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WO2019190263A1 - Drone hybride amélioré - Google Patents

Drone hybride amélioré Download PDF

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Publication number
WO2019190263A1
WO2019190263A1 PCT/KR2019/003702 KR2019003702W WO2019190263A1 WO 2019190263 A1 WO2019190263 A1 WO 2019190263A1 KR 2019003702 W KR2019003702 W KR 2019003702W WO 2019190263 A1 WO2019190263 A1 WO 2019190263A1
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WO
WIPO (PCT)
Prior art keywords
motor
propeller
engine
main
throttle
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/KR2019/003702
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English (en)
Korean (ko)
Inventor
이호형
이완형
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Individual
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Individual
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Filing date
Publication date
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Publication of WO2019190263A1 publication Critical patent/WO2019190263A1/fr
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Ceased legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
    • B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/16—Blades
    • B64C11/20—Constructional features
    • B64C11/28—Collapsible or foldable blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/12—Rotor drives
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B64C27/30—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with provision for reducing drag of inoperative rotor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/04—Aircraft characterised by the type or position of power plants of piston type
    • B64D27/08—Aircraft characterised by the type or position of power plants of piston type within, or attached to, fuselages
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/25—Fixed-wing aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/10—Wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
    • B64U30/296—Rotors with variable spatial positions relative to the UAV body
    • B64U30/297—Tilting rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/11—Propulsion using internal combustion piston engines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/13—Propulsion using external fans or propellers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/19—Propulsion using electrically powered motors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/30—Supply or distribution of electrical power
    • B64U50/31—Supply or distribution of electrical power generated by photovoltaics
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/30—Supply or distribution of electrical power
    • B64U50/34—In-flight charging
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U70/00—Launching, take-off or landing arrangements
    • B64U70/80—Vertical take-off or landing, e.g. using rockets
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention is a combination of the advantages of the engine and the motor, the main power source during the flight to use the engine and take-off and landing using the motor, the combination of the number and installation direction and the driving method of the propeller connected to the engine and the motor is stable It is an improved hybrid drone that can take off, land, hover and fly.
  • the thrust weight ratio of a takeoff and landing plane theoretically must exceed at least '1.0' to be in the air. That is, there must be greater thrust (output conversion) than the weight of the gas.
  • an airplane such as an airliner with a long runway without vertical takeoff and landing function, for example, a thrust weight ratio of 0.15 to 0.35 enables efficient operation with small power.
  • the present inventors use only the advantages of the engine and the motor in combination with the main power source during the flight using the engine and the motor as an auxiliary power source during takeoff and landing, by combining the number and installation direction and driving method of the propeller connected to the engine and the motor
  • the company has developed an improved hybrid drone that can reliably take off, land, hover and fly.
  • the present invention is proposed to solve the conventional problems as described above.
  • the purpose is to combine the advantages of the engine and the motor only, the main power source in the flight when using the engine and the motor as an auxiliary power source during takeoff and landing, but the combination of the number and installation direction and driving method of the propeller connected to the engine and the motor is stable
  • the company aims to provide an improved hybrid drone that can take off, land, hover and fly.
  • the present invention to solve the above technical problem is installed in the main shaft direction 100;
  • a main blade 200 coupled to the fuselage 100 at a right angle to the auxiliary wing 210 and the flap 230;
  • Two motor tube frames 800 respectively installed on the left and right sides of the main blade 200 in the main shaft direction;
  • a vertical stabilization plate 400 coupled to the rear upper portion of the motor tube frame 800 and having a rudder 410 installed therein;
  • the main propeller 700 which is driven by the engine is installed at the rear end of the body 100,
  • the front and rear ends of the motor tube frame 800 provides a hybrid hybrid drone, characterized in that the front propeller 500 and the rear propeller 600 are respectively installed.
  • the main power source for the flight by combining only the advantages of the engine and motor using the engine and the motor as an auxiliary power source during take-off and landing, by combining the number and installation direction and the driving method of the propeller connected to the engine and the motor It offers an improved hybrid drone that can reliably take off, land, hover and fly.
