Wing radiator of a drone

Abstract

The present invention discloses a wing radiator of an unmanned aerial vehicle, the unmanned aerial vehicle comprises a fuselage and a pair of wings symmetrically arranged on both sides of the fuselage, an engine is arranged on the fuselage, a water jacket is arranged on the engine, and the characteristic is that a pair of wing radiators are arranged, and the pair of wing radiators are respectively integrally formed on the pair of wings, at least one side of the upper side and the lower side of each wing is provided with a heat dissipation surface of the wing radiator, the heat dissipation surface is exposed to the outside air, and the pair of wing radiators are both connected to the water jacket through a circulation pipeline, and a driving pump is arranged on the circulation pipeline, and the cooling fluid flows in a closed circulation between the pair of wing radiators and the water jacket under the action of the driving pump. The wing radiator provided by the present invention does not need to open an air bleed port outside the aircraft, and directly uses the airflow outside the aircraft for heat dissipation, which can greatly reduce the aerodynamic resistance of the entire aircraft, improve the endurance of the aircraft, and reduce fuel consumption.

Description

Technical Field

[0001] The invention relates to the technical field of heat dissipation of unmanned aerial vehicles, and in particular to a wing heat sink of a unmanned aerial vehicle. Background Art

[0002] In recent years, drones have become a new and popular industry both at home and abroad, and have broad application prospects in various industries and military fields. At present, the general cruising speed of drones at home and abroad is about 200KM / h. They have the advantages of low cost, easy use and maintenance, good fuel economy and high reliability. They are widely used in intelligence reconnaissance, security surveillance, anti-terrorism operations and civilian fields.

[0003] The high lift-to-drag ratio (generally not less than 15) and long flight time (generally greater than 20 hours) of medium and low-speed UAVs make them far more sensitive to drag than weight. The radiator is the core component that provides cooling for the engine. The heat dissipation of the UAV, which is approximately equivalent to half of the engine output power, needs to be dissipated by the radiator. Generally, the radiator requires an air duct outside the aircraft to introduce low-temperature air from the outside to dissipate the heat. Therefore, while providing heat dissipation, the radiator will generate greater resistance, accounting for about 10% of the aerodynamic resistance of the entire aircraft, resulting in poor endurance and high fuel consumption of the UAV. Summary of the invention

[0004] In view of the deficiencies in the prior art, the present invention provides a wing radiator for an unmanned aerial vehicle. The wing radiator does not require an air duct outside the aircraft, but directly utilizes the external airflow of the aircraft for heat dissipation, which can greatly reduce the aerodynamic resistance of the entire aircraft, improve the aircraft's endurance and reduce fuel consumption.

[0005] The present invention is achieved through the following technical solutions:

[0006] A wing radiator for an unmanned aerial vehicle, the unmanned aerial vehicle comprising a fuselage and a pair of wings symmetrically arranged on both sides of the fuselage, an engine being arranged on the fuselage, and a water jacket being arranged on the engine, characterized in that a pair of wing radiators are arranged, and the pair of wing radiators are respectively integrally formed on the pair of wings, at least one of the upper side and the lower side of each wing is provided with a heat dissipation surface of the wing radiator, the heat dissipation surface is exposed to the outside air, and the pair of wing radiators are both connected to the water jackets through a circulation pipeline, and a driving pump is arranged on the circulation pipeline, and a cooling fluid circulates in a closed manner between the pair of wing radiators and the water jackets under the action of the driving pump.

[0007] Furthermore, the pair of wing radiators are distributed centrally and symmetrically with respect to the fuselage.

[0008] Furthermore, the wing radiator includes an upper heat sink and a lower heat sink located on the outside of the wing radiator and arranged opposite to each other, the upper heat sink is integrally formed with the upper panel surface of the wing, the lower heat sink is integrally formed with the lower panel surface of the wing, and a receiving space for the cooling fluid to flow is formed between the upper heat sink and the lower heat sink.

[0009] Furthermore, the wing radiator also includes an upper fin and a lower fin located between the upper heat sink and the lower heat sink, the upper fin is brazed to the upper heat sink to form a first flow cavity, the lower fin is brazed to the lower heat sink to form a second flow cavity, the first flow cavity and the second flow cavity are distributed along the thickness direction of the wing radiator and are both connected to the water jacket.

