to open through the engine control device 30 when the power production is insufficient, thereby increasing the engine revolution speed.

On the other hand, if the electric power is excessive, the control unit 50 controls the throttle servo 12 to be closed through the engine control unit 30, thereby reducing the engine speed.

In the vertical take-off and landing aircraft using the hybrid electric propulsion system according to the embodiment of the present invention, a plurality of motors 80 may be installed, and an electric speed control device 70 may be provided for each motor 80. Each electronic speed control device 70 can individually control the speed of each motor 80 according to an instruction from the control unit 50 and thereby stabilize the attitude of the air vehicle 1.

In addition, the first battery 62 of the battery management system 60 can supply power to each electronic speed control device 70. [ Each electronic speed control device 70 may be connected to the second battery 94 via a power line 72 to receive power.

The second battery 94 may provide power to drive the control actuator 92. The control actuator 92 can be operated by receiving an instruction from the air control system 90. The control actuator 92 can actuate various devices necessary for the flight of the air vehicle 1, for example, to actuate the movable wing or to operate the tail wing. The second battery 94 can be charged with electricity from the power management device 40. [

On the other hand, the load on the power line 72 may vary according to the degree of power consumption by the respective electronic speed control devices 70. The load detection line 74 may be connected to the power supply line 72 so that the load detection line 74 detects the load value formed on the power supply line 72 as a second detection value, Or may be provided to the control unit 50.

If the second detection value increases, it can be determined that the power consumption increases. In this case, the control unit 50 can control the engine 10 to increase the engine output. Conversely, when the second detected value decreases, it is determined that the power consumption is decreased and the engine output of the engine 10 is decreased.

In other words. The vertical takeoff and landing aircraft using the hybrid electric propulsion system according to the embodiment of the present invention detects the electric power consumed for operating the first propeller 81 in real time to control the engine output of the engine 10, Can be produced.

Hereinafter, various embodiments of a vertical takeoff and landing aircraft using a hybrid electric propulsion system according to an embodiment of the present invention will be described with reference to FIGS. 4 to 9. FIG.

4 and 5 are views for explaining an example of a vertical takeoff and landing aircraft using a hybrid electric propulsion system according to an embodiment of the present invention. Fig. 4 is a plan view of the air vehicle 1, and Fig. 5 is a side view of the air vehicle 1. Fig.

4 and 5, a fixed blade 4 is provided on both sides of the front of the moving body 2, a motor 80 is provided in a substantially vertical direction in front of and behind the both fixed wings 4, The first propeller 81 may be installed in each of the fixed wings 4 and the engine 10 may be installed in the horizontal direction and the second propeller 82 may be installed in each engine 10.

6 and 7 are views for explaining another example of a vertical takeoff and landing aircraft using a hybrid electric propulsion system according to an embodiment of the present invention. Fig. 6 is a plan view of the air vehicle 1, and Fig. 7 is a side view of the air vehicle 1. Fig.

6 and 7, a fixed blade 4 is provided on both sides of the moving body 2 and a motor 80 is provided in a substantially vertical direction in front of and behind the both fixed wings 4, The engine 10 can be installed horizontally on both the fixed wings 4 and the second propeller 82 can be installed on each engine 10. [ Further, the engine 10 and the second propeller 82 may be further provided on the rear side of the air vehicle 1.

FIGS. 8 and 9 are views for explaining another example of a vertical takeoff and landing aircraft using a hybrid electric propulsion system according to an embodiment of the present invention. Fig. 8 is a plan view of the air vehicle 1, and Fig. 9 is a side view of the air vehicle 1. Fig.

8 and 9, a fixed wing 4 is provided on both sides of the rear side of the moving body 2, a motor 80 is provided in a substantially vertical direction in front of and behind the both fixed wings 4, The first propeller 81 may be installed in each of the fixed wings 4 and the engine 10 may be installed in the horizontal direction and the second propeller 82 may be installed in each engine 10.

The vertical takeoff and landing aircraft using the hybrid electric propulsion system according to the embodiment of the present invention can be applied even if the structure of the air vehicle 1 is various as described with reference to FIG. 4 to FIG.

While the present invention has been described in connection with what is presently considered to be practical exemplary embodiments, it is to be understood that the invention is not limited to the disclosed embodiments, but, on the contrary, It will be possible.

It is to be understood, therefore, that the embodiments described above are to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the following claims and any claims which come within the meaning and range of equivalency of the claims and their equivalents All changes or modifications should be construed as being included within the scope of the present invention.

