Heat dissipation device of closed equipment
By employing a heat dissipation device that uses a sliding connecting block to slide in the aircraft shell within a subsonic aircraft, the problem of heat dissipation under the influence of vibration and shock is solved, achieving efficient heat transfer and vibration reduction design, and meeting the requirements for lightweighting.
Patent Information
- Application Number
- CN202423215163.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-25
- Publication Date
- 2025-12-19
- Estimated Expiration
- 2034-12-25
AI Technical Summary
The heat dissipation structure of electronic equipment in subsonic aircraft is affected by vibration and impact, making it unable to effectively dissipate heat. In addition, traditional contact thermal resistance is large, making it difficult to meet the requirements of lightweight and efficient heat exchange.
A heat dissipation device is adopted that uses a sliding connecting block to slide with the aircraft shell. The sliding connecting block has an L-shaped structure and moves along the aircraft axis. The sliding groove restricts circumferential and radial displacement. The gap between the sliding connecting block and the shell is filled with thermally conductive silicone grease. The sliding connecting block is made of a high thermal conductivity metal material and is filled with a phase change medium to achieve rapid heat transfer.
It effectively reduces the impact of vibration and shock on electronic equipment, lowers contact thermal resistance, improves heat transfer efficiency, ensures that electronic equipment operates normally under allowable mechanical conditions, and quickly dissipates heat.
Smart Images
Figure CN223694177U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to electronic equipment heat dissipation technical field especially, relate to a heat dissipation device of closed equipment. BACKGROUND
[0002] In recent years, with the continuously developing of the function composite of subsonic aircraft, the heat power of the internal electronic components of the subsonic aircraft is continuously improved, and the requirement of the subsonic aircraft to the light weight and small size is continuously improved, leading to the rapid rise of the heat flux density of the electronic products in the subsonic aircraft, and the space and weight for the temperature control of the electronic equipment are continuously reduced, which brings great challenge to the thermal management.
[0003] The subsonic aircraft can quickly take away the heat through the convection heat exchange in the flight process, but the subsonic aircraft will generate a large vibration level in the flight process, and the electronic equipment cannot bear the large vibration level due to the strict requirement of the electronic equipment to the mechanical environment condition. The electronic equipment cannot be directly installed on the shell of the subsonic aircraft for heat dissipation, and the vibration reduction design is needed, which will generate great contact thermal resistance and cannot quickly export the heat.
[0004] Therefore, it is needed to optimize the installation mode of the electronic components in the closed subsonic aircraft through the structural design, to reduce the contact thermal resistance as far as possible on the basis of meeting the vibration reduction requirement, and to improve the heat exchange efficiency of the equipment. UTILITY MODEL CONTENT
[0005] In view of the above analysis, the utility model aims at providing a heat dissipation device of closed equipment to solve the problem that the existing heat dissipation structure is directly connected with the shell of the aircraft and is easily affected by the vibration impact to the performance of the electronic equipment.
[0006] The utility model mainly aims at realizing the following technical scheme:
[0007] A heat dissipation device of closed equipment, comprising: a sliding connection block, a heat dissipation plate and an aircraft shell; the sliding connection block is an L-shaped structural member, one end of which is fixedly connected to the outer side of the heat dissipation plate, and the other end is slidingly connected with the aircraft shell; the sliding connection block can displace along the axial direction of the aircraft shell; the inside of the heat dissipation plate is filled with heat absorption medium; the heat dissipation plate is used for dissipating heat of the electronic module and directly contacts with the heat generating device on the electronic module.
[0008] Further, a plurality of sliding connection blocks are fixedly connected on the outer side of the heat dissipation plate.
[0009] Further, a plurality of sliding grooves are arranged on the inner wall surface of the aircraft shell, and the sliding connection block is slidingly installed in the sliding groove.
[0010] Further, the sliding groove extends along the axial direction of the aircraft shell, and the sliding groove can limit the circumferential rotation and radial displacement of the sliding connecting block and the heat dissipation plate after the sliding connecting block is matched with the sliding groove.
[0011] Further, the sliding groove is a rectangular groove, and the bottom surface and the side surface of the sliding groove are in sliding contact with the three outer side surfaces of the sliding connecting block, respectively.
[0012] Further, a plurality of sliding connecting blocks are distributed along the circumference of the heat dissipation plate.
[0013] Further, the sliding connecting block is made of a metal material with high thermal conductivity.
[0014] Further, the inside of the heat dissipation plate is filled with a phase change medium.
[0015] Further, the gap between the sliding connecting block and the inner side wall surface of the aircraft shell is 0.1 mm.
[0016] Further, the gap between the sliding connecting block and the inner side wall surface of the aircraft shell is coated with thermal conductive silicone grease.
