Hydrogen fuel cell unmanned aerial vehicle with liquid cooling heat dissipation structure

Abstract

The invention discloses a hydrogen fuel cell unmanned aerial vehicle with a liquid cooling heat dissipation structure. The hydrogen fuel cell unmanned aerial vehicle comprises an unmanned aerial vehicle body, a hydrogen fuel cell system, a heat dissipation vehicle arm with an inner cavity, a liquid distribution header pipe, a first water pump, a liquid guide downstream pipe, a liquid guide backflow pipe, a propeller, a flow uniformizing mechanism and a liquid collection header pipe. Cooling liquid absorbing heat is evenly distributed to each liquid distribution branch pipe through the liquid distribution header pipe and the flow uniformizing mechanism and then flows into the liquid guide downstream pipe and the liquid guide backflow pipe in the heat dissipation machine arm for heat dissipation, rotor wing wind of a propeller is fully utilized for heat convection heat dissipation, and then the cooling liquid is circulated into a hydrogen fuel cell system through the liquid collection header pipe. Water-cooling heat dissipation is adopted in the whole process, meanwhile, a water-cooling heat dissipation device is combined with the unmanned aerial vehicle frame, the vehicle arms of the unmanned aerial vehicle frame serve as heat dissipation devices, an additional heat dissipation device structure can be omitted, the weight can be reduced, rotor wing wind is fully utilized for heat convection, heat dissipation fan components can be omitted, the weight is reduced, and therefore the heat dissipation effect is guaranteed, and meanwhile the heat dissipation efficiency is improved. And the weight is reduced.

Description

Technical Field

[0001] The present invention belongs to the field of hydrogen fuel cell drones, and in particular relates to a hydrogen fuel cell drone with a liquid cooling and heat dissipation structure. Background Art

[0002] As a product of the 21st century, drones play a vital role in promoting industrial production and military development. Currently, drones on the market are mainly powered by lithium batteries. In order to increase the range, they have to carry larger batteries or larger capacities. When the battery accounts for a large proportion, it will increase the weight and increase the flight energy consumption. Many existing drones will use hydrogen fuel cells for endurance, but the existing hydrogen fuel cells must solve the problem of heat dissipation. The existing drone cooling system is usually air-cooled. At that time, the radiator and the cooling fan need to use strong metal as the installation and manufacturing material; at the same time, in order to achieve better heat dissipation effect and obtain a larger heat dissipation surface area, the volume of the radiator and the blades of the cooling fan need to reach a certain level, which will also cause the body to be too large in size and weight, greatly affecting the endurance and fuel efficiency of the drone. Therefore, it is necessary to propose a hydrogen fuel cell drone with a liquid cooling structure. Summary of the invention

[0003] The purpose of the present invention is to solve the problems in the background technology and provide a hydrogen fuel cell drone with a liquid cooling and heat dissipation structure.

[0004] The above technical objectives of the present invention are achieved through the following technical solutions: A hydrogen fuel cell drone with a liquid cooling and heat dissipation structure comprises a drone fuselage, a hydrogen fuel cell system, a heat dissipation arm in an internal cavity, a liquid distribution main pipe, a first water pump, a liquid guide downstream pipe, a liquid guide return pipe, a propeller, a flow uniformity mechanism, and a liquid collection main pipe. The hydrogen fuel cell system is arranged in the middle of the drone fuselage, the heat dissipation arm is evenly distributed on the side wall of the drone fuselage along the circumferential direction, the inner wall of each heat dissipation arm is provided with the liquid guide downstream pipe and the liquid guide return pipe along the length direction, the output end of the hydrogen fuel cell system is connected to the inlet of the first water pump, and the first water pump is connected to the outlet of the first water pump. The outlet of the pump is connected to the liquid distribution main pipe, and the liquid distribution main pipe is provided with a liquid distribution branch pipe that cooperates with the heat sink arm. The liquid distribution branch pipe is connected to the inlet of the liquid guiding downstream pipe, the outlet of the liquid guiding downstream pipe and the inlet of the liquid guiding return pipe are connected through a pipeline, the outlet of the liquid guiding return pipe is connected to the inlet of the liquid converging main pipe, and the outlet of the liquid converging main pipe is connected to the input end of the hydrogen fuel cell system. The propeller is arranged above the heat sink arm, and the flow uniformity mechanism is provided in each liquid distribution branch pipe. The propeller can rotate. This is an existing mature technology for drones, so it will not be described in detail in this case.

