阅读说明：本技术 混合动力多旋翼无人机水冷却系统及其应用方法 (Hybrid power multi-rotor unmanned aerial vehicle water cooling system and application method thereof ) 是由 闫凤军 李保民 费冬青 王宇鹏 于 2019-10-11 设计创作，主要内容包括：本发明属于无人机技术领域,公开了一种混合动力多旋翼无人机水冷却系统,发动机上设有发动机气缸冷却水套,旋翼驱动电机的定子外壳上设有电机定子散热孔道,旋翼支撑臂上设有旋翼支撑臂散热孔道；所述冷却系统还包括相连接的水箱、水泵；所述旋翼支撑臂散热孔道的出水口与水箱通过管道相连接；所述水泵出水口与旋翼支撑臂散热孔道进水口之间设置发动机气缸冷却水套、电机定子散热孔道；旋翼支撑臂散热孔道、水箱、水泵、发动机气缸冷却水套和/或电机定子散热孔道形成循环回路。本发明还公开了上述系统的应用方法。本发明利用无人机飞行时旋翼产生的风散热,降低散热系统的质量,提高散热系统的效率,降低动力系统的热负荷,增加动力系统的寿命。(The invention belongs to the technical field of unmanned aerial vehicles, and discloses a hybrid power multi-rotor unmanned aerial vehicle water cooling system.A cooling water jacket of an engine cylinder is arranged on an engine, a motor stator heat dissipation pore passage is arranged on a stator shell of a rotor driving motor, and a rotor support arm heat dissipation pore passage is arranged on a rotor support arm; the cooling system also comprises a water tank and a water pump which are connected; the water outlet of the rotor wing supporting arm heat dissipation pore is connected with the water tank through a pipeline; an engine cylinder cooling water jacket and a motor stator heat dissipation pore passage are arranged between the water pump water outlet and the water inlet of the rotor wing support arm heat dissipation pore passage; and the rotor wing supporting arm heat dissipation pore, the water tank, the water pump, the engine cylinder cooling water jacket and/or the motor stator heat dissipation pore form a circulation loop. The invention also discloses an application method of the system. According to the invention, the wind generated by the rotor wing during the flight of the unmanned aerial vehicle is utilized to dissipate heat, the quality of a heat dissipation system is reduced, the efficiency of the heat dissipation system is improved, the heat load of a power system is reduced, and the service life of the power system is prolonged.)

1. A hybrid power multi-rotor unmanned aerial vehicle water cooling system comprises a cabin, rotor support arms (12), an engine and a rotor driving motor (11), and is characterized in that an engine cylinder cooling water jacket (1) is arranged on the engine, a motor stator heat dissipation pore (2) is arranged on a stator shell (8) of the rotor driving motor (11), and a rotor support arm heat dissipation pore (3) is arranged on each rotor support arm (12);

the engine room is provided with a water tank (4) and a water pump (5) which are connected with each other;

the water outlet of the rotor wing supporting arm heat dissipation pore channel (3) is connected with the water tank (4) through a pipeline;

an engine cylinder cooling water jacket (1) and a motor stator cooling pore passage (2) are arranged between the water outlet of the water pump (4) and the water inlet of the rotor wing supporting arm cooling pore passage (3);

the rotor wing supporting arm heat dissipation pore (3), the water tank (4), the water pump (5), the engine cylinder cooling water jacket (1) and/or the motor stator heat dissipation pore (2) form a circulation loop.

2. The hybrid multi-rotor unmanned aerial vehicle water cooling system as defined in claim 1, wherein the engine cylinder cooling water jacket (1) and the motor stator cooling hole (2) are arranged in series.

3. The hybrid multi-rotor unmanned aerial vehicle water cooling system according to claim 1, wherein the engine cylinder cooling water jacket (1) and the motor stator cooling pore passage (2) are arranged in parallel, and valves are correspondingly arranged on the engine cylinder cooling water jacket (1) and the motor stator cooling pore passage (2) which are arranged in parallel.

4. The hybrid multi-rotor unmanned aerial vehicle water cooling system according to claim 1 or 2, wherein the motor stator heat dissipation duct (2) and the rotor support arm heat dissipation duct (3) are both made of 2mm thin-walled aluminum tubes with semicircular sections.

