阅读说明：本技术 一种无人机的发动机用散热结构 (Unmanned aerial vehicle's heat radiation structure for engine ) 是由 王凭慧 沈伟 韩松 于 2020-12-25 设计创作，主要内容包括：本发明公开了一种无人机的发动机用散热结构,包括一个安装座,所述安装座的内部设置有一个驱动机构,所述安装座的顶端设置有一个进气机构,所述驱动机构的内部设置有一个冷却机构,所述安装座的底部设置有一个排风机构,本发明所达到的有益效果是：在使用时,储液腔内部的冷却液会与双头驱动电机进行换热来对其进行冷却,同时双头驱动电机会同步带动进风机构与抽风机构进行运作,进风机构将外部的冷风抽入驱动腔内部,并被输风叶片向下吹动,使得冷风通过进风漏斗进入通风管中,并通过通风管中的冷风与储液腔中逐渐升温的冷却液进行换热,直至被抽风机构抽出,使得冷却液可以保持长时间对发动机进行冷却作业。(The invention discloses a heat dissipation structure for an engine of an unmanned aerial vehicle, which comprises an installation seat, wherein a driving mechanism is arranged in the installation seat, an air inlet mechanism is arranged at the top end of the installation seat, a cooling mechanism is arranged in the driving mechanism, and an air exhaust mechanism is arranged at the bottom of the installation seat, so that the heat dissipation structure has the following beneficial effects that: when using, the inside coolant liquid of stock solution chamber can carry out the heat transfer with double-end driving motor and cool off it, double-end driving motor can drive air inlet mechanism and updraft ventilator mechanism in step simultaneously and function, inside the air inlet mechanism drives the intracavity with outside cold wind suction, and be blown downwards by the defeated wind blade, make during cold wind gets into the ventilation pipe through the air inlet funnel, and carry out the heat transfer through the cold wind in the ventilation pipe and the coolant liquid that heaies up gradually in the stock solution chamber, until being taken out by updraft ventilator mechanism, make the coolant liquid can keep carrying out the cooling operation to the engine for a long time.)

1. The utility model provides an unmanned aerial vehicle's heat radiation structure for engine, its characterized in that includes a mount pad (1), the inside of mount pad (1) is provided with a actuating mechanism (2), the top of mount pad (1) is provided with one and admits air mechanism (3), the inside of actuating mechanism (2) is provided with one cooling body (4), the bottom of mount pad (1) is provided with one exhaust mechanism (5), admit air mechanism (3) and exhaust mechanism (5) all are connected with actuating mechanism (2).

2. The heat radiation structure for the engine of the unmanned aerial vehicle as claimed in claim 1, the driving mechanism (2) comprises a driving cavity (21), the driving cavity (21) is arranged in the mounting seat (1), the inner cavity wall of the driving cavity (21) is fixedly connected with an installation block (22), a double-head driving motor (23) is fixedly arranged in the mounting block (22), a first rotating rod (24) is fixedly connected with the output end of the upper end of the double-head driving motor (23), the output end of the lower end of the first rotating rod (24) and the double-head driving motor (23) is fixedly connected with a second rotating rod (25), the lower end rod wall of the second rotating rod (25) is rotatably connected to the side wall of the bottom end of the mounting seat (1) through a bearing, and the lower end of the second rotating rod (25) penetrates through the lower surface of the mounting seat (1) and extends downwards.

3. The heat radiation structure for the engine of the unmanned aerial vehicle as claimed in claim 1, the air inlet mechanism (3) comprises a connecting rod (31), the connecting rod (31) is rotatably connected to the top cavity wall of the driving cavity (21) through a bearing, the upper end of the connecting rod (31) penetrates through the upper surface of the mounting seat (1) and extends upwards to be fixedly connected with a fixed seat (32) which is arranged in a semicircular shape, a plurality of first air inlet holes (33) are arranged on the rod wall of the connecting rod (31) in a surrounding way, a plurality of second air inlet holes (34) are arranged on the fixed seat (32) corresponding to the positions of the first air inlet holes (33) in a penetrating way, one ends of the second air inlet holes (34) far away from the first air inlet holes (33) are communicated with the outside, and the lower surface of the fixed seat (32) is fixedly connected with a wind shield (35) at the position corresponding to the second air inlet holes (34).

