CN115042982A - Oil-electricity hybrid unmanned aerial vehicle power system and control method thereof - Google Patents
Oil-electricity hybrid unmanned aerial vehicle power system and control method thereof Download PDFInfo
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- CN115042982A CN115042982A CN202210886507.6A CN202210886507A CN115042982A CN 115042982 A CN115042982 A CN 115042982A CN 202210886507 A CN202210886507 A CN 202210886507A CN 115042982 A CN115042982 A CN 115042982A
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- 230000005540 biological transmission Effects 0.000 claims abstract description 26
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- 230000008859 change Effects 0.000 claims description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 3
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 3
- 229910052799 carbon Inorganic materials 0.000 claims description 3
- 229910052744 lithium Inorganic materials 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 7
- 238000010586 diagram Methods 0.000 description 5
- 229910052751 metal Inorganic materials 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
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- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
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- 230000003247 decreasing effect Effects 0.000 description 1
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- 229910052760 oxygen Inorganic materials 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
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- 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
- B64C11/30—Blade pitch-changing mechanisms
- B64C11/44—Blade pitch-changing mechanisms electric
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- B64D27/026—
Abstract
The invention discloses an oil-electricity hybrid unmanned aerial vehicle power system and a control method thereof, wherein the oil-electricity hybrid unmanned aerial vehicle power system comprises a transmission unit, a propeller, a pitch changing unit and a steering engine unit; the transmission unit is used for outputting alternating current after receiving a starting signal sent by the receiver and using the alternating current for driving the propeller; the propeller is driven by the transmission unit to rotate so as to provide energy required by flight; the pitch changing unit is used for changing the pitch of the propeller and controlling the flight state of the unmanned aerial vehicle; the steering engine unit is used for judging the driving direction, driving the pitch changing unit and judging whether the pitch changing unit reaches a preset position or not after receiving a pitch control signal sent by the receiver; the transmission unit comprises a generator and a motor, the motor is connected with the propeller, the generator directly drives the motor by outputting alternating current, and the motor drives the propeller. The invention achieves the purposes of reducing the self weight of the unmanned aerial vehicle and effectively saving the manufacturing cost.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to an oil-electricity hybrid unmanned aerial vehicle power system and a control method thereof.
Background
An Unmanned Aerial Vehicle (UAV) is an unmanned aerial vehicle which can complete various tasks through radio remote control or autonomous control. Compared with a manned airplane, the unmanned aerial vehicle has the advantages of flexible control and operation, small volume, relatively low manufacturing cost, adaptability to various different complex environments, high survival capability and the like, and is widely applied to military fields such as reconnaissance and terrain detection and civil fields such as power inspection, pesticide spraying in farmland, aerial photography, rescue and city monitoring management. Consumer-grade drone application markets, represented by multi-rotor drones, have entered the fast growing period.
At present unmanned aerial vehicle power is mainly with pure electric motor or pure fuel engine more, pure electric unmanned aerial vehicle easily controls, stability is high, but the continuation of the journey mileage is relatively poor, and pure fuel engine can easily solve the continuation of the journey problem, but the engine requires highly to oxygen concentration in the air, and control response and sensitivity can be relatively poor, the pitch of difficult accurate control and coordinated drive rotor, rotational speed etc. can not guarantee unmanned aerial vehicle's stable flight effectively, the high-altitude performance such as high speed and accurate positioning. In order to solve the problems of pure electric unmanned aerial vehicles and pure fuel oil unmanned aerial vehicles, people develop oil-electricity hybrid power unmanned aerial vehicles.
The oil-electricity hybrid unmanned aerial vehicle power system and the control method on the market at present are as follows: the alternating current output by the generator is rectified into direct current through an AC-DC power supply, and then the direct current is supplied to a DC-DC step-down power supply, and then the direct current is supplied to the electronic speed regulator and the motor. The power supply method for rectifying the alternating current into the direct current has the following defects: the first has increased unmanned aerial vehicle's manufacturing cost, and the second has increased unmanned aerial vehicle's weight. And the two above-mentioned shortcomings are especially prominent on heavy load unmanned aerial vehicles.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides the oil-electricity hybrid unmanned aerial vehicle power system and the control method thereof, and solves the technical problems that the weight and the cost of the unmanned aerial vehicle are increased because the conventional unmanned aerial vehicle power system needs to adopt an AC-DC power supply, a DC-DC voltage reduction power supply and an electronic speed regulator, so that the purposes of reducing the self weight of the unmanned aerial vehicle and effectively saving the cost are achieved.
