Flight controller box

Abstract

This utility model discloses a flight control box, relating to the field of flight equipment technology. The flight control box includes a box body, a cover, a circuit board assembly, and a heat-conducting structure. The cover and box body together form a sealed cavity. At least one inner wall surface of the box body and cover, which are arranged opposite to each other, has a mounting protrusion. The circuit board assembly is installed within the sealed cavity and includes a substrate and at least one electrical heating element. The electrical heating element is located on a first or second side of the substrate. The heat-conducting structure is located between the mounting protrusion and the electrical heating element and is thermally connected to both. Through the integrated mounting protrusion and heat-conducting structure, effective support and precise heat conduction for the high-power electrical heating element are achieved. Utilizing the overall thermal conductivity of the box body and cover, the path for heat transfer outwards is broadened, eliminating the need for complex heat dissipation devices such as fans. The structure is simpler, solving the problem of low heat dissipation efficiency in space-constrained environments using traditional heat dissipation methods.

Description

Technical Field

[0001] This utility model relates to the field of flight equipment technology, and in particular to a flight control box. Background Technology

[0002] In existing technologies, the heat dissipation devices used in flight control equipment generally suffer from insufficient heat dissipation performance. The main reasons include the following: First, traditional heat dissipation methods are inefficient. Conventional electronic component heat dissipation relies primarily on natural convection and thermal radiation. While this is sufficient for low-power components, it proves inadequate for high-power components, making it difficult to effectively control temperature rise. Second, the compact internal structure and limited space of the flight control box make it impractical to install additional active cooling devices such as liquid cooling systems or fans. In this situation, simply adding thermally conductive materials to improve heat transfer efficiency may cause mechanical impact or damage to electronic components due to vibration or other issues, thus affecting the stability and reliability of the equipment. Utility Model Content

[0003] The main purpose of this invention is to propose a flight control box that aims to solve the problem of low heat dissipation efficiency of traditional heat dissipation methods in space-constrained situations.

[0004] To achieve the above objectives, the flight control box proposed in this utility model includes:

[0005] The box body and the lid body are provided. The top of the box body is open. The lid body is placed on the open end of the box body to form a sealed cavity together with the box body. At least one of the inner wall surfaces of the box body and the lid body is provided with a mounting protrusion.

[0006] A circuit board assembly is installed in the sealed cavity. The circuit board assembly includes a substrate and at least one electrical heating element. The substrate has a first side facing the open end of the box and a second side away from the open end of the box. The electrical heating element is disposed on the first side or the second side of the substrate and is corresponding to and spaced apart from the mounting protrusion.

[0007] A heat-conducting structure is disposed between the mounting protrusion and the electrical heating element, and is thermally connected to the mounting protrusion and the electrical heating element, wherein the thermal conductivity of the heat-conducting structure, the box body and the cover body is set to be greater than the thermal conductivity of air.

[0008] In one embodiment, the thermally conductive structure includes a thermally conductive adhesive.

[0009] In one embodiment, the thermally conductive adhesive is a silicone sheet.

[0010] In one embodiment, the thickness of the thermally conductive adhesive is set to d, where 1mm ≤ d ≤ 3mm.

[0011] In one embodiment, the thermally conductive structure further includes a heat sink, which is disposed on the side of the thermally conductive adhesive away from the electrical heating element, and the thermal conductivity of the heat sink is set to be greater than that of air.

[0012] In one embodiment, the heat sink is configured as an aluminum alloy block.

[0013] In one embodiment, the box body and the cover body are made of metal.

[0014] In one embodiment, a sealing ring is provided at the open end of the box body, and the sealing ring seals the open end of the box body and the cover body.

[0015] In one embodiment, the sealing ring is made of a conductive material.

[0016] In one embodiment, a sealing groove is provided at the open end of the box body, the sealing groove extends circumferentially along the box body, and the sealing ring is disposed in the sealing groove.

