CN214566192U

CN214566192U - Unmanned helicopter engine heat abstractor

Info

Publication number: CN214566192U
Application number: CN202120720399.6U
Authority: CN
Inventors: 朱悦鑫; 单伟; 刘媛媛
Original assignee: Wuxi Jinye Aviation Safety Equipment Co ltd
Current assignee: Wuxi Jinye Aviation Safety Equipment Co ltd
Priority date: 2021-04-08
Filing date: 2021-04-08
Publication date: 2021-11-02
Anticipated expiration: 2031-04-08

Abstract

The utility model discloses an unmanned helicopter engine heat abstractor, which comprises a helicopter body, wherein a clapboard is fixedly connected in the helicopter body, one side of the clapboard is arranged as a second inner cavity, notches are respectively arranged at the two sides of the second inner cavity, a chute is arranged in each notch, a push plate is arranged in each chute in a sliding way, and an electric push rod is fixedly arranged in the helicopter body; through the setting of push pedal, the telescopic link through electric putter contracts, drive the push pedal and remove in the spacing groove, thereby make the fixed block slide in the spout, the accessible drags behind the fixed block, thereby make external wind enter into the inside of second inner chamber, carry out the forced air cooling to hose and engine, the heat dissipation of hose and engine with higher speed, ventilate through the notch of fuselage opposite side, through the setting of push pedal, can be at unmanned helicopter flight in-process, carry out supplementary heat dissipation to the engine, prevent that the engine from because of the trouble when the high temperature.

Description

Unmanned helicopter engine heat abstractor

Technical Field

The utility model relates to an unmanned helicopter technical field specifically is an unmanned helicopter engine heat abstractor.

Background

An unmanned helicopter is a vertical take-off and landing (VTOL) unmanned aircraft flying by radio ground remote control or/and autonomous control, belongs to a rotor aircraft in structural form, functionally belongs to a VTOL aircraft, has the advantages of low cost, high efficiency, convenience in take-off and landing and the like, is widely applied to various fields, and has wide application prospects in the aspects of civil use, such as atmosphere monitoring, traffic monitoring, resource exploration, power line detection, forest fire prevention and the like.

In the prior art, when the heat dissipation is performed on the engine of the unmanned helicopter, water cooling heat dissipation is often adopted, cooling media are cooled by air in the flight process of the unmanned helicopter, although the heat dissipation effect is good, a device for assisting heat dissipation is lacked, and the heat dissipation cannot be performed on the engine quickly, so that the heat dissipation device for the engine of the unmanned helicopter needs to be provided.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an unmanned helicopter engine heat abstractor can assist the heat dissipation to the engine at unmanned helicopter flight in-process, prevents that the engine from breaking down when the high temperature to solve the problem that proposes in the above-mentioned background art.

In order to achieve the above object, the utility model provides a following technical scheme: an unmanned helicopter engine heat dissipation device comprises a machine body, wherein a partition plate is fixedly connected inside the machine body, one side of the partition plate is arranged into a second inner cavity, notches are formed in two sides of the second inner cavity, sliding grooves are formed in the notches, a pushing plate is slidably mounted in the sliding grooves, a fixed block is fixedly connected to the front side of the pushing plate, an electric push rod is fixedly mounted inside the machine body, a limiting groove is formed inside the machine body, the limiting groove is formed below the fixed block, and a telescopic rod of the electric push rod is fixedly connected with the fixed block;

fixedly connected with engine in the second inner chamber, the spiral is surrounded there is the hose on the engine, the both ends of hose set up to water inlet and delivery port, the top fixed mounting of fuselage has radiator and water pump, the end of drawing water of water pump communicates with one side of radiator, the play water end intercommunication of water pump has the outlet pipe, the opposite side intercommunication of radiator has the inlet tube, outlet pipe and inlet tube communicate with water inlet and delivery port respectively.

Preferably, the other side of baffle sets up to first inner chamber, fixedly connected with fuselage girder in the first inner chamber, the one end of fuselage girder extends to the second inner chamber, fixed mounting has the engine on the part that the fuselage girder extends to the second inner chamber.

Preferably, the first inner cavity is arranged in a sealing manner, a fan is fixedly mounted on one side of the first inner cavity, and the fan is fixedly mounted on the upper portion of the engine.

Preferably, the upper portion integrated into one piece of fuselage has the fixing base, the both ends of fixing base are the opening setting, radiator and water pump all set up inside the fixing base.

Preferably, the hose is attached to four sides of the engine, the hoses are attached to each other, and the hose is fixedly mounted on the engine.

