A heat dissipation structure of a helicopter airborne radar

Abstract

The utility model relates to radar equipment heat dissipation technical field especially, a kind of heat dissipation structure of helicopter airborne radar, the heat dissipation structure includes: heat dissipation plate, heat dissipation component, blow component, set in the heat dissipation layer, and one end is abutted with the disturbing piece, another end is provided with blow fin;Fixed rod, the fixed rod is fixedly arranged on the airborne radar, the end of the fixed rod is abutted with the disturbing piece, when the T / R component position changes, the volume of disturbing piece is changed by fixed rod, to make blow component reciprocating movement along axis;Through integration helicopter vibration energy, active heat dissipation is realized, reciprocating motion actively agitates ambient air, forced air flow flows through heat dissipation layer surface, to avoid hot air recirculation phenomenon under the condition of no external ram air, effectively alleviate the problem that the heat dissipation structure in the prior art has poor heat dissipation effect.

Description

Technical Field

[0001] This utility model relates to the field of radar equipment heat dissipation technology, and in particular to a heat dissipation structure for helicopter airborne radar. Background Technology

[0002] Helicopter-borne radar, especially active electronically scanned array (AESA) radar, generates enormous heat flux density in its T / R (transmit / receive) components and signal processors during operation. However, the confined space inside a helicopter, the harsh vibration environment, and the lack of high-speed ram air during hovering or low-speed flight make radar heat dissipation an extremely challenging technical problem. Currently, the heat dissipation structures for airborne radar mainly rely on forced air cooling or liquid cooling technologies.

[0003] Forced air cooling structures typically utilize fans or introduced cold air flowing over large-area heat dissipation fins to remove heat. However, air has a low specific heat capacity, which naturally limits its heat dissipation efficiency, making it difficult to meet the needs of modern high-power radars. More seriously, when a helicopter is hovering, the external airflow is poor, and the cooling fan is very likely to draw in the hot air that has just been exhausted, causing the hot air to be drawn in again, resulting in a sharp drop in the efficiency of the cooling system, and even causing the radar to overheat, reduce its frequency, or shut down. Utility Model Content

[0004] The main purpose of this invention is to provide a heat dissipation structure for helicopter airborne radar, which aims to alleviate the problem of poor heat dissipation effect of existing heat dissipation structures.

[0005] To achieve the above objectives, this utility model provides a heat dissipation structure for helicopter airborne radar. The heat dissipation structure is used to reduce the temperature of the T / R components inside the airborne radar, and includes: A heat sink is disposed on the lower end face of the T / R assembly; A heat dissipation assembly, comprising a disturbance component and several heat dissipation layers, wherein the disturbance component and several heat dissipation layers are disposed on the side of the heat dissipation plate away from the T / R assembly, and the several heat dissipation layers and the heat dissipation plate are concentrically arranged from the inside to the outside with the center of their surfaces as a reference. A blowing component is disposed on the heat dissipation layer, with one end abutting against the disturbance component and the other end provided with blowing fins; A fixed rod is fixedly mounted on the airborne radar. The end of the fixed rod abuts against the disturbance component. When the position of the T / R assembly changes, the volume of the disturbance component is changed by the fixed rod, so that the blowing assembly can reciprocate along the axis.

[0006] Optionally, the heat dissipation layer includes a plurality of spaced-apart heat dissipation fins.

[0007] Optionally, the blowing assembly includes a blowing rod, the two ends of which are fixedly connected to a disturbance element and a blowing fin, respectively.

[0008] Optionally, the outer periphery of the blowing rod is provided with an elastic element, and the elastic element is also disposed between the two heat dissipation layers.

[0009] Optionally, the heat dissipation fins are provided with heat dissipation holes.

[0010] Optionally, the disturbance element is a plastic sphere.

[0011] Optionally, the blowing fin includes a connecting rod and is connected to the blowing rod via the connecting rod.

[0012] Optionally, the upper end of the fixing rod is provided with a protrusion, and the protrusion is always in contact with the plastic sphere.

