A wind-cooled heat dissipation structure for the power system of a vertical takeoff and landing aircraft

Abstract

This utility model discloses a wind-cooled heat dissipation structure for the energy system of a vertical takeoff and landing (VTOL) aircraft, relating to the field of VTOL aircraft technology. It includes a frame, with a heat dissipation plate inside the frame and air ducts inside the heat dissipation plate. Battery heat conduction mechanisms are located at the top and bottom of the heat dissipation plate. Each battery heat conduction mechanism includes a shell, with bevels on the front of both shells. A battery is attached to the inside of each shell. The heat generated by the battery is first efficiently absorbed by thermally conductive silicone and conducted to the heat conduction plate and heat conduction rod, and then evenly transferred to the heat dissipation plate via thermally conductive grease, significantly improving heat conduction efficiency. The bevels on the shell constrict and accelerate the airflow, causing the high-speed airflow to concentrate and quickly pass through the heat dissipation plate via the air ducts. This device, without requiring additional power, converts flight drag into heat dissipation power, thereby significantly improving heat dissipation efficiency and extending battery life.

Description

Technical Field

[0001] This utility model belongs to the technical field of vertical take-off and landing aircraft, and specifically relates to a wind-cooled heat dissipation structure for the energy system of a vertical take-off and landing aircraft. Background Technology

[0002] Vertical takeoff and landing (VTOL) aircraft have broad application prospects in drones, urban air traffic, and military fields due to their unique takeoff and landing methods and flexible flight capabilities. With the rapid development of VTOL aircraft, the heat dissipation problem of their energy systems has become increasingly prominent. Especially during high-speed flight, the battery generates a lot of heat due to high current discharge. If it cannot be dissipated in time, the battery temperature will rise sharply, affecting performance and even causing safety hazards.

[0003] Traditional small vertical takeoff and landing (VTOL) aircraft install batteries directly inside the battery casing. Because the internal structure lacks heat conduction and cannot transfer heat to the outside of the casing, the heat dissipation efficiency is greatly reduced and the battery life is shortened. To solve the above problems, we provide a wind-cooled heat dissipation structure for the energy system of VTOL aircraft. Utility Model Content

[0004] The purpose of this invention is to provide a wind-cooled heat dissipation structure for the energy system of a vertical takeoff and landing (VTOL) aircraft, in order to solve the problem mentioned in the background art that traditional small VTOL aircraft directly install batteries inside the battery casing, which lacks a heat-conducting structure and cannot transfer heat to the outside of the casing, thus significantly reducing heat dissipation efficiency and shortening battery life.

[0005] The above-mentioned technical objective of this utility model is achieved through the following technical solution: a wind-cooled heat dissipation structure for the energy system of a vertical take-off and landing aircraft, including a frame, a heat dissipation plate is provided inside the frame, an air duct is opened inside the heat dissipation plate, and a battery heat conduction mechanism is provided at the top and bottom of the heat dissipation plate.

[0006] The battery heat conduction mechanism includes a housing, with beveled surfaces on the front of both housings. A battery is bolted inside the housing, and thermally conductive silicone abuts against the surface of the battery. A heat-conducting plate abuts against the surface of the thermally conductive silicone, and a heat-conducting rod is fixedly connected to the surface of the heat-conducting plate.

[0007] Preferably, one end of the heat-conducting rod is inserted into the interior of the thermally conductive silicone, thermally conductive grease is applied between the heat-conducting plate and the heat sink, and a first bolt is fitted inside the heat-conducting plate, with one end of the first bolt threadedly connected to the outer shell.

[0008] Preferably, inserts are bolted to both sides of the outer casing, and a second bolt is fitted inside the insert. One end of the second bolt is threaded to the frame, and a slot adapted to the insert is provided inside the frame.

[0009] Preferably, the frame has a through groove adapted to the heat sink plate inside, a locking block is bolted to the top of the frame, a guide rail is bolted to the inner side of the frame, and sliding grooves adapted to the guide rails are opened on both sides of the heat sink plate. The sliding grooves are slidably connected to the guide rails inside, and a third bolt is fitted on both sides of the frame. One end of the third bolt is threaded to the heat sink plate.

