CN209972792U

CN209972792U - Power system of double-heat-dissipation type oil-to-electricity unmanned aerial vehicle

Info

Publication number: CN209972792U
Application number: CN201921765452.3U
Authority: CN
Inventors: 李鹏飞; 罗伟; 尹彦卿
Original assignee: Avic Jincheng Unmanned System Co Ltd
Current assignee: Avic Jincheng Unmanned System Co Ltd
Priority date: 2019-10-21
Filing date: 2019-10-21
Publication date: 2020-01-21
Anticipated expiration: 2029-10-21

Abstract

The utility model discloses a two heat dissipation formula oil change electric unmanned aerial vehicle's driving system, include: the generator comprises an engine assembly, a generator assembly and a mounting plate arranged between the engine assembly and the generator assembly; the engine assembly includes: the heat dissipation device comprises an engine, a pair of exhaust pipes and a first heat dissipation mechanism; the generator assembly includes: the generator is fixed on the upper surface of the mounting plate, and an outer rotor connecting shaft of the generator is driven by an output shaft of the engine to rotate; the second heat dissipation mechanism comprises a cooling liquid box, and a liquid inlet pipe and a liquid outlet pipe of the cooling liquid box are communicated to the bottom of the inner stator; the lower part and the upper part of the outer rotor are respectively provided with an exhaust port and an air suction port. This system cools off engine and generator in the driving system respectively through two kinds of heat dissipation mechanisms, makes unmanned aerial vehicle can work continuously and stably, ensures effectual heat dispersion, guarantees that generator and engine can not damage because of overheated, has prolonged life.

Description

Power system of double-heat-dissipation type oil-to-electricity unmanned aerial vehicle

Technical Field

The utility model relates to a driving system, concretely relates to two heat dissipation formula oil change electricity unmanned aerial vehicle's driving system belongs to unmanned aerial vehicle technical field.

Background

The unmanned aerial vehicle is an unmanned aerial vehicle controlled by a radio remote control device or an onboard computer program control system, has the advantages of simple structure, small volume, good maneuverability, low manufacturing cost, strong environment adaptability and the like, can complete a plurality of tasks which are difficult to be completed by piloted aircrafts, and has an expanded application range to various fields such as military use, civil use and the like.

The existing power system of the unmanned aerial vehicle mainly has three types, namely engine power, battery power and engine battery parallel power. Compared with helicopters and fixed-wing aircrafts, the multi-rotor aircraft has the advantages of simple mechanical structure, convenience in taking off and landing and easiness in control, and is widely applied to military and civil fields such as surveying, reconnaissance, emergency communication, agriculture and forestry protection and the like. Conventional many rotor unmanned aerial vehicle adopts the pneumatic mode of deciding the pitch, and the rotor that drives fixed pitch respectively by the motor produces lift and drives the aircraft, realizes the balanced manipulation of aircraft through changing the rotor rotational speed, can only use the lithium cell as the power energy. And along with the demand of people on the unmanned aerial vehicle is higher and higher, the shortcomings of the electric multi-rotor unmanned aerial vehicle on load and endurance time become more and more prominent.

And the advantage of petrol on energy density makes the unmanned aerial vehicle who utilizes gasoline engine have the incomparable advantage of electronic many rotors in load and time of endurance, therefore oil changes electric unmanned aerial vehicle and has specific application scope.

Chinese patent application No. 2016210811591 discloses an integral type cooling system of many rotor unmanned aerial vehicle, including paddle, motor, xarm, go up motor locating piece, lower motor locating piece, electricity and transfer the cover with electricity. Paddle fixed connection is in epaxial of motor, motor fixed connection be in on the last motor locating piece, lower motor locating piece fixed connection is in the bottom of last motor locating piece, and the xarm is located go up between motor locating piece and the lower motor locating piece, electricity transfer fixed connection is in the bottom of motor locating piece down, electricity transfer cover fixed connection is in the bottom of motor locating piece down, the utility model discloses, after motor, electricity transfer work generate heat, on the heat that motor, electricity were transferred can give off the motor locating piece, also can give off the heat through the amount of wind when the paddle rotated, effectual type has become the system of the high-efficient power of a low temperature, the loss reduction.

