阅读说明：本技术 一种具有防尘功能的月球低温环境模拟胀板式半体热沉结构 (Moon low temperature environment simulation expansion plate type half body heat sink structure with dustproof function ) 是由 李丽芳 何超 魏翔 闫继宏 李强 吴宜勇 韩潇 张磊 杨晓宁 于 2021-07-29 设计创作，主要内容包括：本发明提出了一种具有防尘功能的月球低温环境模拟胀板式半体热沉结构,属于空间环境模拟技术领域。它立式主热沉、设备/样品通道热沉、原位副舱热沉和过渡舱热沉,所述立式主热沉的两侧分别安装有原位副舱热沉和过渡舱热沉,前侧安装有设备/样品通道热沉；所述设备/样品通道热沉、原位副舱热沉和过渡舱热沉均设置有配有供液管路和回液管路的液氮法兰,所述立式主热沉的筒壁由若干纵向的热沉胀板组成,筒底由若干胀板单元拼成,主要用于月球低温背景环境模拟。(The invention provides a moon low-temperature environment simulation expansion plate type half body heat sink structure with a dustproof function, and belongs to the technical field of space environment simulation. The heat sink comprises a vertical main heat sink, a device/sample channel heat sink, an in-situ auxiliary cabin heat sink and a transition cabin heat sink, wherein the in-situ auxiliary cabin heat sink and the transition cabin heat sink are respectively arranged on two sides of the vertical main heat sink, and the device/sample channel heat sink is arranged on the front side of the vertical main heat sink; the device/sample channel heat sink, the in-situ auxiliary cabin heat sink and the transition cabin heat sink are all provided with liquid nitrogen flanges provided with a liquid supply pipeline and a liquid return pipeline, the cylinder wall of the vertical main heat sink is composed of a plurality of longitudinal heat sink expansion plates, and the cylinder bottom is formed by splicing a plurality of expansion plate units and is mainly used for moon low-temperature background environment simulation.)

1. A moon low-temperature environment simulation expansion plate type half body heat sink structure with a dustproof function is characterized by comprising a vertical main heat sink, a device/sample channel heat sink, an in-situ auxiliary cabin heat sink and a transition cabin heat sink, wherein the in-situ auxiliary cabin heat sink and the transition cabin heat sink are respectively arranged on two sides of the vertical main heat sink, and the device/sample channel heat sink is arranged on the front side of the vertical main heat sink;

the device/sample channel heat sink, the in-situ auxiliary cabin heat sink and the transition cabin heat sink are respectively provided with a liquid nitrogen flange (9) provided with a liquid supply pipeline and a liquid return pipeline, the cylinder wall of the vertical main heat sink is composed of a plurality of longitudinal heat sink expansion plates, and the cylinder bottom is spliced by a plurality of expansion plate units;

liquid nitrogen is introduced into the heat sink expansion plate in the test process, cold energy is transmitted to the heat sink expansion plate, the heat sink expansion plate transmits the cold energy to a test piece in a radiation heat exchange mode, a required low-temperature cold background is provided for the test, the cold and black environment of a moon is simulated, the liquid nitrogen flowing in the heat sink expansion plate and the cabin body of a moon dust cabin perform heat convection, high-temperature nitrogen is introduced into the heat sink structure after the test is finished, the temperature of the heat sink structure is recovered to the room temperature, and therefore the container is opened in a repressing mode.

2. The moon low-temperature environment simulation expansion plate type half body heat sink structure with the dustproof function as claimed in claim 1, wherein the transition cabin heat sink comprises a transition cabin barrel heat sink (1) and a transition cabin door heat sink (2), the transition cabin barrel heat sink (1) is connected with the vertical main heat sink, the transition cabin door heat sink (2) is installed at the open end of the transition cabin barrel heat sink, the inner diameter of the transition cabin barrel heat sink (1) is 800-1200mm, and the axial length of the straight barrel section is 300-700 mm.

3. The moon low-temperature environment simulation half-body expansion plate heat sink structure with the dustproof function as claimed in claim 1, wherein the in-situ sub-compartment heat sink comprises an in-situ sub-compartment cylinder heat sink (3) and an in-situ sub-compartment door heat sink (4), the in-situ sub-compartment cylinder heat sink (3) is connected with the vertical main heat sink, the in-situ sub-compartment door heat sink (4) is installed at the open end of the in-situ sub-compartment cylinder heat sink, the inner diameter of the in-situ sub-compartment cylinder heat sink (3) is 800-1200mm, and the axial length of the straight cylinder section is 800-1200 mm.

