A heat dissipation structure for an engine of a drone

Abstract

The invention discloses a heat dissipation structure for an engine of an unmanned aerial vehicle, comprising a mounting seat, wherein a driving mechanism is arranged inside the mounting seat, an air intake mechanism is arranged at the top of the mounting seat, a cooling mechanism is arranged inside the driving mechanism, and an exhaust mechanism is arranged at the bottom of the mounting seat. The beneficial effect achieved by the invention is that when in use, the coolant inside the liquid storage chamber will exchange heat with the double-headed driving motor to cool it, and at the same time, the double-headed driving motor will synchronously drive the air intake mechanism and the exhaust mechanism to operate, the air intake mechanism draws external cold air into the driving chamber, and is blown downward by air delivery blades, so that the cold air enters the ventilation pipe through the air intake funnel, and exchanges heat with the coolant gradually heated up in the liquid storage chamber through the cold air in the ventilation pipe until it is drawn out by the exhaust mechanism, so that the coolant can keep cooling the engine for a long time.

Description

Technical Field

[0001] 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 Art

[0002] Unmanned aircraft, also known as "drones", are unmanned aircraft that are controlled by radio remote control equipment and self-contained program control devices. There is no cockpit on the aircraft, but it is equipped with autopilots, program control devices and other equipment. Personnel on the ground, on ships or at the remote control station of the mother aircraft use radar and other equipment to track, locate, remotely control, telemeter and transmit digital data to it.

[0003] In order to provide sufficient power, the engine in the drone has a relatively high speed, which generates a lot of heat during operation. If it keeps running for a long time, it is easy to cause inevitable damage to the engine. Therefore, it is necessary to propose a heat dissipation structure for the engine of the drone. Summary of the invention

[0004] The technical problem to be solved by the present invention is to overcome the defects of the prior art and provide a heat dissipation structure for an engine of a drone.

[0005] In order to solve the above technical problems, the present invention provides the following technical solutions:

[0006] The present invention discloses a heat dissipation structure for an engine of an unmanned aerial vehicle, comprising a mounting seat, a driving mechanism disposed inside the mounting seat, an air intake mechanism disposed at the top of the mounting seat, a cooling mechanism disposed inside the driving mechanism, an exhaust mechanism disposed at the bottom of the mounting seat, and both the air intake mechanism and the exhaust mechanism are connected to the driving mechanism.

[0007] As a preferred technical solution of the heat dissipation structure for the engine of an unmanned aerial vehicle of the present invention, the driving mechanism includes a driving cavity, which is opened inside the mounting seat, and a mounting block is fixedly connected to the inner cavity wall of the driving cavity, and a double-headed driving motor is fixedly installed inside the mounting block, and the upper output end of the double-headed driving motor is fixedly connected to a first rotating rod, and the lower output end of the double-headed driving motor is fixedly connected to a second rotating rod, and the lower end rod wall of the second rotating rod is rotatably connected to the bottom side wall of the mounting seat through a bearing, and the lower end of the second rotating rod passes through the lower surface of the mounting seat and extends downward.

[0008] As a preferred technical solution of the heat dissipation structure for the engine of an unmanned aerial vehicle of the present invention, the air intake mechanism includes a connecting rod, which is rotatably connected to the top cavity wall of the driving cavity through a bearing, the upper end of the connecting rod passes through the upper surface of the mounting seat and extends upward to and is fixedly connected to a fixing seat arranged in a semicircular shape, a plurality of first air inlet holes are circumferentially penetrated on the rod wall of the connecting rod, a plurality of second air inlet holes are penetrated on the fixing seat corresponding to the positions of the plurality of first air inlet holes, the ends of the plurality of second air inlet holes away from the first air inlet holes are connected to the outside, and a wind shield is fixedly connected to the positions of the plurality of second air inlet holes on the lower surface of the fixing seat corresponding to the plurality of second air inlet holes.

[0009] As a preferred technical solution of the heat dissipation structure for the engine of an unmanned aerial vehicle of the present invention, the cooling mechanism includes a liquid storage chamber, the interior of the liquid storage chamber is provided with a coolant, the liquid storage chamber is arranged in a circumferential shape inside the mounting block, a plurality of ventilation pipes are fixedly connected to the interior of the liquid storage chamber, the upper and lower ends of the plurality of ventilation pipes respectively penetrate the corresponding cavity walls of the liquid storage chamber and are connected to the driving cavity, a plurality of air inlet funnels are opened on the upper surface of the mounting block corresponding to the pipe opening positions of the upper ends of the plurality of ventilation pipes, and a plurality of air delivery blades are fixedly connected to the wall of the connecting rod located above the plurality of air inlet funnels.

