A health management module for liquid cooling system of avionics equipment

Abstract

The present invention discloses a health management module for a liquid cooling system of avionics equipment, and relates to the technical field of liquid cooling of avionics equipment. The present invention adopts the ASAAC standard of the avionics system, and through real-time monitoring of the temperature, pressure, flow and other state parameters of the fluid in the liquid-cooled electronic equipment and filtering of the pollutants in the fluid, the real-time reporting and early warning of the state parameters of the liquid cooling system are realized, and the problems of liquid leakage, seepage, and equipment temperature out of control caused by abnormal supply temperature, pressure, flow and high contamination level of the liquid cooling system of the avionics liquid-cooled electronic equipment are effectively solved, and the reliability of the liquid cooling system is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of liquid cooling of avionics equipment, and in particular to a health management module of a liquid cooling system of avionics equipment. Background Art

[0002] The statements in this section merely provide background information related to the present disclosure and may not constitute prior art.

[0003] Compared with other platform equipment, avionics equipment has the characteristics of high integration, high heat flux density, tight space volume, harsh environment, closed structure and difficult to observe. With the continuous improvement of the integration and heat flux density of modern avionics equipment, liquid cooling has become an indispensable and widely used system-level cooling method.

[0004] However, phenomena such as seepage, leakage, flow channel blockage, deformation, and cracking in the liquid cooling systems of avionics equipment are still common. The reliability and safety of electronic equipment operation are difficult to improve, and even catastrophic events such as circuit burning and equipment paralysis may occur. The failure of these liquid cooling systems is mainly due to two factors: cooling medium contamination and excessive liquid supply parameters.

[0005] In response to the cooling medium contamination factor, various aviation projects have proposed control requirements for liquid cooling fluid contamination, but fluid contamination control technology and related products suitable for avionics equipment have not yet been explored and developed.

[0006] With regard to the factor of exceeding the limit of liquid supply parameters, there is still no exploration and research on its monitoring technology. As a result, the liquid cooling system of aviation liquid-cooled electronic equipment is in a "black box" with an unknown status after operation. As a result, it is impossible to identify and warn before failure occurs, and it is impossible to stop the loss in time during occurrence, and it is difficult to trace the source after it occurs.

[0007] Therefore, the research and development of liquid cooling system health management and the implementation of its functions are inevitable trends for current and future aviation liquid-cooled electronic equipment. They are also the key foundation for further improving the reliability of liquid cooling systems and the quality of aviation products. Summary of the invention

[0008] The purpose of the present invention is to provide a health management module for the liquid cooling system of avionics equipment in response to the problems existing in the prior art, which can not only meet the ASAAC standard of the avionics system and have universality and applicability; but also have the functions of pollutant filtering and real-time monitoring, reporting and early warning of status parameters, and effectively solve the problems of liquid cooling system leakage, seepage, and equipment temperature out of control caused by abnormal liquid supply temperature, pressure, flow rate and high contamination level of aviation liquid-cooled electronic equipment, thereby realizing the health management of the liquid cooling system.

[0009] The technical solution of the present invention is as follows:

[0010] A health management module for a liquid cooling system of an avionic equipment device comprises: a box body, wherein a liquid inlet, a liquid outlet and an electrical connector are arranged on the outside of the box body; a filter element is arranged inside the box body; the liquid inlet is connected to the filter element inlet through a pipeline, and the filter element outlet is connected to the liquid outlet through a pipeline; a temperature and pressure sensor is arranged on the pipeline connecting the liquid inlet and the filter element inlet; a first pressure sensor, a flow meter and a second pressure sensor are arranged in sequence on the pipeline connecting the filter element outlet and the liquid outlet.

[0011] Furthermore, a bypass valve is provided next to the filter element.

[0012] Furthermore, the bypass valve is composed of a valve body, a valve core and a spring; when the flow resistance of the filter element is greater than the resistance of the bypass valve spring, the bypass valve opens, and the coolant enters the subsequent pipeline through the bypass valve, ensuring normal use of the coolant when the filter element fails.

[0013] Furthermore, a locking strip and an extractor are installed on the box body.

[0014] Furthermore, the filter element is a stainless steel metal fiber sintered felt filter element.

[0015] Furthermore, the back of the box body has a compartment, in which a processing circuit board is installed, and the cables of each sensor and the flow meter are connected to the processing circuit board through a through hole; the data collected by each sensor and the flow meter are processed by the processing circuit board, and then transmitted to the outside of the module through an electrical connector for reporting, and compared with the set value for early warning, and an alarm is triggered if the preset threshold is exceeded.

