Hybrid unmanned aerial vehicle power system

Abstract

The application discloses an oil-electric hybrid unmanned aerial vehicle power system and relates to the technical field of unmanned aerial vehicles and aircrafts. The application is characterized by the coaxial direct-drive direct-connection cooperation design of the propeller, the engine and the direct-current permanent magnet motor, simple structure, reliability, durability and high power-to-weight ratio. The oil-electric hybrid system is formed by the cooperation of the oil engine and the permanent magnet direct-current motor. The permanent magnet direct-current motor can start the engine and convert the excess power into electric energy to charge the storage battery. The torque of the engine can be changed by the direct-current bidirectional electric governor, so the speed of the propeller can be accurately controlled, and a three-in-one machine is formed. Different displacement engines can be matched with corresponding power direct-current permanent magnet motors. Different power ratios can be used for different models of unmanned aerial vehicles and multi-rotor aircrafts. Different accurate control and speed regulation ratios can be combined by the cooperation of different power engines and direct-current permanent magnet motors.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of unmanned aerial vehicles, in particular to a hybrid unmanned aerial vehicle power system. BACKGROUND

[0002] Unmanned aerial vehicles and their supporting communication stations, take-off (launch) and recovery devices, as well as unmanned aerial vehicle transportation, storage and detection devices, etc.

[0003] In the application process of the existing unmanned aerial vehicle power system, the applicant found that the following problems still exist:

[0004] 1. The starting mode of the unmanned aerial vehicle is too single, cannot form a composite efficient starting application, and lacks corresponding mixed adjustment stable starting settings; the starter is idle after starting the engine, increasing the weight of the unmanned aerial vehicle, and cannot achieve one machine with multiple functions

[0005] 2. Lack of charge return circuit design, unable to realize redundant power recycling during the starting process of the unmanned aerial vehicle, reverse battery charging, resulting in reduced endurance application performance;

[0006] 3. Cannot more accurately adjust the precise rotation speed required between each propeller when using multiple engines in parallel;

[0007] Therefore, a new solution is needed to solve the above problems. SUMMARY

[0008] The purpose of the present application is to provide a hybrid unmanned aerial vehicle power system to solve the problems raised in the background art with a super simple structure and ingenious design.

[0009] To achieve the above purpose, the present application provides the following technical scheme: a hybrid unmanned aerial vehicle power system, comprising a remote control receiver and a flight control, further comprising an unmanned aerial vehicle frame, the top end of the unmanned aerial vehicle frame is fixedly connected with a positioning cross beam, the bottom end of the positioning cross beam is fixedly connected with a DC bidirectional electric governor and an oil tank, the DC bidirectional electric governor is located at one end of the oil tank, the top end of the unmanned aerial vehicle frame is fixedly connected with a storage battery, the two sides of the positioning cross beam are respectively fixedly connected with a first hybrid propeller starting module and a second hybrid propeller starting module, and the top end of the positioning cross beam is fixedly connected with a linkage control module.

[0010] Preferably, the first hybrid propeller starting module comprises a first DC brush motor, a first linkage shaft, a first engine, a first throttle valve and a first propeller, the bottom end of one side of the positioning crossbeam is fixedly connected with the first DC brush motor, the top end of the side of the positioning crossbeam close to the first DC brush motor is fixedly connected with the first engine, the output end of the first DC brush motor is fixedly connected with the first linkage shaft, the inner side of the first engine is connected with the first linkage shaft, the top end of the first linkage shaft is fixedly connected with the first propeller, and one side of the first engine is fixedly connected with the first throttle valve and the rudder.

[0011] Preferably, the second hybrid propeller starting module comprises a second DC brush motor, a second linkage shaft, a second engine, a second throttle valve and a second propeller, the bottom end of the side of the positioning crossbeam away from the first DC brush motor is fixedly connected with the second DC brush motor, the top end of the side of the positioning crossbeam close to the second DC brush motor is fixedly connected with the second engine, the output end of the second DC brush motor is fixedly connected with the second linkage shaft, the inner side of the second engine is connected with the second linkage shaft, the top end of the second linkage shaft is fixedly connected with the second propeller, and one side of the second engine is fixedly connected with the second throttle valve and the rudder.