[0010] As a preferred technical solution for the heat dissipation structure of an engine of an unmanned aerial vehicle of the present invention, the exhaust mechanism includes a fixing ring, which is fixedly connected to the lower surface of the mounting seat, and the lower end of the fixing ring is fixedly connected to a first filter screen plate arranged in an arc shape, and a plurality of exhaust blades are fixedly connected to the lower surface of a second rotating rod located outside the mounting seat, and a plurality of exhaust holes are penetrated through the lower surface of the mounting seat corresponding to the positions of the plurality of exhaust blades, and the upper ends of the plurality of exhaust holes are connected to the driving chamber.

[0011] As a preferred technical solution for the heat dissipation structure of an engine of an unmanned aerial vehicle of the present invention, a second filter plate is fixedly connected to the upper end openings of several of the first air inlet holes, a threaded rod is fixedly connected to the center of the lower surface of the fixed seat, a threaded groove is opened on the rod wall of the connecting rod corresponding to the position of the threaded rod, and the lower end of the threaded rod passes through the notch of the threaded groove and is threadedly connected in the threaded groove.

[0012] As a preferred technical solution of the heat dissipation structure for the engine of a drone of the present invention, a plurality of rotating blades are fixedly connected in a circumferential shape on the rod wall of the connecting rod located between the mounting seat and the fixing seat.

[0013] As a preferred technical solution of the heat dissipation structure for the engine of a drone of the present invention, a mounting column is fixedly connected to the side wall on one side of the mounting seat.

[0014] The beneficial effects achieved by the present invention are:

[0015] 1. The present invention provides a heat dissipation structure for an engine of an unmanned aerial vehicle. When in use, the coolant in the liquid storage chamber will exchange heat with the double-headed driving motor to cool it. At the same time, the double-headed driving motor will synchronously drive the air intake mechanism and the air exhaust mechanism to operate. The air intake mechanism draws external cold air into the driving chamber and is blown downward by the air delivery blades, so that the cold air enters the ventilation pipe through the air intake funnel, and the cold air in the ventilation pipe exchanges heat with the coolant in the liquid storage chamber that is gradually heated up until it is extracted by the air exhaust mechanism, so that the coolant can be kept for a long time to cool the engine.

[0016] 2. The present invention provides a heat dissipation structure for an engine of a drone. When the second filter screen filters the incoming cold air, impurities are blocked in the second air inlet. At this time, the fixing seat can be rotated to release the threaded connection between the threaded rod and the threaded groove. At this time, the fixing seat can be taken out and the second air inlet in the fixing seat can be cleaned for subsequent use. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The accompanying drawings are used to provide a further understanding of the present invention and constitute a part of the specification. Together with the embodiments of the present invention, they are used to explain the present invention and do not constitute a limitation of the present invention. In the accompanying drawings:

[0018] Figure 1 It is a schematic diagram of the structure of the present invention;

[0019] Figure 2 is a top structural sectional view of the driving mechanism of the present invention;

[0020] Figure 3 It is a schematic diagram of the top view of the driving mechanism in the present invention;

[0021] Figure 4 It is a bottom view structural schematic diagram of the air intake mechanism in the present invention;

[0022] Figure 5 The present invention Figure 1 Schematic diagram of the enlarged structure of part A.

[0023] In the figure: 1. mounting base; 2. driving mechanism; 21. driving chamber; 22. mounting block; 23. double-headed driving motor; 24. first rotating rod; 25. second rotating rod; 3. air intake mechanism; 31. connecting rod; 32. fixing base; 33. first air inlet hole; 34. second air inlet hole; 35. wind shield; 4. cooling mechanism; 41. liquid storage chamber; 42. ventilation pipe; 43. air inlet funnel; 44. air delivery blade; 5. exhaust mechanism; 51. fixing ring; 52. first filter screen; 53. exhaust blade; 54. exhaust hole; 6. second filter screen; 7. threaded rod; 8. threaded groove; 9. rotating blade; 10. mounting column. DETAILED DESCRIPTION

[0024] The preferred embodiments of the present invention are described below in conjunction with the accompanying drawings. It should be understood that the preferred embodiments described herein are only used to illustrate and explain the present invention, and are not used to limit the present invention.

[0025] Example 1

[0026] like Figure 1-5 As shown, the present invention provides a heat dissipation structure for an engine of a drone, including a mounting seat 1, a driving mechanism 2 is arranged inside the mounting seat 1, an air intake mechanism 3 is arranged at the top of the mounting seat 1, a cooling mechanism 4 is arranged inside the driving mechanism 2, and an exhaust mechanism 5 is arranged at the bottom of the mounting seat 1, and both the air intake mechanism 3 and the exhaust mechanism 5 are connected to the driving mechanism 2.

