Aerospace thermal control system condenser suitable for microgravity environment

Abstract

The utility model discloses a spaceflight thermal control system condenser suitable for a microgravity environment. The spaceflight thermal control system condenser comprises a refrigerant channel, a plurality of U-shaped heat exchange pipelines arranged around the refrigerant channel, and a shell used for containing the refrigerant channel and the U-shaped heat exchange pipelines. A heat exchange pipe inlet and a heat exchange pipe outlet of the U-shaped heat exchange pipeline are positioned outside the same side of the shell; a refrigerant inlet of the refrigerant channel is located in the top of the shell, and a refrigerant outlet is located in the bottom of the shell. The shell is filled with high-porosity foam metal, and the high-porosity foam metal is tightly filled between the U-shaped heat exchange pipeline and the refrigerant channel in the shell and completely wraps the outer wall of the heat exchange pipeline and the outer wall of the refrigerant channel. The heat exchange tube is filled with the high-porosity foam metal, and the internal thread structure is designed in the heat exchange tube, so that the heat transfer area is remarkably increased, the fluid turbulence effect is enhanced, and the heat exchange efficiency is improved.

Description

Technical Field

[0001] The utility model belongs to the technical field of aerospace thermal control, and in particular relates to a condenser of an aerospace thermal control system suitable for a microgravity environment. Background Art

[0002] The condenser is a key component of a spacecraft's thermal control system, used to dissipate excess heat through heat transfer. However, existing condensers used in microgravity environments have the following major issues:

[0003] The heat exchange efficiency of existing condensers is low and they cannot adapt to the special needs of the microgravity environment. Specifically, they usually use simple planar heat exchange tubes or spiral structures, which have limited heat exchange areas and are difficult to meet the needs of high heat flux density working conditions. At the same time, the fluid flow pattern in the heat exchange tubes is difficult to form stable convection and turbulence in a microgravity environment, further reducing the heat transfer effect. Secondly, in existing condensers, refrigerant channels or cooling water channels mostly use smooth surfaces or closed multi-channel structures. Although they can achieve certain heat exchange performance, their flow resistance is high, resulting in a significant increase in system operating power consumption and reducing the energy utilization efficiency of the spacecraft. The existing condenser has a complex structure and low space utilization, making it difficult to meet the needs of compact design. In addition, the use of traditional materials results in a larger overall mass of the equipment, which increases the launch and operation costs of the spacecraft.

[0004] At the same time, existing condensers lack real-time monitoring and control. Most lack temperature and pressure sensors, making it difficult to monitor key parameters during the heat exchange process in real time. This results in a lack of data support for system operation, hindering the dynamic regulation of the thermal control system and increasing the risk of potential failures.

[0005] In summary, existing condenser designs for microgravity environments suffer from significant issues with heat transfer efficiency, flow resistance, structural adaptability, volumetric mass, microgravity adaptability, and real-time monitoring capabilities. These issues directly restrict the performance and operational efficiency of spacecraft thermal control systems, necessitating a condenser design that effectively addresses these challenges. Summary of the Invention

[0006] The purpose of the present invention is to address the deficiencies in the prior art and to provide a condenser for aerospace thermal control systems suitable for microgravity environments that uses water cooling and a high-porosity foam metal reinforced heat exchange structure to improve heat exchange efficiency and reduce flow resistance.

[0007] To solve the above technical problems, the technical method adopted by the present invention is as follows: the present invention discloses a condenser of an aerospace thermal control system suitable for a microgravity environment, comprising a refrigerant channel, a plurality of U-shaped heat exchange pipes arranged around the refrigerant channel, and a shell for accommodating the refrigerant channel and the U-shaped heat exchange pipes;

[0008] The heat exchange pipe inlet and the heat exchange pipe outlet of the U-shaped heat exchange pipe are located outside the same side of the shell;

[0009] The refrigerant inlet of the refrigerant channel is located at the top of the shell, and the refrigerant outlet is located at the bottom of the shell;

[0010] The interior of the shell is filled with high-porosity foam metal, which is tightly filled between the U-shaped heat exchange pipe and the refrigerant channel in the shell and completely covers the outer walls of the heat exchange pipe and the refrigerant channel.

[0011] Furthermore, the lower bottom surface of the shell is provided with a foot pad for support and shock absorption.

[0012] Furthermore, the foam metal is a high-porosity foam metal structure with a porosity of 0.7-0.9 and a pore density of 10-20 PPI.

[0013] Furthermore, the high-porosity foam metal is made of foam copper or foam nickel.

[0014] Furthermore, the inner wall of the U-shaped heat exchange pipe is provided with an internal thread structure for increasing the fluid turbulence effect and improving the heat exchange effect.

[0015] Furthermore, the shell is a galvanized sheet shell, and a sealing ring is provided at the connection between the U-shaped heat exchange pipe and the refrigerant channel and the shell.

[0016] Furthermore, a flexible thermally conductive gasket is provided between the high-porosity foam metal and the inner wall of the shell to improve heat transfer efficiency and buffer mechanical vibration.