[0012] Preferably, the linkage control module comprises a rudder, a push derivation arm and a third linkage rod, the third linkage rod is connected between the first throttle valve and the second throttle valve, the top end of the positioning crossbeam is fixedly connected with the rudder, the rudder and the second throttle valve are connected through the push derivation arm, and the linkage control module is used for one-key control of the output power of the first engine and the output power of the second engine.

[0013] Preferably, the rudder is electrically connected with at least one of a remote control receiver or a flight control, the first DC brush motor and the DC bidirectional electric governor are electrically connected through a back-irrigation diode, the second DC brush motor and the DC bidirectional electric governor are electrically connected through a back-irrigation diode, the oil tank is connected with the first engine through an oil pipe, and the oil tank is connected with the second engine through an oil pipe.

[0014] Preferably, the two sides of the unmanned aerial vehicle frame are respectively fixedly connected with a first controllable boost charging module and a storage battery, the storage battery and the first DC brush motor are connected through the first controllable boost charging module, and the storage battery and the second DC brush motor are connected through a second controllable boost charging module.

[0015] Preferably, the DC bidirectional electric governor is connected through electric communication with the remote control receiver, the flight control, the first throttle valve rudder, and the second throttle valve rudder.

[0016] Preferably, the direct current bidirectional electric governor inside is equipped with two direct current brush electric governors, and a one-key starting switch is further connected between the battery and the first and second direct current brush motors.

[0017] Compared with the prior art, the application has the following advantages:

[0018] 1. The application provides two different starting modes, one of which is to directly guide the battery to the brush permanent magnet motor for starting, and the other is to start the direct current brush electric governor by sending a control command from a remote controller, thereby achieving better application effect and stable remote control starting mode.

[0019] 2. The application adopts coaxial direct drive and direct connection of the propeller, the engine and the direct current permanent magnet motor, and has simple structure, high reliability, durability and high power-to-weight ratio, and realizes one machine with three functions. The first direct current permanent magnet motor is used as a starter, the excess power of the engine is used as a generator, and the third command from the flight control is sent to the direct current brush electric governor to control the output power of the direct current permanent magnet motor, so as to accurately control the torque mixed into the oil-driven engine and realize accurate adjustable hybrid, thereby forming one machine with three functions. Different displacement engines can be matched with corresponding power direct current permanent magnet motors, different power ratios can be used for different models of unmanned aerial vehicles, and different speed control ranges can be built by matching different power engines and direct current permanent magnet motors.

[0020] 3. The application can effectively solve the running conflicts of hybrid control, starting, charging and time, realize some useful energy conversion, and form different starting and charging synchronous applications, so as to realize the recovery and charging of excess power and further save power energy by using the charging module to dampen the propeller. BRIEF DESCRIPTION OF DRAWINGS

[0021] In order to more clearly illustrate the technical solutions of the embodiments of the application, the following will briefly introduce the drawings needed to be used in the embodiment description. Obviously, the drawings in the following description are only some embodiments of the application, and other drawings can be obtained by those skilled in the art without creative labor.

[0022] Figure 1 It is a schematic diagram of the overall mechanical structure of the application.

[0023] Figure 2 It is a schematic diagram of the overall starting, control circuit of the application.

[0024] Figure 3 It is a circuit diagram of power recovery, damping control and charging of the application.

[0025] In the figure: 1, unmanned aerial vehicle frame; 2, positioning crossbeam; 3, battery; 4, DC bidirectional electronic governor; 5, oil tank; 6, first DC brush motor; 7, first controllable boost charging module; 8, first linkage shaft; 9, first oil engine; 10, first throttle valve and rudder; 11, first propeller; 12, second DC brush motor; 13, second controllable boost charging module; 14, second linkage shaft; 15, second oil engine; 16, second throttle valve and rudder; 17, second propeller; 18, throttle valve and rudder; 19, push derivation arm; 20, third linkage rod. DETAILED DESCRIPTION

[0026] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only some of the embodiments of the present application, not all the embodiments.