[0005] The present invention uses a liquid distribution main pipe to evenly distribute the coolant after absorbing heat to each liquid distribution branch pipe through a uniform flow mechanism, and then flows into the liquid guide downstream pipe and the liquid guide return pipe in the heat dissipation arm for heat dissipation, fully utilizing the rotor wind of the propeller for heat convection heat dissipation, and then circulates to the hydrogen fuel cell system through the liquid collection main pipe. The whole process adopts water cooling for heat dissipation, and the effect is significant. At the same time, the water-cooled radiator is combined with the UAV frame, and the arm of the UAV frame is used as a radiator, which can reduce the weight by removing the additional radiator structure, and fully utilizing the rotor wind for heat convection, and can remove the heat dissipation fan component to reduce the weight, thereby ensuring the heat dissipation effect while reducing the weight.

[0006] Preferably, the flow uniforming mechanism includes a water inlet plate, a compression spring, a plug core, and a water inlet pipe. The water inlet pipe is fixedly connected to the liquid separation branch pipe. A fixed block is formed at the end of the water inlet pipe. The fixed block is provided with a conducting groove which communicates with the interior of the liquid separation branch pipe. The plug core is plugged in the conducting groove. The water inlet plate is fixedly connected to the end of the water inlet pipe. The compression spring is arranged between the plug core and the water inlet plate. More than three liquid conduction holes are provided on the top of the water inlet plate. The closer to the liquid separation branch pipe of the first water pump, the greater the force of the compression spring to press the plug core.

[0007] The present invention is fixedly connected with the liquid distribution branch pipe through a water inlet pipe, and the force of the compression spring pressing the plug core is used to control the position of the plug core in the conducting groove, thereby controlling the amount of coolant passing through. The elastic force of the compression spring of each uniform flow structure is different, so that coolant can be distributed to each liquid distribution branch, thereby uniformly distributing the coolant and improving the heat dissipation effect.

[0008] Preferably, the hydrogen fuel cell system includes a hydrogen fuel cell, a plate heat exchanger, and a second water pump. The output end of the hydrogen fuel cell is connected to the inlet of the second water pump, the outlet of the second water pump is connected to the heat medium inlet of the plate heat exchanger, the input end of the hydrogen fuel cell is connected to the heat medium outlet of the plate heat exchanger, the cold medium outlet of the plate heat exchanger is connected to the inlet of the first water pump, and the outlet of the liquid main pipe is connected to the cold medium inlet of the plate heat exchanger, and the plate heat exchanger is used for heat exchange.

[0009] Preferably, the heat sink arm includes a tube body, the liquid guiding downstream pipe and the liquid guiding return pipe are arranged on the left and right sides of the inner cavity of the tube body, and a heat sink structure is provided on the side walls of the tube body located on the liquid guiding downstream pipe and the liquid guiding return pipe. The present invention enhances the heat dissipation effect through the heat sink structure.

[0010] Preferably, the heat sink structure is a strip heat sink arranged along the length direction of the tube body, and more than three strip heat sinks are arranged in an array along the circumferential direction of the tube body, and the width of the strip heat sink located in the middle of the tube body to the strip heat sink away from the middle of the tube body gradually shortens.

[0011] The present invention adopts a strip-shaped heat sink such as a fin heat sink to expand the heat dissipation area and accelerate heat transfer.

[0012] Preferably, the heat sink structure is an arc-shaped heat sink arranged along the circumferential direction of the tube body, and a plurality of the arc-shaped heat sinks are arranged in an array along the length direction of the tube body.

[0013] The present invention adopts arc-shaped heat sinks and cooperates with the rotation of the propeller on the top. Compared with the arrangement of strip-shaped heat sinks, the wind force received between the heat sinks is not blocked, the heat dissipation area is expanded, the heat transfer is accelerated, and the heat dissipation effect is improved.