[0010] Furthermore, the wing radiator also includes a partition plate located between the upper fin and the lower fin, and two sides of the partition plate are respectively brazed to the upper heat dissipation plate and the lower heat dissipation plate.

[0011] Furthermore, a surface of the upper fin facing the upper heat sink and a surface of the lower fin facing the lower heat sink are both provided with flow channels, and the cooling fluid flows along the direction of the flow channels.

[0012] Furthermore, the wing radiator is provided with a liquid outlet and a liquid inlet which are connected to the first flow cavity and the second flow cavity at the same time, and the liquid outlet and the liquid inlet are both connected to the water jacket through the circulation pipeline.

[0013] Furthermore, a plurality of fins evenly distributed at intervals are provided on the heat dissipation surfaces of the upper heat dissipation plate and the lower heat dissipation plate, and the direction of the fins is consistent with the flow direction of the external airflow.

[0014] Furthermore, gas channels for external air flow are formed between adjacent fins among the plurality of fins.

[0015] Furthermore, graphene is plated on the heat dissipation surfaces on both sides of the wing heat sink.

[0016] Compared with the prior art, the advantages of the present invention are:

[0017] 1. By integrally molding the wing radiator on the wing, and the heat dissipation surfaces on both sides of the wing radiator are located above and below the wing respectively and are exposed to the outside air, the wing radiator does not need to have an external air bleed port on the aircraft, and directly uses the external airflow of the aircraft for heat dissipation, which can greatly reduce the aerodynamic resistance of the entire aircraft. Compared with the traditional external air bleed port solution, the resistance is reduced by more than 50%, thereby improving the aircraft's endurance and reducing fuel consumption.

[0018] 2. The wing and the heat sink are integrally formed, and there is no welding scar or other structure on the wing surface, which improves the surface quality of the wing 2 and the stability of the airflow.

[0019] 3. By arranging upper fins and lower fins between the upper heat sink and the lower heat sink, the upper fins are brazed to form a first flow cavity, and the lower fins are brazed to form a second flow cavity. The first flow cavity and the second flow cavity are distributed along the thickness direction of the wing radiator and are both connected to the water jacket. By arranging a double-layer flow cavity, the efficiency of heat exchange can be improved.

[0020] 4. By setting flow channels on the fins, on the one hand, the utilization rate of the space of the first flow cavity and the second flow cavity is improved, and on the other hand, the overall weight can be reduced and the amount of cooling fluid flowing per unit time can be increased to improve the heat dissipation performance of the product.

[0021] 5. By using gas-liquid graphene deposition technology to coat a layer of graphene on the heat dissipation surfaces on both sides of the wing radiator, the product's thermal infrared radiation and temperature uniformity performance are improved, thereby improving the product's overall thermal performance and surface corrosion resistance. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 This is a principle block diagram of a wing radiator of a UAV according to an embodiment of the present invention;

[0023] Figure 2 This is a partial structural diagram of the UAV;

[0024] Figure 3 This is an exploded view of the wing radiator;

[0025] Figure 4 This is a top view of the drone;

[0026] Figure 5 It is a partial structural schematic diagram of the fin;

[0027] Figure 6 A cross-sectional view of the wing radiator.

[0028] 1. Fuselage; 10. Engine; 2. Wing; 3. Water jacket; 4. Wing radiator; 40. Heat dissipation surface; 41. Upper heat sink; 42. Lower heat sink; 43. Upper fin; 44. Lower fin; 45. Partition; 46. Flow channel; 461. First flow; 462. Second flow; 463. Third flow; 464. Fourth flow; 465. Fifth flow; 466. Sixth flow; 467. Seventh flow; 47. Liquid outlet; 48. Liquid inlet; 49. Rib; 490. Gas channel; 5. Circulation pipeline; 6. Drive pump. DETAILED DESCRIPTION

[0029] The following is a further non-restrictive detailed description of the technical solution of the invention in conjunction with the preferred embodiments and the accompanying drawings. In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate the orientation or position relationship based on the orientation or position relationship shown in the accompanying drawings. In addition, the terms "first" and "second" are used only for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "multiple" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and cannot be understood as limitations on the present invention.