4. The moon low-temperature environment simulation half-body expansion plate heat sink structure with the dustproof function as claimed in claim 1, wherein the vertical main heat sink comprises a barrel heat sink (5) and a bottom heat sink (6), the bottom heat sink (6) is installed at the bottom of the barrel heat sink (5), the inner diameter of the barrel heat sink (5) is 3000-4000mm, and the axial length of the straight barrel section is 3000-4000 mm.

5. The moon low-temperature environment simulation expansion plate type half body heat sink structure with the dustproof function as claimed in claim 1, wherein the equipment/sample channel heat sink comprises a channel cabin cylinder heat sink (7) and a gate heat sink (8), the channel cabin cylinder heat sink (7) is connected with a vertical main heat sink, the gate heat sink (8) is installed at the opening end of the channel cabin cylinder heat sink, the inner diameter of the channel cabin cylinder heat sink (7) is 2000-3000mm, and the axial length of a straight cylinder section is 300-700 mm.

6. The moon low-temperature environment simulation expansion plate type half body heat sink structure with the dustproof function according to claim 1, wherein the surface of the whole heat sink structure facing a test piece is coated with special black paint, and the performance indexes of the black paint are as follows: the hemispherical emissivity ε h is more than or equal to 0.88 +/-0.02.

7. The moon low-temperature environment simulation expansion plate type half body heat sink structure with the dustproof function according to claim 1, wherein a plurality of Pt100 platinum resistors are arranged on the surface of the whole heat sink structure facing a test piece and used for measuring the surface temperature of the heat sink.

8. The moon low-temperature environment simulation expansion plate type half body heat sink structure with the dustproof function as claimed in claim 1, wherein a skirt is arranged between adjacent heat sink expansion plates for shielding a mounting gap and preventing dust from entering the gap between the container and the heat sink to cause pollution.

9. The moon low-temperature environment simulation expansion plate type half body heat sink structure with the dustproof function according to claim 1, wherein the heat sink expansion plate comprises an elastic heat sink wall plate (10) and a fixed heat sink wall plate (11), the elastic heat sink wall plate (10) is stacked on the fixed heat sink wall plate (11), and the elastic heat sink wall plate (10) deforms after being heated and is combined with the fixed heat sink wall plate (11) to form two channels for introducing liquid nitrogen and nitrogen.

10. The moon low-temperature environment simulation expansion plate type half body heat sink structure with the dustproof function as claimed in claim 1, wherein the heat sink expansion plate is made of stainless steel.

Technical Field

The invention relates to a heat sink system, in particular to a moon low-temperature environment simulation expansion plate type half body heat sink structure with a dustproof function, and belongs to the technical field of space environment simulation.

Background

The cold black space environment is one of the main environments experienced by the spacecraft in the flight orbit, the equivalent temperature of the cold black space environment is about 3K, the absorptivity of the cold black space environment is 1, the heat energy emitted by the spacecraft is completely absorbed, and the cold black space environment is an ideal absolute black body without radiation and reflection. This property of the universe is spatially uniform, isotropic and invariant over time. The environment not only affects the thermal performance of the spacecraft in operation, but also determines the operating characteristics of certain parts of the spacecraft, and is one of important space environments which need to be simulated in the environment simulation equipment. Devices that simulate a cosmic cold black environment are conventionally referred to as "heat sinks". The heat sink is a large heat exchanger, liquid nitrogen flowing in the heat sink performs heat convection with the wall surface of the heat sink, and cold energy is transferred to the wall plate of the heat sink; the heat sink wall plate transmits cold energy to the test piece in a radiation heat exchange mode.

Traditional stainless steel tube welding copper fin heat sink structure need equipartition heat sink structure on whole device to reach the effect of good simulation black cold environment, and the dust gets into the gap between heat sink structure and the container easily, leads to the phenomenon that the pipeline appears silting, blocks up.

Disclosure of Invention

The present invention is directed to solving the above-mentioned technical problems of the background art that require simulation of a space cold-black environment, and provides a heat sink structure that can achieve the same heat sink effect in a case where the heat sink structure is distributed only on the bottom and the side of a vacuum container (i.e., so-called "half body"). In addition, dust is not easy to enter an interlayer gap between the expansion plate type half body heat sink structure and the container, an optical closed space is formed by the dust, open holes are reduced in design, the holes are shielded when the expansion plate type half body heat sink structure is not used, and pollution and blockage caused by the dust are reduced to the maximum extent.