In order to solve the problems, the technical scheme adopted by the invention is as follows:
an oil-electric hybrid unmanned aerial vehicle power system, comprising:
the transmission unit is used for outputting alternating current after receiving a starting signal sent by the receiver and using the alternating current for driving the propeller;
the propeller is driven by the transmission unit to rotate so as to provide energy required by flight;
the pitch changing unit is used for changing the pitch of the propeller and controlling the flight state of the unmanned aerial vehicle;
the steering engine unit is used for judging the driving direction, driving the pitch changing unit and judging whether the pitch changing unit reaches a preset position or not after receiving a pitch control signal sent by the receiver;
the transmission unit comprises a generator and a motor, the motor is connected with the propeller, the generator directly drives the motor by outputting alternating current, and the motor drives the propeller.
As a preferred embodiment of the present invention, a mounting plate is disposed on the top of the motor, a rotating shaft with a bearing is disposed on the mounting plate, and the motor includes an outer rotor, and the rotating shaft is connected with the outer rotor and driven by the outer rotor to rotate;
the propeller comprises a propeller clamp and a paddle, wherein the paddle is connected to the propeller clamp, and the propeller clamp is arranged at the top of the rotating shaft and driven by the rotating shaft to rotate.
As a preferred embodiment of the invention, a bearing disc is arranged at the bottom of the motor, a hollow shaft is arranged in the motor, the pitch changing unit comprises a steering engine rocker arm and a steering engine connecting rod, the steering engine rocker arm is arranged on the bearing disc and is connected with one end of the steering engine connecting rod, and the other end of the steering engine connecting rod penetrates through the hollow shaft, extends to the top of the motor and is connected with the paddle clamp;
the steering engine rocker arm and the steering engine connecting rod are driven by the steering engine unit to move up and down to drive the paddle clamp to move up and down, and the inclination angle of the paddle is adjusted.
As a preferred embodiment of the present invention, the steering engine unit includes:
the circuit board is used for judging the rotation direction after receiving a pitch control signal sent by the receiver and driving according to a judgment result;
the motor is driven by the circuit board to rotate;
the speed reducer is driven by the motor to drive the rocker arm of the steering engine to move up and down;
and the position detector is used for detecting whether the steering engine rocker arm reaches a preset position or not and transmitting a related signal back to the circuit board.
As a preferred embodiment of the present invention, the hybrid unmanned aerial vehicle power system further includes a power supply for supplying power to the steering engine unit.
In a preferred embodiment of the present invention, the power source is a carbon battery or a lithium battery.
A control method of a power system of an oil-electricity hybrid unmanned aerial vehicle comprises the following steps:
the receiver transmits a starting signal to the transmission unit, the transmission unit receives the starting signal, the generator outputs alternating current to directly drive the motor, and the motor drives the propeller to rotate;
the rotating speed of the motor is continuously increased under the driving of the generator, and when the rotating speed reaches a preset rotating speed, the rotating speed of the motor is stabilized at the preset rotating speed;
the receiver transmits a pitch control signal to the steering engine unit, and the steering engine unit judges the driving direction according to the received pitch control signal;
the steering engine unit drives the pitch changing unit according to the judgment result, judges whether the pitch changing unit reaches a preset position or not, and stops driving the pitch changing unit if the pitch changing unit reaches the preset position;
the pitch changing unit is driven by the steering engine unit to change the pitch of the propeller and control the flight state of the unmanned aerial vehicle;
the oil-electricity hybrid unmanned aerial vehicle power system comprises a transmission unit, a propeller, a pitch changing unit and a steering engine unit, wherein the transmission unit comprises a generator and a motor.
In a preferred embodiment of the present invention, the method for changing the pitch of the propeller includes:
after receiving a pitch control signal sent by the receiver, the circuit board judges the rotation direction and drives a motor according to the judgment result;
the motor drives a speed reducer, and the speed reducer drives the pitch changing unit to change the pitch of the propeller;
the position detector detects whether the pitch changing unit reaches a preset position, and when the pitch changing unit reaches the preset position, the position detector transmits a relevant signal back to the circuit board, and the circuit board stops driving the motor after receiving the relevant signal.