Preferably, the top and the baffle of fuselage are all run through to outlet pipe and inlet tube, all cup jointed the pipe strap on outlet pipe and the inlet tube, the pipe strap all with the top of fuselage and one side fixed connection of baffle.

Compared with the prior art, the beneficial effects of the utility model are that:

through the setting of push pedal, the telescopic link through electric putter contracts, it removes in the spacing inslot to drive the push pedal, thereby make the fixed block slide in the spout, the spacing groove can be spacing to the push pedal, the accessible drags behind the fixed block, open the back with the notch, thereby make external wind enter into the inside of second inner chamber, carry out the forced air cooling to hose and engine, the heat dissipation of hose and engine with higher speed, coolant after the forced air cooling behind delivery port and outlet pipe, it cools off in the radiator to enter into, the notch through the fuselage opposite side ventilates, setting through the push pedal, can be at unmanned helicopter flight in-process, carry out auxiliary heat dissipation to the engine, prevent that the engine from being because of trouble when the high temperature.

Drawings

Fig. 1 is a schematic structural view of a front view section of the present invention;

FIG. 2 is a schematic structural view of the push plate, the sliding groove and the electric push rod of the present invention;

FIG. 3 is a schematic structural view of the present invention;

fig. 4 is an enlarged schematic structural view of a region a in fig. 1 according to the present invention.

In the figure: 1. a body; 2. a fixed seat; 3. a first lumen; 4. a second lumen; 5. a partition plate; 6. a fuselage main beam; 7. an engine; 8. a fan; 9. a heat sink; 10. a water pump; 11. a water inlet pipe; 12. a water outlet pipe; 13. a water outlet; 14. a notch; 15. a water inlet; 16. a hose; 17. a chute; 18. pushing the plate; 19. a limiting groove; 20. a fixed block; 21. an electric push rod.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Referring to fig. 1-4, the present invention provides a technical solution: an engine heat dissipation device of an unmanned helicopter comprises a helicopter body 1, wherein a partition plate 5 is fixedly connected inside the helicopter body 1, one side of the partition plate 5 is arranged to be a second inner cavity 4, notches 14 are formed in two sides of the second inner cavity 4, a sliding groove 17 is formed in each notch 14, a pushing plate 18 is slidably mounted in each sliding groove 17, a fixed block 20 is fixedly connected to the front surface of each pushing plate 18, an electric push rod 21 is fixedly mounted inside the helicopter body 1, a limit groove 19 is formed inside the helicopter body 1, the limit groove 19 is formed below the fixed block 20, and a telescopic rod of the electric push rod 21 is fixedly connected with the fixed block 20;

through the arrangement of the partition plate 5, when the partition plate 5 is closed, the second inner cavity 4 can be sealed, after the partition plate 5 is opened, outside air enters the second inner cavity 4 through the notch 14, and the fixed block 20 is dragged to move by the retraction of the telescopic rod of the electric push rod 21, so that the push plate 18 slides in the sliding groove 17;

an engine 7 is fixedly connected in the second inner cavity 4, a hose 16 is spirally wound on the engine 7, a water inlet 15 and a water outlet 13 are arranged at two ends of the hose 16, a radiator 9 and a water pump 10 are fixedly mounted at the top of the machine body 1, a water pumping end of the water pump 10 is communicated with one side of the radiator 9, a water outlet end of the water pump 10 is communicated with a water outlet pipe 12, the other side of the radiator 9 is communicated with a water inlet pipe 11, and the water outlet pipe 12 and the water inlet pipe 11 are respectively communicated with the water inlet 15 and the water outlet 13;

through the arrangement of the hose 16, the water inlet 15 and the water outlet 13 are convenient for conveying the cooling medium in the hose 16, the radiator 9 can radiate the cooling medium conveyed to the interior of the radiator through the water inlet pipe 11, and the hose 16 is arranged as an aluminum hose;

the other side of the partition plate 5 is provided with a first inner cavity 3, a main body beam 6 is fixedly connected in the first inner cavity 3, one end of the main body beam 6 extends into the second inner cavity 4, an engine 7 is fixedly installed on the part of the main body beam 6 extending into the second inner cavity 4, the first inner cavity 3 is in a sealed arrangement, a fan 8 is fixedly installed on one side of the first inner cavity 3, the fan 8 is fixedly installed on the upper part of the engine 7, a fixed seat 2 is integrally formed on the upper part of the machine body 1, two ends of the fixed seat 2 are in opening arrangements, and a radiator 9 and a water pump 10 are both arranged in the fixed seat 2;

through the arrangement of the fixed seat 2, the radiator 9 can be protected, meanwhile, the radiator 9 can be conveniently radiated, and the fan 8 can radiate the hose 16 and the engine 7;