[0030] like Figure 1-Figure 6As shown, a wing radiator of an unmanned aerial vehicle according to an embodiment of the present invention, wherein the unmanned aerial vehicle comprises a fuselage 1 and a pair of wings 2 symmetrically arranged on both sides of the fuselage 1, an engine 10 is arranged on the fuselage 1, a water jacket 3 is arranged on the engine 10, a pair of wing radiators 4 are arranged, and the pair of wing radiators 4 are respectively integrally formed on the pair of wings 2, at least one side of the upper side and the lower side of each wing 2 is provided with a heat dissipation surface 40 of the wing radiator 4, and the heat dissipation surface 40 is exposed to the outside air, and the pair of wing radiators 4 are connected to the water jacket 3 through a circulation pipe 5, and a driving pump 6 is arranged on the circulation pipe 5, and the cooling fluid circulates in a closed manner between the pair of wing radiators 4 and the water jacket 3 under the action of the driving pump 6. In this embodiment, the upper and lower sides of each wing 2 are provided with a heat dissipation surface 40 of the wing radiator 4. When working, the heat generated by the engine 10 is absorbed by the cooling fluid in the water jacket 3. The cooling fluid that absorbs the heat is converted from a low-temperature fluid to a high-temperature fluid. Driven by the driving pump 6, the high-temperature fluid enters the wing radiator 4 from the water jacket 3. During the operation of the UAV, the external cold air flow will cool down the high-temperature fluid in the wing radiator 4 on the wing 2. The high-temperature fluid is converted from a high-temperature fluid to a low-temperature fluid again under the action of the external cold air flow. The low-temperature fluid returns to the water jacket 3 again under the drive of the driving pump 6, and the cycle is repeated to achieve uninterrupted cooling of the engine 10. In the present invention, the wing radiator 4 is integrally formed on the wing 2. Specifically, the various components of the wing radiator 4 are brazed first, and then the wing radiator 4 is integrally machined on the wing 2. The heat dissipation surfaces 40 on both sides of the wing radiator 4 are respectively located above and below the wing 2 and are exposed to the outside air. The wing radiator does not need an external air bleed port on the aircraft, and directly uses the external airflow of the aircraft for heat dissipation, which can greatly reduce the aerodynamic resistance of the entire aircraft. Compared with the traditional external air bleed port solution, the resistance is reduced by more than 50%, thereby improving the aircraft's endurance and reducing fuel consumption.

[0031] like Figure 2 As shown, in this embodiment, a pair of wing radiators 4 are centrally symmetrically distributed about the fuselage 1, and a pair of wing radiators 4 are connected in series on both sides of the water jacket 3. Of course, an axially symmetrical distribution can also be selected to enable the cooling fluid to circulate between the wing radiators 4 and the water jacket 3.

[0032] like Figure 3 As shown, the wing radiator 4 includes an upper heat sink 41 and a lower heat sink 42 located on the outside of the wing radiator 4 and arranged opposite to each other. The upper heat sink 41 is integrally formed with the upper plate surface of the wing 2, and the lower heat sink 42 is integrally formed with the lower plate surface of the wing 2, and a receiving space for the flow of cooling fluid is formed between the upper heat sink 41 and the lower heat sink 42. By integrally processing and forming the wing 2 and the heat sink, there is no structure such as welding scar on the surface of the wing 2, thereby improving the surface quality of the wing 2 and the stability of the airflow.

[0033] The wing radiator 4 also includes an upper fin 43 and a lower fin 44 located between the upper heat sink 41 and the lower heat sink 42. The upper fin 43 is brazed to the upper heat sink 41 to form a first flow cavity, and the lower fin 44 is brazed to the lower heat sink 42 to form a second flow cavity. The first flow cavity and the second flow cavity are distributed along the thickness direction of the wing radiator 4 and are both connected to the water jacket 3. By setting a double-layer flow cavity, the efficiency of heat exchange can be improved. The high-temperature fluid flows out of the water jacket 3 and enters the first flow cavity and the second flow cavity of the wing radiator 4 at the same time. The high-temperature fluid in the first flow cavity is mainly cooled by the external airflow above the upper heat sink 41, and the high-temperature fluid in the second flow cavity is mainly cooled by the external airflow below the lower heat sink 42.