Wherein, steering wheel unit includes: circuit board, motor, reduction gear and position detector.
As a preferred embodiment of the present invention, the pitch changing unit, when changing the pitch of the propeller, includes: the steering engine rocker arm moves up and down under the positive and negative rotation of the speed reducer, and the steering engine rocker arm pushes the steering engine connecting rod to move up and down through the up-and-down movement of the steering engine rocker arm, so that the pitch of the propeller is changed;
wherein, the pitch changing unit comprises a steering engine rocker arm and a steering engine connecting rod.
As a preferred embodiment of the present invention, when the steering engine link changes the pitch of the propeller, the steering engine link further includes: the paddle clamp is driven by the steering engine connecting rod to move up and down, the inclination angle of the paddles is changed, and the distance between the paddles is changed;
wherein, the screw propeller comprises a propeller clamp and a blade.
Compared with the prior art, the invention has the beneficial effects that:
(1) according to the unmanned aerial vehicle power system, the alternating current of the generator is directly adopted to supply power to the power system of the unmanned aerial vehicle, the main circuit of the whole power system is completely the alternating current, and an AC-DC power supply and a DC-DC power supply are completely omitted in the middle, so that the self weight of the unmanned aerial vehicle is reduced, and the manufacturing cost of the unmanned aerial vehicle is reduced;
(2) the power system is directly powered by the generator, and an AC-DC power supply and a DC-DC power supply are omitted, so that the response speed of the power system is improved;
(3) the invention adopts the screw propeller with variable pitch to control the flight state of the unmanned aerial vehicle, thereby saving an electronic speed regulator, further lightening the weight of the unmanned aerial vehicle and reducing the manufacturing cost of the unmanned aerial vehicle.
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
Drawings
FIG. 1 is a schematic structural diagram of a hybrid unmanned aerial vehicle power system of an embodiment of the invention;
FIG. 2 is a schematic structural diagram of a blade of the hybrid unmanned aerial vehicle power system of the embodiment of the invention;
FIG. 3 is a schematic overall flow chart of a control method of the hybrid unmanned aerial vehicle power system according to the embodiment of the invention;
FIG. 4 is a wiring diagram of a steering engine unit of the hybrid unmanned aerial vehicle power system according to the embodiment of the invention;
fig. 5-is a step diagram of a control method of the hybrid unmanned aerial vehicle power system according to the embodiment of the invention.
The reference numbers illustrate: 1. a paddle; 2. a paddle clamp; 3. a steering engine connecting rod; 4. mounting a plate; 5. an electric motor; 6. A bearing disk; 7. a hollow shaft; 8. a steering engine rocker arm; 9. a steering engine unit; 10. a receiver; 11. a controller; 12. a power source.
Detailed Description
The invention provides an oil-electricity hybrid unmanned aerial vehicle power system, which comprises: a transmission unit, a propeller, a pitch changing unit and a steering engine unit 9. The transmission unit is used for outputting alternating current after receiving a starting signal sent by the receiver 10 and using the alternating current to drive the propeller; the propeller is driven by the transmission unit to rotate so as to provide energy required by flight; the pitch changing unit is used for changing the pitch of the propeller and controlling the flight state of the unmanned aerial vehicle; the steering engine unit 9 is used for judging the driving direction, driving the pitch changing unit and judging whether the pitch changing unit reaches a preset position after receiving a pitch control signal sent by the receiver 10.
Further, as shown in fig. 1, the transmission unit includes a generator and a motor 5, the motor 5 is connected to the propeller, the generator directly drives the motor 5 by outputting alternating current, and the motor 5 drives the propeller.
Further, as shown in fig. 1, a mounting plate 4 is arranged on the top of the motor 5, a rotating shaft with a bearing is arranged on the mounting plate 4, the motor 5 comprises an outer rotor, and the rotating shaft is connected with the outer rotor and driven by the outer rotor to rotate;
furthermore, as shown in fig. 1, the propeller includes a blade holder 2 and a blade 1, the blade 1 is connected to the blade holder 2, the blade holder 2 is disposed on the top of the rotating shaft and is driven by the rotating shaft to rotate, and the blade 1 is specifically shown in fig. 2.