The invention provides a moon low-temperature environment simulation expansion plate type half body heat sink structure with a dustproof function, which comprises a vertical main heat sink, a device/sample channel heat sink, an in-situ auxiliary cabin heat sink and a transition cabin heat sink, wherein the in-situ auxiliary cabin heat sink and the transition cabin heat sink are respectively arranged on two sides of the vertical main heat sink, and the device/sample channel heat sink is arranged on the front side of the vertical main heat sink;

the device/sample channel heat sink, the in-situ auxiliary cabin heat sink and the transition cabin heat sink are all provided with liquid nitrogen flanges provided with a liquid supply pipeline and a liquid return pipeline, the cylinder wall of the vertical main heat sink is composed of a plurality of longitudinal heat sink expansion plates, and the cylinder bottom is formed by splicing a plurality of expansion plate units;

liquid nitrogen is introduced into the heat sink expansion plate in the test process, the cold quantity is transmitted to the heat sink expansion plate, the heat sink expansion plate transmits the cold quantity to a test piece in a radiation heat exchange mode, a required low-temperature cold background is provided for the test, the cold black environment of the outer space is simulated, liquid nitrogen flowing in the heat sink expansion plate and the cabin body of the lunar dust cabin perform heat convection, high-temperature nitrogen is introduced into the heat sink structure after the test is finished, the temperature of the heat sink structure is recovered to the room temperature, and therefore the container is opened in a re-pressing mode.

Preferably, the transition cabin heat sink comprises a transition cabin cylinder heat sink and a transition cabin door heat sink, the transition cabin cylinder heat sink is connected with the vertical main heat sink, the transition cabin door heat sink is installed at the opening end of the transition cabin cylinder heat sink, the inner diameter of the transition cabin cylinder heat sink is 1200mm, and the axial length of the straight cylinder section is 700 mm.

Preferably, the in-situ auxiliary cabin heat sink comprises an in-situ auxiliary cabin cylinder heat sink and an in-situ auxiliary cabin door heat sink, the in-situ auxiliary cabin cylinder heat sink is connected with the vertical main heat sink, the open end of the in-situ auxiliary cabin door heat sink is provided with the in-situ auxiliary cabin door heat sink, the inner diameter of the in-situ auxiliary cabin cylinder heat sink is 800-minus 1200mm, and the axial length of the straight cylinder section is 800-minus 1200 mm.

Preferably, the vertical main heat sink comprises a cylinder heat sink and a bottom heat sink, the bottom heat sink is installed at the bottom of the cylinder heat sink, the inner diameter of the cylinder heat sink is 3000-4000mm, and the axial length of the straight cylinder section is 3000-4000 mm.

Preferably, the device/sample channel heat sink comprises a channel cabin cylinder heat sink and a gate heat sink, the channel cabin cylinder heat sink is connected with the vertical main heat sink, the gate heat sink is installed at the opening end of the channel cabin cylinder heat sink, the inner diameter of the channel cabin cylinder heat sink is 3000mm, and the axial length of the straight cylinder section is 700 mm.

Preferably, the surface of the whole heat sink structure facing the test piece is coated with special black paint, and the performance indexes of the black paint are as follows: the hemispherical emissivity ε h is more than or equal to 0.88 +/-0.02.

Preferably, several Pt100 platinum resistors are arranged on the surface of the whole heat sink structure facing the test piece for measuring the surface temperature of the heat sink.

Preferably, a skirt is arranged between adjacent heat sink expansion plates and used for shielding the mounting gap and preventing dust from polluting the gap between the container and the heat sink.

Preferably, the heat sink expansion plate comprises an elastic heat sink wall plate and a fixed heat sink wall plate, the elastic heat sink wall plate is stacked on the fixed heat sink wall plate, and the elastic heat sink wall plate deforms after being heated and is combined with the fixed heat sink wall plate to form two channels for communicating liquid nitrogen and nitrogen.

Preferably, the heat sink expansion plate is made of stainless steel.

The moon low-temperature environment simulation expansion plate type half body heat sink structure with the dustproof function has the beneficial effects that:

1. the container has large volume (the effective space of the straight cylinder section is phi 2000 plus 3000mm plus 300 plus 700mm), and can meet the test requirements of most spacecrafts.

2. The heat sink structure can bear the average heat load of less than or equal to 400W/m in most occasions²The lower average temperature of the inner surface is realized, the average temperature of the inner surface of the heat sink structure is less than or equal to 100K, the temperature uniformity is good, the temperature uniformity error is less than or equal to +/-5K, the heat absorption rate of the surface of the heat sink structure is high, and the surface absorption rate of the heat sink structure is more than 0.9 because the heat sink structure is reasonably distributed and properly arranged.