The vertical takeoff and landing aircraft and the control method thereof using the hybrid electric propulsion system according to the embodiment of the present invention can be used to control flight such as vertical take off and landing flights, transition flights, and cruise flights.

1: Flight 2: Fuselage
4: Fixed wing 10: Engine
12: throttle servo 14: fuel system
20: generator 22: sensor
30: engine control device 40: power management device
50: master control device 60: battery management system
62, 94: first and second batteries 70: electronic speed control device
72: power supply line 74: load detection line
80: motor 81, 82: first and second propellers
90: air control system 92: control actuator
94: second battery 100: pitch control device
102: clutch device

Claims (8)

A flying body (1) having a fixed blade (4) on the body (2);
An engine (10) installed in the air vehicle (1) for burning fuel to produce power;
A generator (20) connected to the engine (10) to produce electric power;
A power management device (40) for managing the power;
A battery management system 60 in which the power provided from the power management device 40 is charged;
A motor 80 installed in the fixed wing 4 and operated by receiving power from the battery management system 60;
A first propeller 81 operated by the motor 80;
A second propeller 82 operating as the engine 10;
A clutch device (102) located between the engine (10) and the second propeller (82) for disconnecting or connecting power transmitted from the engine (10) to the second propeller (82);
A sensor (22) connected to the power management device (40) and provided in the generator (20) for monitoring the generator (20) to generate a first detection value; And
(50) for controlling the operation of the engine (10), the generator (20), the motor (80), the second propeller (82) and the clutch device (102)
The control unit 50 controls the motor 80 to supply power from the generator 20, the power management unit 40 and the battery management system 60 to the motor 80 at the same time when the air vehicle 1 takes off and land vertically. 80,
Based on the first detection value, the controller 50 determines whether current power generation produced by the generator 20 is appropriate,
The engine 10 is fixed to the airplane 1 such that the second propeller 82 generates propulsion force in the second direction,
The motor 80 is fixed to the fixed wing 4 so that the first propeller 81 generates a propelling force in the first direction,
Wherein the first direction and the second direction are directions that are not equal to each other,
The control unit 50 controls the hybrid electric propulsion system 102 to shut off the power connection between the engine 10 and the second propeller 82 when the airplane 1 vertically takes off and land via the clutch device 102. [ Vertical takeoff and landing aircraft.
The method according to claim 1,
The control unit 50 controls the thrust of the second propeller 82 to prevent the flight of the airplane 1 from affecting the flying of the airplane 1 when the airplane 1 takes off and land vertically;
A vertical takeoff and landing aircraft utilizing a hybrid electric propulsion system including a propulsion system.
delete The method according to claim 1,
The control unit 50 increases the thrust of the second propeller 82 when the airplane 1 is cruising or transiting and the surplus electric power generated by the generator 20 is supplied to the battery management system 60 And to charge the battery 62
A vertical takeoff and landing aircraft utilizing a hybrid electric propulsion system including a propulsion system.
A first step of producing power;
A second step of operating the generator (20) with the power to produce electric power;
A third step of distributing power to each configuration of the air vehicle 1 by the power management device 40;
A fourth step in which a part of the electric power is charged in the battery 62 of the battery management system 60; And
And a fifth step of operating the first propeller (81) with the motor (80)
The power from the generator 20, the power management device 40 and the battery 62 is controlled to be supplied to the motor 80 at the same time when the air vehicle 1 vertically rises or falls vertically
Controls the clutch device 102 to block the power connection between the engine 10 and the second propeller 82,
The engine 10 is fixed to the airplane 1 such that the second propeller 82 generates propulsion force in the second direction,
The motor 80 is fixed to the fixed wing 4 so that the first propeller 81 generates a propelling force in the first direction,
Wherein the first direction and the second direction are directions that are not equal to each other,
The clutch device 102 is disposed between the engine 10 and the second propeller 82 and includes a hybrid electric motor 82 that disconnects or connects power transmitted from the engine 10 to the second propeller 82, Control method of vertical takeoff and landing aircraft using propulsion system.
6. The method of claim 5,
The thrust of the second propeller 82 for cruising is controlled so as not to have any effect on the flight of the air vehicle 1 when the air vehicle 1 is vertically taken off and landed;
Wherein the control unit controls the vertical electric takeoff and landing aircraft using the hybrid electric propulsion system.
delete The method according to claim 6,
The surplus electric power generated by the generator 20 is supplied to the battery 62 of the battery management system 60 by increasing the thrust of the second propeller 82 when the air vehicle 1 is cruising or transiting, To be controlled;
Wherein said control means is operable to control said vertical electric take-off aircraft.

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