  • 1 is a plan view of an improved hybrid drone of the present invention.
  • FIG. 2 is a side view of an improved hybrid drone of the present invention.
  • Figure 3 shows the tilting function of the propeller in the improved hybrid drone of the present invention.
  • Figure 6 shows the operation concept in the hovering mode in the hovering mode (yawing) in the improved hybrid drone of the present invention from the left side, front and rear.
  • FIG. 7 is a plan view of FIG. 6.
  • FIG. 8 illustrates the operation concept of the engine release mode when the engine is stopped during flight in the improved hybrid drone of the present invention.
  • FIG. 10 conceptually illustrates signal path and program mixing of a motherboard, receiver and transmitter in an improved hybrid drone of the present invention.
  • the present invention is a fuselage 100 is installed in the main axis direction;
  • a main blade 200 coupled to the fuselage 100 at a right angle to the auxiliary wing 210 and the flap 230;
  • Two motor tube frames 800 respectively installed on the left and right sides of the main blade 200 in the main shaft direction;
  • a vertical stabilization plate 400 coupled to the rear upper portion of the motor tube frame 800 and having a rudder 410 installed therein;
  • the main propeller 700 which is driven by the engine is installed at the rear end of the body 100,
  • the front and rear ends of the motor tube frame 800 provides a hybrid hybrid drone, characterized in that the front propeller 500 and the rear propeller 600 are respectively installed.
  • FIG. 1 is a plan view of an improved hybrid drone of the present invention
  • Figure 2 is a side view of an improved hybrid drone of the present invention.
  • the symbols 'RF', 'LF', 'RR', and 'LR' in the drawing mean 'front right', 'left front', 'right rear' and 'left rear' on the plane, respectively.
  • 1 is a line passing through the fuselage from left to right in FIG. 1
  • the 'right axis' is a line perpendicular to the main axis in FIG.
  • Improved hybrid drone of the present invention is a fuselage 100 is installed in the main axis direction;
  • a main blade 200 coupled to the fuselage 100 at a right angle to the auxiliary wing 210 and the flap 230;
  • Two motor tube frames 800 respectively installed on the left and right sides of the main blade 200 in the main shaft direction;
  • a vertical stabilization plate 400 coupled to the rear upper portion of the motor tube frame 800 and having a rudder 410 installed therein;
  • the main propeller 700 which is driven by the engine is installed at the rear end of the body 100,
  • the front and rear ends of the motor tube frame 800 are respectively provided with a front propeller 500 and a rear propeller 600 driven by a motor.
  • the front center of the motor tube frame 800 includes a pair of motors having a higher output than the rear end in consideration of the center of gravity of the whole body in front of the engine according to the position of the engine, and the rear end has a lower output than the front end. It consists of a pair of motors to drive.
  • Figure 3 shows the tilting function of the propeller in the improved hybrid drone of the present invention.
  • the main propeller 700 rotates between the rear and the lower side around the engine tilt axis
  • the front propeller 500 rotates the upper and front sides around the motor tilt axis
  • the rear propeller 600 is characterized in that the rotational movement between the rear and the lower side around the motor tilt axis (tilt axis).
  • It has a structure having two rotation shafts to rotate between the rear and downward about the motor tilting axis, and rotate the motor tube frame 800 in the left and right directions about the axis.
  • the main propeller 700 is fixed in a state that the wings are opened in a push type (push type),
  • the front propeller 500 is a full type (pull type) when the wing is spread out,
  • the rear propeller 600 is a push type (push type) is characterized in that the wings spread when rotated.
  • the front propeller 500 and the rear propeller 600 has a folding function (folding) is automatically unfolded when a lift occurs in the wing using a hinge or a spring and automatically folded when the lift is reduced.
  • folding function can be given by controlling the driving means mechanically or electrically.
  • the present invention consists of an engine which is a main power source located in the center and two pairs of motors and propellers different in output from the front and rear.