However, because contain two devices of generator and engine among the oil commentaries on classics electric unmanned aerial vehicle driving system, can produce a large amount of heat energy at the in-process of work, generate heat when the motor can not in time dispel the heat and will cause the damage to unmanned aerial vehicle's driving system, influence unmanned aerial vehicle normal work.

Disclosure of Invention

The utility model aims at providing a novel two heat dissipation formula oil change electric unmanned aerial vehicle's driving system to the above-mentioned problem that exists among the prior art.

In order to achieve the above object, the present invention adopts the following technical solutions:

the utility model provides a two heat dissipation formula oil change electric unmanned aerial vehicle's driving system, includes: the generator comprises an engine assembly, a generator assembly and a mounting plate arranged between the engine assembly and the generator assembly; the engine assembly includes: the engine is fixed on the lower surface of the mounting plate and connected with an oil tank of the unmanned aerial vehicle, and the exhaust pipe is connected with an exhaust port of the engine; the generator assembly includes: the generator is fixed on the upper surface of the mounting plate, and an outer rotor connecting shaft of the generator is driven by an output shaft of the engine to rotate; the second heat dissipation mechanism comprises a cooling liquid box, and a liquid inlet pipe and a liquid outlet pipe of the cooling liquid box are communicated to the bottom of the inner stator; and an air outlet and an air suction opening are formed at the lower part and the upper part of the outer rotor respectively.

Preferably, the first heat dissipation mechanism is a fan heat dissipation structure, adopts a heat dissipation mode of bottom-in and top-out, sucks cold air through a lower air suction port, takes away heat of the engine, discharges the heat along an air outlet channel, and plays a role in heat dissipation of the engine.

Preferably, above-mentioned engine housing top is provided with a pair of wind-guiding structure in the position that is located the generator below, wind-guiding structure will be carried to side from casing top combustion gas, avoids fan exhaust hot-blast to carry the generator subassembly department to the top, influences the stationarity of unmanned aerial vehicle normal work.

More preferably, the air guide structure includes: a pair of curb plate of integrated into one piece and the roof of connecting a pair of curb plate, leave the air-out passageway between wind-guiding structure and the engine housing, and the sectional area of air-out passageway increases gradually from inside to outside, guarantees that hot-blast can be discharged smoothly.

Preferably, the cooling liquid tank is installed above the generator, the weight of the cooling liquid tank is uniformly distributed above the generator to keep the whole machine body balanced, and the surface of the cooling liquid tank is provided with a plurality of air-cooled radiating fins to effectively radiate the heat of the cooling medium after heat exchange.

Further preferably, a liquid inlet/outlet for connecting a liquid inlet pipe/liquid outlet pipe is formed at the bottom of the inner stator of the generator and connected with a cooling liquid tank, so that the cyclic utilization of the cooling medium is realized.

Still more preferably, the flow path of the cooling medium in the inner stator cavity is a serpentine flow path, and is particularly a winding structure, so that the flow path of the cooling medium is increased, and the cooling effect is enhanced.

Still further preferably, the bottom of the inner stator extends upwards to form a plurality of baffle plates, a diversion cover body is installed at the top of the inner stator cavity, the diversion cover body is provided with a plurality of diversion sheets extending towards the direction of the inner stator cavity, the baffle plates and the diversion sheets are arranged in a staggered mode, a gap is reserved between the baffle plates and the diversion cover body, and a gap is also reserved between the diversion sheets and the bottom wall of the inner stator cavity to form a serpentine flow channel.

Still further preferably, the diversion cover body and the inner stator body are in interference fit, so that the sealing performance of the cooling medium is ensured.

And the outer rotor of the generator is an air-cooling heat dissipation type outer rotor, an upper suction and lower discharge heat dissipation mode is adopted, and the air suction ports and the air exhaust ports of the upper cover and the lower cover are both in a centrifugal blade shape and rotate to suck air.

The utility model discloses an useful part lies in:

i) the power system is suitable for the oil-to-electricity unmanned aerial vehicle, and can provide more advantages for the unmanned aerial vehicle in loading and endurance time;

ii) the power system is of a double-heat-dissipation structure and is provided with the first heat dissipation mechanism and the second heat dissipation mechanism, so that the generator and the engine of the unmanned aerial vehicle power system can be effectively dissipated in time, the safety of the engine and the generator is protected, the damage of devices caused by overheating is avoided, the normal work of the unmanned aerial vehicle is ensured, and the reliable service life is realized;

iii) the independence of the two heat dissipation modes is fully considered in the double heat dissipation type structure, mutual interference is avoided, especially, the structure of the air outlet channel of the first heat dissipation mechanism is optimized, and the position of the second heat dissipation mechanism is ingeniously arranged, so that the structure of the whole power system is more compact and reasonable, and the heat dissipation performance is more optimized.

