A heat dissipation structure for an aircraft motor
By installing heat dissipation copper fins and heat insulation pads between the motor and the pipe clamp in the drone aircraft, and using a fan to generate airflow, the problem of creep or melting caused by the transfer of heat from the motor to the pipe clamp is solved, achieving efficient heat dissipation and a compact structure.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- SHENZHEN HOBBYWING TECH CO LTD
- Filing Date
- 2025-07-21
- Publication Date
- 2026-07-03
AI Technical Summary
In drone aircraft, when the motor is connected to the tube clamp, the heat of the motor is transferred to the tube clamp, which may cause the non-metallic tube clamp to creep or melt. Existing heat dissipation structures have failed to effectively meet the heat dissipation requirements of the tube clamp.
A heat dissipation copper fin and a heat insulation pad are installed between the motor and the pipe clamp. The heat dissipation copper fin transfers the heat from the motor to the air in a timely manner, while the heat insulation pad prevents the heat from being transferred to the pipe clamp. Combined with the fan, airflow is formed to enhance the heat dissipation effect.
It improves the heat dissipation between the motor and the pipe clamp, reduces the risk of high-temperature creep or melting of non-metallic pipe clamps, and has a compact structure without changing the external dimensions.
Smart Images
Figure CN224459461U_ABST
Abstract
Description
Technical Field
[0001] This application relates to the field of heat dissipation technology, and in particular to a heat dissipation structure for an aircraft motor. Background Technology
[0002] In unmanned aerial vehicles (UAVs), the motor is typically connected to a pipe clamp. During flight, the motor generates a significant amount of heat. The heat dissipation between the motor and the pipe clamp usually relies solely on the motor's own cooling system. However, this cooling system is generally designed to meet only the motor's own cooling needs, without considering the cooling requirements of the pipe clamp. Because the pipe clamp is connected to the motor, the motor's heat is transferred to the pipe clamp. When the pipe clamp is made of non-metallic materials, the connection between the pipe clamp and the motor may experience creep or even melt due to high temperatures.
[0003] Therefore, there is a need for a motor cooling structure for aircraft that can improve the heat dissipation effect between the pipe clamp and the motor, and prevent the non-metallic pipe clamp from creeping or even melting due to high temperature. Utility Model Content
[0004] Therefore, it is necessary to provide a heat dissipation structure for the motor of an aircraft, and the specific technical solution is as follows.
[0005] A heat dissipation structure for an aircraft motor includes a motor, a heat dissipation copper sheet, a heat insulation pad, and a pipe clamp seat arranged and connected in one direction, so that an annular gap is formed between the motor and the pipe clamp seat.
[0006] The heat sink copper plate includes a mounting part and a heat dissipation part; the mounting part is attached to the motor; the heat dissipation part is connected to the mounting part and extends into the annular gap.
[0007] One side of the heat insulation pad is attached to the mounting part, and the other side is attached to the pipe clamp seat.
[0008] Furthermore, the heat dissipation part is bent relative to the mounting part and is in an inclined state, so that the heat dissipation part does not contact the motor or the pipe clamp seat.
[0009] Furthermore, the mounting part includes a heat-conducting ring and a first mounting ear; the heat insulation pad includes a heat insulation ring and a second mounting ear; and the mounting screw passes through the pipe clamp seat, the second mounting ear, and the first mounting ear before being connected to the motor.
[0010] Furthermore, the motor includes an outer rotor, on which a fan is provided, so that when the fan rotates, it generates an airflow from the tube clamp towards the motor channel.
[0011] Furthermore, the motor is provided with a first airflow channel, and the pipe clamp is provided with a second airflow channel, so that when the fan rotates, airflow is generated from the second airflow channel toward the first airflow channel.
[0012] Furthermore, the heat dissipation section includes a plurality of heat dissipation fins arranged around the outside of the mounting section, with airflow gaps formed between adjacent heat dissipation fins.
[0013] Furthermore, when the fan rotates, it creates an airflow that flows from the annular gap into the first airflow channel.
[0014] Furthermore, the heat insulation pad is a silicone pad.
[0015] Beneficial effects: 1. The heat dissipation structure for an aircraft motor provided by this utility model improves heat dissipation by setting a heat dissipation copper sheet and a heat insulation pad between the motor and the pipe clamp seat. The heat dissipation copper sheet promptly transfers the heat generated by the motor working coil and the accumulated heat inside the stator structure to the air, thereby improving the heat dissipation effect. The heat insulation pad prevents the heat dissipation copper sheet from directly contacting the pipe clamp seat, effectively isolating the heat transfer and reducing the risk of high-temperature creep or melting of the non-metallic material pipe clamp seat. Furthermore, the heat dissipation copper sheet and the heat insulation pad do not change the external dimensions between the motor and the pipe clamp seat, resulting in a compact structure.