  • the center of gravity of the gas is located on the main blade 200 in FIG. 1, it is preferable to use the motor having a higher output than the motor at the rear when taking off and landing.
  • the present invention is a mixed structure of the engine plane and multicopter, the main power source engine is equipped with a push propeller (push propeller) and the engine mount is mounted in a hinged form with the bracket of the fuselage to enable tilting downward and backward It is a structure that can be forcibly removed.
  • the motor and the propeller are composed of a high output motor and propeller parts on the front and a low output motor and propeller parts on the rear,
  • the front group is a pull type propeller and is composed of a large diameter propeller in combination with a high output motor compared to the rear part.
  • the rear group is a push type propeller and is composed of a small diameter propeller in combination with a motor having a lower output than the front part.
  • the front propeller is tilted forward and upward and the rear propeller is tilted downward and backward and left and right, respectively, and it is preferable to apply a folding propeller to reduce air resistance.
  • Motor A in the drawing.
  • Motor B and the engine are power sources for driving the front propeller 500, the rear propeller 600 and the main propeller 700, respectively.
  • propeller shafts are aligned with engine-down, front-up and rear-down, all generating lift downwards.
  • the aircraft will slowly fly horizontally, at which time the output power of the motor will be lowered according to the inclination of the propeller shaft. Rotation will cause the motor to stop and start the engine.
  • the present invention is in the hovering mode including the rising or falling of the gas
  • the main propeller 700 is located downward to generate a lift downwards
  • the front propeller 500 is located upwards and generates a lift downwards
  • the rear propeller 600 is positioned downward to generate a lift downward.
  • the throttle of the motor is mixed with the throttle of the engine through the reserve channel and the mixing volume thereof is adjusted to be adjusted to the downward angle of the flap so that the flap is pulled down when hovering, and the throttle of the main engine and the motor is synchronized 100%.
  • this mode enables maximum output.
  • the main propeller 700 is inclined backward from the bottom to generate a lift to be inclined downward from the rear,
  • the front propeller 500 is inclined forward from the top to generate a lift inclined downward from the rear,
  • the rear propeller 600 is positioned to be inclined rearward from the bottom to generate a lift force inclined downward from the rear.
  • the throttle of the motor is mixed with the throttle of the engine through the reserve channel, and the mixing volume thereof is adjusted to be adjusted to the downward angle of the flap, so that the throttle of the main engine and the motor is reduced to a part of the flap (eg, 50%) during low-speed flight.
  • This mode is for mixing only part of the tune (eg 50%).
  • the throttle of the motor and the engine are mixed through the spare channel, and the inclination angle and flap angle of the main propeller 700, the front propeller 500, the rear propeller 600, etc. are automatically controlled.
  • One gas can be controlled.
  • the main propeller 700 is located rear to generate a lift in the rear
  • the front propeller 500 and the rear propeller 600 is characterized in that it does not drive.
  • the throttle of the motor is mixed with the throttle of the main engine through the preliminary channel, and the mixing volume of the motor is mixed to be adjusted to the downward angle of the flap.
  • the tuning rate is 0%, and the mode is turned off.
  • front propeller 500 and the rear propeller 600 may be located in the front and rear, respectively, and may not be driven in a folded state.
  • Figure 6 shows the operation concept in the hovering mode in the hovering mode in the improved hybrid drone of the present invention from the left side, front and rear,
  • FIG. 7 is a plan view of FIG. 6.
  • the rear propeller 600 is inclined to the left or right from the lower side is characterized in that the lifting force is inclined to the left or right.
  • the rear propeller 600 is characterized in that the lifting force is generated to be inclined to the left or right by rotating the motor tube frame 800 inclined to the left or right from the bottom.
  • Torque is the force (physical action) for rotating the propellers of the engine and motor
  • Anti torque refers to the force that resists counter torque (the magnitude and direction of torque and anti torque must be the same for straight flight without gas rotation).
  • FIG. 8 illustrates the operation concept of the engine release mode when the engine is stopped during flight in the improved hybrid drone of the present invention.