Drawings

Fig. 1 is a three-dimensional structure diagram of a power system of a double-heat dissipation type oil-to-electricity unmanned aerial vehicle according to the present invention;

fig. 2 is an exploded view of the generator assembly of the present invention;

FIG. 3 is a perspective view of the cross-sectional structure of the inner stator of the present invention;

FIG. 4 is a cross-sectional view of the cooling medium deflector of the inner stator of the present invention;

fig. 5 is a perspective view of an upper suction cover of the outer rotor of the present invention;

fig. 6 is a perspective view of the lower air discharge cover of the outer rotor of the present invention.

The meaning of the reference symbols in the figures:

1. the air-cooling generator comprises an engine assembly, 2, a generator assembly, 3, a shell, 4, an exhaust pipe, 5, an air suction port, 6, an air outlet channel, 7, a cooling liquid tank, 8, a liquid outlet pipe, 9, a liquid inlet pipe, 10, an outer rotor connecting shaft, 11, an upper air suction cover, 12, a mounting plate, 13, an outer rotor shell, 14, a flow guide cover body, 15, an inner stator coil, 16, an upper bearing of an inner stator, 17, an inner stator cavity, 18, a lower bearing of the inner stator, 19, a lower air suction cover, 20, an upper cover air vent, 21, a centrifugal blade-shaped air suction inlet, 22, a lower cover air vent, 23, a centrifugal blade-shaped air outlet, 24, an air-cooling radiating fin, 25, a baffle, 26, a flow guide blade, 27.

Detailed Description

The invention is described in detail below with reference to the figures and the embodiments.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

Referring to fig. 1 and fig. 2, the power system of the double-heat dissipation type oil-to-electricity unmanned aerial vehicle of the embodiment mainly comprises an engine assembly 1, a generator assembly 2 and a mounting plate 12, wherein the engine assembly 1 and the generator assembly 2 are respectively arranged on the upper side and the lower side of the mounting plate 12. Wherein, engine assembly 1 includes: set up engine, a pair of blast pipe 4 in casing 3 and be used for carrying out radiating first heat dissipation mechanism to the engine, the engine is fixed in mounting panel 12 lower surface and is connected with unmanned aerial vehicle's oil tank, and blast pipe 4 is connected with the gas vent of engine. The generator assembly 2 comprises: generator and second heat dissipation mechanism, generator are fixed in the upper surface of mounting panel 12, and its outer rotor connecting axle 10 is rotated by the output shaft drive of engine, can realize like this that oil changes the electricity, provides lasting stable power for unmanned aerial vehicle.

Because the engine can all produce a large amount of heats in the course of the work, in order to guarantee the life of engine, need in time give off the heat that produces in the course of the work. The first heat dissipation mechanism is used for dissipating heat of the engine in the casing 3, and specifically is a heat dissipation structure of a fan, which adopts a heat dissipation mode of downward inlet and upward outlet, wherein the lower part of the casing 3 is an air inlet 5 of the fan, and hot air is discharged from the upper part of the casing 3 after the sucked cold air exchanges heat with the engine in the casing 3. Since the generator module 2 is provided above the housing 3, in order to prevent hot air discharged from the generator from affecting the performance of the generator, a pair of air guide structures are provided above the engine housing 3 and below the generator, and the air guide structures convey air discharged from the top of the housing 3 to the side. Specifically, in this embodiment, the air guiding structure includes: a pair of integrally formed side plates and a top plate connected with the side plates, an air outlet channel 6 is left between the air guide structure and the engine shell 3, and the sectional area of the air outlet channel 6 is gradually increased from inside to outside. Therefore, the hot air can be smoothly discharged, and the heat dissipation performance is optimized.