[0017] The technical scheme of the utility model can at least realize one of the following effects:
[0018] 1. The heat dissipation device of the utility model can block the transmission of vibration impact generated by the aircraft shell to the heat dissipation plate through the sliding contact between the sliding connecting block and the aircraft shell, thereby ensuring that the electronic components on the electronic module work in the allowable mechanical environment.
[0019] 2. The heat dissipation device of the utility model can conduct heat through the sliding contact between the sliding connecting block and the aircraft shell, and the heat generated by the electronic module is transmitted to the heat dissipation plate and the sliding connecting block, and then transmitted to the aircraft shell through the sliding connecting block, which greatly reduces the contact thermal resistance, and finally the heat on the aircraft shell can be quickly transmitted to the air, thereby forming a heat transfer path and realizing rapid heat dissipation, thereby improving the heat transfer efficiency.
[0020] In the utility model, the above technical schemes can be combined with each other to realize more preferred combination schemes. Other features and advantages of the utility model will be described in the subsequent specification, and some advantages can become apparent from the specification or can be understood by implementing the utility model. The purpose and other advantages of the utility model can be realized and obtained through the contents specifically pointed out in the specification and the drawings. BRIEF DESCRIPTION OF DRAWINGS
[0021] The accompanying drawings are for the purpose of illustrating preferred embodiments of the present application and are not to be construed as limiting the present application, wherein the same reference notations in different drawings represent the same elements.
[0022] Figure 1 A structural schematic view of a heat dissipation device of a closed device of the present application;
[0023] Figure 2 A schematic view of a cooperation mode of a heating device and a heat dissipation fin of the present application;
[0024] Figure 3 A schematic view of an installation state of a heat dissipation fin and a sliding connecting block of the present application.
[0025] Reference signs:
[0026] 1 - electronic module; 2 - sliding connecting block; 3 - heat dissipation plate; 4 - aircraft shell; 5 - heating device. DETAILED DESCRIPTION
[0027] The preferred embodiments of the present application will be described in detail below with reference to the drawings, wherein the drawings constitute a part of the present application and serve to explain the principles of the present application together with the embodiments of the present application, but are not intended to limit the scope of the present application.
[0028] Embodiment 1
[0029] One specific embodiment of the present application discloses a heat dissipation device of a closed device, as shown in Figure 1 , Figure 2 , Figure 3 , which comprises a sliding connecting block 2, a heat dissipation plate 3 and an aircraft shell 4; the sliding connecting block 2 is an L-shaped structural member, one end of which is fixedly connected to the outside of the heat dissipation plate 3, and the other end is in sliding connection with the aircraft shell 4; the sliding connecting block 2 can displace along the axial direction of the aircraft shell 4; the inside of the heat dissipation plate 3 is filled with heat-absorbing medium; the heat dissipation plate 3 is used for dissipating heat of an electronic module 1 and directly contacts with a heating device 5 on the electronic module 1.
[0030] The heat dissipation device of the present application, after the electronic equipment generates heat, quickly conducts the heat to the heat dissipation plate 3 of the metal structure through the form of contact heat dissipation, the heat dissipation plate 3 absorbs the heat and rises in temperature, quickly transmits the heat to the sliding connecting block 2, the sliding connecting block 2 directly contacts with the aircraft shell 4 and can also axially relatively move, since the sliding connecting block 2 and the aircraft shell 4 directly contact, the heat can also be quickly transmitted, and finally the heat is conducted to the aircraft shell, the external environment of the aircraft shell is high-speed airflow, which can quickly dissipate the heat to the air, so as to realize temperature control of the heating device.
[0031] In subsonic flight, the temperature of the airflow outside the aircraft shell 4 is much lower than the temperature of the electronic components, and the gas flow rate is high, which can quickly transfer the heat on the aircraft shell to the air, thereby forming a heat transfer path and achieving rapid heat dissipation.
[0032] Further, the sliding connection block 2 is fixedly connected to the outer side of the heat sink 3.
[0033] Further, a plurality of sliding grooves are arranged on the inner wall surface of the aircraft shell 4, and the sliding connection block 2 is slidingly installed in the sliding grooves. The aircraft shell 4 is the boundary between the inside and the outside, and in addition to meeting the structural support function, it also has the function of rapidly conducting heat to the outside through high-speed airflow convection heat exchange.
[0034] Further, the sliding grooves extend along the axial direction of the aircraft shell 4, allowing the sliding connection block 2 to displace along the axial direction of the aircraft shell 4; after the sliding connection block 2 cooperates with the sliding grooves, the sliding grooves can limit the circumferential rotation and radial displacement of the sliding connection block 2 and the heat sink 3.