[0017] Furthermore, a plurality of guide vanes for guiding the flow of the refrigerant are provided inside the refrigerant channel, so as to guide the flow of the refrigerant, evenly distribute the flow velocity, and improve the heat exchange efficiency.

[0018] Furthermore, temperature and pressure sensors are provided inside the condenser to monitor the real-time temperature and pressure in the U-shaped heat exchange pipe and the refrigerant channel respectively, and transmit the data to an external control system.

[0019] Furthermore, a group of temperature and pressure sensors are provided at the heat exchange tube inlet and heat exchange tube outlet of the U-shaped heat exchange pipe and the refrigerant inlet and refrigerant outlet of the refrigerant channel. Beneficial effects

[0020] 1. Improve heat transfer efficiency and adapt to microgravity environment

[0021] This new design utilizes high-porosity foam metal to fill the exterior of the heat exchange tubes and incorporates internal threads to significantly increase the heat transfer area and enhance fluid turbulence, thereby improving heat exchange efficiency. Furthermore, it optimizes the flow paths of the refrigerant and cooling water, utilizing countercurrent heat exchange to maintain uniform fluid distribution, overcoming fluid instability in microgravity environments and effectively enhancing the condenser's thermal management performance.

[0022] 2. Compact structure and modular design to meet multi-task requirements

[0023] This new design utilizes a compact housing design, combined with lightweight, high-porosity metal foam, to significantly reduce the volume and mass of the device, saving both space and payload costs. Furthermore, through its modular design, the condenser size and number of modules can be flexibly adjusted to meet the heat exchange requirements of different missions, enhancing the system's adaptability and scalability.

[0024] 3. Intelligent monitoring and efficient operation

[0025] Temperature and pressure sensors are installed at key locations on the condenser's heat exchange tube inlet and outlet, as well as in the refrigerant channel, to monitor temperature and pressure changes during the heat exchange process in real time, providing data support for the dynamic regulation of the thermal control system. The porosity and pore density of the metal foam are optimized to improve the safety and intelligence of the aerospace thermal control system. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 Schematic diagram of the cross-section of the condenser in the present invention;

[0027] Figure 2 Schematic diagram of the overall structure of the condenser in the present invention;

[0028] Figure 3 This is a schematic diagram of the intelligent detection module of the condenser in the present invention. DETAILED DESCRIPTION

[0029] The present invention will be described in further detail below with reference to the accompanying drawings and specific implementation methods.

[0030] like Figure 1 、 2 As shown, the high-efficiency modular condenser for a microgravity thermal control system described in the present invention basically comprises: 1- shell, 2- U-shaped heat exchange pipe, 2a- heat exchange pipe inlet, 2b- heat exchange pipe outlet, 3- refrigerant channel, 3a- refrigerant inlet, 3b- refrigerant outlet, 4- high-porosity foam metal, and 5- foot pad.

[0031] like Figure 1-2As shown, the galvanized steel shell 1 has been degreased, rust-removed, painted, and baked for excellent corrosion resistance. The U-shaped heat exchange pipe 2 is a copper tube, fixedly mounted within the shell 1 via bolts. Water flows through the pipe, while the refrigerant channel 3 circulates refrigerant. The U-shaped heat exchange pipe 2 and the refrigerant channel 3 are filled with a high-porosity, through-hole metal foam 4. This device fully utilizes the excellent properties of the metal foam 4: low density and high porosity, high specific strength and stiffness, large specific surface area, corrosion and high temperature resistance, and noise reduction. The metal foam 4 is made of copper foam or nickel foam, with a porosity of 0.7-0.9 and a pore density of 10-20 PPI.

[0032] The condenser measures 175mm in length, 160mm in width, and 80mm in height. It is a modular condenser with significantly enhanced heat exchange capacity. For thermal control systems with large cooling capacity requirements, the number of modules can be adjusted according to the specific heat exchange requirements, the heat exchange capacity can be flexibly changed, and the adaptability of the heat exchanger can be enhanced. Enhanced condensers of different sizes can also be prepared separately.

[0033] like Figure 1 As shown in the internal structure diagram, the heat exchange tube outlet 2b is positioned higher than the heat exchange tube inlet 2a. Water flows from bottom to top within the U-shaped heat exchange tube 2, while refrigerant flows from top to bottom through the refrigerant channel 3 outside the tube. This device utilizes water cooling, resulting in low condensation temperatures and economical and energy-efficient operation. The heat exchange tube 2 is filled with a high-porosity metal foam 4, which increases the heat exchange area, reduces vibration, and reduces noise. The high porosity also enhances heat transfer. The inner wall of the heat exchange tube 2 is internally threaded, further enhancing heat transfer. The compact design of this device enables efficient heat dissipation within a limited space.

[0034] Among them, the intelligent detection function of the condenser, such as Figure 3 As shown, it includes a temperature sensor 6, a pressure sensor 7, a data acquisition module 8, a central processing unit 9, a communication module 10, a display and alarm module 11 and a power supply system 12.