[0016] 2. The motor heat dissipation structure for an aircraft provided by this utility model generates negative pressure through a fan, thereby creating an airflow from the tube clamp to the motor, improving the heat dissipation effect of the heat sink copper fins, and further preventing heat transfer to the tube clamp. Attached Figure Description
[0017] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0018] Figure 1 This is a schematic diagram of the overall heat dissipation structure;
[0019] Figure 2 This is an exploded view of the heat dissipation structure;
[0020] Figure 3 Cross-sectional view of the heat dissipation structure;
[0021] Figure 4 This is a top view of the copper heat sink.
[0022] Figure 5 This is a front view of the copper heat sink.
[0023] Explanation of reference numerals in the attached diagram: 1. Motor; 2. Copper heat sink; 3. Heat insulation pad; 4. Pipe clamp; 5. Mounting screw; 6. Annular gap;
[0024] 11. Fan; 12. First airflow channel; 13. Air outlet;
[0025] 21. Mounting section; 22. Heat dissipation section; 23. Heat conduction ring; 24. First mounting lug; 25. Heat dissipation fins;
[0026] 31. Heat insulation ring; 32. Second mounting lug;
[0027] 41. Upper casing; 42. Lower casing; 43. Second airflow channel; 44. Second air inlet. Detailed Implementation
[0028] To make the above-mentioned objectives, features, and advantages of this application more apparent and understandable, the specific embodiments of this application are described in detail below with reference to the accompanying drawings. Many specific details are set forth in the following description to provide a thorough understanding of this application. However, this application can be implemented in many other ways different from those described herein, and those skilled in the art can make similar modifications without departing from the spirit of this application. Therefore, this application is not limited to the specific embodiments disclosed below.
[0029] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application.
[0030] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.
[0031] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.
[0032] In this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.
[0033] It should be noted that when an element is referred to as being "fixed to" or "set on" another element, it can be directly on the other element or there may be an intervening element. When an element is considered to be "connected to" another element, it can be directly connected to the other element or there may be an intervening element. The terms "vertical," "horizontal," "upper," "lower," "left," "right," and similar expressions used herein are for illustrative purposes only and do not represent the only possible implementation.
[0034] Example
[0035] Reference Figure 1 and Figure 2 As shown, this embodiment provides a motor heat dissipation structure for an aircraft, including a motor 1, a heat dissipation copper fin 2, a heat insulation pad 3, and a pipe clamp seat 4; the motor 1, the heat dissipation copper fin 2, the heat insulation pad 3, and the pipe clamp seat 4 are arranged and connected along the axial direction of the motor 1. An annular gap 6, 32 is formed between the motor 1 and the pipe clamp seat 4, that is, a gap is formed between the non-mounting surfaces of the motor 1 and the pipe clamp seat 4.
[0036] Reference Figure 4 As shown, the heat sink 2 includes a mounting portion 21 and a heat dissipation portion 22. (Refer to...) Figure 3 As shown, the mounting part 21 is attached to the motor 1, specifically to the mounting surface of the motor 1. The heat sink copper plate 2 absorbs the heat generated by the coil inside the motor 1 and the heat accumulated in the stator socket. The heat dissipation part 22 is connected to the mounting part 21 and extends into the annular gap 6, conducting the heat absorbed by the heat sink copper plate 2 into the air, thereby improving the heat dissipation effect on the motor 1.
[0037] Reference Figure 3 As shown, one side of the heat insulation pad 3 is attached to the mounting part 21, and the other side is attached to the pipe clamp seat 4. The heat insulation pad 3 prevents heat from being transferred from the heat dissipation copper sheet 2 to the pipe clamp seat 4.
[0038] In this embodiment, the housing of the pipe clamp seat 4 is made of non-metallic material. The pipe clamp seat 4 includes an upper housing 41 and a lower housing 42, so that the upper housing 41 is in contact with the heat insulation pad 3.
[0039] The present invention provides a heat dissipation structure for an aircraft motor. By setting a heat dissipation copper sheet 2 and a heat insulation pad 3 between the motor 1 and the pipe clamp seat 4, the heat dissipation copper sheet 2 promptly transfers the heat generated by the working coil of the motor 1 and the accumulated heat inside the stator structure to the air, thereby improving the heat dissipation effect. The heat insulation pad 3 prevents the heat dissipation copper sheet 2 from directly contacting the pipe clamp seat 4, effectively isolating the heat transfer and reducing the risk of high-temperature creep or melting of the non-metallic material pipe clamp seat 4. Furthermore, the heat dissipation copper sheet 2 and the heat insulation pad 3 do not change the external dimensions between the motor 1 and the pipe clamp seat 4, resulting in a compact structure.
