CN110667864A - Hybrid power multi-rotor unmanned aerial vehicle water cooling system and application method thereof - Google Patents
Hybrid power multi-rotor unmanned aerial vehicle water cooling system and application method thereof Download PDFInfo
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- CN110667864A CN110667864A CN201910962296.8A CN201910962296A CN110667864A CN 110667864 A CN110667864 A CN 110667864A CN 201910962296 A CN201910962296 A CN 201910962296A CN 110667864 A CN110667864 A CN 110667864A
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 title claims abstract description 153
- 238000001816 cooling Methods 0.000 title claims abstract description 83
- 238000000034 method Methods 0.000 title claims abstract description 11
- 239000011148 porous material Substances 0.000 claims abstract description 104
- 230000017525 heat dissipation Effects 0.000 claims abstract description 100
- 239000000498 cooling water Substances 0.000 claims abstract description 52
- 239000002826 coolant Substances 0.000 claims description 21
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 4
- 229910052782 aluminium Inorganic materials 0.000 claims description 4
- 230000002093 peripheral effect Effects 0.000 claims description 3
- 230000002035 prolonged effect Effects 0.000 abstract 1
- 239000000110 cooling liquid Substances 0.000 description 32
- 239000000725 suspension Substances 0.000 description 5
- 238000004804 winding Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 238000013475 authorization Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000020169 heat generation Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000013021 overheating Methods 0.000 description 1
- 238000004781 supercooling Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
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Classifications
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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
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
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- B64D27/026—
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- 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
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- 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
Abstract
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.
Description
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
Example 1
As shown in fig. 1, the light and efficient hybrid power multi-rotor unmanned aerial vehicle water cooling system comprises an engine cylinder cooling water jacket 1, a motor stator heat dissipation pore passage 2, a rotor support arm heat dissipation pore passage 3, a small water tank 4, a water pump 5, a thermosensitive temperature sensor 6 and rotor blades 7.
The water outlet of the rotor wing supporting arm heat dissipation pore 3 is connected with the water tank 4 through a pipeline.
An engine cylinder cooling water jacket 1 and a motor stator heat dissipation pore channel 2 are arranged between the water outlet of the water pump 4 and the water inlet of the rotor wing support arm heat dissipation pore channel 3. The engine cylinder cooling water jacket 1 and the motor stator heat dissipation pore channel 2 are connected in series, and the engine cylinder cooling water jacket 1 is located at the upstream of the motor stator heat dissipation pore channel 2.
The bottom of the cabin is provided with two suspension beams, the suspension beams 14 are arranged below the main control panel 13 of the unmanned aerial vehicle, and the water tank 4 is arranged on the two suspension beams 14; the water pump 5 is rigidly connected to the engine 15, and the water pump 5 is integrally assembled with the engine 15.
And a rotor wing supporting arm heat dissipation pore 3, a water tank 4, a water pump 5, an engine cylinder cooling water jacket 1 and a motor stator heat dissipation pore 2 form a circulation loop.
As shown in fig. 2 and fig. 3, the heat dissipation duct 2 of the motor stator is a semicircular 2mm thin aluminum pipe, which is uniformly attached to the outer side of the stator housing 8, and the cooling liquid enters from the inlet 201 and flows out from the outlet 202 to take away the heat of the motor. The inner side of the stator shell 8 is provided with a stator core for winding a motor stator winding 9.
As shown in fig. 4 and 5, the rotor support arm heat-dissipating tunnel 3 is a thin semicircular aluminum tube, and is uniformly attached to the outer side of the rotor support arm 12. The two rotor wing support arm heat dissipation pore channels 3 and the motor stator heat dissipation pore channel 2 are a pipeline, and can also be three or two pipelines. The three are a pipeline in this embodiment, and this pipeline encircles on one of them rotor support arm earlier, encircles on motor stator shell again, encircles on the rotor support arm heat dissipation pore that the symmetry set up again, adopts such structure, and one of them rotor support arm heat dissipation pore 3 is the inlet channel, and another rotor support arm heat dissipation pore 3 is outlet conduit. In fig. 1, rotor wing support arm heat dissipation pore canals between an engine cylinder cooling water jacket 1 and a motor stator heat dissipation pore canal 2 are omitted.
The coolant liquid gets into from entry 301, and export 302 flows out, and unmanned aerial vehicle during operation, and electronic governor 10 driving motor 11 is rotatory, and it is rotatory to drive rotor blade 7, and the heat in rotor support arm heat dissipation pore 3 is taken away to decurrent air current.