4. The heat radiation structure for the engine of the unmanned aerial vehicle as claimed in claim 1, wherein the cooling mechanism (4) comprises a liquid storage cavity (41), the liquid storage cavity (41) is arranged in the mounting block (22) in a surrounding manner, the cooling liquid is arranged in the liquid storage cavity (41), a plurality of ventilation pipes (42) are fixedly connected in the liquid storage cavity (41), the upper and lower ends of the ventilation pipes (42) respectively penetrate through the corresponding cavity wall of the liquid storage cavity (41) and are communicated with the driving cavity (21), a plurality of air inlet funnels (43) are arranged on the upper surface of the mounting block (22) at the pipe orifice positions on the upper ends of the ventilation pipes (42), and a plurality of air conveying blades (44) are fixedly connected on the rod wall of the connecting rod (31) at the positions above the air inlet funnels (43).

5. The heat radiation structure for the engine of the unmanned aerial vehicle as claimed in claim 1, wherein the exhaust mechanism (5) comprises a fixing ring (51), the fixing ring (51) is fixedly connected to the lower surface of the mounting seat (1), the lower end of the fixing ring (51) is fixedly connected with a first filter screen plate (52) which is arranged in an arc shape, a plurality of air draft blades (53) are fixedly connected to the lower surface of a second rotating rod (25) which is positioned outside the mounting seat (1), a plurality of air draft holes (54) are formed in the lower surface of the mounting seat (1) corresponding to the positions of the air draft blades (53) in a penetrating manner, and the upper ends of the air draft holes (54) are communicated with the driving cavity (21).

6. The heat dissipation structure for the engine of the unmanned aerial vehicle according to claim 3, wherein a second filter plate (6) is fixedly connected to the upper end openings of a plurality of the first air inlet holes (33), a threaded rod (7) is fixedly connected to the center of the lower surface of the fixing seat (32), a threaded groove (8) is formed in the rod wall of the connecting rod (31) corresponding to the position of the threaded rod (7), and the lower end of the threaded rod (7) penetrates through the opening of the threaded groove (8) and is screwed in the threaded groove (8).

7. The heat dissipation structure for the engine of the unmanned aerial vehicle of claim 1, characterized in that a plurality of rotating blades (9) are fixedly connected to the rod wall of the connecting rod (31) between the mounting seat (1) and the fixing seat (22) in a surrounding manner.

8. The heat dissipation structure for the engine of the unmanned aerial vehicle of claim 1, characterized in that a mounting column (10) is fixedly connected to a side wall of one side of the mounting seat (1).

Technical Field

The invention relates to a heat dissipation structure for an engine of an unmanned aerial vehicle, and belongs to the technical field of engines.

Background

The unmanned plane is called unmanned plane for short, and is an unmanned plane operated by radio remote control equipment and a self-contained program control device. The machine has no cockpit, but is provided with an automatic pilot, a program control device and other equipment. The personnel on the ground, the naval vessel or the mother aircraft remote control station can track, position, remotely control, telemeter and digitally transmit the personnel through equipment such as a radar.

In order to provide sufficient power, the rotating speed of the engine in the unmanned aerial vehicle is relatively high, so that a large amount of heat can be generated during operation of the engine, and the engine is easy to cause inevitable damage when the engine is kept in operation for a long time.

Disclosure of Invention

The invention aims to overcome the defects of the prior art and provides a heat radiation structure for an engine of an unmanned aerial vehicle.

In order to solve the technical problems, the invention provides the following technical scheme:

the invention relates to a heat dissipation structure for an engine of an unmanned aerial vehicle, which comprises an installation seat, wherein a driving mechanism is arranged inside the installation seat, an air inlet mechanism is arranged at the top end of the installation seat, a cooling mechanism is arranged inside the driving mechanism, an air exhaust mechanism is arranged at the bottom of the installation seat, and the air inlet mechanism and the air exhaust mechanism are both connected with the driving mechanism.