[0027] Please refer to Figure 1 - Figure 3 A hybrid unmanned aerial vehicle power system, comprising a remote control receiver and a flight control, further comprising an unmanned aerial vehicle frame 1, the top end of the unmanned aerial vehicle frame 1 is fixedly connected with a positioning crossbeam 2, the bottom end of the positioning crossbeam 2 is fixedly connected with a DC bidirectional electronic governor 4 and an oil tank 5, the DC bidirectional electronic governor 4 is located at one end of the oil tank 5, the top end of the unmanned aerial vehicle frame 1 is fixedly connected with a battery 3, the two sides of the positioning crossbeam 2 are respectively fixedly connected with a first hybrid propeller starting module and a second hybrid propeller starting module, and the top end of the positioning crossbeam 2 is fixedly connected with a linkage control module.

[0028] The first hybrid propeller starting module comprises a first DC brush motor 6, a first linkage shaft 8, a first oil engine 9, a first throttle valve 10 and a first propeller 11, the bottom end of one side of the positioning crossbeam 2 is fixedly connected with the first DC brush motor 6, the top end of the side of the positioning crossbeam 2 close to the first DC brush motor 6 is fixedly connected with the first oil engine 9, the output end of the first DC brush motor 6 is fixedly connected with the first linkage shaft 8, the first linkage shaft 8 is connected with the inner side of the first engine 9, and the top end of the first linkage shaft 8 is fixedly connected with the first propeller 11, one side of the first oil engine 9 is fixedly connected with the first throttle valve 10.

[0029] The second hybrid propeller starting module comprises a second direct-current brush motor 12, a second linkage shaft 14, a second fuel engine 15, a second throttle valve 16 and a second propeller 17, the bottom end of the positioning cross beam 2 away from the first direct-current brush motor 6 is fixedly connected with the second direct-current brush motor 12, the top end of the positioning cross beam 2 close to the second direct-current brush motor 12 is fixedly connected with the second fuel engine 15, the output end of the second direct-current brush motor 12 is fixedly connected with the second linkage shaft 14, the second linkage shaft 14 is connected with the inner side of the second engine 15, the top end of the second linkage shaft 14 is fixedly connected with the second propeller 17, and one side of the second fuel engine 15 is fixedly connected with the second throttle valve 16;

[0030] The linkage control module comprises a rudder 18, a deduced arm 19 and a third linkage rod 20, the first throttle valve 10 and the second throttle valve 16 are connected through the third linkage rod 20, the top end of the positioning cross beam 2 is fixedly connected with the rudder 18, the rudder 18 and the second throttle valve 16 are connected through the deduced arm 19, and the linkage control module is used for one-key control of the output power of the first engine 9 and the output power of the second engine 15;

[0031] The rudder 18 is electrically connected with at least one of a remote control receiver or a flight control, the first direct-current brush motor 6 and the direct-current bidirectional electric governor 4 are electrically connected through a back-irrigation diode, the second direct-current brush motor 12 and the direct-current bidirectional electric governor 4 are electrically connected through a back-irrigation diode, the oil tank 5 and the first fuel engine 9 are connected through an oil pipe, and the oil tank 5 and the second fuel engine 15 are connected through an oil pipe;

[0032] The two sides of the unmanned aerial vehicle frame 1 are respectively fixedly connected with a first controllable boost charging module 7 and a storage battery 3, the storage battery 3 and the first direct-current brush motor 6 are connected through the first controllable boost charging module 7, and the storage battery 3 and the second direct-current brush motor 12 are connected through a second controllable boost charging module 13;

[0033] The direct-current bidirectional electric governor 4 is connected through electric communication with the remote control receiver, the flight control, the first throttle valve rudder 10 and the second throttle valve rudder 16;

[0034] The direct-current bidirectional electric governor 4 is internally provided with two direct-current electric governors, one of which is connected with the first direct-current brush motor 6, and the other of which is connected with the second direct-current brush motor 12, and a one-key starting switch is further connected between the storage battery 3 and the first direct-current brush motor 6 and the second direct-current permanent magnet motor 12;

