Fully-reinforced LRM case

Abstract

The utility model relates to the technical field of LRM cases, and provides a fully-reinforced LRM case, in which a front panel is arranged on the front side of a case shell, a front door module is hinged with the front panel, a reinforced cold plate module is inserted into the front panel and is connected with one side of an LRM back plate module arranged in the case shell, a heat dissipation module is arranged on the other side of the LRM back plate module, and the front door module is connected with the reinforced cold plate module. The heat dissipation module is fixedly connected with the rear panel, the rear panel is arranged on the rear side of the case shell, the aviation plugboard module and the power supply filtering module are arranged on the rear panel, the power supply filtering module is electrically connected with the signal switching module, and the aviation plugboard module is connected with the LRM backboard module through the signal switching module. The heat dissipation device can be used in severe environments such as high vibration, strong impact and serious electromagnetic interference, is high in heat dissipation efficiency, can meet the heat dissipation requirements of high-performance electronic equipment, is high in modularization degree and integration degree, and can adapt to various application occasions.

Description

Technical Field

[0001] This utility model relates to the field of LRM chassis technology, and in particular to a fully ruggedized LRM chassis. Background Technology

[0002] In today's era of rapid technological advancement, fully ruggedized LRM (Lightweight Resistant Mounting) chassis are finding increasingly widespread applications across numerous fields. In the military, their stable operation is crucial to mission success, from command and control systems to electronic control units in weaponry. In the aerospace field, electronic equipment in satellites and spacecraft relies on LRM chassis to cope with the complex space environment. In industrial control, production automation systems also depend on them to ensure reliable equipment operation under harsh conditions.

[0003] For example, in the ATR-type air-cooled LRM ruggedized chassis disclosed in application number CN202311556956.5, the areas between the top cover plate, socket plate, bottom mounting plate and frame partition, and the areas between the bottom cover plate and bottom mounting plate are sealed areas; the areas between the top cover plate, wall panel, front slot plate, rear slot plate, partition and bottom mounting plate are unsealed areas; an LRM module is provided on the bottom mounting plate, and heat dissipation holes are provided on the front slot plate and rear slot plate corresponding to the unsealed areas, and the LRM module achieves heat dissipation through air convection between the front slot plate and rear slot plate.

[0004] However, the existing LMR chassis designs are less flexible and less integrated, making them unable to fully adapt to rapidly evolving and diverse application scenarios. Utility Model Content

[0005] To address the issue that existing LMR chassis designs lack flexibility and integration, making them unable to fully adapt to rapidly evolving and diverse application scenarios, this invention provides a fully ruggedized LMR chassis to solve this problem.

[0006] To achieve the above objectives, this utility model provides the following technical solution:

[0007] A fully ruggedized LRM chassis includes: a chassis shell, an LRM backplane module, a ruggedized cooling plate module, a front door module, a front panel, a heat dissipation module, a signal conversion module, an aviation connector module, a rear panel, and a power filtering module. The front panel is located on the front side of the chassis shell, and the front door module is hinged to the front panel. The ruggedized cooling plate module is inserted into the front panel and connected to one side of the LRM backplane module located inside the chassis shell. The heat dissipation module is located on the other side of the LRM backplane module and is fixedly connected to the rear panel. The rear panel is located on the rear side of the chassis shell, and the aviation connector module and the power filtering module are located on the rear panel. The power filtering module is electrically connected to the signal conversion module, and the aviation connector module is connected to the LRM backplane module through the signal conversion module.

[0008] Preferably, the chassis shell adopts a fully reinforced structure design, and all splicing seams are designed with conductive sealing strips.

[0009] Preferably, the front door module is provided with multiple sets of filter meshes.

[0010] Preferably, the heat dissipation module includes: a cooling fan and a V-shaped air guide plate, one side of the V-shaped air guide plate is fixedly connected to the rear panel, the air outlet of the V-shaped air guide plate corresponds to the ventilation hole of the rear panel, and the other side of the V-shaped air guide plate is fixedly connected to multiple sets of cooling fans.

[0011] Preferably, the ventilation holes occupy 10% of the rear panel area.

[0012] Preferably, the aircraft insert module and the LRM backplane module are interconnected using an LRM connector.

[0013] Preferably, the chassis housing is made of 5052 aluminum alloy and is anodized.

[0014] Preferably, the reinforced cold plate module is equipped with high-efficiency heat dissipation fins.