[0016] Furthermore, the flow meter is a volumetric flow meter with a metal turbine structure.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] 1. The present invention monitors the pressure, temperature, flow and other state parameters of the liquid cooling system through sensors and flow meters arranged at the module liquid inlet, liquid outlet and filter outlet, and reports and warns in real time after processing the data through the embedded circuit board.

[0019] 2. The present invention filters the pollutants in the coolant through the stainless steel metal fiber sintered felt filter element, so that the contamination level of the coolant output by the module is better than the required level, thereby ensuring the normal operation of the liquid cooling channel and the fluid connector.

[0020] 3. The present invention combines the structural features of typical avionics equipment in the design process, adopts the ASAAC standard system of avionics systems, meets the environmental adaptability requirements of the aviation field, and has universality and can be interchanged on different avionics equipment, thereby improving the maintainability of avionics equipment. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic diagram of the external structure of the module;

[0022] Figure 2 It is a schematic diagram of the internal structure of the module;

[0023] Figure 3 This is a schematic diagram of the module back structure;

[0024] Figure 4 It is a schematic diagram of the internal structure of the module processing circuit board compartment;

[0025] Figure 5 It is a cross-sectional view of the bypass valve.

[0026] Figure markings: 1-box body, 2-front cover, 3-liquid inlet, 4-liquid outlet, 5-electric connector, 6-locking strip, 7-puller, 8-filter element, 9-bypass valve, 10-rear cover, 11-temperature and pressure sensor, 12-first pressure sensor, 13-second pressure sensor, 14-flow meter, 15-first pipeline, 16-second pipeline, 17-third pipeline, 18-fourth pipeline, 19-processing circuit board, 901-valve body, 902-valve core, 903-spring. DETAILED DESCRIPTION

[0027] It should be noted that relational terms such as "first" and "second" 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", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including 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 device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the existence of other identical elements in the process, method, article or device including the elements.

[0028] The features and performance of the present invention are further described in detail below in conjunction with the embodiments.

[0029] Embodiment 1

[0030] See also Figure 1-Figure 5 , an avionics equipment liquid cooling system health management module, specifically comprising: a box body 1;

[0031] A front cover plate 2 can be installed on the box body 1;

[0032] The corresponding positions of the outer side of the box body 1 are provided with a liquid inlet 3, a liquid outlet 4 and an electrical connector 5; the liquid inlet 3 and the liquid outlet 4 are connected to the external liquid cooling system; the electrical connector 5 is electrically connected to the external system;

[0033] A filter element 8 is provided in the box body 1, and a bypass valve 9 is provided next to the filter element 8; if instructions are required, the filter element 8 and the bypass valve 9 are installed through the installation groove and thread on the box body 1;

[0034] The liquid inlet 3 is connected to the inlet of the filter element 8 through a pipeline, and the outlet of the filter element 8 is connected to the liquid outlet 4 through a pipeline; a temperature and pressure sensor 11 is provided on the pipeline connecting the liquid inlet 3 and the inlet of the filter element 8; a first pressure sensor 12, a flow meter 14 and a second pressure sensor 13 are provided in sequence on the pipeline connecting the outlet of the filter element 8 and the liquid outlet 4; that is, Figure 1 As shown, the coolant enters the box body 1 from the liquid inlet 3, passes through the first pipeline 15, obtains the current temperature and pressure state data of the coolant through the temperature and pressure sensor 11, and then enters the filter element 8 to filter the pollutants. If the flow resistance of the filter element 8 is greater than the resistance of the spring 903 of the bypass valve 9, the coolant enters the subsequent pipeline through the bypass valve 9. After leaving the filter element 8, the coolant enters the second pipeline 16 and the third pipeline 17, and the current pressure data is collected through the first pressure sensor 12. The coolant enters the flow meter 14 through the pipeline to collect the current flow data, and then passes through the fourth pipeline 18 to reach the liquid outlet 4 to leave the module, and the current pressure data is collected through the second pressure sensor 13; the state monitoring of the coolant fluid and the pollutant filtering control are completed;

[0035] That is, through the flow meter 14 and the pressure data before and after the filter element 8, the pressure drop of the filter element 8 before and after filtration can be calculated, and the remaining service life of the filter element 8 can be derived;

[0036] At the same time, the pressure drop of the fluid connectors of the liquid inlet 3 and the liquid outlet 4 is a property of the connector itself and is only related to the flow rate. Therefore, the pressure drop of the two fluid connectors can be obtained through the data of the flow meter 14. The pressure sensor data of the liquid inlet 3 plus the pressure drop of the fluid connector of the liquid inlet 3 can be added to obtain the system supply pressure of the coolant;

[0037] The pressure of the coolant supplied to the electronic device can be obtained by subtracting the pressure drop of the fluid connector of the liquid outlet 4 from the pressure sensor data of the liquid outlet 4.