[0017] In the technical solution of this utility model, a mounting protrusion and a heat-conducting structure are provided between the electrical heating element and the bottom wall of the box. This allows the heat generated by the electrical heating element during operation to be transferred sequentially to the box and / or cover through the heat-conducting structure and the mounting protrusion. The integrated mounting protrusion and heat-conducting structure effectively support and precisely conduct heat to the high-power electrical heating element. By utilizing the overall heat conduction performance of the box and cover, the path for heat transfer to the outside is widened, improving the overall heat dissipation efficiency and reducing the risk of local hot spots. Since complex heat dissipation devices such as fans and liquid cooling are eliminated, the overall structure is simpler and more reliable. It is especially suitable for the harsh operating environment of flight control equipment, such as strong vibration and compact space, to solve the problem of low heat dissipation efficiency of traditional heat dissipation methods in space-constrained situations. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of this utility model 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 utility model. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0019] Figure 1 A schematic diagram of the structure of an embodiment of the flight control box provided by this utility model;

[0020] Figure 2 for Figure 1 Schematic diagram of the middle box structure;

[0021] Figure 3 for Figure 1 An explosion diagram of the flight control box;

[0022] Figure 4 for Figure 1 A plan view of the middle housing, circuit board assembly, and heat-conducting structure;

[0023] Figure 5 for Figure 4 Schematic diagram of the cross section of AA;

[0024] Figure 6 for Figure 1 A schematic diagram of the circuit board assembly and heat-conducting structure;

[0025] Figure 7 for Figure 1 An explosion diagram of the flight control box.

[0026] Explanation of icon numbers:

[0027] 100. Flight controller box; 1. Box body; 1a. Sealing groove; 2. Cover; 10. Mounting protrusion; 3. Circuit board assembly; 31. Substrate; 32. Electrical heating element; 4. Thermal conductive structure; 41. Thermal conductive adhesive; 42. Heat sink; 5. Sealing ring.

[0028] The realization of the purpose, functional features and advantages of this utility model will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0029] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present utility model.

[0030] It should be noted that if the embodiments of this utility model involve directional indicators (such as up, down, left, right, front, back, etc.), the directional indicators are only used to explain the relative positional relationship and movement of the components in a specific posture. If the specific posture changes, the directional indicators will also change accordingly.

[0031] Furthermore, if the embodiments of this utility model involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the use of "and / or" or "and / or" throughout the text includes three parallel solutions. For example, "A and / or B" includes solution A, solution B, or a solution where both A and B are satisfied simultaneously. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed by this utility model.

[0032] In existing technologies, the heat dissipation devices used in flight control equipment generally suffer from insufficient heat dissipation performance. The main reasons include the following: First, traditional heat dissipation methods are inefficient. Conventional electronic component heat dissipation relies primarily on natural convection and thermal radiation. While this is sufficient for low-power components, it proves inadequate for high-power components, making it difficult to effectively control temperature rise. Second, the compact internal structure and limited space of the flight control box make it impractical to install additional active cooling devices such as liquid cooling systems or fans. In this situation, simply adding thermally conductive materials to improve heat transfer efficiency may cause mechanical impact or damage to electronic components due to vibration or other issues, thus affecting the stability and reliability of the equipment.

[0033] This utility model proposes a flight controller box 100, which aims to solve the problem of low heat dissipation efficiency of traditional heat dissipation methods in space-constrained situations.

[0034] Please see Figures 1 to 3In one embodiment of this utility model, the flight control box 100 includes a box body 1, a cover 2, a circuit board assembly 3, and a heat-conducting structure 4. The top of the box body 1 is open, and the cover 2 covers the open end of the box body 1 to form a sealed cavity together with the box body 1. At least one of the inner wall surfaces of the box body 1 and the cover 2, which are arranged opposite to each other, has a mounting protrusion 10. The circuit board assembly 3 is installed in the sealed cavity, and the circuit board assembly 3 includes a substrate 31 and at least one electrical heating element 32. The substrate 31 has a first side facing the open end of the housing 1 and a second side away from the open end of the housing 1. The electric heating element 32 is disposed on the first side or the second side of the substrate 31 and is corresponding to and spaced apart from the mounting protrusion 10. The heat-conducting structure 4 is disposed between the mounting protrusion 10 and the electric heating element 32 and is thermally connected to the mounting protrusion 10 and the electric heating element 32. The thermal conductivity of the heat-conducting structure 4, the housing 1 and the cover 2 is set to be greater than the thermal conductivity of air.

[0035] The top of the box 1 is open, and the cover 2 is sealed to the top of the box 1, forming a relatively closed sealed cavity, thereby providing a good protective environment for the internal electronic components.

[0036] Please see Figure 2 Mounting protrusions 10 are provided on the inner wall surface of at least one of the box body 1 and the cover body 2. These mounting protrusions 10 are preferably integrally formed with the box body 1 or the cover body 2, which not only enhances the structural strength, but also simplifies the processing technology and avoids the introduction of additional parts.