[0015] The advantages of this utility model are as follows: The chassis shell is made of high-strength alloy material combined with a precise structural design, which has a strong anti-vibration and anti-impact capability. By setting up a heat dissipation module, the cooling fan and the internal air duct work together to allow cold air to flow efficiently through the heat-generating components, remove heat in time, maintain a balanced temperature inside the chassis, prevent local overheating, provide a suitable thermal environment for high-performance electronic components, and ensure stable performance of the equipment under high load. By setting up a chassis shell, LRM backplane module, reinforced cold plate module, front door module, front panel, heat dissipation module, signal conversion module, aviation plug-in board module, rear panel and power filtering module, the modular design allows the chassis to be flexibly configured with functional modules according to needs, which is convenient for rapid assembly and upgrades. Attached Figure Description

[0016] The accompanying drawings, which form part of this utility model, are used to provide a further understanding of the utility model. The illustrative embodiments of the utility model and their descriptions are used to explain the utility model and do not constitute an undue limitation of the utility model. In the drawings:

[0017] Figure 1 This is an exploded view of this utility model;

[0018] Figure 2 This is an isometric view of the structure of this utility model at angle one;

[0019] Figure 3 This is an isometric view of the structure of this utility model at angle one;

[0020] Figure 4 This is a diagram showing the airflow direction inside the chassis of this utility model.

[0021] Explanation of reference numerals in the attached figures:

[0022] 1. Chassis housing; 2. LRM backplane module; 4. Reinforced cold plate module; 5. Front door module; 6. Front panel; 7. Heat dissipation module; 8. Signal conversion module; 9. Aviation plug board module; 10. Rear panel; 11. Power filter module; 12. Cooling fan; 13. V-shaped air deflector. Detailed Implementation

[0023] It should be noted that, unless otherwise specified, the embodiments and features described in these embodiments can be combined with each other.

[0024] In the description of this utility model, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating orientation or positional relationships based on the orientation or positional relationships shown in the accompanying drawings, are only for the convenience of describing this utility model 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 utility model. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, features defined with "first," "second," etc., may explicitly or implicitly include one or more of that feature. In the description of this utility model, unless otherwise stated, "a plurality of" means two or more.

[0025] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; 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; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0026] Example 1, combined with Figure 1 , Figure 2 and Figure 3 Please provide an explanation:

[0027] A fully ruggedized LRM chassis includes: chassis shell 1, LRM backplate module 2, ruggedized cold plate module 3, front door module 4, front panel 5, heat dissipation module 6, signal conversion module 7, aviation plug-in board module 8, rear panel 9, and power filtering module 10.

[0028] The front panel 5 is located on the front side of the chassis housing 1. The front door module 4 is hinged to the front panel 5. The front door module 4 can rotate around the pivot, which facilitates the quick assembly and disassembly of the reinforced cold plate module 3.

[0029] The reinforced cold plate module 3 is inserted into the front panel 5 and connected to one side of the LRM backplate module 2 located inside the chassis housing 1.

[0030] The heat dissipation module 6 is located on the other side of the LRM backplate module 2. The heat dissipation module 6 is fixedly connected to the rear panel 9. Ventilation openings are provided on the LRM backplate module 2 to ensure unobstructed airflow at the front and rear of the chassis and to ensure sufficient airflow performance.

[0031] The rear panel 9 is located on the rear side of the chassis housing 1. The aviation plug-in module 8 and the power filter module 10 are located on the rear panel 9. The power filter module 10 is electrically connected to the signal conversion module 7.

[0032] The aircraft plug-in module 8 is connected to the LRM backplane module 2 via a signal adapter module 7. The signal adapter module 7 is connected to both the LRM backplane module 2 and the aircraft plug-in module 8 via CPCI-E connectors. The interconnection between the aircraft plug-in module 8 and the LRM backplane module 2 uses the signal adapter module 7 instead of conventional cable connections, improving equipment stability and facilitating equipment installation and maintenance.

[0033] All external connectors are mounted using a solder plate method, and the aviation plug-in module 8 and the rear panel 9 are integrated into one unit, which facilitates equipment maintenance.

[0034] The chassis housing 1 adopts a fully reinforced structure design, and all splicing seams are designed with conductive sealing strips, which has excellent electromagnetic compatibility characteristics and meets the electromagnetic compatibility requirements of GJB151B-2013.

[0035] The front door module 4 is equipped with multiple sets of filter meshes to ensure electromagnetic compatibility.

[0036] The aviation plug-in board module 8 and the LRM backplane module 2 are interconnected using an LRM connector to achieve high-speed signal transmission, which has high stability and reliability.

[0037] The chassis housing 1 is made of 5052 aluminum alloy, anodized, and possesses excellent mechanical properties, meeting environmental test requirements such as GJB150.16A vibration test-2009 and GJB150.18A impact test-2009. The chassis shell is made of high-permeability metal, combined with a multi-layer shielding design. Electromagnetic sealing strips are used at the interfaces to precisely block external electromagnetic interference. The internal circuit layout is optimized to reduce self-interference and ensure clean signal transmission.

[0038] The reinforced cold plate module 3 is equipped with high-efficiency heat dissipation fins, and the chassis shell 1 is also equipped with phase change material. By using the phase change material and the high-efficiency heat dissipation fins in synergy, the phase change material releases heat at low temperatures, and the heat dissipation fins enhance convection heat dissipation at high temperatures, so as to achieve stable operation in an ultra-wide temperature range of -45℃ to +55℃.

[0039] The chassis surface is treated with a special nano-anti-corrosion coating, and the sealing strips are made of materials with excellent weather resistance, with a seamless fit, effectively preventing moisture and salt spray from entering.