5. The hybrid multi-rotor unmanned aerial vehicle water cooling system according to claim 1, wherein the number of the rotor support arm heat dissipation channels (3) is two, and the two rotor support arm heat dissipation channels (3) are symmetrically arranged.

6. The hybrid multi-rotor unmanned aerial vehicle water cooling system as claimed in claim 1, wherein the motor stator heat dissipation duct (2) surrounds the outer circumferential wall of the motor stator housing (8).

7. The hybrid multi-rotor unmanned aerial vehicle water cooling system according to claim 1, wherein the rotor support arm heat-dissipating duct (3) surrounds the rotor support arm (12) peripheral wall.

8. The method of application of the water cooling system of a hybrid multi-rotor unmanned aerial vehicle of any one of claims 1 to 7, wherein the method of application is specifically:

firstly, under the action of a water pump, a cooling medium in a water tank flows through an engine cylinder cooling water jacket (1) and/or a motor stator cooling pore passage (2), at the moment, the cooling medium exchanges heat with an engine cylinder and/or a motor stator, at the moment, the temperature of the cooling medium is increased, and the temperature of the engine cylinder and/or the motor stator is reduced;

secondly, under the action of a water pump, the cooling medium reaches a rotor wing supporting arm heat dissipation pore (3); the downward air flow generated by rotation of the rotor blades when the unmanned aerial vehicle works is used, the downward air flow cools the cooling medium in the rotor support arm heat dissipation pore (3), the temperature of the cooling medium is reduced, and the cooled cooling medium returns to the water tank to circulate next time.

9. The application method of the water cooling system of the hybrid power multi-rotor unmanned aerial vehicle according to claim 8 is characterized in that a temperature sensor (6) and a main controller are arranged on the engine cylinder, and the temperature sensor (6) and the water pump (5) are respectively connected with the main controller;

when the value detected by the thermosensitive temperature sensor is greater than 95 ℃, the rotating speed of the water pump is controlled to be 1000-1300rpm by the controller;

when the value detected by the thermosensitive temperature sensor is less than 80 ℃, the rotating speed of the water pump is controlled to be 500-800rpm by the controller;

when the value detected by the thermosensitive temperature sensor is 80-95 ℃, the rotating speed of the water pump is controlled to be 800-1000rpm by the controller.

Technical Field

The invention relates to the technical field of engine cooling and hybrid power multi-rotor unmanned aerial vehicles, in particular to a light and efficient water cooling system for a hybrid power multi-rotor unmanned aerial vehicle.

Background

At present, medium-sized multi-rotor unmanned aerial vehicles have good market prospects and are very wide in application, such as aerial photography, routing inspection, logistics, plant protection and the like. Many rotor unmanned aerial vehicle of present volume production use the mode of power battery power supply to give first place to, and the time of flight is limited, and full-load longest 10 to 15 minutes. In a period of time in the future, the battery technology is difficult to have breakthrough progress, and the time-of-flight problem caused by using the power battery is difficult to fundamentally solve. The mode of adopting the oil-electricity hybrid power system to supply power not only keeps the characteristic of flexible electric drive operation, but also can well solve the problem of time of flight.

The first principle of the design of the aviation hybrid power system is compact structure, light weight, high efficiency and high power-to-weight ratio. The hybrid power system structurally comprises a high-speed two-stroke gasoline engine and a high-speed permanent magnet brushless direct current motor which are directly connected through machinery, and is compact in structure. The cooling system directly determines the output characteristics of the power system, including dynamic performance, economical efficiency, load intensity and service life, and is a core subsystem of the hybrid power system. The working speed of the aviation hybrid power system is high, the aviation hybrid power system works at 12000r/min, and an engine cylinder body and a motor stator and a motor rotor generate heat seriously. However, the aviation hybrid power system has poor heat dissipation conditions, most of the aviation hybrid power system adopts a forced air cooling mode, and is limited by mass, heat dissipation area and cooling air flow; in addition, under the general operating condition of many rotor unmanned aerial vehicle, flight speed is lower, and the driving system surface cooling amount of wind is serious not enough. The heat generation and heat dissipation problems limit the limit output power of the hybrid power system, so that the power-to-weight ratio of the hybrid power system is difficult to improve.