According to the preferable technical scheme of the heat dissipation structure for the engine of the unmanned aerial vehicle, the driving mechanism comprises a driving cavity, the driving cavity is formed in the mounting seat, the wall of the inner cavity of the driving cavity is fixedly connected with an installation block, a double-end driving motor is fixedly installed in the installation block, the output end of the upper end of the double-end driving motor is fixedly connected with a first rotating rod, the output end of the lower end of the first rotating rod is fixedly connected with a second rotating rod, the lower end rod wall of the second rotating rod is rotatably connected to the bottom end side wall of the mounting seat through a bearing, and the lower end of the second rotating rod penetrates through the lower surface of the mounting seat and extends downwards.

According to the preferable technical scheme of the heat dissipation structure for the engine of the unmanned aerial vehicle, the air inlet mechanism comprises a connecting rod, the connecting rod is rotatably connected to the top end cavity wall of the driving cavity through a bearing, the upper end of the connecting rod penetrates through the upper surface of the mounting seat and extends upwards to be fixedly connected with a semi-circular fixing seat, a plurality of first air inlet holes are formed in the rod wall of the connecting rod in a penetrating mode in a surrounding mode, a plurality of second air inlet holes are formed in the fixing seat corresponding to the positions of the first air inlet holes in a penetrating mode, one ends, far away from the first air inlet holes, of the second air inlet holes are communicated with the outside, and a wind shield is fixedly connected to the lower surface of the fixing seat corresponding to the positions of the second air inlet holes.

As a preferred technical scheme of the heat dissipation structure for the engine of the unmanned aerial vehicle, the cooling mechanism comprises a liquid storage cavity, cooling liquid is arranged in the liquid storage cavity, the liquid storage cavity is arranged in the mounting block in a surrounding manner, a plurality of ventilation pipes are fixedly connected in the liquid storage cavity, the upper end and the lower end of each ventilation pipe penetrate through the corresponding cavity wall of the liquid storage cavity and are communicated with the driving cavity, a plurality of air inlet funnels are arranged on the upper surface of the mounting block corresponding to pipe orifices at the upper ends of the ventilation pipes, and a plurality of air delivery blades are fixedly connected to connecting rod walls above the air inlet funnels.

As a preferred technical scheme of the heat dissipation structure for the engine of the unmanned aerial vehicle, the exhaust mechanism comprises a fixing ring, the fixing ring is fixedly connected to the lower surface of the mounting seat, the lower end of the fixing ring is fixedly connected with a first filter screen plate which is arranged in an arc shape, the lower surface of a second rotating rod which is positioned outside the mounting seat is fixedly connected with a plurality of air exhaust blades, a plurality of air exhaust holes are formed in the lower surface of the mounting seat corresponding to the positions of the air exhaust blades in a penetrating mode, and the upper ends of the air exhaust holes are communicated with the driving cavity.

According to the preferable technical scheme of the heat dissipation structure for the engine of the unmanned aerial vehicle, the orifices at the upper ends of the first air inlet holes are fixedly connected with the second filter plate, the center of the lower surface of the fixed seat is fixedly connected with the threaded rod, the wall of the connecting rod corresponding to the threaded rod is provided with the threaded groove, and the lower end of the threaded rod penetrates through the opening of the threaded groove and is in threaded connection with the inside of the threaded groove.

As the preferable technical scheme of the heat dissipation structure for the engine of the unmanned aerial vehicle, a plurality of rotating blades are fixedly connected to the rod wall of the connecting rod between the mounting seat and the fixed seat in a surrounding manner.

As the preferable technical scheme of the heat radiation structure for the engine of the unmanned aerial vehicle, a mounting column is fixedly connected to the side wall of one side of the mounting seat.