As shown in the exploded view of fig. 2, the generator assembly 2 includes: the cooling liquid box 7, the liquid outlet pipe 8, the liquid inlet pipe 9, the engine and outer rotor connecting shaft 10, the outer rotor upper air suction cover 11, the outer rotor shell 13, the diversion cover body 14, the inner stator coil 15, the inner stator upper bearing 16, the inner stator cavity 17, the inner stator lower bearing 18 and the outer rotor lower air suction cover 19. The inner stator and the outer stator can generate a large amount of heat in the working process of the generator, and the second heat dissipation mechanism can effectively dissipate heat. The second heat dissipation mechanism actually comprises the comprehensive utilization of two heat dissipation modes, wherein the first heat dissipation mode is cooling liquid cooling (such as water cooling) and is used for cooling the inner stator of the generator; the second is air cooling, which is used for cooling the outer rotor of the generator.

Referring to fig. 5 and 6, the air-cooled heat dissipation of the outer rotor is realized by: an outer rotor upper cover ventilation opening 20 and a centrifugal blade-shaped air suction opening 21 are arranged on the upper air suction cover 11, and an outer rotor lower cover ventilation opening 22 and a centrifugal blade-shaped air outlet 23 are arranged on the outer rotor lower air discharge cover 19. In the working process, the outer rotor rotates to drive the upper air suction cover 11 of the outer rotor and the lower air suction cover 19 of the outer rotor to rotate together, air is sucked from the upper cover ventilation opening 20 and the centrifugal blade-shaped air suction opening 21 of the upper air suction cover 11 of the outer rotor, and after the air flows through the outer rotor to exchange heat with the outer rotor, the air is discharged from the lower cover ventilation opening 22 and the centrifugal blade-shaped air outlet 23 of the lower air suction cover 19 of the outer rotor, so that generated heat is taken away. The centrifugal blade-shaped air outlet 23 and the centrifugal blade-shaped air suction opening 21 have better air suction and exhaust effects during rotation, so that a better heat dissipation effect can be achieved.

The cooling of the cooling liquid tank 7 is to the inner stator part of the generator, the cooling liquid flows in from the cooling liquid tank 7 through the liquid inlet pipe 9 from the liquid inlet 27 at the bottom of the inner stator, circulates in the serpentine flow channel which is tortuous inside the inner stator, returns to the cooling liquid tank 7 from the liquid outlet pipe 8 through the liquid outlet 28, and is recycled after being radiated by the air-cooled radiating fins 24, so that the effect of radiating the inner stator is achieved. Specifically, in the present embodiment, referring to fig. 3 and 4, the bottom of the inner stator extends upward to form a plurality of baffle plates 25, the top of the cavity 17 of the inner stator is provided with a diversion cover 14, the diversion cover 14 has a plurality of diversion sheets 26 extending toward the direction of the cavity 17 of the inner stator, the baffle plates 25 and the diversion sheets 26 are arranged in a staggered manner, a gap is left between the baffle plates 25 and the diversion cover 14, and a gap is also left between the diversion sheets 26 and the bottom wall of the cavity 17 of the inner stator, so that a serpentine channel is formed inside the inner stator, which can increase the flow of the cooling liquid in the inner stator, so as to achieve a better cooling effect.

The heat dissipation process of the power system of the unmanned aerial vehicle is further described below with reference to fig. 1 to 6:

in the invention, two heat dissipation modes of air cooling and water cooling are fully, comprehensively and effectively utilized, the engine component 1 adopts an air cooling heat dissipation mode (a first heat dissipation mechanism) with the lower inlet and the upper outlet, the inner stator part of the generator component 2 adopts a heat dissipation mode of cooling medium cooling (water cooling), and the outer rotor part adopts a heat dissipation mode of upper suction and lower discharge. When the first heat dissipation mechanism works, the air suction port 5 at the bottom of the shell 3 sucks cold air, when the cold air flows through the engine, the cold air takes away heat generated by the engine, and then the cold air is discharged out of hot air through the side air outlet channels 6 at two sides. In the second heat dissipation mechanism, the inner stator cooling liquid tank 7 of the generator is arranged above the generator, a liquid inlet 27/a liquid outlet 28 for connecting the liquid outlet pipe 8/the liquid inlet pipe 9 is formed at the bottom of the inner stator of the generator, and a plurality of air-cooled heat dissipation fins 24 are arranged on the surface of the inner stator cooling liquid tank 7 of the generator and used for cooling the used cooling liquid, so that the circulation and effective utilization of a cooling medium are realized.