The water-cooling heat dissipation mode has high heat dissipation efficiency, good cooling effect and reliable work, and can improve the limit output power of the engine. The traditional heat dissipation mode that uses water pump cooperation fin, radiator fan can greatly increased cooling system's quality, and fan and water pump increase power loss in addition reduces the power-to-weight ratio of driving system. A new water cooling mode needs to be designed, so that the water cooling device has lighter weight and high heat dissipation efficiency. Therefore, on the premise of unchanged or small increase of the mass, the output power of the power system is improved, and the power-to-weight ratio of the hybrid power system is improved.

The patent specification of the invention discloses a Chinese patent with an authorization notice number of CN U and a notice date of 201 years, months and days. With the above structure. Therefore, a hybrid multi-rotor drone water cooling system is needed.

Disclosure of Invention

The invention aims to provide a hybrid power multi-rotor unmanned aerial vehicle water cooling system and an application method thereof.

The invention provides a hybrid power multi-rotor unmanned aerial vehicle water cooling system, which comprises an engine room, a rotor wing supporting arm, an engine and a rotor wing driving motor, and is characterized in that an engine cylinder cooling water jacket is arranged on the engine, a motor stator heat dissipation pore channel is arranged on a stator shell of the rotor wing driving motor, and a rotor wing supporting arm heat dissipation pore channel is arranged on the rotor wing supporting arm;

the engine room is provided with a water tank and a water pump which are connected;

the water outlet of the rotor wing supporting arm heat dissipation pore is connected with the water tank through a pipeline;

an engine cylinder cooling water jacket and a motor stator heat dissipation pore passage are arranged between the water pump water outlet and the water inlet of the rotor wing support arm heat dissipation pore passage;

and the rotor wing supporting arm heat dissipation pore, the water tank, the water pump, the engine cylinder cooling water jacket and/or the motor stator heat dissipation pore form a circulation loop.

Preferably, the engine cylinder cooling water jacket and the motor stator heat dissipation pore passage are arranged in series.

Preferably, the engine cylinder cooling water jacket and the motor stator heat dissipation pore channel are arranged in parallel, and valves are correspondingly arranged on the engine cylinder cooling water jacket and the motor stator heat dissipation pore channel which are arranged in parallel.

Preferably, the motor stator heat dissipation pore and the rotor wing support arm heat dissipation pore both adopt 2mm thin-wall aluminum pipes with semicircular sections.

Preferably, the quantity of rotor support arm heat dissipation pore is two, and two rotor support arm heat dissipation pore symmetries set up.

Preferably, the motor stator heat dissipation hole is arranged around the outer peripheral wall of the motor stator shell.

Preferably, the rotor support arm heat dissipation holes encircle the rotor support arm peripheral wall.

Preferably, the water tank is arranged on the two suspension beams and suspended below the main control panel of the unmanned aerial vehicle; the water pump is rigidly connected to the engine and assembled with the engine into a whole.

The second purpose of the invention is to provide an application method of the water cooling system of the hybrid multi-rotor unmanned aerial vehicle, which comprises the following steps:

firstly, under the action of a water pump, a cooling medium in a water tank flows through a cooling water jacket of an engine cylinder and/or a heat dissipation pore passage of a motor stator, at the moment, the cooling medium exchanges heat with the engine cylinder and/or the motor stator, at the moment, the temperature of the cooling medium is increased, and the temperature of the engine cylinder and/or the motor stator is reduced;

secondly, under the action of a water pump, the cooling medium reaches a rotor wing supporting arm heat dissipation pore channel; the downward air flow generated by rotation of the rotor blade when the unmanned aerial vehicle works is used, the downward air flow cools the cooling medium in the rotor support arm heat dissipation pore, the temperature of the cooling medium is reduced, and the cooled cooling medium returns to the water tank to circulate next time.