[0010] This utility model has the following beneficial effects:

[0011] The heat generated by the battery in this device is first efficiently absorbed by thermally conductive silicone and conducted to the heat-conducting plate and heat-conducting rod. Then, the heat is evenly transferred to the heat dissipation plate through thermally conductive grease, which significantly improves the heat conduction efficiency. The airflow is accelerated by the contraction of the outer shell, which concentrates the high-speed airflow and quickly passes through the heat dissipation plate through the air duct. Without the need for additional power, this device converts flight drag into heat dissipation power, thereby greatly improving heat dissipation efficiency and extending battery life. Attached Figure Description

[0012] Figure 1 This is a three-dimensional structural schematic diagram of the present invention;

[0013] Figure 2 This is an exploded view of the structure of this utility model;

[0014] Figure 3 This is an exploded view of a partial structure of this utility model;

[0015] Figure 4 This is an exploded view of a partial structure of this utility model.

[0016] Reference numerals: 1. Frame; 2. Heat sink; 3. Air duct; 4. Battery heat conduction mechanism; 41. Outer shell; 42. Battery; 43. Thermal conductive silicone; 44. Heat conduction plate; 45. Heat conduction rod; 46. First bolt; 47. Insert block; 48. Second bolt; 5. Through slot; 6. Locking block; 7. Guide rail; 8. Slide groove; 9. Third bolt; 10. Slot. Detailed Implementation

[0017] The present invention will be further described in detail below with reference to the accompanying drawings.

[0018] Example 1:

[0019] refer to Figure 1-4 A wind-cooled heat dissipation structure for the energy system of a vertical take-off and landing aircraft includes a frame 1, a heat dissipation plate 2 is provided inside the frame 1, an air duct 3 is provided inside the heat dissipation plate 2, and a battery heat conduction mechanism 4 is provided at the top and bottom of the heat dissipation plate 2.

[0020] The battery heat conduction mechanism 4 includes a housing 41. Both housings 41 have beveled surfaces on their front sides. A battery 42 is bolted inside the housing 41. The surface of the battery 42 abuts against a thermally conductive silicone 43. The surface of the thermally conductive silicone 43 abuts against a heat-conducting plate 44. A heat-conducting rod 45 is fixedly connected to the surface of the heat-conducting plate 44.

[0021] Specifically, by setting thermally conductive silicone 43, the thermally conductive silicone 43 can cover a large area of ​​the battery 42 and increase the contact surface between the thermally conductive silicone 43 and the battery 42, thereby improving the thermal conductivity. By setting thermally conductive rod 45, the thermally conductive rod 45 can be inserted into the interior of the thermally conductive silicone 43 to conduct heat. Through the inclined design of the two outer shells 41, the airflow is contracted. The airflow speed increases when passing through the contraction section, so that the high-speed airflow can be concentrated and pass through the air duct 3 and the heat sink 2. The high-speed airflow can carry away heat more efficiently, thereby improving the heat dissipation efficiency of the battery 42.

[0022] refer to Figure 2 , Figure 3 and Figure 4 One end of the heat-conducting rod 45 is inserted into the interior of the thermally conductive silicone 43. Thermally conductive grease is applied between the heat-conducting plate 44 and the heat sink 2. A first bolt 46 is fitted inside the heat-conducting plate 44. One end of the first bolt 46 is threaded to the outer shell 41. By setting thermally conductive grease, heat can be transferred between the heat-conducting plate 44 and the heat sink 2. By setting the first bolt 46, the heat-conducting plate 44 can be effectively fixed and installed.

[0023] refer to Figure 2 , Figure 3 and Figure 4 Both sides of the outer casing 41 are bolted with insert blocks 47. The insert blocks 47 are fitted with second bolts 48. One end of the second bolts 48 is threaded to the frame 1. The frame 1 has slots 10 that are compatible with the insert blocks 47. By setting the second bolts 48, the battery heat conduction mechanism 4 can be effectively installed.