  • the motor is driven so that the front propeller 500 is located forward to generate a lift in the rear, the rear propeller 600 is located rear to generate lift in the rear,
  • the main propeller 700 may be separated and separated from the engine.
  • Configuration based on fixed wing such as fuselage, main wing, horizontal, vertical tail wing (stable plate), landing gear, main engine propellant.
  • the motor consists of a pair of high-power motor parts in the front left and right and a pair of low-power motor parts in the rear left and right
  • -A pair of motor parts on the rear part is linked with the rudder of the vertical tail (stable plate) when starting yawing, and the function of offsetting the propeller's anti-torque according to the change of direction and vertical rotation of the main engine by tilting left and right in the vertical direction.
  • motor tube frame frame which is the frame of the tail blades, to protrude toward the front of the main blade, and serves as the support shaft of 12 motor mount.
  • motor tube frame frame which is the frame of the tail wing, to protrude toward the rear of the tail wing (stable plate), and acts as a rotating shaft support 34 motor mount.
  • the auxiliary blade of the vertical stabilization plate 400 and in conjunction with the rudder rudder 410 also tilts the motor tube frame 800 in the axis.
  • the engine + propeller is mounted on the fuselage and the engine mount is mounted on the rotating shaft to rotate (tilting) backwards and downwards.
  • the tilt of the engine mount is mixed with the flap so that the flap moves backwards in the normal state, and the motor shaft moves in the downward direction when the flap is operated 100% (about 45 ⁇ ).
  • the engine and rear motor parts have a downward reverse pitch propeller (PUSHtype).
  • Front motor part is forward full pitch propeller (pull type), flap is fully lowered (100% of total angle)
  • Throttle Up-Down Hovering up and down operation with engine + motor output control (100% tuning of engine and motor throttle)
  • Elevator up-down front tilt of the fuselage posture, tilt back (forward and backward movement in hovering state), control the motor output of the front and rear motor parts to be in opposition, engine not affected. Elevator up-down linkage of horizontal tail wing (horizontal stabilization plate)
  • Aileron Left-Right Tilt the left and right of the fuselage posture. Control the motor output of the left and right motor parts to be the same as before and after. The engine is not affected. Left and right movement interlocking of main wing auxiliary wing (Aileron).
  • Rudder Left-Right The fuselage turns left and right of the nose with respect to the vertical axis. (The axis of motor B is in the vertical downward direction and the left and right tilting of the motor tube frame and the auxiliary wing of the vertical tail (stable plate) interlock)
  • the engine and rear motor parts In hovering mode, the engine and rear motor parts (reverse pitch propellers) partially tilt from downward to backward.
  • the front motor part Pull pitch propeller
  • the front motor part is partly tilted upwards and forwards, mixed with the flaps and interlocked during the flap operation (20-50% of the total down angle) to tilt the engine and the motor shaft. Flap partially lowered (20-50% of total lower angle)
  • Throttle Up-Down Hovering Up / Down Operation with Engine + Motor Output Control
  • Elevator up-down Tilt to the front and rear of the fuselage. (Forward and backward movements in hovering state). Control the motor output of the front and rear motor parts to be opposite. The engine has no effect. Up-down linkage of the elevator of the horizontal tail wing (horizontal stabilizer plate).
  • Aileron Left-Right tilting the fuselage left and right. If you change the direction of movement (Bank turn). Control the motor output of the left and right motor parts to be the same as before and after. The engine has no effect. Left and right movement interlocking of main wing auxiliary wing (Aileron).
  • Rudder Left-Right The fuselage yawing the nose to the left and right of the vertical axis. When the axis of motor B is vertical It is partly tilted backward (linked with flap lowering angle) and tilted in the left and right direction around the motor tube frame and interlocked with the auxiliary wing of the vertical tail (stable plate).
  • the rotation axis of the motor linked with the flap of the main wing is tilted according to the operating angle of the flap.
  • the engine part is fully tilted from downward to backward, generating a reverse pitch propeller (push type) thrust.