[0037] Please see Figures 4 to 5 The circuit board assembly 3 is located in a sealed cavity. Multiple electrical heating elements 32 are provided on one or both sides of its substrate 31. The positions of these heating elements are reasonably distributed in different areas of the substrate 31 according to their heat generation and working characteristics, and a certain distance is maintained between them and the mounting protrusion 10, so as to provide installation space for the heat conduction structure 4.

[0038] The heat-conducting structure 4 is located between the mounting protrusion 10 and the electrical heating element 32, serving as a heat conduction bridge. Its material has a thermal conductivity higher than that of air, which can effectively and quickly transfer the heat generated by the electrical heating element 32 to the mounting protrusion 10, and further dissipate it outward through the box 1 or the cover 2.

[0039] It should be noted that when multiple electrical heating elements 32 are provided inside the sealed cavity, the multiple heating elements can adopt different heat conduction structures 4 to achieve efficient heat conduction based on the difference in distance between them and the mounting protrusion 10.

[0040] Specifically, for electrical heating elements 32 with a small distance from the mounting protrusion 10, thermally conductive adhesive 41 can be used directly as the thermally conductive structure 4. Its high thermal conductivity and good vibration damping performance can ensure that heat can be efficiently and stably transferred from the electrical heating element 32 to the mounting protrusion 10. For electrical heating elements 32 with a large distance from the mounting protrusion 10, it may be more suitable to use a separate thermally conductive block or a composite thermally conductive structure 4 formed by combining a thermally conductive block and thermally conductive adhesive 41.

[0041] It should also be noted that the form of the heat conduction structure 4 described here is not fixed, but can be flexibly adjusted according to actual application needs, aiming to provide the most suitable heat dissipation solution for each electrical heat-generating component 32, thereby ensuring the stable operation of the entire flight control box system.

[0042] Since the mounting protrusion 10 itself has good thermal conductivity, it can not only position and support the electrical heating element 32, but also serve as part of the structural heat transfer channel and participate in the efficient heat dissipation process of the entire system.

[0043] By designing both the housing 1 and the cover 2 as components made of high thermal conductivity materials, the entire outer shell system can provide mechanical protection while also having good heat dissipation capabilities, thereby significantly improving the operational stability and reliability of the flight control equipment under complex operating conditions.

[0044] In the technical solution of this utility model, a mounting protrusion 10 and a heat-conducting structure 4 are provided between the electrical heating element 32 and the bottom wall of the box 1. This allows the heat generated by the electrical heating element 32 during operation to be transferred sequentially to the box 1 and / or the cover 2 through the heat-conducting structure 4 and the mounting protrusion 10. Through the integrated mounting protrusion 10 and the heat-conducting structure 4, effective support and precise heat conduction for the high-power electrical heating element 32 are achieved. By utilizing the overall heat conduction performance of the box 1 and the cover 2, the path for heat transfer to the outside is widened, the overall heat dissipation efficiency is improved, and the risk of local hot spots is reduced. Since complex heat dissipation devices such as fans and liquid cooling are eliminated, the overall structure is simpler and more reliable. It is especially suitable for the harsh operating environment of flight control equipment, such as strong vibration and compact space, so as to solve the problem of low heat dissipation efficiency of traditional heat dissipation methods in space-constrained situations.

[0045] Specifically, please refer to Figures 4 to 6 In one specific embodiment, the thermally conductive structure 4 includes a thermally conductive adhesive 41.

[0046] The heat-conducting structure 4 is specifically implemented using thermally conductive adhesive 41, which fills the space between the electrical heating element 32 and the mounting protrusion 10, forming a good heat conduction path. As a functional material with a high thermal conductivity, thermally conductive adhesive 41 not only plays a role in efficient heat conduction in this technical solution, but also has buffering and vibration reduction functions, which can effectively cope with the complex vibration environment in which the flight control equipment operates.

[0047] Compared to air (whose thermal conductivity is approximately 0.0267 W / m·K at 50°C), the thermal conductivity of thermally conductive adhesive 41 is significantly improved, for example, its thermal conductivity can reach 12 W / m·K, which greatly enhances the efficiency of heat transfer from the heating element to the housing 1 or the cover 2.

[0048] It should be noted that thermal conductivity is a physical quantity that measures a material's ability to conduct heat. The higher the value, the stronger the material's ability to transfer heat under the same temperature difference.