[0035] Temperature sensors 6 are respectively installed at the heat exchange tube inlet 2a and heat exchange tube outlet 2b of the U-shaped heat exchange pipe 2, and the refrigerant inlet 3a and refrigerant outlet 3b of the refrigerant channel 3, for real-time monitoring of the temperature changes of the fluid in the heat exchange tube and the refrigerant in the refrigerant channel.

[0036] The pressure sensor 7 is installed at the same position as the temperature sensor 6, and is respectively installed at the heat exchange tube inlet 2a and the heat exchange tube outlet 2b of the U-shaped heat exchange pipe 2, and the refrigerant inlet 3a and the refrigerant outlet 3b of the refrigerant channel 3, for real-time monitoring of the pressure conditions of the fluid in the heat exchange tube and the refrigerant channel.

[0037] Data acquisition module 8 is used to receive signals from temperature and pressure sensors, convert analog signals into digital signals, and pre-process the data. Central processing unit 9 is used to process the temperature and pressure data transmitted by data acquisition module 8, analyze the operating status of the condenser, and determine whether any abnormalities exist. The device is also equipped with a communication module 10, which transmits the processed data to an external control system or monitoring terminal via wired or wireless means such as Ethernet, Wi-Fi, or Bluetooth. Display and alarm module 11 is used to display temperature and pressure data at each monitoring point of the condenser in real time; when an abnormality is detected, an audible and visual alarm is issued.

[0038] The power supply system 12 is used to provide stable power to all the above hardware modules to ensure the reliable operation of the intelligent monitoring system.

[0039] The basic principles, main features, and advantages of the present invention are shown and described above. Those skilled in the art should understand that the present invention is not limited to the foregoing embodiments. The foregoing embodiments and descriptions are merely illustrative of the principles of the present invention. Various changes and modifications may be made to the present invention without departing from the spirit and scope of the present invention. Such changes and modifications are intended to fall within the scope of the present invention. The scope of protection claimed in the present invention is defined by the appended claims and their equivalents.

Claims

1. A condenser for a space thermal control system suitable for a microgravity environment, comprising a refrigerant channel (3) and a plurality of U-shaped heat exchange pipes (2) arranged around the refrigerant channel (3), characterized in that: It comprises a shell (1) for accommodating the refrigerant channel (3) and the U-shaped heat exchange pipe (2); The heat exchange pipe inlet (2a) and the heat exchange pipe outlet (2b) of the U-shaped heat exchange pipe (2) are located outside the same side of the shell (1); The refrigerant inlet (3a) of the refrigerant channel (3) is located at the top of the shell (1), and the refrigerant outlet (3b) is located at the bottom of the shell (1); The shell (1) is filled with high-porosity foam metal (4), and the high-porosity foam metal (4) is tightly filled between the U-shaped heat exchange pipe (2) and the refrigerant channel (3) in the shell, and completely covers the outer walls of the heat exchange pipe and the refrigerant channel.

2. The aerospace thermal control system condenser suitable for a microgravity environment according to claim 1, characterized in that: The lower bottom surface of the shell (1) is provided with a foot pad (5) for supporting and absorbing shock.

3. The aerospace thermal control system condenser suitable for a microgravity environment according to claim 1, characterized in that: The foam metal is a high-porosity foam metal structure with a porosity of 0.7-0.9 and a pore density of 10-20 PPI.

4. The aerospace thermal control system condenser suitable for a microgravity environment according to claim 3, characterized in that: The high-porosity foam metal (4) is made of foam copper or foam nickel.

5. The aerospace thermal control system condenser suitable for a microgravity environment according to claim 1, characterized in that: The inner wall of the U-shaped heat exchange pipe (2) is provided with an internal thread structure for increasing the fluid turbulence effect and improving the heat exchange effect.

6. The aerospace thermal control system condenser suitable for a microgravity environment according to claim 1, characterized in that: The shell (1) is a galvanized sheet shell, and a sealing ring is provided at the connection between the U-shaped heat exchange pipe (2) and the refrigerant channel (3) and the shell (1).

7. The aerospace thermal control system condenser suitable for a microgravity environment according to claim 1, characterized in that: A flexible heat-conducting gasket for improving heat transfer efficiency and buffering mechanical vibrations is provided between the high-porosity foam metal (4) and the inner wall of the housing (1).

8. The aerospace thermal control system condenser suitable for a microgravity environment according to claim 1, characterized in that: A plurality of groups of guide plates for guiding the flow of the refrigerant are arranged inside the refrigerant channel (3).

9. The aerospace thermal control system condenser suitable for a microgravity environment according to claim 1, characterized in that: Temperature and pressure sensors are provided inside the condenser to monitor the real-time temperature and pressure in the U-shaped heat exchange pipe (2) and the refrigerant channel (3), respectively, and transmit the data to an external control system.

10. The aerospace thermal control system condenser suitable for a microgravity environment according to claim 9, characterized in that: A set of temperature and pressure sensors are provided at the heat exchange tube inlet (2a) and the heat exchange tube outlet (2b) of the U-shaped heat exchange pipe (2) and the refrigerant inlet (3a) and the refrigerant outlet (3b) of the refrigerant channel (3).

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