  • Throttle Up-Down Program mixing of flap and motor throttle. When flap angle is 0 °, motor power is cut off, propeller rotation stops and folding state is maintained. Throttle up-down controls the aircraft's flight speed by adjusting the engine speed on a horizontal axis.
  • Elevator up-down Tilt front, tilt back.
  • the motor of the front motor part and the rear motor part stops rotating, and there is no control function in the folding state. Control the up and down of the aircraft with the elevator of the horizontal tail wing (horizontal stabilizer).
  • Aileron Left-Right tilting the fuselage left and right. Left or right direction movement in bank turn or hover state. Motor of left and right motor parts stops rotating and there is no control function in folding state. Left and right movement of the main wing auxiliary wing (Aileron) to control the aircraft's left and right bank angle.
  • Rudder Left-Right The fuselage turns left and right of the nose with respect to the vertical axis.
  • Motor B frame of motor B Left and right tilting and auxiliary wing linkage of vertical tail (stabilization plate) The motor's axis of rotation is tilted, but the motor is stopped by flap and program mixing, so there is no influence on the control.
  • the engine parts are separated by one step and the motor is driven horizontally to generate thrust and fly.
  • Throttle Up-Down Program mixing of the flap and motor throttle shuts off, enabling motor power even at zero flap angles. Propulsion due to propeller rotation. Throttle up-down controls the aircraft's flight speed by adjusting the engine speed in the horizontal axis.
  • Elevator up-down Tilt front, tilt back.
  • the motor of the front motor part and the rear motor part maintains the opposite RPM, but the flight attitude is insignificant. Control the up and down of the aircraft with the elevator of the horizontal tail wing (horizontal stabilizer).
  • Aileron Left-Right tilting the fuselage left and right. Left or right direction movement in bank turn or hover state. It is effective for yawing phenomenon and bank turn operation because the rotational speed RPM of the motor of the left and right motor parts reacts in opposition. Left and right movement of the main wing auxiliary wing (Aileron) to control the aircraft's left and right bank angle.
  • Rudder Left-Right The fuselage turns left and right of the nose with respect to the vertical axis. In the vertical axis of the motor B, the left and right tilting is tilted in the horizontal direction backward and tilted left and right about the motor tube frame, but the power of the motor is cut off and the same axis as the motor axis (motor tube frame). Does not affect flight posture. Controlled only by the auxiliary wing (rudder) of the vertical tail wing (stable plate).
  • FIG. 10 conceptually illustrates signal path and program mixing of a motherboard, receiver and transmitter in an improved hybrid drone of the present invention.
  • FIG. 10 The configuration of FIG. 10 is as follows.
  • Receiver Receives radio signals from the controller and transmits them to the servo motor and transmission.
  • a processing device that automatically controls the posture of the improved hybrid drone according to the present invention by processing a combination of data similar to a receiver or a three-axis gyro, an acceleration sensor, a GPS, and a controller signal.
  • the gearbox In response to a signal from the receiver or main board, the gearbox controls the rotational speed of the motor and the servomotor operates.
  • Servo motor receiving the signal from receiver or main board executes operation such as throttle cable and tilting.
  • the mixing of the program is as follows.
  • Elevator (Elevator) ⁇ Receiver (Elevator) ⁇ Horizontal Wing (Elevator) Servo ⁇ Receiver (Elevator) ⁇ Main Board Elevator (Elevator) Port ⁇ Motor Transmission
  • Controller flap Receiver flap ⁇ Main flap Flap Servo controller (Flap + Spare channel-1) Program mixing ⁇ Receiver spare channel-1 ⁇ Motherboard throttle * Throttle port ⁇ Motor transmission
  • the present invention is equipped with a gas (aileron, elevator, rudder, flap auxiliary wing) equipped with a push-type engine + propeller set mounted on the rear of the fuselage to enable tilting downward and backward;
  • the frame is fixed, and the front end of the frame protruding to the main wing is equipped with the front motor A part of the multicopter on the left and right,
  • the frame extending to the rear of the main wing is connected to the tail wing (vertical and horizontal stabilization plate) and extends to the tail wing rear, and the protruding end has a rear motor B part mounted on the left and right sides.