[0014] Preferably, a temperature sensor is also provided on the output end of the hydrogen fuel cell, and the arc-shaped heat sink and the tube body are detachably connected.

[0015] The present invention detects the temperature through a temperature sensor, so that before going out, the number of heat sinks can be selected according to hydrogen fuel cells of different powers, thereby ensuring the heat dissipation effect while reducing the weight as much as possible.

[0016] Preferably, a clamping column is provided at the bottom of the arc-shaped heat sink, an annular clamping ring is provided on the circumferential direction of the side wall of the clamping column, and an annular groove cooperating with the annular clamping ring is provided on the tube body.

[0017] The invention enables the arc-shaped heat sink to be detachably connected through the cooperation of the annular clamping ring and the annular groove.

[0018] Preferably, the space between the clamping column and the annular groove is also filled with thermally conductive silicone, which can enhance the connection between the arc-shaped heat sink and the tube body and enhance the heat conduction effect.

[0019] Preferably, the liquid separation main pipe and the liquid collection main pipe are both made of heat-conducting materials to enhance the overall heat conduction effect.

[0020] In summary, the beneficial effects of the present invention are: 1. The present invention uses a paging main pipe to evenly distribute the cooling liquid after absorbing heat to each liquid distribution branch pipe through a uniform flow mechanism, and then flows into the liquid guide downstream pipe and the liquid guide return pipe in the heat dissipation arm for heat dissipation, making full use of the rotor wind of the propeller for heat convection heat dissipation, and then circulates to the hydrogen fuel cell system through the liquid converging main pipe. The whole process adopts water cooling heat dissipation, and the effect is significant. At the same time, the water-cooled radiator is combined with the UAV frame, and the arm of the UAV frame is used as a radiator, which can reduce the weight by removing the additional radiator structure, and make full use of the rotor wind for heat convection, and can reduce the heat dissipation fan component to reduce the weight, thereby ensuring the heat dissipation effect while reducing the weight; 2. The present invention is fixedly connected with the liquid distribution branch pipe through the water inlet pipe, and the position of the plug core in the conducting groove is controlled by the force of the compression spring to press the plug core, thereby controlling the amount of coolant passing through. The elastic force of the compression spring of each uniform flow structure is different, so that each liquid distribution branch pipe can be distributed with coolant, thereby uniformly distributing the coolant and improving the heat dissipation effect; 3. The present invention adopts arc-shaped heat sinks to cooperate with the rotation of the propeller on the top. Compared with the arrangement of strip-shaped heat sinks, the wind force received between the heat sinks is not blocked, which expands the heat dissipation area, accelerates heat transfer, and improves the heat dissipation effect; 4. The present invention detects the temperature through a temperature sensor, so that before going out, the number of heat sinks can be selected according to the hydrogen fuel cells of different powers, thereby ensuring the heat dissipation effect while reducing the weight as much as possible. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 is a schematic diagram of the fuselage of the drone of the present invention; Figure 2 The present invention Figure 1 An enlarged schematic diagram of point B; Figure 3 is a schematic diagram of the arc-shaped heat sink of the present invention; Figure 4 is a schematic diagram of the flow uniforming mechanism of the present invention; Figure 5 It is a schematic diagram of the separation of the plug core and the conducting groove of the flow equalizing mechanism of the present invention; Figure 6 is a cross-sectional schematic diagram of the arc-shaped heat sink and the tube body of the present invention; Figure 7 The present invention Figure 6 An enlarged schematic diagram of point C; Figure 8 is an overall schematic diagram of the drone of the present invention; Fig. 9 is a schematic diagram of a strip heat sink of the present invention; Fig.10 The present invention Fig. 9 An enlarged schematic diagram of point A; Fig.11 It is a schematic diagram of the present invention without adding a plate heat exchanger. DETAILED DESCRIPTION

[0022] The following specific embodiments are merely explanations of the present invention and are not limitations of the present invention. After reading this specification, those skilled in the art may make modifications to the embodiments without any creative contribution as needed. However, such modifications are protected by the patent law as long as they are within the scope of the claims of the present invention.

[0023] The present invention will be described in detail below with reference to the accompanying drawings by way of embodiments.

