A five-sided cooling high temperature environment aviation chassis

Abstract

The utility model discloses a high-temperature environment aviation chassis with five-side cooling, comprising a chassis and a heat-insulating cover plate, wherein the heat-insulating cover plate is installed on the open side of the chassis; wall cooling circulation channels are opened around the chassis, and an S-shaped bottom cooling circulation channel is opened at the bottom of the chassis; the bottom cooling circulation channel is connected with the wall cooling circulation channel to form a cooling circulation channel with an outlet and an inlet; a temperature equalizing plate is arranged on the inner side of the heat-insulating cover plate; a heat-insulating component is also installed on the heat-insulating cover plate; the utility model has a reasonable design and an ingenious structure, can meet the heat insulation requirements of the chassis and the heat dissipation requirements of internal components in a high-temperature environment of 350°C, and ensures that the internal components can maintain good operation under extreme working conditions (highest ambient temperature, maximum controller power).

Description

Technical Field

[0001] The utility model relates to an aviation case, in particular to a five-side cooling high-temperature environment aviation case. Background Art

[0002] Aviation chassis is a common equipment in aircraft. Due to the harsh working environment, it has high requirements, especially for high temperature environments (such as 350℃ ambient temperature). Traditional chassis have poor heat dissipation capacity and mostly use welded flow channels for multi-faceted liquid flow structures, which have poor reliability and maintainability. In addition, traditional aviation chassis are easily affected by the external environment at the cover end, which reduces the heat dissipation performance. Utility Model Content

[0003] Therefore, in order to solve the above-mentioned deficiencies, the utility model provides a five-sided cooling high-temperature environment aviation chassis with a reasonable design and ingenious structure. The aviation chassis structure meets the requirements of chassis insulation and heat dissipation of internal components in a high-temperature environment of 350°C, ensuring that the internal components can maintain good operation under extreme working conditions (highest ambient temperature and maximum controller power).

[0004] Specifically, a five-sided cooling high-temperature environment aviation chassis comprises a box body and a heat-insulating cover plate, wherein the heat-insulating cover plate is installed on an opening side of the box body;

[0005] The box body is provided with a wall cooling circulation channel around it, and an S-shaped bottom cooling circulation channel is provided at the bottom of the box body; the bottom cooling circulation channel is connected with the wall cooling circulation channel to form a cooling circulation channel with an outlet and an inlet;

[0006] A temperature-averaging plate is provided on the inner side of the heat-insulating cover plate;

[0007] The heat insulation cover plate is also equipped with a heat insulation component.

[0008] The box body is formed by 3D printing using a high-temperature alloy (such as TC4 titanium alloy).

[0009] Optionally, the inlet is provided with a cold source inlet joint installed on the box body, and the outlet is provided with a cold source outlet joint installed on the box body.

[0010] Optionally, the thermal insulation cover plate includes a thermal insulation cover plate frame and a sealing plate, and the sealing plate is fixedly mounted on an opening side of the thermal insulation cover plate frame.

[0011] Optionally, a first barrier layer, a second barrier layer and a third barrier layer are sequentially installed in the insulation cover frame, and the first barrier layer, the second barrier layer and the third barrier layer form an insulation assembly.

[0012] Optionally, the first barrier layer and / or the third barrier layer are formed of a high-temperature and heat-resistant composite material.

[0013] Optionally, the second barrier layer is formed of a material with low thermal conductivity.

[0014] The utility model has the following advantages:

[0015] The utility model has a reasonable design and ingenious mechanism, and can meet the requirements of heat insulation of the chassis and heat dissipation of internal components in a high temperature environment of 350°C, ensuring that the internal components can maintain good operation under extreme working conditions (highest ambient temperature, maximum controller power), and the maximum temperature of all module boards does not exceed 115°C. The materials of all structural parts can work for a long time at the maximum temperature, and the working life is not less than 15 years. At the same time, the chassis mechanism needs to meet the corresponding three-proof, electromagnetic shielding, vibration, impact, rain and other environmental requirements. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a three-dimensional schematic diagram of the utility model;

[0017] Figure 2 It is a three-dimensional schematic diagram from another perspective of the utility model;

[0018] Figure 3 It is a structural schematic diagram of the box body of the utility model;

[0019] Figure 4 It is a schematic diagram of the main view of the box body of the utility model;

[0020] Figure 5 yes Figure 4 Schematic diagram of the box structure at the middle BB section;

[0021] Figure 6 yes Figure 4 Schematic diagram of the box structure at the AA section;

[0022] Figure 7 It is a three-dimensional schematic diagram of the heat-insulating cover plate installed with the temperature-averaging plate of the utility model;

[0023] Figure 8 It is a schematic diagram of the disassembled structure of the heat-insulating cover plate of the utility model;

[0024] In the figure: 100, thermal insulation cover plate; 101, thermal insulation cover plate frame; 102, first barrier layer; 103, second barrier layer; 104, third barrier layer; 105, sealing plate; 200, box body; 300, temperature equalizing plate; 400, cold source inlet joint; 500, cold source outlet joint. DETAILED DESCRIPTION

[0025] The embodiments of the present application are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present application, and should not be construed as limiting the present application.

[0026] In this document, relational terms such as first and second, etc., are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprises", or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, article, or apparatus that includes a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article, or apparatus.

[0027] As described in the background technology, the traditional chassis has poor heat dissipation capacity and mostly uses welded flow channels for multi-faceted liquid flow, which has poor reliability and maintainability; and the traditional aviation chassis is easily affected by the external environment at the cover end, thereby reducing the heat dissipation performance.