3. The invention reduces the temperature (from normal temperature and pressure to the test working pressure 10)^-5Pa magnitude, heat sink temperature less than or equal to 100K) and the time required for heating (the heat sink temperature returns to normal temperature from 100K and the container returns to normal pressure) is less than or equal to 10h due to liquid nitrogenAnd the nitrogen has good heat conduction effect, so the device has high cooling and heating speed.

4. When the test device is cooled, liquid nitrogen is introduced into the heat sink structure, so that a required low-temperature cold background is provided for the test, and the cold-black environment of the outer space is simulated. When the temperature rises, high-temperature nitrogen is introduced into the heat sink, so that the temperature of the heat sink is restored to room temperature, and the container is opened by repressing. The whole system completes thermal cycle by using liquid nitrogen and nitrogen gas, and the cost is low.

5. The heat sink structure designed by the invention forms an optical closed space, the optical closed space is formed, the opening of the heat sink is reduced, dust is not easy to enter an interlayer gap between the expansion plate type half body heat sink structure and the container, and the heat sink structure is shielded by the baffle when a heat counter bore is not used, so that dust particles such as lunar dust are prevented from entering an interlayer between the heat sink expansion plate and the container wall, and pollution and blockage caused by the dust are reduced to the maximum extent.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention.

In the drawings:

fig. 1 is a system block diagram of a moon low-temperature environment simulation expansion plate type half body heat sink structure with a dustproof function according to the present invention;

fig. 2 is an exploded view of a moon low-temperature environment simulation expansion plate type half heat sink structure with a dustproof function according to the present invention;

fig. 3 is a schematic structural diagram of a heat sink expansion plate according to the present invention;

FIG. 4 is a schematic view of the integral heat sink of the lunar dust cabin of the present invention

FIG. 5 is a schematic diagram of a transition cabin and an in-situ sub-cabin heat sink according to the present invention

Fig. 6 is a schematic structural diagram of a bottom heat sink according to the present invention;

fig. 7 is a top view of a bottom heatsink of the present invention;

FIG. 8 is a schematic view of a heat sink structure of the wicket according to the present invention;

fig. 9 is a schematic structural diagram of a gate heat sink according to the present invention;

FIG. 10 is a schematic structural view of an in-situ sub-bay door heat sink according to the present invention;

FIG. 11 is a schematic structural view of a pod door heat sink according to the present invention;

the system comprises a transition cabin barrel heat sink 1, a transition cabin door heat sink 2, an in-situ auxiliary cabin barrel heat sink 3, an in-situ auxiliary cabin door heat sink 4, an in-situ auxiliary cabin door heat sink 5, a barrel heat sink 6, a bottom heat sink 7, a channel cabin barrel heat sink 8, a channel cabin door heat sink 9, a liquid nitrogen flange 10, an elastic heat sink wall plate 10 and a fixed heat sink wall plate 11.

Detailed Description

The following detailed description of embodiments of the invention is provided in conjunction with the appended drawings:

the first embodiment is as follows: the present embodiment is explained with reference to fig. 1 to 11. The moon low-temperature environment simulation expansion plate type half body heat sink structure with the dustproof function comprises a vertical main heat sink, a device/sample channel heat sink, an in-situ auxiliary cabin heat sink and a transition cabin heat sink, wherein the in-situ auxiliary cabin heat sink and the transition cabin heat sink are respectively arranged on two sides of the vertical main heat sink, and the device/sample channel heat sink is arranged on the front side of the vertical main heat sink;

the device/sample channel heat sink, the in-situ auxiliary cabin heat sink and the transition cabin heat sink are all provided with liquid nitrogen flanges 9 provided with liquid supply pipelines and liquid return pipelines, the cylinder wall of the vertical main heat sink is composed of a plurality of longitudinal heat sink expansion plates, and the cylinder bottom is formed by splicing a plurality of expansion plate units;

liquid nitrogen is introduced into the heat sink expansion plate in the test process, the cold quantity is transmitted to the heat sink expansion plate, the heat sink expansion plate transmits the cold quantity to a test piece in a radiation heat exchange mode, a required low-temperature cold background is provided for the test, the cold black environment of the outer space is simulated, liquid nitrogen flowing in the heat sink expansion plate and the cabin body of the lunar dust cabin perform heat convection, high-temperature nitrogen is introduced into the heat sink structure after the test is finished, the temperature of the heat sink structure is recovered to the room temperature, and therefore the container is opened in a re-pressing mode.