[0024] Example 1

[0025] like Figure 1-2 As shown, a hydrogen fuel cell drone with a liquid cooling structure includes a drone body 1, a hydrogen fuel cell system 2, a heat sink arm 3 with an internal cavity, a liquid distribution main pipe 4, a first water pump 5, a liquid guide downstream pipe 6, a liquid guide return pipe 7, a propeller 8, a flow equalization mechanism 9, and a liquid collection main pipe 40. The hydrogen fuel cell system 2 is arranged in the middle of the drone body 1, and the heat sink arms 3 are evenly distributed on the side walls of the drone body 1 along the circumferential direction. The inner wall of each heat sink arm 1 is provided with the liquid guide downstream pipe 6 and the liquid guide return pipe 7 along the length direction. The output end of the hydrogen fuel cell system 2 is connected to the inlet of the first water pump 5, and the outlet of the first water pump 5 is connected to the liquid distribution main pipe 4. The liquid distribution main pipe 4 is provided with a liquid distribution branch pipe 401 that cooperates with the heat sink arm 3, and the liquid distribution branch pipe 401 is connected to the inlet of the liquid guide downstream pipe 6. The outlet of the liquid guide downstream pipe 6 and the inlet of the liquid guide return pipe 7 are connected through a pipeline. The outlet of the pipe 7 is connected to the inlet of the liquid collecting main pipe 40, the outlet of the liquid collecting main pipe 40 is connected to the input end of the hydrogen fuel cell system 2, the propeller 8 is arranged above the radiator arm 3, and each liquid distribution branch pipe 401 is provided with the flow uniformity mechanism 9; the hydrogen fuel cell system 2 includes a hydrogen fuel cell 21, a plate heat exchanger 22, and a second water pump 23, the output end of the hydrogen fuel cell 21 is connected to the inlet of the second water pump 23, the outlet of the second water pump 23 is connected to the hot medium inlet of the plate heat exchanger 22, the input end of the hydrogen fuel cell is connected to the hot medium outlet of the plate heat exchanger 22, the cold medium outlet of the plate heat exchanger is connected to the inlet of the first water pump 5, the outlet of the liquid collecting main pipe 40 is connected to the cold medium inlet of the plate heat exchanger 22, the liquid distribution main pipe 4 and the liquid collecting main pipe 40 are both made of heat conductive materials, and the cold source fluid channel in the plate heat exchanger adopts superconducting liquid, which is a new technology of superconducting heat transfer and high-efficiency heat exchange. The main function of superconducting liquid under normal pressure is to conduct electricity faster than water. Generally, it does not freeze at minus 40 degrees Celsius. Its boiling point is higher than that of water. Now many people use antifreeze instead, which is also cheap. The heat source fluid channel in the plate heat exchanger uses deionized antifreeze to facilitate later maintenance.

[0026] In order to reduce weight, the hydrogen fuel cell system 2 does not need to use a plate heat exchanger. The output end of the hydrogen fuel cell 2 is directly connected to the liquid distribution main pipe 4. The coolant introduced is deionized antifreeze, which can also achieve the effect of heat dissipation.

[0027] like Figure 4-5As shown, the flow uniforming mechanism 9 includes a water inlet plate 91, a compression spring 92, a plug core 93, and a water inlet pipe 94. The water inlet pipe 94 is fixedly connected to the liquid branch pipe 401. A fixing block 941 is formed at the end of the water inlet pipe 94. The fixing block 941 is provided with a conducting groove 942 which communicates with the interior of the liquid branch pipe 401. The plug core 93 is plugged in the conducting groove 942. The water inlet plate 91 is fixedly connected to the end of the water inlet pipe 414. The compression spring 92 is arranged between the plug core 453 and the water inlet plate 91. More than three liquid guide holes 95 are provided on the top of the water inlet plate 91. The closer to the liquid branch pipe 401 of the first water pump 5, the greater the force of the compression spring 92 pressing the plug core 93.

[0028] like Figure 3 As shown, the heat sink arm 3 includes a tube body 31, the liquid guiding downstream pipe 6 and the liquid guiding return pipe 7 are arranged on the left and right sides of the inner cavity of the tube body 31, and the tube body 31 is provided with a heat sink structure 90 on the side walls of the liquid guiding downstream pipe 6 and the liquid guiding return pipe 7. The heat sink structure 90 is an arc-shaped heat sink 902 arranged along the circumferential direction of the tube body 31, and a plurality of the arc-shaped heat sinks 902 are arranged in an array along the length direction of the tube body 31.