[0027] Among them, the driving mechanism 2 includes a driving cavity 21, the driving cavity 21 is opened inside the mounting base 1, a mounting block 22 is fixedly connected to the inner cavity wall of the driving cavity 21, a double-headed driving motor 23 is fixedly installed inside the mounting block 22, the upper output end of the double-headed driving motor 23 is fixedly connected to a first rotating rod 24, the first rotating rod 24 and the lower output end of the double-headed driving motor 23 are fixedly connected to a second rotating rod 25, the lower end rod wall of the second rotating rod 25 is rotatably connected to the bottom side wall of the mounting base 1 through a bearing, and the lower end of the second rotating rod 25 passes through the lower surface of the mounting base 1 and extends downward.

[0028] Among them, the air intake mechanism 3 includes a connecting rod 31, which is rotatably connected to the top cavity wall of the driving cavity 21 through a bearing, and the upper end of the connecting rod 31 passes through the upper surface of the mounting seat 1 and extends upward to and is fixedly connected to a semicircular fixed seat 32, and a plurality of first air inlet holes 33 are circumferentially penetrated on the rod wall of the connecting rod 31, and a plurality of second air inlet holes 34 are penetrated on the fixed seat 32 corresponding to the positions of the plurality of first air inlet holes 33, and the ends of the plurality of second air inlet holes 34 away from the first air inlet holes 33 are all connected to the outside, and a wind shield plate 35 is fixedly connected to the positions of the plurality of second air inlet holes 34 on the lower surface of the fixed seat 32.

[0029] Among them, the cooling mechanism 4 includes a liquid storage chamber 41, which is arranged in a circumferential shape inside the mounting block 22. Cooling liquid is arranged inside the liquid storage chamber 41. A plurality of ventilation pipes 42 are fixedly connected to the inside of the liquid storage chamber 41. The upper and lower ends of the plurality of ventilation pipes 42 respectively penetrate the corresponding cavity walls of the liquid storage chamber 41 and are connected to the driving cavity 21. A plurality of air inlet funnels 43 are arranged on the upper surface of the mounting block 22 corresponding to the pipe opening positions of the upper ends of the plurality of ventilation pipes 42. A plurality of air delivery blades 44 are fixedly connected to the rod wall of the connecting rod 31 located above the plurality of air inlet funnels 43.

[0030] Among them, the exhaust mechanism 5 includes a fixed ring 51, which is fixedly connected to the lower surface of the mounting base 1, and a first filter screen 52 arranged in an arc shape is fixedly connected to the lower end of the fixed ring 51. A plurality of exhaust blades 53 are fixedly connected to the lower surface of the second rotating rod 25 located outside the mounting base 1, and a plurality of exhaust holes 54 are penetrated through the lower surface of the mounting base 1 corresponding to the positions of the plurality of exhaust blades 53, and the upper ends of the plurality of exhaust holes 54 are connected to the driving chamber 21.

[0031] Among them, a second filter plate 6 is fixedly connected to the upper end openings of several first air inlet holes 33, a threaded rod 7 is fixedly connected to the center of the lower surface of the fixing seat 32, and a threaded groove 8 is opened on 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 passes through the notch of the threaded groove 8 and is threadedly connected in the threaded groove 8.

[0032] A plurality of rotating blades 9 are fixedly connected in a circumferential shape to the rod wall of the connecting rod 31 between the mounting seat 1 and the fixing seat 22 .

[0033] A mounting column 10 is fixedly connected to the side wall of one side of the mounting seat 1 .

[0034] Specifically, when the present invention is used, the double-headed drive motor 23 can be cooled by exchanging heat with the coolant in the liquid storage chamber 41. Then, during the operation of the double-headed drive motor 23, the double-headed drive motor 23 synchronously drives the first rotating rod 24 and the second rotating rod 25 to rotate. The first rotating rod 24 will synchronously drive the connecting rod 31 and the fixed seat 32 to rotate. When the fixed seat 32 rotates, the wind will be input into the first air inlet 33 through the wind shield 35, and then input into the drive chamber 21 through the second air inlet 34. At the same time, the connecting rod 31 moves the air delivery blades 44 to blow the incoming cold air downward, and it is successively transported downward through the air inlet funnel 43, the ventilation pipe 42 and the exhaust hole 54. The cold air in the ventilation pipe 42 can cool the coolant inside the liquid storage chamber 41 by heat exchange with the coolant, thereby extending the use time of the coolant to ensure the cooling of the engine and the use time. At the same time, the second rotating rod 25 will drive the exhaust blade 53 to extract air from the exhaust hole 54 and discharge the hot air to avoid hot air remaining inside. At the same time, the incoming cold air can be filtered by the second filter plate 6, which will block impurities in the second air inlet hole 34. At this time, the fixed seat 32 can be rotated to release the threaded connection between the threaded rod 7 and the threaded groove 8. At this time, the fixed seat 32 can be taken out, and the second air inlet hole 34 in the fixed seat 32 can be cleaned for subsequent use.