Six rotor unmanned aerial vehicle are equipped with rotor support arm heat dissipation pore 3 on the rotor support arm of a pair of symmetry, guarantee the heat-sinking capability promptly, maintain the unmanned aerial vehicle focus, reduce cooling system's quality again.
The rotating speed of the water pump 5 is adjusted according to the AD conversion value of the thermosensitive temperature sensor 6, the current water temperature is converted by the controller MCU according to the AD value, and the temperature sensor is communicated with the controller MCU (STM32 chip main controller) through an SPI protocol. When the temperature is higher than 95 ℃, the controller MCU increases the PWM duty ratio output by the electric regulation, thereby increasing the rotating speed of the motor and increasing the rotating speed of the water pump 5 to 1000 and 1300 rpm; when the value is less than 80 ℃, the rotating speed of the water pump 5 is reduced to 500-800rpm by the same method; when the value is between 80 ℃ and 95 ℃, the current rotation speed value (800-.
The flow direction of the coolant of the water cooling system of the light and efficient hybrid power multi-rotor unmanned aerial vehicle is as follows:
the engine cylinder cooling water jacket comprises an outlet of an engine cylinder cooling water jacket 1, an inlet 201 and an outlet 202 of a motor stator heat dissipation pore channel 2, an inlet 301 and an outlet 302 of a rotor wing support arm heat dissipation pore channel 3, a small water tank 4, a water pump 5 and an inlet of the engine cylinder cooling water jacket 1.
The invention relates to a water cooling system of a hybrid power multi-rotor unmanned aerial vehicle, which comprises the following working steps:
the water pump is used as cooling circulation power to do work to drive cooling liquid to flow, the cooling liquid flows through a heat dissipation pore canal of an engine cylinder and a heat dissipation pore canal of a motor stator to take away heat, and the temperature of the cooling liquid is raised; the cooling liquid flows continuously and flows through the heat dissipation pore of the rotor wing supporting arm, and when the rotor wing rotates, air is driven to flow vertically downwards and flow through the rotor wing supporting arm, so that the cooling liquid is cooled; and the cooled cooling liquid enters the small water tank, then enters a heat dissipation pore of the engine cylinder and a heat dissipation pore of the motor stator, and is subjected to the next circulation.
Example 2
Different from the embodiment 1, the engine cylinder cooling water jacket 1 and the motor stator cooling pore passage 2 are connected in series, and in the hydraulic loop, the engine cylinder cooling water jacket 1 is positioned at the downstream of the motor stator cooling pore passage 2, namely, a water outlet of the motor stator cooling pore passage is connected with a water inlet of the engine cylinder cooling water jacket. The rotor wing supporting arm heat dissipation pore 3, the water tank 4, the water pump 5, the motor stator heat dissipation pore 2 and the engine cylinder cooling water jacket 1 are sequentially connected in series according to an inlet and an outlet to form a circulation loop.
The flow direction of the coolant of the water cooling system of the light and efficient hybrid power multi-rotor unmanned aerial vehicle is as follows:
the cooling structure comprises an outlet of a motor stator cooling pore passage 2, an inlet 201 and an outlet 202 of an engine cylinder cooling water jacket 1, an inlet 301 and an outlet 302 of a rotor wing support arm cooling pore passage 3, a small water tank 4, a water pump 5 and an inlet of the motor stator cooling pore passage 2.
The invention relates to a water cooling system of a hybrid power multi-rotor unmanned aerial vehicle, which comprises the following working steps:
the water pump is used as cooling circulation power to do work to drive cooling liquid to flow, the cooling liquid flows through a motor stator cooling pore passage and an engine cylinder cooling water jacket to take away heat, and the cooling liquid is heated; the cooling liquid flows continuously and flows through the heat dissipation pore of the rotor wing supporting arm, and when the rotor wing rotates, air is driven to flow vertically downwards and flow through the rotor wing supporting arm, so that the cooling liquid is cooled; and the cooled coolant enters a small water tank, then enters a motor stator heat dissipation pore and an engine cylinder cooling water jacket, and then is circulated next time.
Example 3
Different from the embodiment 1, 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 engine cylinder cooling water jacket 1 and the motor stator heat dissipation pore channel 2 are connected in parallel.
The flow direction of the coolant of the water cooling system of the light and efficient hybrid power multi-rotor unmanned aerial vehicle is as follows:
the engine cylinder cooling water jacket comprises an outlet 1 of an engine cylinder cooling water jacket and an outlet 202 of a motor stator cooling pore passage 2 which are arranged in parallel, an inlet 301 and an outlet 302 of a rotor wing supporting arm cooling pore passage 3, a small water tank 4, a water pump 5, an inlet 1 of the engine cylinder cooling water jacket and an inlet 201 of the motor stator cooling pore passage 2 which are arranged in parallel.