According to the container structure and technical requirements, the heat sink compartment heat sink structure is composed of a vertical main heat sink, a device/sample channel heat sink, an in-situ sub-compartment heat sink and a transition compartment heat sink, as shown in the figure. The vertical main heat sink comprises a cylinder heat sink 5 and a bottom heat sink 6, the effective space of the cylinder heat sink 5 is phi 3000-.

(1) Transit cabin heat sink

The transition cabin heat sink is of a horizontal structure and comprises two parts, namely a transition cabin barrel heat sink 1 and a transition cabin door heat sink 2, the transition cabin barrel heat sink 1 is connected with the vertical main heat sink, the transition cabin door heat sink 2 is installed at the opening end of the transition cabin barrel heat sink 1, the effective space is phi 800 plus materials 1200mm x 300 plus materials 700mm (straight barrel section), and the structural form is the same as that of the equipment/sample channel heat sink 7. The transition cabin heat sink is provided with two liquid supply pipelines and two liquid return pipelines, and 4 liquid nitrogen flanges 9 in total.

The heat sink 1 manifold pipes of the transition cabin barrel are arranged at the upper end and the lower end. The transition section cylinder heat sink 1 is provided with two liquid nitrogen flanges 9 which are provided with an inlet and an outlet.

The heat sink 2 of the transition cabin door is a disc-shaped heat sink with the diameter phi of 800 and 1200 mm.

The heat sink 2 of the transition cabin door has a downward-inlet-upward-outlet mode, one path of liquid supply pipeline and one path of liquid return pipeline, as shown in fig. 11.

(2) In-situ auxiliary cabin heat sink

The in-situ auxiliary cabin heat sink is of a horizontal structure and consists of two parts, namely an in-situ auxiliary cabin cylinder heat sink 3 and an in-situ auxiliary cabin door heat sink 4, the in-situ auxiliary cabin cylinder heat sink 3 is connected with the vertical main heat sink, the open end of the in-situ auxiliary cabin door heat sink 4 is provided with the in-situ auxiliary cabin door heat sink 4, the effective space is phi 800 plus 1200mm plus 800 plus 1200mm, and the structural form is the same as that of the equipment/sample channel heat sink 7. The heat sink of the in-situ auxiliary cabin is provided with two liquid supply pipelines and two liquid return pipelines, and the total number of the liquid nitrogen flanges 9 is 4, and liquid nitrogen can be supplied to enter and exit.

And the in-situ auxiliary cabin barrel heat sink 3 collecting pipes are arranged at the upper end and the lower end. The in-situ auxiliary cabin cylinder heat sink 3 is provided with two liquid nitrogen flanges 9 of a liquid supply pipeline and a liquid return pipeline.

The heat sink 4 of the in-situ auxiliary cabin door is a disc-shaped heat sink with the diameter phi of 800 and 1200 mm. The heat sink 4 of the in-situ auxiliary cabin door has liquid inlet and outlet in a downward inlet and upward outlet mode, one path of liquid supply pipeline and one path of liquid return pipeline.

(3) Tubular heat sink

The cylinder heat sink 5 is a cylindrical heat sink, the inner diameter phi is 3000-. The barrel heat sink is composed of 10 expansion plate units, and a skirt edge is arranged between every two adjacent expansion plate units and used for shielding an installation gap. The heat sink is provided with two pairs of liquid nitrogen inlet and outlet flanges, and a liquid supply mode of lower inlet and upper outlet is adopted.

(4) Bottom heat sink

The bottom heat sink 6 is a disc-shaped heat sink, the bottom heat sink 6 is arranged at the bottom of the barrel heat sink 5, the diameter phi of the bottom heat sink 6 is 3000 + 4000mm, as shown in fig. 9, the bottom heat sink 6 is formed by splicing 4 expansion plates, and a round hole is formed in the bottom heat sink 6 and used for penetrating through a support platform column.

The bottom heat sink 6 is reserved with a small entrance door with the size of 800mm multiplied by 650mm, so that the people can conveniently enter and exit the bottom of the container to clean the lunar dust. The small in-out door is in a rotary door opening mode, so that the heat sink open hole can be shielded, and the small in-out door can serve as an anti-pollution plate in the early stage of the test and the shutdown process.