To sum up, the utility model relates to a two heat dissipation formula oil commentaries on classics electric unmanned aerial vehicle's driving system possesses two kinds of heat dissipation mechanisms, cools off engine and generator in the driving system respectively for unmanned aerial vehicle can work continuously and stably, has guaranteed that generator and engine can not damage because of overheated, has prolonged life. Meanwhile, the cooling modes of circulating liquid cooling and air cooling can effectively avoid resource waste and reduce the use cost.

In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

The foregoing illustrates and describes the principles, general features, and advantages of the present invention. It should be understood by those skilled in the art that the above embodiments do not limit the present invention in any way, and all technical solutions obtained by using equivalent alternatives or equivalent variations fall within the scope of the present invention.

Claims

1. The utility model provides a two heat dissipation formula oil change electric unmanned aerial vehicle's driving system which characterized in that includes: the generator comprises an engine assembly, a generator assembly and a mounting plate arranged between the engine assembly and the generator assembly;

the engine assembly includes: the engine is fixed on the lower surface of the mounting plate and connected with an oil tank of the unmanned aerial vehicle, and the exhaust pipe is connected with an exhaust port of the engine;

the generator assembly includes: the generator is fixed on the upper surface of the mounting plate, and an outer rotor connecting shaft of the generator is driven by an output shaft of the engine to rotate; the second heat dissipation mechanism comprises a cooling liquid box, and a liquid inlet pipe and a liquid outlet pipe of the cooling liquid box are communicated to the bottom of the inner stator; and an exhaust port and an air suction port are formed at the lower part and the upper part of the outer rotor respectively.

2. The power system of a dual-heat dissipation type oil-to-electricity unmanned aerial vehicle according to claim 1, wherein the first heat dissipation mechanism is a fan heat dissipation structure, and adopts a bottom-in and top-out heat dissipation mode.

3. The power system of a double-heat dissipation type oil-to-electricity unmanned aerial vehicle as claimed in claim 1, wherein a pair of air guide structures is arranged above the engine housing and below the generator, and the air guide structures convey air exhausted from the top of the housing to the side.

4. The power system of a double-heat dissipation type oil-to-electricity unmanned aerial vehicle according to claim 3, wherein the air guide structure comprises: the air guide structure comprises a pair of side plates and a top plate, wherein the side plates are integrally formed, the top plate is connected with the side plates, an air outlet channel is reserved between the air guide structure and the engine shell, and the sectional area of the air outlet channel is gradually increased from inside to outside.

5. The power system of a double-heat dissipation type oil-to-electricity unmanned aerial vehicle according to claim 1, wherein the coolant tank is installed above the generator, and a plurality of air-cooled heat dissipation fins are arranged on the surface of the coolant tank.

6. The power system of a double-heat dissipation type oil-to-electricity unmanned aerial vehicle as claimed in claim 1, wherein a liquid inlet/outlet for connecting a liquid inlet/outlet pipe is formed at the bottom of the inner stator of the generator.

7. The power system of a double-heat dissipation type oil-to-electricity unmanned aerial vehicle as claimed in claim 1, wherein the flow path of the cooling medium in the inner stator cavity is a serpentine flow path.

8. The power system of a dual heat dissipation type oil-to-electricity unmanned aerial vehicle according to claim 1 ~ 7, wherein a plurality of blocking pieces extend upward from the bottom of the inner stator, a diversion cover is installed on the top of the inner stator cavity, the diversion cover has a plurality of diversion pieces extending toward the inner stator cavity, the blocking pieces and the diversion pieces are arranged in a staggered manner, and a gap is left between the blocking pieces and the diversion cover, and a gap is also left between the diversion pieces and the bottom wall of the inner stator cavity, thereby forming a serpentine flow channel.

9. The power system of a double-heat dissipation type oil-to-electricity unmanned aerial vehicle according to claim 8, wherein the diversion cover body is in interference fit with the inner stator body.

10. The power system of a double-heat-dissipation type oil-to-electricity unmanned aerial vehicle according to claim 1, wherein the outer rotor of the generator is an air-cooling heat-dissipation type outer rotor, a heat dissipation mode of upper suction and lower discharge is adopted, and the suction inlet and the air outlet of the upper cover and the lower cover are both arranged in a centrifugal blade shape.