the hose 16 is attached to four sides of the engine 7, the hoses 16 are attached to each other, the hose 16 is fixedly mounted on the engine 7, the water outlet pipe 12 and the water inlet pipe 11 both penetrate through the top of the machine body 1 and the partition plate 5, pipe clamps are sleeved on the water outlet pipe 12 and the water inlet pipe 11, and the pipe clamps are both fixedly connected with the top of the machine body 1 and one side of the partition plate 5;

the water outlet pipe 12 and the water inlet pipe 11 can be fixed by the pipe clamp through the arrangement of the pipe clamp, the hose 16 is fixed on the engine 7, and the hose 16 is prevented from being blown off by external wind after the push plate 18 is opened;

the working principle is as follows: when the cooling device works, the water pump 10 works, one end of the water pump 10 pumps the cooling medium to the radiator 9, the pumped cooling medium is transported through the water outlet pipe 12, and the transported cooling medium enters the hose 16 through the water inlet 15;

when the electric push rod 21 works, the telescopic rod of the electric push rod 21 retracts to drive, the push plate 18 moves to drive the push plate 18 to move in the limiting groove 19, the limiting groove 19 can limit the push plate 18 to prevent the push plate 18 from deviating in the moving process, after the push plate 18 is opened, external air enters the second inner cavity 4 through the notch 14 to cool the hose 16 and the engine 7, ventilation can be realized through the notch 14 on the other side of the machine body 1, after cooling media in the hose 16 take away heat emitted by the engine 7 during working, the cooling media enter the water inlet pipe 11 through the water outlet 13, and the cooling media are transported to the radiator 9 through the water inlet pipe 11 to dissipate heat;

when the unmanned helicopter is in stay operation, the fan 8 works, and the fan 8, the radiator 9 and the notch 14 are matched to radiate heat of the hose 16 and the engine 7.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. The utility model provides an unmanned helicopter engine heat abstractor, includes fuselage (1), its characterized in that: the novel multifunctional electric fan is characterized in that a partition plate (5) is fixedly connected to the inside of the machine body (1), one side of the partition plate (5) is arranged to be a second inner cavity (4), notches (14) are formed in two sides of the second inner cavity (4), sliding grooves (17) are formed in the notches (14), a pushing plate (18) is slidably mounted in the sliding grooves (17), a fixed block (20) is fixedly connected to the front side of the pushing plate (18), an electric push rod (21) is fixedly mounted inside the machine body (1), a limiting groove (19) is formed inside the machine body (1), the limiting groove (19) is formed below the fixed block (20), and a telescopic rod of the electric push rod (21) is fixedly connected with the fixed block (20);

fixedly connected with engine (7) in second inner chamber (4), the spiral is around having hose (16) on engine (7), the both ends of hose (16) set up to water inlet (15) and delivery port (13), the top fixed mounting of fuselage (1) has radiator (9) and water pump (10), the end of drawing water of water pump (10) communicates with one side of radiator (9), the play water end intercommunication of water pump (10) has outlet pipe (12), the opposite side intercommunication of radiator (9) has inlet tube (11), outlet pipe (12) and inlet tube (11) communicate with water inlet (15) and delivery port (13) respectively.

2. The unmanned helicopter engine heat sink of claim 1, wherein: the opposite side of baffle (5) sets up to first inner chamber (3), fixedly connected with fuselage girder (6) in first inner chamber (3), the one end of fuselage girder (6) extends to in second inner chamber (4), fixed mounting has engine (7) on the part that fuselage girder (6) extend to in second inner chamber (4).

3. The unmanned helicopter engine heat sink of claim 2, wherein: first inner chamber (3) are sealed setting, one side fixed mounting of first inner chamber (3) has fan (8), fan (8) fixed mounting is on the upper portion of engine (7).

4. The unmanned helicopter engine heat sink of claim 1, wherein: the upper portion integrated into one piece of fuselage (1) has fixing base (2), the both ends of fixing base (2) are the opening setting, radiator (9) all set up inside fixing base (2) with water pump (10).

5. The unmanned helicopter engine heat sink of claim 1, wherein: the flexible pipe (16) is attached to four sides of the engine (7), the flexible pipe (16) is attached to each other, and the flexible pipe (16) is fixedly installed on the engine (7).

6. The unmanned helicopter engine heat sink of claim 1, wherein: the water outlet pipe (12) and the water inlet pipe (11) penetrate through the top of the machine body (1) and the partition plate (5), the water outlet pipe (12) and the water inlet pipe (11) are sleeved with pipe clamps, and the pipe clamps are fixedly connected with the top of the machine body (1) and one side of the partition plate (5).