Further, as shown in fig. 1, a bearing disc 6 is arranged at the bottom of the motor 5, a hollow shaft 7 is arranged inside the motor, the pitch changing unit comprises a steering engine rocker arm 8 and a steering engine connecting rod 3, the steering engine rocker arm 8 is arranged on the bearing disc 6 and is connected with one end of the steering engine connecting rod 3, and the other end of the steering engine connecting rod 3 penetrates through the hollow shaft 7, extends to the top of the motor 5 and is connected with the paddle clamp 2;
furthermore, the steering engine rocker arm 8 and the steering engine connecting rod 3 move up and down under the driving of the steering engine unit to drive the paddle clamp 2 to move up and down, and the inclination angle of the paddle 1 is adjusted.
The lift force of the unmanned aerial vehicle is determined by the rotating speed of the propeller and the inclination angle of the propeller, namely the inclination angle of the propeller blade. The lift increases with increasing rotational speed and blade 1 pitch and decreases with decreasing rotational speed and blade 1 pitch. When the unmanned aerial vehicle flies, the blades 1 rotate for each circle, the inclination angles of the blades 1 are different, and the inclination angle of each blade 1 is also different, so that the unmanned aerial vehicle can pitch forward and pitch backward, pitch left and pitch right, and various flying postures are completed.
Further, the steering engine unit 9 includes a circuit board, a motor, a speed reducer, and a position detector. The circuit board is used for judging the rotation direction after receiving a pitch control signal sent by the receiver 10 and driving according to the judgment result; the motor is driven by the circuit board to rotate; the speed reducer drives the steering engine rocker arm 8 to move up and down under the driving of the motor; the position detector detects whether the steering engine rocker arm 8 reaches a preset position or not, and transmits a relevant signal back to the circuit board,
furthermore, the position detector may be a detection device other than a variable resistor, and when the variable resistor is used as the position detector, when the steering engine rocker arm 8 rotates, the resistance value of the variable resistor changes accordingly, and at this time, the rotating angle of the steering engine rocker arm can be known by detecting the resistance value.
Further, the speed reducer may be a speed reduction device other than a speed reduction gear, and the motor transmits power to the steering engine rocker arm 8 through the speed reduction gear, thereby driving the steering engine rocker arm 8.
Further, the reduction gear is a metal reduction gear. Unmanned aerial vehicle is according to the load demand of difference, and steering wheel unit's reduction gear has the differentiation of plastic and metal, adopts metal reduction gear to have can not collapse the advantage of tooth because of the load is too big.
Further, the motor is a coreless motor, and the moment of inertia of an object is proportional to the mass according to the principles of physics, so that the larger the mass of the object to be rotated, the larger the force required. In order to achieve the purposes of high rotating speed and low power consumption, the steering engine unit can wind a thin copper wire into an extremely thin hollow cylinder to form an extremely light five-pole hollow rotor, and a magnet is arranged in the hollow cylinder, so that the coreless motor is formed.
Further, the oil-electricity hybrid unmanned aerial vehicle power system further comprises a power supply 12 for supplying power to the steering engine unit.
Further, the power source 12 is a carbon battery or a lithium battery.
Further, the oil-electricity hybrid unmanned aerial vehicle power system further comprises a controller 11, and the controller 11 is used for achieving attitude tracking, speed tracking, fixed point tracking, path tracking and trajectory tracking of the unmanned aerial vehicle. The controller 11 may be a controller 11 other than a proportional integral derivative controller.
A control method of a power system of a hybrid unmanned aerial vehicle, as shown in fig. 5, includes the following steps:
step S1: the receiver 10 transmits a starting signal to the transmission unit, after the transmission unit receives the starting signal, the generator outputs alternating current to directly drive the motor 5, and the motor 5 drives the propeller to rotate;
step S2: the rotating speed of the motor 5 is continuously increased under the driving of the generator, and when the rotating speed reaches the preset rotating speed, the rotating speed of the motor 5 is stabilized at the preset rotating speed;
step S3: the receiver 10 transmits a pitch control signal to the steering engine unit, and the steering engine unit 9 judges the driving direction according to the received pitch control signal;
step S4: the steering engine unit 9 drives the pitch changing unit according to the judgment result, judges whether the pitch changing unit reaches a preset position, and stops driving the pitch changing unit if the pitch changing unit reaches the preset position;
step S5: the pitch changing unit changes the pitch of the propeller under the driving of the steering engine unit 9, and controls the flight state of the unmanned aerial vehicle;
the oil-electricity hybrid unmanned aerial vehicle power system comprises a transmission unit, a propeller, a pitch changing unit and a steering engine unit 9, wherein the transmission unit comprises a generator and a motor 5.