[0035] Since the first direct current brush motor 6 and the first fuel engine 9 are coaxially connected in direct transmission, it is used to start the first fuel engine 9 and generate electric energy and output under the driving of the first fuel engine 9 when the first direct current brush motor 6 works, and it is in an electric mode and provides auxiliary power to the first fuel engine 9 when the power of the first fuel engine 9 is insufficient;

[0036] Since the second direct current brush motor 12 and the second fuel engine 15 are coaxially connected in direct transmission, it is used to start the second fuel engine 15 and generate electric energy and output under the driving of the second fuel engine 15 when the second direct current brush motor 12 works, and it is in an electric mode and provides auxiliary power to the second fuel engine 15 when the power of the second fuel engine 15 is insufficient;

[0037] When the first direct current brush motor 6 needs to be accelerated, the first controllable boost charging module 7 connected with the first direct current brush motor 6 is closed, the second controllable boost charging module 13 connected with the second direct current brush motor 12 is opened, and the direct current electric governor connected with the first direct current brush motor 6 works, so as to realize the fast charging mode, and the second direct current brush motor generates a damping effect on the second fuel engine 15 in the case of generating electric energy and output, so as to reduce the speed of the engine 15 and realize the reverse speed regulation. The process when the second direct current brush motor 12 needs to be started and accelerated is opposite, that is, the second direct current brush motor control electric governor is opened, the second controllable boost charging module 13 is closed, and the first controllable boost charging module 7 is opened;

[0038] The first direct current brush motor generates electric energy and reduces the speed of the first fuel engine 9.

[0039] When the first direct current brush motor 6 and the second direct current brush motor 12 do not accelerate the hybrid, the first controllable boost charging module 7 and the second controllable boost charging module 13 are opened in the slow charging mode, so that the first direct current brush motor 6 and the second direct current brush motor 12 are in the slow charging and generating electric energy mode.

[0040] When the first direct current brush motor 6 and the second direct current brush motor 12 need to accelerate the hybrid, all the direct current electric governors are opened, and the first controllable boost charging module 7 and the second controllable boost charging module 13 are closed;

[0041] Specifically, the first direct current brush motor 6 and the second direct current brush motor 12 are direct current permanent magnet brush motors, and when the motor is rotated by the fuel engine, a back electromotive force is generated, which generates a voltage that increases with the increase of the speed. Through the cooperation of the first controllable boost charging module 7 and the second controllable boost charging module 13, the storage battery 3 is charged.

[0042] Electric speed regulation state, when the speed of the propeller 11 is to be changed, the DC permanent magnet motor 6 is started to provide auxiliary power to the fuel engine 9;

[0043] The first linkage shaft 8 and the second linkage shaft 14 are straight connection shafts. Due to the coaxial straight connection and direct drive design of the first DC brush motor 6, the first linkage shaft 8, the first fuel engine 9 and the first propeller 11, and the coaxial straight connection and direct drive design of the second DC brush motor 12, the second linkage shaft 14, the second fuel engine 15 and the second propeller 17, the first fuel engine 9 is started by controlling the first throttle valve 10 by the remote controller, and the second fuel engine 15 is started by controlling the second throttle valve 16, to provide the first torque to the first linkage shaft 8 and the second linkage shaft 14. In order to stabilize the torque power or provide more, the rudder 18 is controlled to drive the derivation arm 19 to complete rotation, the rotation of the derivation arm 19 drives the second throttle valve 16 to adjust the opening angle, which is transmitted by the third linkage rod 20, to drive the first throttle valve 10 to complete synchronous opening angle adjustment, so as to control the synchronous output power of the first fuel engine 9 and the second fuel engine 15, and the output power of the first DC brush motor 6 and the second DC brush motor 12 is controlled by the bidirectional electric governor to intervene into the rotation speed of the first linkage shaft 8 and the rotation speed of the second linkage shaft 14, so as to assist in accurately controlling the output torque of the first propeller 11 and the second propeller 17, and the output power of the first DC brush motor 6 and the second DC brush motor 12 is controlled by the remote controller, so as to complete fine adjustment of the rotation speed of the two propellers.