[0024] refer to Figure 2 , Figure 3 and Figure 4 The frame 1 has a through groove 5 that matches the heat sink 2 inside. A locking block 6 is bolted to the top of the frame 1. A guide rail 7 is bolted to the inside of the frame 1. Both sides of the heat sink 2 have sliding grooves 8 that match the guide rails 7. The inside of the sliding grooves 8 is slidably connected to the guide rails 7. Both sides of the frame 1 are fitted with third bolts 9. One end of the third bolt 9 is threaded to the heat sink 2. By setting the third bolts 9, the heat sink 2 can be effectively installed and fixed.

[0025] Brief description of usage: The user attaches the device to the bottom of the aircraft using the clip 6. During rapid flight, the increased energy consumption causes the battery 42 to overheat. First, the thermal conductive silicone 43 conducts heat from the battery 42. Then, the heat-conducting plate 44 and the heat-conducting rod 45 conduct heat by directly contacting the thermal conductive silicone 43. Afterward, thermal conductive grease conducts heat from the heat-conducting plate 44 to the heat sink 2. During flight, the airflow on the front of the two outer shells 41 is compressed by the two inclined surfaces. The airflow speed increases when passing through the compression section, allowing the high-speed airflow to concentrate and pass through the air duct 3 and the heat sink 2. The high-speed airflow can more efficiently remove the heat from the heat sink 2, thereby improving the heat dissipation efficiency of the battery 42.

[0026] This specific embodiment is merely an explanation of the present utility model and is not intended to limit the present utility model. After reading this specification, those skilled in the art can make modifications to this embodiment without contributing any inventive step, but as long as they are within the scope of the claims of the present utility model, they are protected by patent law.

Claims

1. A wind-cooled heat dissipation structure for the energy system of a vertical takeoff and landing aircraft, comprising a frame (1), characterized in that: The frame (1) is provided with a heat sink (2) inside, and the heat sink (2) is provided with an air duct (3) inside. The top and bottom of the heat sink (2) are provided with battery heat conduction mechanisms (4). The battery heat conduction mechanism (4) includes a housing (41), and both housings (41) have a beveled surface on their front sides. A battery (42) is bolted inside the housing (41), and a thermally conductive silicone (43) abuts against the surface of the battery (42). A heat-conducting plate (44) abuts against the surface of the thermally conductive silicone (43), and a heat-conducting rod (45) is fixedly connected to the surface of the heat-conducting plate (44).

2. The air-cooled heat dissipation structure for the energy system of a vertical takeoff and landing aircraft according to claim 1, characterized in that: One end of the heat-conducting rod (45) is inserted into the interior of the thermally conductive silicone (43). Thermally conductive grease is applied between the heat-conducting plate (44) and the heat sink (2). A first bolt (46) is fitted inside the heat-conducting plate (44), and one end of the first bolt (46) is threadedly connected to the outer shell (41).

3. The air-cooled heat dissipation structure for the energy system of a vertical takeoff and landing aircraft according to claim 1, characterized in that: Both sides of the outer shell (41) are bolted with inserts (47), and a second bolt (48) is fitted inside the insert (47). One end of the second bolt (48) is threaded to the frame (1). The frame (1) has a slot (10) that matches the insert (47).

4. The air-cooled heat dissipation structure for the energy system of a vertical takeoff and landing aircraft according to claim 1, characterized in that: The frame (1) has a through groove (5) that matches the heat sink (2) inside. A locking block (6) is bolted to the top of the frame (1). A guide rail (7) is bolted to the inner side of the frame (1). Sliding grooves (8) that match the guide rail (7) are opened on both sides of the heat sink (2). The inside of the sliding groove (8) is slidably connected to the guide rail (7). A third bolt (9) is fitted on both sides of the frame (1). One end of the third bolt (9) is threadedly connected to the heat sink (2).

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