[0028] Based on the above problems, this embodiment provides a five-sided cooling high-temperature environment aviation chassis, and the use environment conditions of the aviation chassis are as follows:

[0029] This project specifically addresses the need for aviation chassis structures that meet various environmental requirements in 350° high temperature environments.

[0030] Environmental conditions for use:

[0031] a) Long-term working temperature: (-55~+350)℃;

[0032] b) Cooling method: fuel liquid cooling;

[0033] c) Cooling medium: No. 3 aviation kerosene, temperature not exceeding 75°C;

[0034] d) Maximum temperature change rate: 20℃ / s;

[0035] e) Working environment pressure: (2.55~230) kPa;

[0036] f) Working environment pressure change rate: 10kPa / min.

[0037] g) Storage environment temperature: (-55~+71)℃.

[0038] In view of the above-mentioned use environment, the aviation chassis includes a box body 200 and a heat-insulating cover plate 100, and the heat-insulating cover plate 100 is installed on the opening side of the box body 200;

[0039] The box body 200 is provided with several layers of interconnected wall cooling circulation channels 201 around it, and an S-shaped bottom cooling circulation channel 202 is provided at the bottom of the box body; the bottom cooling circulation channel 202 is connected with the wall cooling circulation channel 201 to form a cooling circulation channel with an outlet and an inlet;

[0040] A temperature equalizing plate 300 is provided on the inner side of the heat insulating cover plate;

[0041] The thermal insulation cover plate 100 is also equipped with a thermal insulation component.

[0042] The above technology can meet the requirements of chassis insulation and internal component heat dissipation in a high temperature environment of 350°C, ensuring that the internal components can maintain good operation under extreme working conditions (highest ambient temperature and maximum controller power).

[0043] In order to facilitate the introduction of a cold source into the cooling circulation channel, in one embodiment, the inlet is provided with a cold source inlet joint 400 installed on the box body, and the outlet is provided with a cold source outlet joint 500 installed on the box body.

[0044] In order to reduce the cooling performance of the insulation cover plate by the external environment, in one embodiment, the insulation cover plate 100 includes an insulation cover plate frame 101 and a sealing plate 105, and the sealing plate is fixedly installed on the opening side of the insulation cover plate frame; the insulation cover plate frame is sequentially installed with a first barrier layer 102, a second barrier layer 103 and a third barrier layer 104, and the first barrier layer 102, the second barrier layer 103 and the third barrier layer 104 form an insulation component

[0045] Optionally, the first barrier layer and / or the third barrier layer are formed of a high-temperature heat-resistant composite material; the second barrier layer is formed of a low thermal conductivity material (such as aerogel, air, etc.).

[0046] The box body of the utility model is completed by 3D printing with a high-temperature alloy (such as TC4 titanium alloy). The five sides of the box body are ventilated with liquid. Through the optimization of the flow channel, the flow resistance is reduced while ensuring that the five sides of the main body are ventilated with liquid. At the same time, in order to ensure the rapid maintenance of the chassis, the bottom surface of the chassis adopts a detachable insulation cover plate, and the insulation cover plate adopts a three-layer insulation design. At the same time, a temperature equalizing plate is used inside the chassis to dissipate heat from the device, and the insulation cover plate side is further dissipated.

[0047] At the same time, the aviation chassis structure meets the requirements of chassis insulation and heat dissipation of internal components in a high temperature environment of 350°C, ensuring that internal components can maintain good operation under extreme working conditions (highest ambient temperature, maximum controller power), the maximum temperature of all module boards does not exceed 115°C, and all structural parts are selected to work for a long time at the maximum temperature, with a service life of not less than 15 years. At the same time, the chassis structure needs to meet the corresponding three-proof, electromagnetic shielding, vibration, impact, rain and other environmental requirements.

[0048] The above description of the disclosed embodiments enables those skilled in the art to implement or use the present invention. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention will not be limited to the embodiments shown herein, but will conform to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A five-sided cooling high temperature environment aviation chassis, characterized in that: It comprises a box body and a heat-insulating cover plate, wherein the heat-insulating cover plate is installed on the opening side of the box body; The box body is provided with a wall cooling circulation channel around it, and an S-shaped bottom cooling circulation channel is provided at the bottom of the box body; the bottom cooling circulation channel is connected with the wall cooling circulation channel to form a cooling circulation channel with an outlet and an inlet; A temperature-averaging plate is provided on the inner side of the heat-insulating cover plate; The heat insulation cover plate is also equipped with a heat insulation component.

2. A five-sided cooling high temperature environment aviation chassis according to claim 1, characterized in that: The inlet is provided with a cold source inlet joint installed on the box body, and the outlet is provided with a cold source outlet joint installed on the box body.

3. The five-sided cooling high temperature environment aviation chassis according to claim 1, characterized in that: The heat-insulating cover plate comprises a heat-insulating cover plate frame and a sealing plate, and the sealing plate is fixedly installed on the opening side of the heat-insulating cover plate frame.

4. A five-sided cooling high temperature environment aviation chassis according to claim 3, characterized in that: The first barrier layer, the second barrier layer and the third barrier layer are sequentially installed in the thermal insulation cover frame, and the first barrier layer, the second barrier layer and the third barrier layer form a thermal insulation component.

5. A five-sided cooling high temperature environment aviation chassis according to claim 4, characterized in that: The first barrier layer and / or the third barrier layer are formed of a high-temperature heat-resistant composite material.

6. A five-sided cooling high temperature environment aviation chassis according to claim 4, characterized in that: The second barrier layer is formed of a material with low thermal conductivity.

7. A five-sided cooling high temperature environment aviation chassis according to any one of claims 1 to 6, characterized in that: The box body is formed by 3D printing of high-temperature alloy.

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