[0013] Optionally, the heat dissipation holes are angled.

[0014] Optionally, the heat sink is provided with a water cooling channel.

[0015] This invention achieves active heat dissipation by integrating helicopter vibration energy. Specifically, a heat sink is directly installed on the lower end face of the T / R assembly, and heat is efficiently conducted to the heat sink, laying the foundation for subsequent heat dissipation. The heat dissipation assembly consists of a disturbance component and several heat dissipation layers, both located on the side of the heat sink away from the T / R assembly. The heat dissipation layers are concentrically arranged from the inside to the outside with the center of the heat sink as the reference. This concentric arrangement makes the heat flow distribution more uniform, effectively reducing the risk of local overheating, while the expanded heat dissipation area improves the overall heat dissipation capacity. The fixing rod is fixed to the airborne radar body, and its end is in contact with the disturbance component. When the helicopter vibration causes the T / R assembly to shift position, the fixing rod pushes the disturbance component to change volume. This change directly drives the blowing component to reciprocate along the axis. The blowing component is installed on the heat dissipation layer, with one end in contact with the disturbance component and the other end equipped with blowing fins. Its reciprocating motion actively agitates the surrounding air, forcing the airflow to flow across the surface of the heat dissipation layer, thereby avoiding hot air recirculation in the absence of external ram air. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of a heat dissipation structure in an embodiment of the present invention; Figure 2 This is another schematic diagram of the heat dissipation structure in an embodiment of this utility model; Figure 3 Appendix to this utility model Figure 2 A magnified structural diagram of A in the middle.

[0017] Figure label: 1-T / R assembly, 2-Heat plate, 3-Heat dissipation assembly, 4-Blowing assembly, 5-Fixing rod; 31-Disturbing component, 32-Heat dissipation layer, 33-Heat dissipation fins, 34-Heat dissipation holes; 41-blowing fins, 42-blowing rod, 43-elastic element, 44-connecting rod.

[0018] 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

[0019] 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 protection scope of the present utility model.

[0020] It should be noted that all directional indicators (such as up, down, left, right, front, back, etc.) in this utility model embodiment are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indicator will also change accordingly.

[0021] In this utility model, unless otherwise explicitly specified and limited, the terms "connection," "fixing," etc., should be interpreted broadly. For example, "fixing" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection or an electrical connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0022] 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 meaning of "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.

[0023] Example: Please refer to the attached document as well. Figures 1 to 3 This embodiment provides a heat dissipation structure for a helicopter-borne radar. The heat dissipation structure is used to reduce the temperature of the T / R component 1 inside the airborne radar. The heat dissipation structure includes: Heat sink 2, which is disposed on the lower end face of the T / R assembly 1; The heat dissipation component 3 includes a disturbance element 31 and a plurality of heat dissipation layers 32. The disturbance element 31 and the plurality of heat dissipation layers 32 are all disposed on the side of the heat dissipation plate 2 away from the T / R component 1, and the plurality of heat dissipation layers 32 and the heat dissipation plate 2 are arranged concentrically from the inside to the outside with the center of the surface as a reference. The blowing component 4 is disposed on the heat dissipation layer 32, with one end abutting against the disturbance component 31 and the other end provided with blowing fins 41; The fixed rod 5 is fixedly mounted on the airborne radar. The end of the fixed rod 5 abuts against the disturbance component 31. When the position of the T / R assembly 1 changes, the volume of the disturbance component 31 is changed by the fixed rod 5 so that the blowing assembly 4 can reciprocate along the axis.

[0024] It should be noted that in the traditional existing helicopter airborne radar heat dissipation structure, due to insufficient external airflow during hovering or low-speed flight, the hot air exhausted by the cooling fan is prone to forming a recirculation in the confined space, resulting in the re-intake of hot air and a significant reduction in heat dissipation efficiency. In particular, the inherent characteristics of air specific heat capacity limit the heat transfer capability, and the vibration environment further exacerbates the airflow turbulence, making it impossible for the heat of T / R component 1 to be dissipated in time, which seriously affects the temperature control stability and thus threatens the continuous operation capability of the radar system.