  • the motor A part mounted at the front has higher output than the motor B part at the rear, and is mounted to tilt forward to upward by a combination of large forward pitch propellers.
  • the motor B part at the rear is tilted downward and backward by a combination of low power and small reverse pitch propeller type compared to the motor A part at the front.
  • the nose When hovering, the nose can be tilted left to right in a downward state to rotate horizontally horizontally.
  • the yaw maneuver is not controlled. During flight, it is controlled by the wing of the vertical tail wing (vertical stabilizer). It has a structure in which the rear motor B part is controlled by tilting from left to right in the vertical downward state in the stop flight or the low speed flight mode.
  • the throttle of the remote controller is linked with the throttle of the receiver, the program throttle of the remote controller and the program mixing of the spare channel-1 of the remote controller, and the spare channel-1 of the remote controller and the receiver are connected to the throttle port of the motherboard,
  • the flap of the controller is the flap of the receiver and the flap of the controller is a program mixing that controls the throttle of the controller and the mixing volume of the spare channel-1.
  • the flap angle is 0 even when the throttle of the controller is controlled, so that the mixing volume of the throttle and the spare channel-1 is "0" so that the program is mixed in two times so as not to respond to the controller throttle.
  • Spare channel-2 is program mixed to function as a switch to switch the controller throttle and spare channel-1 on and off.
  • the spare channel-2 of the remote controller is connected to the receiver spare channel-2, and the receiver spare channel-2 is connected to the engine grip servomotor mounted on the engine mount hinge bracket.
  • the engine can be forcibly disengaged by releasing the grip of the engine mount rotation shaft of the main engine.
  • the throttle of the motor releases the program mixing with the flap and interlocks with the engine throttle. Therefore, the transmission of the motor is activated and the rotating shaft of the motor is in the flight mode. It is equipped with a function to return to the flight driven by the motor, which is activated while maintaining the shaft to obtain the propulsion force,
  • the takeoff weight is an indication of the airplane's ability to fly, and during vertical takeoffs, it typically runs 70-90% of its power, consuming a lot of fuel or batteries.
  • the present invention operates all the power, increases the takeoff weight and increases the output in the vertical takeoff, landing, and stop mode, and the power of the motor is cut off when switching to the flight mode through the takeoff or stop flight and low speed mode. It relies solely on the thrust of the engine. At this time, the output is driven to the minimum of the engine, which increases fuel efficiency and allows for a long flight depending on the capacity of the fuel tank.
  • the engine or motor also increases as the gas increases, so that a solar module may be installed on the wing or the fuselage, or an auxiliary generator may be installed in the engine to charge the battery to secure power of a motor required for takeoff, landing, or stop flight.
  • a solar module may be installed on the wing or the fuselage, or an auxiliary generator may be installed in the engine to charge the battery to secure power of a motor required for takeoff, landing, or stop flight.
  • stops or slow flights may be made as necessary from time to time.
  • the advantage of the present invention is to improve the takeoff weight of vertical takeoffs and to extend the flight time extremely.
  • the engine mount shaft and engine mount are separated by one step to force the main engine off, and the mixing of the motor and flap is released, and the engine throttle and the transmission of the motor are synchronized so that the motor propeller shaft is in the horizontal state. It will have the ability to fly and return with the power of the motor.
  • the lift of the engine + motor and the wing is added to be efficient.
  • the present invention is a combination of the advantages of the engine and the motor, the main power source during the flight to use the engine and take-off and landing using the motor, the combination of the number and installation direction and the driving method of the propeller connected to the engine and the motor is stable It is an improved hybrid drone that can take off, land, hover and fly.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Remote Sensing (AREA)
  • Toys (AREA)

Abstract

La présente invention concerne un drone hybride amélioré, dans lequel un moteur thermique est utilisé comme source d'alimentation principale tout en volant et un moteur est utilisé en tant que source d'énergie auxiliaire tout en prenant en charge ou en train d'atterrir, en combinant uniquement les avantages du moteur thermique et du moteur. Le drone hybride amélioré peut effectuer un décollage ou un atterrissage stable, un vol stationnaire et un vol, en utilisant une combinaison d'un nombre, d'une direction d'installation et d'un schéma d'entraînement d'hélices reliées au moteur thermique et au moteur.