[0049] By using thermally conductive adhesive 41 as the thermally conductive structure 4, rigid contact between the electrical heating element 32 and the mounting protrusion 10 can be avoided. While ensuring good heat conduction, it absorbs the mechanical impact caused by vibration during flight, preventing damage or loosening of components due to stress concentration. This achieves efficient heat dissipation from the electrical heating element 32 and effectively mitigates the impact of vibration between structures by utilizing its flexible characteristics, avoiding the mechanical damage problems that may be caused by traditional rigid connections. This improves the stability and service life of the entire flight control box under harsh conditions such as high vibration and confined spaces.

[0050] In addition, thermally conductive adhesive 41 is easy to apply and highly adaptable, requiring no additional complex assembly structure, further simplifying the overall process and improving product consistency and reliability. It is particularly suitable for avionics applications where space is limited and heat dissipation and vibration resistance are critical.

[0051] More specifically, in one embodiment, the thermally conductive adhesive 41 is a silicone sheet. The silicone sheet possesses excellent thermal conductivity, good flexibility, and strong adaptability, and can maintain stable physical and chemical properties over a wide temperature range.

[0052] It should be noted that in practical applications, other types of thermal pads or gels can be selected as alternative materials to achieve the best heat dissipation effect, depending on the specific heat dissipation requirements and design considerations.

[0053] Specifically, in this embodiment, the thickness of the thermally conductive adhesive 41 is set to d, where 1mm ≤ d ≤ 3mm. Setting the thickness of the thermally conductive adhesive 41 within this range effectively balances heat conduction efficiency and structural adaptability, forming a stable and reliable heat conduction path between the electrical heating element 32 and the mounting protrusion 10.

[0054] If the thermal conductive adhesive 41 is too thin (e.g., less than 1 mm), although it can further shorten the heat conduction path and improve the heat conduction efficiency, its insufficient compression margin may not be able to effectively fill the tiny gap between the two, resulting in increased contact thermal resistance and affecting the overall heat dissipation effect. At the same time, if the thermal conductive adhesive 41 is too thin, it will be difficult to absorb the stress caused by processing errors or installation deviations during the assembly process, which can easily cause local pressure concentration and affect the stability and reliability of the components.

[0055] Conversely, if the thermally conductive adhesive 41 is too thick (more than 3mm), although it has a stronger ability in terms of buffering and vibration reduction, its relatively high thermal resistance will significantly prolong the heat conduction path and reduce the heat conduction rate, resulting in heat not being transferred from the electrical heating element 32 to the mounting protrusion 10 and the housing 1 in a timely and effective manner.

[0056] Therefore, controlling the thickness of thermally conductive adhesive 41 between 1mm and 3mm can ensure good thermal conductivity while also taking into account the requirements for vibration damping, assembly tolerance, and structural stability. This is especially suitable for precision electronic devices such as flight controller box 100 that operate in high-vibration, space-constrained environments.

[0057] In other embodiments, please continue to refer to Figures 4 to 6 The heat-conducting structure 4 further includes a heat sink 42, which is disposed on the side of the heat-conducting adhesive 41 away from the electrical heating element 32. The thermal conductivity of the heat sink 42 is set to be greater than that of air.

[0058] The heat sink 42 is located on the side of the thermally conductive adhesive 41 away from the electrical heating element 32, that is, facing the mounting protrusion 10 or the box 1 / cover 2, to further enhance the efficiency of heat conduction from the electrical heating element 32 to the outside.

[0059] It should be noted that the heat sink 42 is typically made of materials with good thermal conductivity, such as metals (e.g., copper, aluminum, and their alloys) or high thermal conductivity composite materials, whose thermal conductivity is significantly higher than that of air (e.g., the thermal conductivity of air at 50°C is approximately 0.0267 W / m·K), thereby effectively preventing heat accumulation in this area and improving the overall heat conduction capacity. The heat sink 42 and the thermally conductive adhesive 41 are tightly bonded together, forming a continuous heat conduction path, allowing heat to pass sequentially through the electrical heating element 32, the thermally conductive adhesive 41, and the heat sink 42, and finally be transferred to the mounting protrusion 10 and the housing 1 or cover 2, achieving efficient heat dissipation.

[0060] The heat sink 42 not only enhances the thermal conductivity of localized areas but also plays a role in heat diffusion when multiple electrical heat-generating components 32 are unevenly distributed, helping to balance temperature gradients in different areas and reduce the risk of localized hot spots. Furthermore, the heat sink 42 can be modularly designed according to the actual location and power differences of the heat-generating components, adapting to different flight control box internal layouts and improving the flexibility and applicability of the structural design. Simultaneously, due to its inherent rigidity, the heat sink 42 can also serve as a supporting structure during assembly, assisting the thermally conductive adhesive 41 in maintaining stable contact and preventing interruptions in the heat conduction path due to vibration or external forces, further enhancing the system's stability and durability.