Specifically, the overall flowchart of the control method is shown in fig. 3.
In the step S5, the method includes, when changing the pitch of the propeller:
after receiving the pitch control signal sent by the receiver 10, the circuit board judges the rotation direction and drives the motor according to the judgment result;
the motor drives the speed reducer, and the speed reducer drives the pitch changing unit to change the pitch of the propeller;
the position detector detects whether the pitch changing unit reaches a preset position, when the pitch changing unit reaches the preset position, the position detector transmits a relevant signal back to the circuit board, and the circuit board stops driving the motor after receiving the relevant signal;
the steering engine unit 9 includes a circuit board, a motor, a speed reducer, and a position detector, and a wiring diagram of the steering engine unit 9 is shown in fig. 4.
Further, when the pitch changing unit changes the pitch of the propeller, it includes: the steering engine rocker arm 8 moves up and down under the positive and negative rotation of the speed reducer, and the steering engine rocker arm 8 pushes the steering engine connecting rod 3 to move up and down through the up-and-down movement of the steering engine rocker arm 8, so that the pitch of the propeller is changed;
wherein, the pitch changing unit comprises a steering engine rocker arm 8 and a steering engine connecting rod 3.
Furthermore, when the steering engine connecting rod 3 changes the pitch of the propeller, the method further comprises the following steps: the paddle clamp 2 moves up and down under the driving of the steering engine connecting rod 3, changes the inclination angle of the paddles 1 and changes the distance between the paddles 1;
wherein, the screw includes oar clamp 2, paddle 1.
Compared with the prior art, the invention has the beneficial effects that:
(1) according to the unmanned aerial vehicle power system, the alternating current of the generator is directly adopted to supply power to the power system of the unmanned aerial vehicle, the main circuit of the whole power system is completely the alternating current, and an AC-DC power supply and a DC-DC power supply are completely omitted in the middle, so that the self weight of the unmanned aerial vehicle is reduced, and the manufacturing cost of the unmanned aerial vehicle is reduced;
(2) the power system is directly powered by the generator, and an AC-DC power supply and a DC-DC power supply are omitted, so that the response speed of the power system is improved;
(3) the invention adopts the screw propeller with variable pitch to control the flight state of the unmanned aerial vehicle, thereby saving an electronic speed regulator, further lightening the weight of the unmanned aerial vehicle and reducing the manufacturing cost of the unmanned aerial vehicle.
The above embodiments are only preferred embodiments of the present invention, and the protection scope of the present invention is not limited thereby, and any insubstantial changes and substitutions made by those skilled in the art based on the present invention are within the protection scope of the present invention.
Claims (10)
1. The utility model provides a hybrid unmanned aerial vehicle driving system which characterized in that includes:
the transmission unit is used for outputting alternating current after receiving a starting signal sent by the receiver and using the alternating current for driving the propeller;
the propeller is driven by the transmission unit to rotate so as to provide energy required by flight;
the pitch changing unit is used for changing the pitch of the propeller and controlling the flight state of the unmanned aerial vehicle;
the steering engine unit is used for judging the driving direction, driving the pitch changing unit and judging whether the pitch changing unit reaches a preset position or not after receiving a pitch control signal sent by the receiver;
the transmission unit comprises a generator and a motor, the motor is connected with the propeller, the generator directly drives the motor by outputting alternating current, and the motor drives the propeller.
2. The hybrid unmanned aerial vehicle power system of claim 1, wherein a mounting plate is disposed on a top of the motor, a rotating shaft with a bearing is disposed on the mounting plate, and the motor comprises an outer rotor, and the rotating shaft is connected with the outer rotor and driven by the outer rotor to rotate;
the propeller comprises a propeller clamp and a paddle, wherein the paddle is connected to the propeller clamp, and the propeller clamp is arranged at the top of the rotating shaft and driven by the rotating shaft to rotate.