The invention has the following beneficial effects:

1. the invention provides a heat dissipation structure for an engine of an unmanned aerial vehicle, when the heat dissipation structure is used, cooling liquid in a liquid storage cavity exchanges heat with a double-end driving motor to cool the double-end driving motor, meanwhile, the double-end driving motor synchronously drives an air inlet mechanism and an air draft mechanism to operate, the air inlet mechanism sucks external cold air into the driving cavity and blows the cold air downwards by an air conveying blade, so that the cold air enters a ventilation pipe through an air inlet funnel and exchanges heat with the cooling liquid gradually heated in the liquid storage cavity through the cold air in the ventilation pipe until the cold air is drawn out by the air draft mechanism, and the cooling liquid can keep cooling operation on the engine for a long time.

2. The invention provides a heat radiation structure for an engine of an unmanned aerial vehicle, which can block impurities in a second air inlet hole when a second filter screen plate filters cold air entering the heat radiation structure, can enable a threaded rod to be disconnected with a thread groove by rotating a fixed seat, can take out the fixed seat, and can clean the second air inlet hole in the fixed seat, thereby facilitating subsequent use.

Drawings

The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention and not to limit the invention. In the drawings:

FIG. 1 is a schematic structural view of the present invention;

FIG. 2 is a sectional view of the drive mechanism of the present invention in a top view;

FIG. 3 is a schematic top view of the drive mechanism of the present invention;

FIG. 4 is a schematic bottom view of the air intake mechanism of the present invention;

fig. 5 is an enlarged schematic view of a portion a of fig. 1 according to the present invention.

In the figure: 1. a mounting seat; 2. a drive mechanism; 21. a drive chamber; 22. mounting blocks; 23. a double-headed drive motor; 24. a first rotating lever; 25. a second rotating lever; 3. an air intake mechanism; 31. a connecting rod; 32. a fixed seat; 33. a first air intake hole; 34. a second air intake hole; 35. a wind deflector; 4. a cooling mechanism; 41. a liquid storage cavity; 42. a vent pipe; 43. an air inlet funnel; 44. a wind delivery blade; 5. an air exhaust mechanism; 51. a fixing ring; 52. a first filter screen plate; 53. air draft blades; 54. a suction hole; 6. a second filter screen plate; 7. a threaded rod; 8. a thread groove; 9. a rotor blade; 10. and (6) mounting the column.

Detailed Description

The preferred embodiments of the present invention will be described in conjunction with the accompanying drawings, and it will be understood that they are described herein for the purpose of illustration and explanation and not limitation.

Example 1

As shown in fig. 1-5, the present invention provides a heat dissipation structure for an engine of an unmanned aerial vehicle, including a mounting base 1, a driving mechanism 2 is disposed inside the mounting base 1, an air intake mechanism 3 is disposed at a top end of the mounting base 1, a cooling mechanism 4 is disposed inside the driving mechanism 2, an air exhaust mechanism 5 is disposed at a bottom of the mounting base 1, and both the air intake mechanism 3 and the air exhaust mechanism 5 are connected to the driving mechanism 2.

Wherein, actuating mechanism 2 includes a drive chamber 21, drive chamber 21 sets up in the inside of mount pad 1, an installation piece 22 of fixedly connected with on the inner chamber wall of drive chamber 21, the inside fixed mounting of installation piece 22 has a double-end driving motor 23, the upper end output end fixedly connected with of double-end driving motor 23 has a first dwang 24, a second dwang 25 of double-end driving motor 23's lower extreme output end fixedly connected with, the lower extreme pole wall of second dwang 25 passes through the bearing and rotates and connect on the bottom lateral wall of mount pad 1, and the lower extreme of second dwang 25 runs through the lower surface and the downwardly extending of mount pad 1.

Wherein, air inlet mechanism 3 includes a connecting rod 31, connecting rod 31 rotates through the bearing and connects on the top chamber wall of drive chamber 21, connecting rod 31's upper end runs through the upper surface of mount pad 1 and upwards extends to and a fixedly connected with is the fixing base 32 that semicircle form set up, it runs through the first fresh air inlet 33 of a plurality of to be the form of encircleing on connecting rod 31's the pole wall, run through on the fixing base 32 that corresponds the first fresh air inlet 33 position of a plurality of and seted up a plurality of second fresh air inlet 34, the one end that first fresh air inlet 33 was kept away from to a plurality of second fresh air inlet 34 all is linked together with the outside, and equal fixedly connected with deep bead 35 on the position that the lower surface of fixing base 32 corresponds a plurality of second fresh air inlet 34.