[0061] Specifically, in this embodiment, the heat sink 42 is set as an aluminum alloy block. 6061 aluminum alloy can be used, as this material has good mechanical strength, processing performance, and excellent thermal conductivity, with a thermal conductivity of approximately 180 W / m·K, far exceeding that of air (approximately 0.0267 W / m·K) and thermally conductive adhesive 41 (e.g., 12 W / m·K), which can significantly improve the overall thermal conductivity efficiency of the thermally conductive structure 4.

[0062] An aluminum alloy block 42 is placed on the side of the thermally conductive adhesive 41 away from the electrical heating element 32, so that the heat can be quickly absorbed by the highly thermally conductive aluminum alloy block and diffused laterally after passing through the thermally conductive adhesive 41, thereby accelerating the heat transfer speed to the box 1 or cover 2, reducing local temperature accumulation, and effectively improving the thermal environment inside the flight control box.

[0063] The aluminum alloy heat sink 42 not only possesses excellent thermal conductivity but also boasts advantages such as low density, strong corrosion resistance, and ease of processing and forming, making it particularly suitable for aerospace applications that demand both lightweight design and high performance. Furthermore, the aluminum alloy material and the thermally conductive adhesive 41 exhibit excellent interfacial adhesion, ensuring the continuity and stability of the heat conduction path during assembly. Due to its structural rigidity, the heat sink 42 also enhances the overall support of the thermally conductive structure 4 to a certain extent, preventing excessive deformation of the thermally conductive adhesive 41 due to vibration or external forces, which could negatively impact thermal conductivity.

[0064] Furthermore, in this embodiment, the box body 1 and the cover body 2 are made of metal.

[0065] It should be noted that the metal material can be aluminum alloy, magnesium alloy, or stainless steel, etc. These metal materials not only have high structural strength, meeting the requirements of flight control equipment for mechanical protection and environmental adaptability, but also have good thermal conductivity. Their thermal conductivity is generally much higher than that of non-metallic materials (such as plastics or composite materials). For example, the thermal conductivity of aluminum alloy can reach about 180 W / m·K, which is significantly better than air (about 0.0267 W / m·K) and general insulating materials. Making the box body 1 and the cover 2 of metal helps to improve the heat dissipation capability of the entire flight control box. This allows the heat generated by the electrical heating element 32 to be conducted to the box body 1 or the cover 2 through the heat-conducting structure 4 and the mounting protrusion 10, and then quickly dissipated outward through the metal shell, thereby effectively reducing the operating temperature of the internal components and improving the stability and reliability of the system operation.

[0066] Furthermore, in the environment where the flight controller box is used, the metal casing 1 and cover 2 also possess excellent electromagnetic shielding performance. Flight control systems are extremely sensitive to electromagnetic interference (EMI), and the metal casing can form an effective electromagnetic shielding layer, suppressing interference from external electromagnetic waves, while also preventing electromagnetic radiation generated by internal electronic components from affecting external equipment.

[0067] Further, please refer to Figure 7 In this embodiment, a sealing ring 5 is provided at the open end of the box body 1, and the sealing ring 5 seals the opening of the box body 1 and the cover body 2.

[0068] Specifically, the sealing ring 5 is embedded in the connection between the box body 1 and the cover body 2. After the cover body 2 is closed on the box body 1, the sealing ring 5 undergoes a certain compression deformation, thereby forming a good sealing fit between the two. The sealing ring 5 is usually made of elastic and weather-resistant materials, such as silicone rubber or fluororubber, which can maintain stable sealing performance over a wide temperature range and under complex environmental conditions.

[0069] By setting the sealing ring 5, not only can external moisture, dust or other impurities be effectively prevented from entering the sealed cavity and the circuit board assembly 3 be protected from environmental factors, but the overall protection level of the flight controller box can also be improved, ensuring that it can maintain normal operation even in extreme situations such as humidity changes, air pressure fluctuations or short-term water immersion during the operation of the flight controller box.

[0070] Especially in the environment where the flight control box is used, the aircraft may face various potential water threats such as high humidity, rain, and condensation. The sealing ring 5 provides reliable waterproof protection for the flight control box, avoiding problems such as short circuits, corrosion, or signal abnormalities caused by water ingress. In addition, the sealing ring 5 also has a certain buffering effect, absorbing manufacturing errors and deformation stress between the box body 1 and the cover body 2 during the assembly process.