[0044] It will be obvious to a person skilled in the art that, without departing from the spirit or essential characteristics of the application, the present application can be implemented in other specific forms. The present application is thus not limited to the examples described hereinabove; rather, the scope of the application is to be determined exclusively by the appended claims. In the claims, any reference signs placed between parentheses shall not be construed as limiting the claim. Any reference to "an alternative" or "an alternative embodiment" etc. means that a further alternative embodiment, regardless of whether it is expressly stated or not, is also possible.

Claims

1. A hybrid unmanned aerial vehicle power system comprising a remote control receiver and a flight control, characterized in that: Also include unmanned aerial vehicle frame (1), the top end of the unmanned aerial vehicle frame (1) is fixedly connected with positioning cross beam (2), the bottom end of the positioning cross beam (2) is fixedly connected with direct current bidirectional electric governor (4) and oil tank (5), direct current bidirectional electric governor (4) is located in one end of oil tank (5), the top end of the unmanned aerial vehicle frame (1) is fixedly connected with battery (3), the both sides of the positioning cross beam (2) are fixedly connected with first hybrid propeller starting module and second hybrid propeller starting module respectively, the top end of the positioning cross beam (2) is fixedly connected with linkage control module; The first hybrid propeller starting module includes first direct current brush motor (6), first linkage shaft (8), first engine (9), first throttle valve (10) and first propeller (11), the bottom end of the one side of the positioning cross beam (2) is fixedly connected with first direct current brush motor (6), the top end of the one side of the positioning cross beam (2) close to first direct current brush motor (6) is fixedly connected with first engine (9), the output end of first direct current brush motor (6) is fixedly connected with first linkage shaft (8), the inner side of first linkage shaft (8) is connected with first engine (9), the top end of first linkage shaft (8) is fixedly connected with first propeller (11), the one side of first engine (9) is fixedly connected with first throttle valve (10); The second hybrid propeller starting module includes second direct current brush motor (12), second linkage shaft (14), second engine (15), second throttle valve (16) and second propeller (17), the bottom end of the one side of the positioning cross beam (2) away from first direct current brush motor (6) is fixedly connected with second direct current brush motor (12), the top end of the one side of the positioning cross beam (2) close to second direct current brush motor (12) is fixedly connected with second engine (15), the output end of second direct current brush motor (12) is fixedly connected with second linkage shaft (14), the inner side of second linkage shaft (14) is connected with second engine (15), the top end of second linkage shaft (14) is fixedly connected with second propeller (17), the one side of second engine (15) is fixedly connected with second throttle valve (16); First direct current brush motor (6) and direct current bidirectional electric governor (4) are electrically connected through back-priming diode, second direct current brush motor (12) and direct current bidirectional electric governor (4) are electrically connected through back-priming diode; The both sides of the unmanned aerial vehicle frame (1) are fixedly connected with first controllable boost charging module (7) and battery (3) respectively, battery (3) and first direct current brush motor (6) are connected through first controllable boost charging module (7), battery (3) and second direct current brush motor (12) are connected through second controllable boost charging module (13); The linkage control module comprises a steering engine (18), a deducing arm (19) and a third linkage rod (20), the first throttle valve (10) and the second throttle valve (16) are connected through the third linkage rod (20), the top end of the positioning cross beam (2) is fixedly connected with the steering engine (18), the steering engine (18) and the second throttle valve (16) are connected through the deducing arm (19), and the linkage control module is used for one-key control of the output power of the first engine (9) and the output power of the second engine (15).

2. The hybrid unmanned aerial vehicle power system of claim 1, wherein: The steering engine (18) is electrically connected with at least one of a remote control receiver or a flight control, the oil tank (5) is connected with the first engine (9) through an oil pipe, and the oil tank (5) is connected with the second engine (15) through an oil pipe.

3. The hybrid unmanned aerial vehicle power system of claim 2, wherein: The DC bidirectional electric governor (4) is connected with the remote control receiver, the flight control, the first throttle valve steering engine (10) and the second throttle valve steering engine (16) through electric signals.

4. The hybrid unmanned aerial vehicle power system of claim 3, wherein: Two DC electric governors are carried in the inner side of the DC bidirectional electric governor (4), and a one-key starting switch is further connected between the storage battery (3) and the first DC brush motor (6) and the second DC brush motor (12).

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