[0029] like Figure 2 As shown, a temperature sensor 211 is also provided on the output end of the hydrogen fuel cell 21, and the arc-shaped heat sink 902 and the tube body 31 are detachably connected.

[0030] like Figure 6-7 As shown, a clamping column 903 is provided at the bottom of the arc-shaped heat sink 902, and an annular clamping ring 904 is provided on the circumferential direction of the side wall of the clamping column 903. An annular groove 905 that cooperates with the annular clamping ring 904 is provided on the tube body 31, and thermal conductive silicone 906 is also filled between the clamping column 903 and the annular groove 905.

[0031] Working principle: Figure 1-10As shown, when in use, the plate heat exchanger transfers the absorbed heat cooling liquid through the liquid distribution main pipe 4 through heat exchange, and then the absorbed heat cooling liquid is evenly distributed to each liquid distribution branch pipe 401 through the flow equalization mechanism 9, and then flows into the liquid guide downstream pipe 6 and the liquid guide return pipe 7 in the heat dissipation arm 3 for heat dissipation. Through the heat sink structure 90, the heat dissipation area is expanded, the heat transfer is accelerated, and the rotor wind of the propeller 8 is fully utilized for heat convection heat dissipation. Then it is circulated to the hydrogen fuel cell system 2 through the liquid collection main pipe 40. The whole process adopts water cooling for heat dissipation, and the effect is significant. At the same time, the water-cooled radiator is combined with the UAV frame, and the arm of the UAV frame is used as a radiator. The additional radiator structure can be subtracted to reduce weight, and the rotor wind is fully utilized for heat convection. The heat dissipation fan component can be subtracted to reduce weight, thereby ensuring the heat dissipation effect while reducing weight.

[0032] Example 2

[0033] Different from Example 1, Figure 9-10 As shown, the heat sink structure 90 is a strip heat sink 901 arranged along the length direction of the tube body 31, and more than three strip heat sinks 901 are arranged in an array along the circumferential direction of the tube body 31. The width of the strip heat sink 901 located in the middle of the tube body 31 to the strip heat sink 901 away from the middle of the tube body 31 gradually shortens.

[0034] Example 3

[0035] like Fig.11 As shown, different from Example 1, the hydrogen fuel cell system 2 is a hydrogen fuel cell 21, the output end of the hydrogen fuel cell 21 is connected to the inlet of the first water pump 5, and the outlet of the liquid main pipe 40 is connected to the input end of the hydrogen fuel cell 21. Deionized antifreeze is used as the coolant throughout the process, and a plate heat exchanger is not used, which can reduce weight but increase the maintenance cost of the coolant.

Claims

1. A hydrogen fuel cell drone with a liquid cooling structure, characterized in that: The invention comprises an unmanned aerial vehicle body (1), a hydrogen fuel cell system (2), a heat sink arm (3) with an internal cavity, a liquid distribution main pipe (4), a first water pump (5), a liquid downstream pipe (6), a liquid return pipe (7), a propeller (8), a flow equalization mechanism (9), and a liquid collection main pipe (40), wherein the hydrogen fuel cell system (2) is arranged in the middle of the unmanned aerial vehicle body (1), the heat sink arms (3) are evenly distributed on the side wall of the unmanned aerial vehicle body (1) in an array along a circumferential direction, the inner wall of each heat sink arm (1) is provided with the liquid downstream pipe (6) and the liquid return pipe (7) along the length direction, and the output end of the hydrogen fuel cell system (2) is connected to the inlet of the first water pump (5). The outlet of the first water pump (5) is connected to a liquid distribution main pipe (4), the liquid distribution main pipe (4) is provided with a liquid distribution branch pipe (401) matched with the heat sink arm (3), the liquid distribution branch pipe (401) is connected to the inlet of the liquid guide downstream pipe (6), the outlet of the liquid guide downstream pipe (6) and the inlet of the liquid guide return pipe (7) are connected through a pipeline, the outlet of the liquid guide return pipe (7) is connected to the inlet of the liquid collection main pipe (40), the outlet of the liquid collection main pipe (40) is connected to the input end of the hydrogen fuel cell system (2), the impeller (8) is arranged above the heat sink arm (3), and each liquid distribution branch pipe (401) is provided with the flow equalization mechanism (9).