[0025] Based on the above problems, this embodiment provides a heat dissipation structure for helicopter airborne radar, which achieves active heat dissipation by integrating helicopter vibration energy. Specifically, the heat dissipation plate 2 is directly disposed on the lower end face of the T / R assembly 1, and heat is efficiently conducted to the heat dissipation plate 2, laying the foundation for the subsequent heat dissipation process. The heat dissipation assembly 3 is composed of a disturbance element 31 and several heat dissipation layers 32, both of which are located on the side of the heat dissipation plate 2 away from the T / R assembly 1. The heat dissipation layers 32 are arranged concentrically from the inside to the outside with the center of the heat dissipation plate 2 as the reference. This concentric arrangement makes the heat flow distribution more uniform, effectively reducing the risk of local overheating, while the expanded heat dissipation area improves the overall heat dissipation capacity. The fixing rod 5 is fixed to the airborne radar body, and its end is in contact with the disturbance component 31. When the helicopter vibration causes the T / R component 1 to shift position, the fixing rod 5 pushes the disturbance component 31 to change volume. This change directly drives the blowing component 4 to reciprocate along the axis. The blowing component 4 is set on the heat dissipation layer 32, with one end in contact with the disturbance component 31 and the other end equipped with blowing fins 41. Its reciprocating motion actively stirs the surrounding air and forces the airflow to flow through the surface of the heat dissipation layer 32, thereby avoiding the phenomenon of hot air recirculation under the condition of no external ram air.

[0026] It should also be noted that, in this embodiment, through the cooperation of the fixed rod 5 and the disturbance component 31, when the position of the T / R component 1 changes due to helicopter vibration, the volume of the disturbance component 31 is changed, driving the blowing component 4 to reciprocate along the axis, actively generating airflow through the heat dissipation layer 32, thereby avoiding the re-inhalation of hot air and solving the problem of heat dissipation efficiency during hovering or low-speed flight.

[0027] In some embodiments, the heat dissipation layer 32 refers to a heat dissipation structure that is concentrically arranged from the inside to the outside with reference to the center of the heat dissipation plate 2. It can be implemented by using annular metal sheets or a mesh structure, such as aluminum concentric rings or stainless steel mesh, mainly to provide an expanded heat dissipation surface area.

[0028] In some embodiments, the disturbance element 31 refers to a component that can change its volume in response to changes in the position of the T / R component 1. It can be implemented using an inflatable elastic bladder or bellows structure, such as a rubber bladder or a silicone capsule, primarily to convert positional changes into volume changes.

[0029] In this embodiment, the heat dissipation layer 32 includes a plurality of spaced heat dissipation fins 33.

[0030] It is understandable that the spaced heat dissipation fins 33 can be understood as an arrangement structure in which the heat dissipation fins 33 maintain a regular spacing. This can be achieved by means of parallel arrangement with equal spacing, non-uniform array distribution, or staggered layout. The purpose is to form a continuous and evenly distributed airflow channel, avoid local airflow blockage caused by dense fins, and thus improve air circulation efficiency.

[0031] It is also understandable that the aforementioned structure, through the regularly spaced arrangement of the heat dissipation fins 33, allows airflow to be evenly distributed and flow smoothly along the surface of the heat dissipation layer 32. Because the spacing of the heat dissipation fins 33 forms a stable and continuous airflow path, turbulence and eddies are avoided when air flows through the heat dissipation layer 32, thereby reducing hot air stagnation. Simultaneously, this layout, in conjunction with the overall configuration of the heat dissipation component 3, allows cool air to continuously replenish the heat dissipation surface, while hot air is efficiently exhausted, effectively suppressing hot air recirculation. This design is particularly suitable for the low-speed airflow environment during helicopter hovering, ensuring stable heat dissipation under vibration and space-constrained conditions by optimizing aerodynamic characteristics.

[0032] In this embodiment, the blowing assembly 4 includes a blowing rod 42, and the two ends of the blowing rod 42 are fixedly connected to the disturbance member 31 and the blowing fin 41, respectively.