[0034] The wing radiator 4 also includes a partition 45 located between the upper fin 43 and the lower fin 44. Both sides of the partition 45 are brazed to the upper heat sink 41 and the lower heat sink 42 respectively to enhance the stability of the wing radiator 4 structure, thereby improving the stability of the wing 2 during operation.

[0035] The side of the upper fin 43 facing the upper heat sink 41 and the side of the lower fin 44 facing the lower heat sink 42 are both provided with flow channels 46, and the cooling fluid flows along the direction of the flow channels 46. By providing the flow channels 46, on the one hand, the utilization rate of the space of the first flow cavity and the second flow cavity is improved, and on the other hand, by providing the flow channels 46, the overall weight can be reduced and the amount of cooling fluid flowing per unit time can be increased, so as to improve the heat dissipation performance of the product.

[0036] like Figure 5 As shown, in this embodiment, the flow channel 46 is formed by connecting multiple paths in sequence. Specifically, the flow channel 46 includes a first flow 461, a second flow 462, a third flow 463, a fourth flow 464, a fifth flow 465, a sixth flow 466, and a seventh flow 467 that are connected in sequence, wherein the first flow 461, the third flow 463, the fifth flow 465 and the seventh flow 467 are distributed in parallel with each other and are designed perpendicular to the fuselage 1, and the second flow 462, the fourth flow 464 and the sixth flow 466 are distributed in parallel with each other and are designed parallel to the fuselage 1.

[0037] The wing radiator 4 is provided with a liquid outlet 47 and a liquid inlet 48 which are connected to the first flow cavity and the second flow cavity at the same time, and the liquid outlet 47 and the liquid inlet 48 are both connected to the water jacket 3 through the circulation pipe 5. The liquid outlet 47 and the liquid inlet 48 are connected to the first flow cavity and the second flow cavity at the same time, ensuring that the high-temperature fluid flowing out of the water jacket 3 can enter the first flow cavity and the second flow cavity at the same time through the liquid inlet 48, and after being cooled by the external cold air flow, the low-temperature fluid in the first flow cavity and the second flow cavity can flow into the water jacket 3 at the same time through the liquid outlet 47.

[0038] In this embodiment, the liquid inlet 48 is aligned with the position of the first flow path 461, and the liquid outlet 47 is aligned with the position of the seventh flow path 467. When the high-temperature fluid enters from the liquid inlet 48, it first enters the flow channel 46 from the first flow path 461, and finally exits the flow channel 46 from the seventh flow path 467, and flows out from the liquid outlet 47 and returns to the water jacket 3 again.

[0039] like Figure 4 As shown, in order to improve the cooling efficiency of the upper heat sink 41 and the lower heat sink 42, a plurality of fins 49 evenly spaced are provided on the heat dissipation surfaces 40 of the upper heat sink 41 and the lower heat sink 42 to increase the contact area between the upper heat sink 41 and the lower heat sink 42 and the external cold air. In this embodiment, the fins 49 are integrally formed on the upper heat sink 41 and the lower heat sink 42 by processing. It is worth noting that the fins 49 can be needle-shaped fins, sheet-shaped fins, etc. In order to reduce the wind resistance of the external airflow, sheet-shaped fins are selected in this embodiment, specifically rectangular fins, and the axial direction of the rectangular fins is ensured to be consistent with the direction of the external airflow to minimize the impact of wind resistance.

[0040] In order to prevent the fins 49 from being affected by the resistance of the external airflow, the setting direction of the fins 49 is consistent with the flow direction X of the external airflow, that is, the setting direction of the fins 49 is ensured to be consistent with the axial direction of the fuselage 1.

[0041] A gas channel 490 for external airflow is formed between adjacent fins 49 among several fins 49. When the external airflow exchanges heat with the high-temperature fluid in the wing radiator 4, the external airflow can flow along the direction of the gas channel 490, so that the external cold airflow can fully contact the side of the fin 49 and quickly take away the heat in the high-temperature fluid.