3. The gasoline-electric hybrid unmanned aerial vehicle power system of claim 2, wherein a bearing disc is arranged at the bottom of the electric motor, a hollow shaft is arranged inside the electric motor, the pitch changing unit comprises a steering engine rocker arm and a steering engine connecting rod, the steering engine rocker arm is arranged on the bearing disc and connected with one end of the steering engine connecting rod, and the other end of the steering engine connecting rod penetrates through the hollow shaft, extends to the top of the electric motor and is connected with the paddle clamp;
the steering engine rocker arm and the steering engine connecting rod are driven by the steering engine unit to move up and down to drive the paddle clamp to move up and down, and the inclination angle of the paddle is adjusted.
4. The hybrid unmanned aerial vehicle power system of claim 3, wherein the steering engine unit comprises:
the circuit board is used for judging the rotation direction after receiving a pitch control signal sent by the receiver and driving according to a judgment result;
the motor is driven by the circuit board to rotate;
the speed reducer is driven by the motor to drive the rocker arm of the steering engine to move up and down;
and the position detector is used for detecting whether the steering engine rocker arm reaches a preset position or not and transmitting a related signal back to the circuit board.
5. The hybrid electric unmanned aerial vehicle power system of claim 1, further comprising a power source for powering the steering engine unit.
6. The hybrid unmanned aerial vehicle power system of claim 5, wherein the power source is a carbon battery or a lithium battery.
7. A control method of a power system of an oil-electricity hybrid unmanned aerial vehicle is characterized by comprising the following steps:
the receiver transmits a starting signal to the transmission unit, the transmission unit receives the starting signal, the generator outputs alternating current to directly drive the motor, and the motor drives the propeller to rotate;
the rotating speed of the motor is continuously increased under the driving of the generator, and when the rotating speed reaches a preset rotating speed, the rotating speed of the motor is stabilized at the preset rotating speed;
the receiver transmits a pitch control signal to the steering engine unit, and the steering engine unit judges the driving direction according to the received pitch control signal;
the steering engine unit drives the pitch changing unit according to the judgment result, judges whether the pitch changing unit reaches a preset position or not, and stops driving the pitch changing unit if the pitch changing unit reaches the preset position;
the pitch changing unit is driven by the steering engine unit to change the pitch of the propeller and control the flight state of the unmanned aerial vehicle;
the oil-electricity hybrid unmanned aerial vehicle power system comprises a transmission unit, a propeller, a pitch changing unit and a steering engine unit, wherein the transmission unit comprises a generator and a motor.
8. The control method of the hybrid unmanned aerial vehicle power system according to claim 7, wherein when the pitch of the propeller is changed, the method comprises:
after receiving a pitch control signal sent by the receiver, the circuit board judges the rotation direction and drives a motor according to the judgment result;
the motor drives a speed reducer, and the speed reducer drives the pitch changing unit to change the pitch of the propeller;
the position detector detects whether the pitch changing unit reaches a preset position or not, when the pitch changing unit reaches the preset position, the position detector transmits a relevant signal back to the circuit board, and the circuit board stops driving the motor after receiving the relevant signal;
wherein, steering wheel unit includes: circuit board, motor, reduction gear and position detector.
9. The control method of the hybrid unmanned aerial vehicle power system according to claim 8, wherein when the pitch changing unit changes the pitch of the propeller, the method comprises: the steering engine rocker arm moves up and down under the positive and negative rotation of the speed reducer, and the steering engine rocker arm pushes the steering engine connecting rod to move up and down through the up-and-down movement of the steering engine rocker arm, so that the pitch of the propeller is changed;
wherein, the pitch changing unit comprises a steering engine rocker arm and a steering engine connecting rod.
10. The control method of the oil-electric hybrid unmanned aerial vehicle power system according to claim 7, wherein when the steering engine connecting rod changes the pitch of the propeller, the method further comprises: the paddle clamp is driven by the steering engine connecting rod to move up and down, the inclination angle of the paddles is changed, and the distance between the paddles is changed;
wherein, the screw propeller comprises a propeller clamp and a blade.
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