[0071] Specifically, because the electromagnetic environment of the flight control system is complex and variable during the operation of the flight control box, the electromagnetic interference between various radars, communication equipment and electronic systems is particularly prominent. In order to further improve the overall electromagnetic compatibility performance of the flight control box, in this embodiment, the sealing ring 5 is made of a conductive material.

[0072] The sealing ring 5 can be made of conductive rubber strips or similar materials. By incorporating conductive fillers (such as silver powder, carbon black, or metal-coated particles) into the rubber matrix, it achieves good conductivity. When the cover 2 and the box 1 are closed, the conductive sealing ring 5 fits tightly between them, achieving a physical seal while also forming a continuous conductive path. This creates a complete electromagnetic shielding layer, effectively reducing the impact of external electromagnetic interference on the internal circuitry of the flight controller box and suppressing the electromagnetic radiation of internal high-frequency signals to the external environment.

[0073] Furthermore, without adding additional shielding structures, the conductive sealing ring 5 maintains basic sealing functions such as waterproofing and dustproofing, and can also maintain a stable conductive connection under complex working conditions such as vibration and temperature changes, ensuring long-term reliability of the shielding effect.

[0074] For details, please continue reading Figure 7 In this embodiment, a sealing groove 1a is provided at the open end of the box body 1. The sealing groove 1a extends along the circumference of the box body 1, and the sealing ring 5 is disposed in the sealing groove 1a.

[0075] The sealing groove 1a is structurally designed to accommodate and position the sealing ring 5. During assembly of the cover 2 and the box 1, the sealing ring 5 is pressed between the sealing groove 1a and the cover 2, thereby achieving a reliable seal at the connection point. The sealing groove 1a is typically formed in one piece by machining or casting in the peripheral area of ​​the open end of the box 1. Its cross-sectional shape can be adapted to the shape of the sealing ring 5 to ensure that the sealing ring 5 can be evenly stressed under compression, maintaining good fit and resilience. By placing the sealing ring 5 within the sealing groove 1a, not only is the stability and consistency of the sealing structure improved, but it also effectively prevents the sealing ring 5 from shifting, twisting, or falling off during assembly or use, thereby improving the overall sealing reliability of the flight control box.

[0076] The above description is merely an exemplary embodiment of the present utility model and does not limit the patent scope of the present utility model. Any equivalent structural transformations made based on the technical concept of the present utility model and the contents of the present utility model specification and drawings, or direct / indirect applications in other related technical fields, are included within the patent protection scope of the present utility model.

Claims

1. A flight control box, characterized by, include: The box body and the lid body are provided. The top of the box body is open. The lid body is placed on the open end of the box body to form a sealed cavity together with the box body. At least one of the inner wall surfaces of the box body and the lid body is provided with a mounting protrusion. A circuit board assembly is installed in the sealed cavity. The circuit board assembly includes a substrate and at least one electrical heating element. The substrate has a first side facing the open end of the box and a second side away from the open end of the box. The electrical heating element is disposed on the first side or the second side of the substrate and is corresponding to and spaced apart from the mounting protrusion. A heat-conducting structure is disposed between the mounting protrusion and the electrical heating element, and is thermally connected to the mounting protrusion and the electrical heating element, wherein the thermal conductivity of the heat-conducting structure, the box body and the cover body is set to be greater than the thermal conductivity of air.

2. The flight control box of claim 1, wherein, The thermally conductive structure includes thermally conductive adhesive.

3. The flight control box of claim 2, wherein, The thermally conductive adhesive is a silicone sheet.

4. The flight control box of claim 2, wherein, The thickness of the thermally conductive adhesive is set to d, where 1mm ≤ d ≤ 3mm.

5. The flight control box of any one of claims 2 to 3, wherein, The thermally conductive structure also includes a heat sink, which is disposed on the side of the thermally conductive adhesive away from the heat-generating component of the appliance, and the thermal conductivity of the heat sink is set to be greater than that of air.

6. The flight control box of claim 5, wherein, The heat sink is made of aluminum alloy.

7. The flight control box of claim 1, wherein, The box and the cover are made of metal.

8. The flight control box of claim 1, wherein, A sealing ring is provided at the open end of the box body, and the sealing ring seals the opening of the box body and the cover body.

9. The flight control box of claim 8, wherein, The sealing ring is made of a conductive material.

10. The flight control box of claim 8, wherein, The open end of the box is provided with a sealing groove, which extends along the circumference of the box, and the sealing ring is disposed in the sealing groove.

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