[0035] Finally, it should be noted that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or replace some of the technical features therein by equivalents. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A heat dissipation structure for an engine of an unmanned aerial vehicle, characterized in that: The mounting seat (1) comprises a driving mechanism (2) disposed inside the mounting seat (1), an air intake mechanism (3) disposed at the top of the mounting seat (1), a cooling mechanism (4) disposed inside the driving mechanism (2), and an exhaust mechanism (5) disposed at the bottom of the mounting seat (1), wherein the air intake mechanism (3) and the exhaust mechanism (5) are both connected to the driving mechanism (2); The air intake mechanism (3) comprises a connecting rod (31), the connecting rod (31) being rotatably connected to the top cavity wall of the driving cavity (21) via a bearing, the upper end of the connecting rod (31) passing through the upper surface of the mounting seat (1) and extending upward to and being fixedly connected to a semicircular fixed seat (32), a plurality of first air intake holes (33) being circumferentially penetrated through the rod wall of the connecting rod (31), a plurality of second air intake holes (34) being penetrated through the fixed seat (32) at positions corresponding to the plurality of first air intake holes (33), the ends of the plurality of second air intake holes (34) being away from the first air intake holes (33) being connected to the outside, and a wind shield (35) being fixedly connected to the positions of the plurality of second air intake holes (34) on the lower surface of the fixed seat (32); A second filter plate (6) is fixedly connected to the upper 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 provided on 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) passes through the notch of the threaded groove (8) and is threadedly connected in the threaded groove (8); A plurality of rotating blades (9) are fixedly connected in a circumferential manner to the rod wall of the connecting rod (31) located between the mounting seat (1) and the fixing seat (32).

2. The heat dissipation structure for an engine of an unmanned aerial vehicle according to claim 1, characterized in that: The driving mechanism (2) comprises a driving cavity (21), wherein the driving cavity (21) is opened inside the mounting seat (1), a mounting block (22) is fixedly connected to the inner cavity wall of the driving cavity (21), a double-headed driving motor (23) is fixedly installed inside the mounting block (22), an upper output end of the double-headed driving motor (23) is fixedly connected to a first rotating rod (24), and a lower output end of the double-headed driving motor (23) is fixedly connected to a second rotating rod (25), a lower end wall of the second rotating rod (25) is rotatably connected to the bottom side wall of the mounting seat (1) via a bearing, and the lower end of the second rotating rod (25) passes through the lower surface of the mounting seat (1) and extends downward.

3. The heat dissipation structure for an engine of a drone according to claim 1, characterized in that: The cooling mechanism (4) comprises a liquid storage cavity (41), the liquid storage cavity (41) is arranged in a circumferential shape inside the mounting block (22), a cooling liquid is arranged inside the liquid storage cavity (41), a plurality of ventilation pipes (42) are fixedly connected inside the liquid storage cavity (41), upper and lower ends of the plurality of ventilation pipes (42) respectively penetrate corresponding cavity walls of the liquid storage cavity (41) and are connected to the driving cavity (21), a plurality of air inlet funnels (43) are arranged on the upper surface of the mounting block (22) at the positions of the upper ends of the plurality of ventilation pipes (42), and a plurality of air delivery blades (44) are fixedly connected to the rod wall of the connecting rod (31) located above the plurality of air inlet funnels (43).

4. The heat dissipation structure for an engine of an unmanned aerial vehicle according to claim 1, characterized in that: The exhaust mechanism (5) comprises a fixing ring (51), the fixing ring (51) being fixedly connected to the lower surface of the mounting seat (1), the lower end of the fixing ring (51) being fixedly connected to a first filter screen plate (52) arranged in an arc shape, a plurality of exhaust blades (53) being fixedly connected to the lower surface of a second rotating rod (25) located outside the mounting seat (1), a plurality of exhaust holes (54) being penetrated through the lower surface of the mounting seat (1) corresponding to the positions of the plurality of exhaust blades (53), and the upper ends of the plurality of exhaust holes (54) are all in communication with the drive chamber (21).

5. The heat dissipation structure for an engine of a drone according to claim 1, characterized in that: A mounting column (10) is fixedly connected to a side wall on one side of the mounting seat (1).

Images