The invention relates to a water cooling system of a hybrid power multi-rotor unmanned aerial vehicle, which comprises the following working steps:
the water pump is used as cooling circulation power to do work to drive cooling liquid to flow, the cooling liquid is divided into two paths through a water inlet manifold, one path of the cooling liquid flows through a motor stator radiating pore channel to take away heat, the other path of the cooling liquid flows through an engine cylinder cooling water jacket to take away heat, and the cooling liquid is heated; the cooling liquid continues to flow and is converged through the water outlet manifold when flowing through the heat dissipation pore of the rotor wing supporting arm, and when the rotor wing rotates, the air is driven to vertically flow downwards and flows through the rotor wing supporting arm, so that the cooling liquid is cooled; the cooled coolant enters the small water tank, continues to be divided into two paths through the water inlet manifold, and flows through the motor stator heat dissipation pore and the engine cylinder cooling water jacket respectively to perform the next cycle.
Example 4
Different from the embodiment 3, 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 engine cylinder cooling water jacket 1 and the motor stator heat dissipation pore channel 2 are connected in parallel. Valves are respectively and independently arranged on the two pipelines of the water inlet manifold.
Example 4 is the same as example 3 when both valves are open.
When a valve on an engine cylinder cooling water jacket 1 is opened and a valve on a motor stator cooling pore passage 2 pipeline is closed, the flow direction of the cooling liquid of the water cooling system of the light and efficient hybrid power multi-rotor unmanned aerial vehicle is as follows:
the engine cylinder cooling water jacket 1 outlet, rotor wing support arm heat dissipation pore 3 entry 301, export 302, little water tank 4, water pump 5, engine cylinder cooling water jacket 1 entry.
The invention relates to a water cooling system of a hybrid power multi-rotor unmanned aerial vehicle, which comprises the following working steps:
the water pump is used as cooling circulation power to do work to drive the cooling liquid to flow, the cooling liquid flows through the cooling water jacket of the engine cylinder to take away heat, and the cooling liquid is heated; the cooling liquid flows continuously and flows through the heat dissipation pore of the rotor wing supporting arm, and when the rotor wing rotates, air is driven to flow vertically downwards and flow through the rotor wing supporting arm, so that the cooling liquid is cooled; the cooled coolant enters the small water tank and is pumped by the water pump to flow through the cooling water jacket of the engine cylinder for the next circulation.
When a valve on the cooling water jacket 1 of the engine cylinder is closed and a valve on a pipeline of the cooling pore passage 2 of the motor stator is opened, the flow direction of the cooling liquid of the water cooling system of the light and high-efficiency hybrid power multi-rotor unmanned aerial vehicle is as follows:
an outlet of the motor stator heat dissipation pore passage 2, an inlet 301 and an outlet 302 of the rotor wing support arm heat dissipation pore passage 3, a small water tank 4, a water pump 5 and an inlet of the motor stator heat dissipation pore passage 2.
The invention relates to a water cooling system of a hybrid power multi-rotor unmanned aerial vehicle, which comprises the following working steps:
the water pump is used as cooling circulation power to do work to drive the cooling liquid to flow, the cooling liquid flows through a motor stator heat dissipation pore channel to take away heat, and the temperature of the cooling liquid is raised; the cooling liquid flows continuously and flows through the heat dissipation pore of the rotor wing supporting arm, and when the rotor wing rotates, air is driven to flow vertically downwards and flow through the rotor wing supporting arm, so that the cooling liquid is cooled; the cooled cooling liquid enters the small water tank and is pumped out by the water pump to flow through the motor stator heat dissipation pore channel for the next circulation.
Claims (9)
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.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111501636A (en) * | 2020-04-26 | 2020-08-07 | 徐州徐工环境技术有限公司 | Energy-saving control system and control method for sweeping machine |
| CN112357094A (en) * | 2020-11-24 | 2021-02-12 | 北京炫影智能科技有限公司 | Double-heat-dissipation oil-electricity hybrid power system for unmanned aerial vehicle and unmanned aerial vehicle |
| CN113830314A (en) * | 2021-08-31 | 2021-12-24 | 深圳天鹰兄弟无人机创新有限公司 | Water-cooling heat dissipation system for range extender of oil-electricity hybrid unmanned aerial vehicle |
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