PCT/KR2019/003702 2018-03-29 2019-03-29 Drone hybride amélioré Ceased WO2019190263A1 (fr)

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KR1020180036411A KR101895366B1 (ko) 2018-03-29 2018-03-29 개량형 하이브리드 드론
KR10-2018-0036411 2018-03-29

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CN110963050A (zh) * 2019-10-30 2020-04-07 河北淳博航空科技有限公司 一种用于无人机的多能量混合推进动力系统
WO2021234657A1 (fr) 2020-05-22 2021-11-25 Nelson Mandela University Aéronef à décollage et atterrissage verticaux, procédés et systèmes de commande d'un aéronef à décollage et atterrissage verticaux
US11420736B1 (en) * 2021-10-30 2022-08-23 Beta Air, Llc System and method for vibration monitoring of an electric aircraft
IT202100018170A1 (it) * 2021-07-09 2023-01-09 Gen Electric Aeroplano elettrico ibrido con controllo di stabilizzazione giroscopico
EP4116191A1 (fr) * 2021-07-09 2023-01-11 General Electric Company Aéronef électrique hybride avec contrôle de la stabilisation gyroscopique
WO2024252755A1 (fr) * 2023-06-08 2024-12-12 国立研究開発法人宇宙航空研究開発機構 Aéronef à décollage et atterrissage verticaux
WO2024263593A3 (fr) * 2023-06-19 2025-04-10 Method Aeronautics, LLC Avion à décollage et atterrissage vertical
WO2025106127A3 (fr) * 2023-06-19 2025-07-24 Method Aeronautics, LLC Aéronef à décollage et atterrissage verticaux

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CN110155317A (zh) * 2019-05-13 2019-08-23 中国人民解放军国防科技大学 一种油电混合垂直起降固定翼飞机
CN110182361B (zh) * 2019-05-28 2022-09-27 湖北电鹰科技有限公司 一种可倾转的垂直起降固定翼无人机
AU2020332673B2 (en) * 2019-08-16 2024-04-04 Textron Systems Corporation Separated lift-thrust VTOL aircraft with articulated rotors
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CN110963050A (zh) * 2019-10-30 2020-04-07 河北淳博航空科技有限公司 一种用于无人机的多能量混合推进动力系统
CN110963050B (zh) * 2019-10-30 2021-07-20 河北淳博航空科技有限公司 一种用于无人机的多能量混合推进动力系统
WO2021234657A1 (fr) 2020-05-22 2021-11-25 Nelson Mandela University Aéronef à décollage et atterrissage verticaux, procédés et systèmes de commande d'un aéronef à décollage et atterrissage verticaux
IT202100018170A1 (it) * 2021-07-09 2023-01-09 Gen Electric Aeroplano elettrico ibrido con controllo di stabilizzazione giroscopico
EP4116191A1 (fr) * 2021-07-09 2023-01-11 General Electric Company Aéronef électrique hybride avec contrôle de la stabilisation gyroscopique
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US11420736B1 (en) * 2021-10-30 2022-08-23 Beta Air, Llc System and method for vibration monitoring of an electric aircraft
WO2024252755A1 (fr) * 2023-06-08 2024-12-12 国立研究開発法人宇宙航空研究開発機構 Aéronef à décollage et atterrissage verticaux
WO2024263593A3 (fr) * 2023-06-19 2025-04-10 Method Aeronautics, LLC Avion à décollage et atterrissage vertical
WO2025106127A3 (fr) * 2023-06-19 2025-07-24 Method Aeronautics, LLC Aéronef à décollage et atterrissage verticaux

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