[0033] Understandably, the above structure, through the rigid support characteristics of the blowing rod 42, directly transmits the volume change of the disturbance component 31 to the blowing fins 41. This means that when the T / R assembly 1 changes position, the fixing rod 5 pushes the disturbance component 31, which in turn drives the blowing fins 41 to reciprocate along the axis via the blowing rod 42. This creates continuous airflow disturbance within the heat dissipation layers 32, effectively enhancing the heat exchange efficiency between the heat dissipation layers 32 and the air. In this embodiment, an elastic element 43 is provided on the outer periphery of the blowing rod 42, and the elastic element 43 is also disposed between the two heat dissipation layers 32. By tightly surrounding the outer periphery of the blowing rod 42, the elastic element 43 can effectively absorb the radial impact energy generated by the helicopter vibration when the blowing rod 42 is driven to move axially by the disturbance member 31, thus avoiding micro-cracks or fractures at the rigid connection due to stress concentration. At the same time, the structural design of the elastic element 43 extending between the two heat dissipation layers 32 allows the elastic element 43 to apply a restraining force to the adjacent heat dissipation layers 32 during the movement of the blowing assembly 4, preventing the heat dissipation fins 33 from colliding or displacing due to vibration, ensuring that the airflow channel between the heat dissipation layers 32 remains unobstructed, thereby ensuring the continuity of airflow disturbance and the stability of heat dissipation efficiency when the blowing fins 41 move back and forth. In this embodiment, the heat dissipation fins 33 are provided with heat dissipation holes 34. The design of the heat dissipation holes 34 allows airflow to penetrate the structure of the heat dissipation fins 33. Combined with the reciprocating movement of the blowing component 4, the airflow is effectively disturbed, breaking the laminar flow state in the gap between the fins and preventing the local accumulation of hot air inside the heat dissipation layer 32.

[0034] In this embodiment, the disturbance element 31 is a plastic sphere. A plastic sphere refers to a spherical structure with controllable deformation characteristics, which can be made of elastic materials such as silicone, rubber, or thermoplastic elastomers. When the T / R assembly 1 shifts position due to helicopter vibration, the fixing rod 5 continuously contacts the plastic sphere. The plastic sphere undergoes uniform deformation using its material properties, achieving smooth volume adjustment, thereby driving the blowing assembly 4 to move stably back and forth along the axis. This process avoids the contact instability phenomenon caused by the rigid disturbance element 31 under vibration environment, ensuring that the blowing fins 41 can continuously disturb the airflow between the heat dissipation layers 32, maintaining the continuity of airflow disturbance, and effectively preventing hot air recirculation.

[0035] In this embodiment, the blowing fin 41 includes a connecting rod 44, which is connected to the blowing rod 42. When the disturbance member 31 drives the blowing assembly 4 to reciprocate, the connecting rod 44 acts as a flexible intermediary, effectively absorbing the impact energy generated by the helicopter vibration and reducing the direct impact on the connection point. At the same time, this design allows the blowing fin 41 to maintain a stable posture during movement, continuously disturbing the airflow between the heat dissipation layers 32 and enhancing the heat dissipation effect.

[0036] In this embodiment, the upper end of the fixing rod 5 is provided with a protrusion, and the protrusion is always in contact with the plastic sphere.

[0037] It is understandable that a protrusion refers to a local protruding structure set on the upper end of the fixed rod 5, which can be implemented in the form of a cone, hemisphere or pyramid.

[0038] It is also understandable that by forming a local high-point contact between the protrusion at the upper end of the fixed rod 5 and the plastic sphere, the rolling and displacement of the plastic sphere are effectively limited during the vibration of the helicopter, thereby ensuring the axial consistency of the volume change of the disturbance component 31; when the position of the T / R assembly 1 changes, the fixed rod 5 transmits the thrust stably through the protrusion, causing the disturbance component 31 to undergo controllable plastic deformation, thereby driving the blowing assembly 4 to reliably reciprocate along the predetermined axis, maintaining the uniformity and continuity of the heat dissipation airflow disturbance.