Preferably, a temperature sensor and an STM32 chip main controller are arranged on the engine cylinder, and the temperature sensor and the water pump are respectively connected with the controller;

when the value detected by the thermosensitive temperature sensor is greater than 95 ℃, the rotating speed of the water pump is controlled to be 1000-1300rpm by the controller;

when the value detected by the thermosensitive temperature sensor is less than 80 ℃, the rotating speed of the water pump is controlled to be 500-800rpm by the controller;

when the value detected by the thermosensitive temperature sensor is 80-95 ℃, the rotating speed of the water pump is controlled to be the current rotating speed value by the controller, and the current rotating speed value is any one of 800 plus 1000 rpm.

Compared with the prior art, the invention has the following beneficial effects:

the invention relates to a light and efficient hybrid power multi-rotor unmanned aerial vehicle water cooling system which comprises a water pump, an engine cylinder cooling water jacket, a motor stator heat dissipation pore passage, a rotor wing support arm heat dissipation pore passage, a small water tank and a thermosensitive temperature sensor. The outlet of the cooling water jacket of the engine cylinder is connected with the inlet of a heat dissipation pore passage of the motor stator, the outlet of the heat dissipation pore passage of the motor stator is connected with the inlet of a heat dissipation pore passage of the rotor wing support arm, the outlet of the heat dissipation pore passage of the rotor wing support arm is connected with the water tank, and the water tank is connected with the water pump and then connected with the inlet of the cooling water jacket of the engine cylinder to.

Secondly, the invention also comprises a control method of the water cooling system, which comprises the following steps: a centrifugal pump with compact structure, light weight and high efficiency is selected as a water pump and is used as an actuator for controlling the temperature of the whole cooling system. The specific working method comprises the following steps: detecting the value of the thermosensitive temperature sensor, and increasing the rotating speed of the water pump when the value is higher than 95 ℃; when the value is less than 80 ℃, reducing the rotating speed of the water pump; when the value is between 80 ℃ and 95 ℃, the rotating speed of the water pump is kept constant. The light and efficient hybrid power multi-rotor unmanned aerial vehicle water cooling system disclosed by the invention can be used for accurately controlling the temperature of the engine by utilizing the water pump, avoiding the adverse effect on the engine caused by supercooling or overheating, and improving the dynamic property and the economical efficiency of the engine.

Thirdly, the light and efficient hybrid power multi-rotor unmanned aerial vehicle water cooling system utilizes the air flow generated by the rotor to dissipate heat, removes the radiating fins and the radiating fans of the traditional water cooling system, simplifies the structure of the cooling system, reduces the quality of the cooling system, saves the energy consumption of the radiating fans and improves the power-to-weight ratio of the hybrid power system.

Fourthly, the light and efficient hybrid power multi-rotor unmanned aerial vehicle water cooling system utilizes water cooling to dissipate heat of the motor, improves heat dissipation performance of the motor, improves reliability of the system and prolongs service life of the system.

Drawings

Fig. 1 is a schematic view of a light weight and efficient hybrid multi-rotor drone water cooling system of the present invention;

fig. 2 is a three-dimensional view of a motor stator portion of the water cooling system of the hybrid multi-rotor unmanned aerial vehicle of the present invention;

fig. 3 is a longitudinal section of the motor stator part in the water cooling system of the hybrid power multi-rotor unmanned aerial vehicle of the invention with light weight and high efficiency;

fig. 4 is a three-dimensional view of a portion of a rotor arm of a hybrid multi-rotor drone water cooling system of the present invention that is lightweight and efficient;

fig. 5 is a longitudinal section of the rotor arm portion of the lightweight high efficiency hybrid multi-rotor drone water cooling system of the present invention.

In the figure: 1-engine cylinder cooling water jacket; 2-motor stator heat dissipation pore channel; 3-rotor wing support arm heat dissipation pore; 4-a small water tank; 5, a water pump; 6-a thermosensitive temperature sensor; 7-rotor blades; 8-motor stator housing; 9-motor stator winding; 10-driving an electric regulator; 11-a drive motor; 12-a rotor support arm; 13 a main control panel; 14, a suspension beam; 15 an engine; 201-motor stator heat dissipation pore channel inlet; 202-motor stator heat dissipation pore channel outlet; 301-rotor wing support arm heat dissipating tunnel entrance; 302-rotor support arm heat sink port exit.

Detailed Description