[0040] Specifically, refer to Figure 5 As shown, the heat dissipation part 22 is bent relative to the mounting part 21 and is in an inclined state, so that the heat dissipation part 22 does not contact the motor 1 or the pipe clamp seat 4. This allows the heat dissipation part 22 to better conduct heat to the air and ensure the heat dissipation effect.
[0041] Specifically, refer to Figure 2 As shown, the mounting part 21 includes a heat-conducting ring 23 and a first mounting ear 24; the heat insulation pad 3 includes a heat insulation ring 31 and a second mounting ear 32; and the mounting screw 5 passes through the pipe clamp seat 4, the second mounting ear 32, and the first mounting ear 24 and is connected to the motor 1.
[0042] Specifically, refer to Figure 3 As shown, the motor 1 includes an outer rotor, on which a fan 11 is mounted. When the fan 11 rotates, it generates an airflow from the tube clamp 4 toward the flow channel of the motor 1. The airflow carries heat toward the motor 1, thereby improving the heat dissipation effect of the heat sink 2 and further preventing heat from being transferred to the tube clamp 4.
[0043] Specifically, refer to Figure 3 As shown, the motor 1 has a first airflow channel 12, and the pipe clamp 4 has a second airflow channel 43, so that when the fan 11 rotates, airflow is generated from the second airflow channel 43 toward the first airflow channel 12. When the fan 11 rotates, airflow is generated from the annular gap 6 toward the first airflow channel 12. The annular gap 6 serves as the first air inlet, and a second air inlet 44 communicating with the second airflow channel 43 is provided at the bottom of the pipe clamp 4; an air outlet 13 is provided at the top of the motor 1.
[0044] The airflow forms from the second air inlet 44 outside the tube clamp 4 to the second airflow channel 43, through the annular gap 6, through the first airflow channel 12 and then to the air outlet 13, and from the annular gap 6 to the first airflow channel 12 and then to the air outlet 13, respectively, thereby improving the heat dissipation effect of the heat sink copper plate 2 and preventing heat from being transferred to the tube clamp 4.
[0045] Specifically, refer to Figure 4As shown, the heat dissipation part 22 includes a plurality of heat dissipation fins 25 arranged around the outer side of the mounting part 21, with airflow gaps formed between adjacent heat dissipation fins 25. This ensures the passage of airflow at the heat dissipation copper plate 2 and guarantees the heat dissipation effect of the heat dissipation copper plate 2.
[0046] Specifically, the heat insulation pad 3 is a silicone pad, which has high heat insulation properties and effectively prevents heat from being transferred to the pipe clamp seat 4.
[0047] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.
[0048] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the patent application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.
Claims
1. An electric motor cooling structure for an aircraft, comprising: It includes a motor, a heat sink, a heat insulation pad, and a pipe clamp that are arranged and connected in one direction, so that an annular gap is formed between the motor and the pipe clamp. The heat sink copper fin includes a mounting part and a heat dissipation part; the mounting part is attached to the motor; the heat dissipation part is connected to the mounting part and extends into the annular gap; One side of the heat insulation pad is attached to the mounting part, and the other side is attached to the pipe clamp seat.
2. The motor heat dissipation structure of an aircraft according to claim 1, wherein The heat dissipation part is bent relative to the mounting part and is in an inclined state, so that the heat dissipation part does not come into contact with the motor or the pipe clamp seat.
3. The motor heat sink structure of claim 1, wherein, The mounting part includes a heat-conducting ring and a first mounting ear; the heat insulation pad includes a heat insulation ring and a second mounting ear; and the mounting screw passes through the pipe clamp seat, the second mounting ear, and the first mounting ear before being connected to the motor.
4. The motor heat sink structure of claim 1, wherein, The motor includes an outer rotor, on which a fan is provided, so that when the fan rotates, it generates an airflow from the tube clamp towards the motor channel.
5. The motor heat sink structure of claim 4, wherein, The motor has a first airflow channel and the pipe clamp has a second airflow channel, so that when the fan rotates, airflow is generated from the second airflow channel toward the first airflow channel.
6. The motor heat sink structure of claim 5, wherein, The heat dissipation section includes a plurality of heat dissipation fins arranged around the outside of the mounting section, with airflow gaps formed between adjacent heat dissipation fins.
7. The motor heat sink structure of claim 5, wherein, When the fan rotates, it creates an airflow that flows from the annular gap into the first airflow channel.
8. The motor heat sink structure of claim 1, wherein, The heat insulation pad is a silicone pad.