[0035] In this embodiment, the connection between the sliding connection block 2 and the aircraft shell 4 is similar to a sliding rail, which can move axially, thereby ensuring that the shock absorber can work normally and that the electronic components can work under allowable mechanical conditions. During movement, the sliding connection block is always in contact with the aircraft shell, which can achieve rapid heat conduction.
[0036] Further, the sliding grooves are rectangular grooves, and the bottom surface and the side surface of the sliding grooves are in sliding contact with the three outer surfaces of the sliding connection block 2, respectively.
[0037] Further, a plurality of sliding connection blocks 2 are distributed along the circumferential direction of the heat sink 3.
[0038] In this embodiment, the sliding connection block 2 is directly connected to the heat sink 3, which can rapidly conduct heat, and the contact surface between the sliding connection block 2 and the aircraft shell 4 is large and arranged in multiple directions, which can rapidly and uniformly transfer heat to the aircraft shell.
[0039] Further, the sliding connection block 2 is made of a high-thermal-conductivity metal material.
[0040] Further, the interior of the heat sink 3 is filled with a phase change medium. Specifically, the electronic module 1 is fastened to the heat sink 3 by screwing, which can rapidly conduct heat.
[0041] Further, the gap between the sliding connection block 2 and the inner wall surface of the aircraft shell 4 is 0.1 mm.
[0042] Further, the gap between the sliding connecting block 2 and the inner side wall of the aircraft shell 4 is coated with heat-conducting silicone grease.
[0043] In this embodiment, the heat sink 3 is in direct contact with the heat generating device 5, and the heat generated by the electronic components is quickly conducted away by using the high heat-conducting performance of the metal structural member. The sliding connecting block 2 is a connecting device of the heat sink 3 and the aircraft shell 4, which functions to conduct the heat of the heat sink 3 to the aircraft shell 4. The sliding connecting block 2 is rigidly connected with the heat sink 3 and can have relative movement with the aircraft shell 4 in the axial direction, which can meet the requirements of heat dissipation and relative movement of the shock absorber.
[0044] The above is only the preferred specific implementation of the present application, but the protection scope of the present application is not limited to this. Any person skilled in the art can easily think of changes or replacements within the technical range disclosed by the present application, which should be covered within the protection scope of the present application.
Claims
1. A heat dissipating device for enclosing equipment, characterized by, The utility model relates to an electronic module (1) cooling device, including: Sliding connecting block (2), heat dissipation plate (3) and aircraft shell (4); The sliding connecting block (2) is L-shaped structural member, and one end is fixedly connected on the outside of heat dissipation plate (3), and the other end is slidably connected with aircraft shell (4); The sliding connecting block (2) can displace along the axial direction of aircraft shell (4); The inside of heat dissipation plate (3) is filled with heat-absorbing medium; The heat dissipation plate (3) is used for heat dissipation of electronic module (1), and is directly contacted with heating device (5) on electronic module (1).
2. The heat dissipating device of an enclosed apparatus according to claim 1, wherein The sliding connecting block (2) is fixedly connected with multiple blocks on the outside of heat dissipation plate (3).
3. A heat dissipating device for enclosing equipment according to claim 2, wherein The inner wall of aircraft shell (4) is provided with multiple sliding grooves, and the sliding connecting block (2) is slidably installed in the sliding groove.
4. The heat dissipating device of an enclosed apparatus according to claim 3, wherein The sliding groove extends along the axial direction of aircraft shell (4), can allow the sliding connecting block (2) to displace along the axial direction of aircraft shell (4), and after the sliding connecting block (2) is matched with the sliding groove, the sliding groove can limit the circumferential rotation and radial displacement of the sliding connecting block (2) and heat dissipation plate (3).
5. The heat dissipating device of an enclosed apparatus according to claim 4, wherein The sliding groove is rectangular groove, and the bottom and side of sliding groove are slidably contacted with three outer sides of sliding connecting block (2) respectively.
6. A heat dissipating device for enclosing equipment according to claim 5, wherein Multiple sliding connecting blocks (2) are distributed along the circumference of heat dissipation plate (3).
7. A heat dissipating device for enclosing equipment according to claim 6, wherein The sliding connecting block (2) is high-thermal-conductivity metal material.
8. A heat dissipating device for enclosing equipment according to claim 7, wherein The inside of heat dissipation plate (3) is filled with phase-change medium.
9. A heat dissipating device for enclosing equipment according to any one of claims 1-8, characterized in that The gap between the sliding connecting block (2) and the inner wall of aircraft shell (4) is 0.1mm.
10. A heat dissipating device for enclosing equipment according to claim 9, wherein The gap between the sliding connecting block (2) and the inner wall of aircraft shell (4) is coated with thermal conductive silicone grease.