[0040] Example 2, based on Example 1, combined with... Figure 4 Please provide an explanation:

[0041] The heat dissipation module 6 includes a heat dissipation fan 61 and a V-shaped air guide plate 62. One side of the V-shaped air guide plate 62 is fixedly connected to the rear panel 9, the air outlet of the V-shaped air guide plate 62 corresponds to the ventilation hole 91 of the rear panel 9, and the other side of the V-shaped air guide plate 62 is fixedly connected to multiple sets of heat dissipation fans 61.

[0042] The ventilation hole 91 occupies 10% of the area of ​​the rear panel 9, and 90% of the space of the rear panel can be used to place external connectors, which can accommodate a larger number of connectors.

[0043] The working principle of this utility model: When using this device, as follows: Figure 4 As shown, the cooling fan 61 on the heat dissipation module 6 starts. Based on the pressure difference generated by the rotation of the cooling fan 61, a low-pressure area is created on the left side of the chassis shell 1. Atmospheric pressure forces cold air into the chassis through the filter mesh of the front door module 4. As the air passes through the surface of the reinforced cold plate module 3, it carries away heat and becomes hot air. The hot air passes through the cooling fan 61 and enters the V-shaped cavity of the heat dissipation module 6, forming a high-pressure area within the V-shaped cavity. This forces the hot air to be discharged from the ventilation hole 91 on the rear panel 9, forming an air convection circulation. During this process, the air duct structure inside the chassis shell 1 is optimized to ensure uniform airflow distribution and avoid localized overheating areas. At the same time, to ensure electromagnetic compatibility, the filter mesh and the area around the ventilation hole 91 are specially treated to prevent electromagnetic interference from entering and exiting the chassis with the airflow. This allows the chassis to maintain stable operation of the equipment while efficiently dissipating heat. This utility model has strong protective capabilities and can be used in harsh environments such as high vibration, strong impact, and severe electromagnetic interference. It has high heat dissipation efficiency, can meet the heat dissipation requirements of high-performance electronic equipment, and has a high degree of modularity and integration, making it suitable for various applications.

[0044] For those skilled in the art, this utility model is not limited to the details of the exemplary embodiments described above, and can be implemented in other specific forms without departing from the spirit or essential characteristics of this utility model; therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of this utility model is defined by the appended claims rather than the foregoing description. Therefore, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within this utility model. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0045] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any minor modifications, equivalent substitutions and improvements made to the above embodiments based on the technical essence of the present utility model should be included within the protection scope of the technical solution of the present utility model.

Claims

1. A fully rugged LRM chassis, characterized by, include: The chassis housing (1), LRM backplate module (2), reinforced cold plate module (3), front door module (4), front panel (5), heat dissipation module (6), signal conversion module (7), aviation plug-in board module (8), rear panel (9), and power filtering module (10) are provided. The front panel (5) is located on the front side of the chassis housing (1). The front door module (4) is hinged to the front panel (5). The reinforced cold plate module (3) is inserted into the front panel (5) and the LRM backplate located inside the chassis housing (1). The module (2) is connected on one side, and the heat dissipation module (6) is set on the other side of the LRM backplane module (2). The heat dissipation module (6) is fixedly connected to the rear panel (9). The rear panel (9) is set on the rear side of the chassis housing (1). The aviation plug board module (8) and the power filter module (10) are set on the rear panel (9). The power filter module (10) is electrically connected to the signal conversion module (7). The aviation plug board module (8) is connected to the LRM backplane module (2) through the signal conversion module (7).

2. The ruggedized LRM chassis of claim 1, wherein, The chassis housing (1) adopts a fully reinforced structure design, and all splicing seams are designed with conductive sealing strips.

3. The ruggedized LRM chassis of claim 1, wherein, The front door module (4) is provided with multiple sets of filter meshes.

4. The fully rugged LRM chassis of claim 1, wherein, The heat dissipation module (6) includes a heat dissipation fan (61) and a V-shaped guide plate (62). One side of the V-shaped guide plate (62) is fixedly connected to the rear panel (9), the air outlet of the V-shaped guide plate (62) corresponds to the ventilation hole (91) of the rear panel (9), and the other side of the V-shaped guide plate (62) is fixedly connected to multiple sets of heat dissipation fans (61).

5. A fully rugged LRM chassis according to claim 4, characterized in that, The ventilation hole (91) occupies 10% of the area of ​​the rear panel (9).

6. The fully rugged LRM chassis of claim 1, wherein, The aircraft insert module (8) and the LRM backplane module (2) are interconnected using an LRM connector.

7. The fully rugged LRM chassis of claim 1, wherein, The chassis housing (1) is made of 5052 aluminum alloy and is anodized.

8. The fully rugged LRM chassis of claim 1, wherein, The outer side of the chassis housing (1) is provided with high-efficiency heat dissipation fins.

9. The fully rugged LRM chassis of claim 1, wherein, The reinforced cold plate module (3) is equipped with high-efficiency heat dissipation fins.

Images