[0039] In this embodiment, the heat dissipation hole 34 is opened at an angle. By opening the heat dissipation hole 34 at an angle, when the blowing component 4 drives the airflow through the heat dissipation fins 33, the airflow can form a directional flow path along the guide of the angled hole; on this basis, the hot air is effectively guided to be quickly discharged outside the heat dissipation structure along the angled direction, avoiding the phenomenon of airflow forming eddies or stagnation in local areas when it is opened vertically.

[0040] In this embodiment, the heat sink 2 is provided with a water cooling channel.

[0041] It is understandable that the water cooling channel refers to the channel structure inside the heat sink 2 for circulating coolant. It can be implemented using generalized structures such as spiral flow channel, serpentine flow channel or parallel straight pipe flow channel. Its purpose is to use the high specific heat capacity of liquid cooling to provide an active heat dissipation mechanism that does not rely on external air flow, thereby overcoming the heat dissipation bottleneck caused by poor air flow when the helicopter is hovering.

[0042] It is also understandable that by integrating water-cooling channels inside the heat sink 2, the coolant can continuously flow through the channels, efficiently absorbing the heat conducted from the T / R component 1 to the heat sink 2, and carrying the heat out through the circulation system, thus avoiding the dependence of traditional air-cooled structures on ambient airflow.

[0043] The above are merely preferred embodiments of this utility model and do not limit the patent scope of this utility model. Any equivalent structural or procedural transformations made based on the description and drawings of this utility model, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this utility model.

Claims

1. A heat dissipation structure for a helicopter-borne radar, characterized in that, The heat dissipation structure is used to reduce the temperature of the T / R components inside the airborne radar. The heat dissipation structure includes: A heat sink is disposed on the lower end face of the T / R assembly; A heat dissipation assembly, comprising a disturbance element and several heat dissipation layers, wherein the disturbance element and several heat dissipation layers are disposed on the side of the heat dissipation plate away from the T / R assembly, and the several heat dissipation layers and the heat dissipation plate are concentrically arranged from the inside to the outside with the center of their surfaces as a reference. A blowing component is disposed on the heat dissipation layer, with one end abutting against the disturbance component and the other end provided with blowing fins; A fixed rod is fixedly mounted on the airborne radar. The end of the fixed rod abuts against the disturbance component. When the position of the T / R assembly changes, the volume of the disturbance component is changed by the fixed rod, so that the blowing assembly can reciprocate along the axis.

2. The heat dissipation structure for a helicopter-borne radar as described in claim 1, characterized in that, The heat dissipation layer includes a number of spaced-apart heat dissipation fins.

3. The heat dissipation structure for a helicopter-borne radar as described in claim 1, characterized in that, The blowing assembly includes a blowing rod, the two ends of which are fixedly connected to a disturbance element and a blowing fin, respectively.

4. The heat dissipation structure for a helicopter airborne radar as described in claim 3, characterized in that, An elastic element is provided on the outer periphery of the blowing rod, and the elastic element is also disposed between the two heat dissipation layers.

5. The heat dissipation structure for a helicopter-borne radar as described in claim 2, characterized in that, The heat dissipation fins are provided with heat dissipation holes.

6. The heat dissipation structure for a helicopter airborne radar as described in claim 1, characterized in that, The disturbance element is a plastic sphere.

7. The heat dissipation structure for a helicopter-borne radar as described in claim 3, characterized in that, The blowing fin includes a connecting rod and is connected to the blowing rod via the connecting rod.

8. The heat dissipation structure for a helicopter airborne radar as described in claim 6, characterized in that, The upper end of the fixing rod is provided with a protrusion, and the protrusion is always in contact with the plastic sphere.

9. The heat dissipation structure for a helicopter airborne radar as described in claim 5, characterized in that, The heat dissipation holes are angled.

10. The heat dissipation structure for a helicopter airborne radar as described in claim 1, characterized in that, The heat sink is equipped with a water-cooling channel.

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