[0038] In this embodiment, specifically, the flow meter 14 is a volumetric flow meter 14 with a metal turbine structure, which can calculate the flow data of the liquid in the current pipeline and meet the environmental adaptability requirements of the avionics equipment platform.

[0039] In this embodiment, specifically, Figure 5As shown, the bypass valve 9 is composed of a valve body 901, a valve core 902 and a spring 903; when the flow resistance of the filter element 8 is greater than the resistance of the spring 903 of the bypass valve 9, the bypass valve 9 opens, and the coolant enters the subsequent pipeline through the bypass valve 9, ensuring the normal use of the coolant when the filter element 8 fails.

[0040] In this embodiment, specifically, a locking strip 6 and a puller 7 are installed on the box body 1 to achieve positioning, installation and fixation of the module and the external rack.

[0041] In this embodiment, specifically, the filter element 8 is a stainless steel metal fiber sintered felt filter element. This type of filter element 8 has adaptability to the temperature range of the avionics equipment platform and the requirements of impact, vibration, flow resistance, flow rate, pressure resistance, corrosion resistance, and filtering accuracy. Its structure consists of a pleated filtering surface and an internal metal support frame, which form a hollow cylindrical structure.

[0042] In this embodiment, specifically, the back of the box body 1 has a compartment, and a processing circuit board 19 is installed in the compartment. The cables of each sensor and the flow meter 14 are connected to the processing circuit board 19 through a through hole; the data collected by each sensor and the flow meter 14 are processed by the processing circuit board 19, and then transmitted to the outside of the module through the electrical connector 5 for reporting, and a comparison warning is performed through a set value. If the preset threshold is exceeded, an alarm is triggered; that is, the processing circuit board 19 is installed on the back of the box body 1, and the rear cover 10 is installed on the box body 1. The cables are connected to the processing circuit board 19 through a through hole, and the through hole is sealed with a sealant to realize a liquid-electric separation design to prevent the printed circuit board from being affected by condensation water and leakage of the liquid cooling pipeline.

[0043] The above-mentioned embodiments only express the specific implementation methods of the present application, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the protection scope of the present application. It should be pointed out that, for ordinary technicians in this field, several variations and improvements can be made without departing from the technical solution concept of the present application, and these all belong to the protection scope of the present application.

[0044] This background section is provided to generally present the context of the invention, and the work of the presently named inventors, the work to the extent described in this background section, and aspects of this section that did not constitute prior art at the time of application are neither explicitly nor implicitly admitted to be prior art to the present invention.

Claims

1. A health management module for liquid cooling system of avionics equipment, characterized in that: include: A box body (1), wherein the box body (1) is provided with a liquid inlet (3), a liquid outlet (4) and an electrical connector (5) on the outside; a filter element (8) is provided inside the box body (1); the liquid inlet (3) is connected to the inlet of the filter element (8) through a pipeline, and the outlet of the filter element (8) is connected to the liquid outlet (4) through a pipeline; a temperature and pressure sensor (11) is provided on the pipeline connecting the liquid inlet (3) and the inlet of the filter element (8); and a first pressure sensor (12), a flow meter (14) and a second pressure sensor (13) are provided in sequence on the pipeline connecting the outlet of the filter element (8) and the liquid outlet (4).

2. The avionics equipment liquid cooling system health management module according to claim 1, characterized in that: A bypass valve (9) is provided next to the filter element (8).

3. The avionics equipment liquid cooling system health management module according to claim 2, characterized in that: The bypass valve (9) is composed of a valve body (901), a valve core (902) and a spring (903); when the flow resistance of the filter element (8) is greater than the resistance of the bypass valve (9) spring (903), the bypass valve (9) opens, and the coolant enters the subsequent pipeline through the bypass valve (9), thereby ensuring normal use of the coolant when the filter element (8) fails.

4. The avionics equipment liquid cooling system health management module according to claim 1, characterized in that: A locking strip (6) and an extractor (7) are installed on the box body (1).

5. The avionics equipment liquid cooling system health management module according to claim 1, characterized in that: The filter element (8) is a stainless steel metal fiber sintered felt filter element.

6. The avionics equipment liquid cooling system health management module according to claim 1, characterized in that: The box body (1) has a compartment at the back, in which a processing circuit board (19) is installed, and cables of each sensor and the flow meter (14) are connected to the processing circuit board (19) through through holes; data collected by each sensor and the flow meter (14) are processed by the processing circuit board (19) and then transmitted to the outside of the module through the electrical connector (5) for reporting, and compared with the set value for early warning, and an alarm is issued if the preset threshold is exceeded.

7. The avionics equipment liquid cooling system health management module according to claim 1, characterized in that: The flow meter (14) is a volumetric flow meter (14) with a metal turbine structure.

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