Wherein, cooling body 4 includes a stock solution chamber 41, stock solution chamber 41 is the inside of encircleing the form and seting up at installation piece 22, the inside of stock solution chamber 41 is provided with the coolant liquid, a plurality of ventilation pipes 42 of the inside fixedly connected with of stock solution chamber 41, the upper and lower both ends of a plurality of ventilation pipes 42 run through the corresponding chamber wall of stock solution chamber 41 respectively and are linked together with drive chamber 21, a plurality of air inlet funnel 43 has been seted up to the installation piece 22 upper surface that corresponds a plurality of ventilation pipes 42 upper end mouth of pipe position, a plurality of air delivery blades 44 of fixedly connected with on the connecting rod 31 pole wall that is located a plurality of air inlet funnel 43 top position.

Wherein, exhaust mechanism 5 includes a solid fixed ring 51, gu fixed ring 51 fixed connection is at the lower surface of mount pad 1, gu fixed ring 51's lower extreme fixedly connected with one is the first filter screen board 52 that the arc set up, be located a plurality of convulsions blade 53 of surface fixedly connected with under the second dwang 25 outside mount pad 1, a plurality of convulsions hole 54 has been seted up in the lower surface of mount pad 1 that corresponds a plurality of convulsions blade 53 positions runs through, the upper end of a plurality of convulsions hole 54 all is linked together with drive chamber 21.

Wherein, the equal fixedly connected with a slice second filter 6 of the upper end aperture department of the first inlet air 33 of a plurality of, threaded rod 7 of fixedly connected with is located at the center of fixing base 32 lower surface, has seted up a thread groove 8 on the connecting rod 31 pole wall of corresponding threaded rod 7 position, and the lower extreme of threaded rod 7 runs through the notch and the threaded connection of thread groove 8 in the thread groove 8.

Wherein, a plurality of rotating blades 9 are fixedly connected on the rod wall of the connecting rod 31 between the mounting seat 1 and the fixed seat 22 in a surrounding manner.

Wherein, a mounting column 10 is fixedly connected to the side wall of one side of the mounting seat 1.

Specifically, when the invention is used, the double-head driving motor 23 can be cooled by exchanging heat with the cooling liquid in the liquid storage cavity 41, then in the process of running the double-head driving motor 23, the double-head driving motor 23 synchronously drives the first rotating rod 24 and the second rotating rod 25 to rotate, the first rotating rod 24 can synchronously drive the connecting rod 31 and the fixed seat 32 to rotate, when the fixed seat 32 rotates, the wind is input into the first wind inlet hole 33 through the wind shield 35, then is input into the driving cavity 21 through the second wind inlet hole 34, and simultaneously the connecting rod 31 drives the wind conveying blade 44 to blow the entering cold wind downwards, and the cold wind passes through the wind inlet funnel 43, the ventilating pipe 42 and the wind suction hole 54 and is conveyed downwards, the heat can be cooled by exchanging heat with the cooling liquid in the liquid storage cavity 41 through the cold wind in the ventilating pipe 42, and then the live time that can prolong the coolant liquid, in order to guarantee the cooling to the engine, and long when using, second dwang 25 can drive convulsions blade 53 by convulsions in the convulsions hole 54 simultaneously, and discharge hot-blast, in order to avoid having hot-blast to remain at its inside, simultaneously can filter the cold wind that gets into through second filter screen board 6, it can be with the impurity separation in second fresh air inlet 34, can be through rotating fixing base 32 this moment, make threaded rod 7 relieve with the threaded connection of thread groove 8, can take out fixing base 32 this moment, and clear up second fresh air inlet 34 in the fixing base 32, be convenient for subsequent use.

Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that changes may be made in the embodiments and/or equivalents thereof without departing from the spirit and scope of the invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.