2. The hydrogen fuel cell drone with a liquid cooling structure according to claim 1, characterized in that: The flow-uniform mechanism (9) comprises a water inlet plate (91), a compression spring (92), a plug core (93), and a water inlet pipe (94); the water inlet pipe (94) is fixedly connected to the liquid separation branch pipe (401); a fixing block (941) is formed at the end of the water inlet pipe (94); a conducting groove (942) communicating with the interior of the liquid separation branch pipe (401) is formed on the fixing block (941); the plug core (93) is plugged in the conducting groove (942); the water inlet plate (91) is fixedly connected to the end of the water inlet pipe (414); the compression spring (92) is arranged between the plug core (453) and the water inlet plate (91); and more than three liquid guide holes (95) are formed on the top of the water inlet plate (91); the closer to the liquid separation branch pipe (401) of the first water pump (5), the greater the force of the compression spring (92) pressing the plug core (93) tightly.

3. The hydrogen fuel cell drone with a liquid cooling structure according to claim 1, characterized in that: The hydrogen fuel cell system (2) comprises a hydrogen fuel cell (21), a plate heat exchanger (22), and a second water pump (23); the output end of the hydrogen fuel cell (21) is connected to the inlet of the second water pump (23); the outlet of the second water pump (23) is connected to the heat medium inlet of the plate heat exchanger (22); the input end of the hydrogen fuel cell is connected to the heat medium outlet of the plate heat exchanger (22); the cold medium outlet of the plate heat exchanger is connected to the inlet of the first water pump (5); and the outlet of the liquid main pipe (40) is connected to the cold medium inlet of the plate heat exchanger (22).

4. The hydrogen fuel cell drone with a liquid cooling structure according to claim 1, characterized in that: The heat sink arm (3) comprises a tube body (31), the liquid guiding downstream tube (6) and the liquid guiding return tube (7) are arranged on the left and right sides of the inner cavity of the tube body (31), and a heat sink structure (90) is provided on the side walls of the tube body (31) located on the liquid guiding downstream tube (6) and the liquid guiding return tube (7).

5. The hydrogen fuel cell drone with a liquid cooling structure according to claim 4, characterized in that: The heat sink structure (90) is a strip heat sink (901) arranged along the length direction of the tube body (31), wherein more than three strip heat sinks (901) are arranged in an array along the circumferential direction of the tube body (31), and the width of the strip heat sink (901) located in the middle of the tube body (31) gradually decreases to that of the strip heat sink (901) away from the middle of the tube body (31).

6. The hydrogen fuel cell drone with a liquid cooling structure according to claim 5, characterized in that: The heat sink structure (90) is an arc-shaped heat sink (902) arranged along the circumferential direction of the tube body (31), and a plurality of the arc-shaped heat sinks (902) are arranged in an array along the length direction of the tube body (31).

7. The hydrogen fuel cell drone with a liquid cooling structure according to claim 5, characterized in that: A temperature sensor (211) is also provided on the output end of the hydrogen fuel cell (21), and the arc-shaped heat sink (902) and the tube body (31) are detachably connected.

8. The hydrogen fuel cell drone with a liquid cooling structure according to claim 5, characterized in that: A clamping column (903) is provided at the bottom of the arc-shaped heat sink (902), an annular clamping ring (904) is provided in the circumferential direction of the side wall of the clamping column (903), and an annular groove (905) cooperating with the annular clamping ring (904) is provided on the tube body (31).

9. The hydrogen fuel cell drone with a liquid cooling structure according to claim 9, characterized in that: Heat-conductive silica gel (906) is also filled between the clamping column (903) and the annular groove (905).

10. The hydrogen fuel cell drone with a liquid cooling structure according to claim 1, characterized in that: The liquid separation main pipe (4) and the liquid collection main pipe (40) are both made of heat-conducting materials.

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