[0042] Graphene is plated on both side heat dissipation surfaces 40 of the wing radiator 4. Specifically, a layer of graphene is plated on both side heat dissipation surfaces 40 of the wing radiator 4 by gas-liquid graphene deposition technology to improve the thermal infrared radiation and temperature uniformity performance of the product, thereby improving the overall thermal performance and surface anti-corrosion performance of the product.

[0043] The above-mentioned embodiments only express several implementation methods of the present invention, and the description thereof is relatively specific and detailed, but it cannot be understood as limiting the scope of the patent of the present invention. It should be pointed out that, for ordinary technicians in this field, several variations and improvements can be made without departing from the concept of the present invention, which all belong to the protection scope of the present invention. Therefore, the protection scope of the patent of the present invention shall be subject to the attached claims.

Claims

1. A wing radiator for an unmanned aerial vehicle, the unmanned aerial vehicle comprising a fuselage (1) and a pair of wings (2) symmetrically arranged on both sides of the fuselage (1), an engine (10) being arranged on the fuselage (1), and a water jacket (3) being arranged on the engine (10), characterized in that: A pair of wing radiators (4) are provided, and the pair of wing radiators (4) are respectively integrally formed on the pair of wings (2); at least one of the upper side and the lower side of each wing (2) is provided with a heat dissipation surface (40) of the wing radiator (4); the heat dissipation surface (40) is exposed to the outside air; the pair of wing radiators (4) are both connected to the water jacket (3) through a circulation pipe (5); a driving pump (6) is provided on the circulation pipe (5); and a cooling fluid flows in a closed circulation between the pair of wing radiators (4) and the water jacket (3) under the action of the driving pump (6); The wing radiator (4) comprises an upper radiator plate (41) and a lower radiator plate (42) which are located on the outside of the wing radiator (4) and are arranged opposite to each other, the upper radiator plate (41) and the upper plate surface of the wing (2) are integrally formed, the lower radiator plate (42) and the lower plate surface of the wing (2) are integrally formed, and a receiving space for the cooling fluid to flow is formed between the upper radiator plate (41) and the lower radiator plate (42); The wing radiator (4) further comprises an upper fin (43) and a lower fin (44) located between the upper heat dissipation plate (41) and the lower heat dissipation plate (42); the upper fin (43) and the upper heat dissipation plate (41) are brazed to form a first flow cavity; the lower fin (44) and the lower heat dissipation plate (42) are brazed to form a second flow cavity; the first flow cavity and the second flow cavity are distributed along the thickness direction of the wing radiator (4) and are both connected to the water jacket (3).

2. The wing radiator according to claim 1, characterized in that: The pair of wing radiators (4) are distributed in a centrally symmetrical manner with respect to the fuselage (1).

3. The wing radiator according to claim 1, characterized in that: The wing radiator (4) further comprises a partition plate (45) located between the upper fin (43) and the lower fin (44), and two sides of the partition plate (45) are respectively brazed to the upper heat dissipation plate (41) and the lower heat dissipation plate (42).

4. The wing radiator according to claim 1, characterized in that: A flow channel (46) is provided on one side of the upper fin (43) facing the upper heat dissipation plate (41) and a flow channel (46) is provided on one side of the lower fin (44) facing the lower heat dissipation plate (42), and the cooling fluid flows along the direction of the flow channel (46).

5. The wing radiator according to claim 1, characterized in that: The wing radiator (4) is provided with a liquid outlet (47) and a liquid inlet (48) which are connected to both the first flow cavity and the second flow cavity, and the liquid outlet (47) and the liquid inlet (48) are both connected to the water jacket (3) through the circulation pipeline (5).

6. The wing radiator according to claim 1, characterized in that: A plurality of fins (49) evenly spaced and distributed are provided on the heat dissipation surfaces (40) of the upper heat dissipation plate (41) and the lower heat dissipation plate (42); the direction of the fins (49) is consistent with the flow direction (X) of the external airflow.

7. The wing radiator according to claim 6, characterized in that: A gas channel (490) for external air flow is formed between adjacent fins (49) among the plurality of fins (49).

8. The wing radiator according to claim 1, characterized in that: Graphene is plated on the heat dissipation surfaces (40) on both sides of the wing heat sink (4).

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