(5) Device/sample channel heat sink

The device/sample channel chamber heat sink is arranged in the sample conveying channel and consists of a channel chamber cylinder heat sink 7 and a channel chamber gate heat sink 8, the channel chamber cylinder heat sink 7 is connected with the vertical main heat sink, the gate heat sink 8 is arranged at the opening end of the channel chamber cylinder heat sink, and the effective space is phi 2000-3000mm (inner diameter) x 300-700mm (straight cylinder section). The channel cabin barrel heat sink 7 is of a horizontal structure, and the collecting pipes are arranged at the upper end and the lower end. The transition section cylinder heat sink is provided with two liquid nitrogen flanges 9 with one inlet and one outlet.

The channel cabin gate heat sink 8 is a disc-shaped heat sink with a diameter of phi 2000 and 3000 mm. The heat sink inlet and outlet of the gate are in a downward inlet and upward outlet mode, one path of liquid supply pipeline and the other path of liquid return pipeline.

In order to facilitate the installation and maintenance of the heat sink structure, the liquid inlet and outlet structure of the heat sink structure must be designed by adopting a detachable inlet and outlet structure.

In order to reduce the cold loss of the heat sink structure and ensure the working efficiency of the heat sink structure, a detachable shielding cover plate is required to be adopted for standby holes on the heat sink structure to shield the holes, and the positions and the number of the holes of the heat sink structure are designed to correspond to the liquid nitrogen flanges of the containers one to one according to the use requirement. Additionally, apertures for controlling the passage of measurement cables, suspension point heat sink openings, guide rail leg apertures, and pedal leg apertures are also provided. When the liquid nitrogen flange of part of the container is not used, the heat sink structure is provided with a baffle for blocking heat radiation, so that the heat sink opening can be shielded to make up the influence of the reduction of the cold and black area caused by the heat sink opening, and simultaneously prevent gas particles generated in the test from falling into an interlayer between the heat sink structure and the container; for the spare hole on the heat sink structure, a detachable shielding cover plate is adopted in the design to block the hole so as to ensure the cold loss of the heat sink structure;

the heat sink expansion plate unit is composed of an elastic heat sink wall plate 10 and a fixed heat sink wall plate 11, the elastic heat sink wall plate 10 is fixed on the fixed heat sink wall plate 11, and the elastic heat sink wall plate 10 deforms after being heated and is combined with the fixed heat sink wall plate 11 to form two channels for communicating liquid nitrogen and nitrogen.

The elastic heat sink wall plate 10 and the fixed heat sink wall plate 11 are welded together to form different types of flow channels, and then the two plates are expanded by a hydraulic means to form a final flow channel.

The heat sink with the structure has the advantages of short processing period, good low-temperature performance of the stainless steel material and excellent vacuum performance, and the surface of the heat sink can be contacted with a low-temperature medium due to the structure, so that the temperature uniformity is good. The capacity of bearing heat load and temperature uniformity are better than those of a tube-plate heat sink, and the defect of slow heat conduction of stainless steel is overcome, and the problem that a heat sink structure needs to adopt a structure, materials and a surface treatment scheme which are easy to prevent dust and remove dust is solved; the heat sink expansion plate is made of stainless steel plates, the two wall plates of the heat sink expansion plate are smooth in surface and free of obvious grooves, and compared with a traditional stainless steel tube welding copper fin structure, the heat sink expansion plate is not prone to deposition of particle solids such as lunar dust.

The heat sink structure lets in liquid nitrogen in the heat sink expansion plate at the test process, for the cold black environment of the cold of required low temperature of experimental provision, simulation space, the liquid nitrogen that flows in the heat sink expansion plate carries out the heat convection with the cabin body in lunar dust cabin, gives the heat sink wallboard with cold volume transmission, and heat sink wallboard rethread radiation heat transfer's mode gives the test piece with cold volume transmission. After the test is finished, high-temperature nitrogen is introduced into the heat sink structure, so that the temperature of the heat sink structure is restored to room temperature, and the container is opened by repressing.

In addition, the heat sink structure is an optical closed space, and dust and the like are not easy to enter an interlayer gap between the heat sink and the container. In the design process, the heat sink opening is considered to be reduced as much as possible, and meanwhile, under the condition that the heat sink hole is not used, the hole is shielded by using a baffle plate, so that dust particles such as lunar dust and the like are prevented from entering an interlayer between the heat sink structure and the wall of the container.

The heat sink structure is subjected to average heat load of less than or equal to 400W/m²When the temperature is higher than the average temperature of the inner surface of the heat sink structure, the average temperature of the inner surface of the heat sink structure is less than or equal to 100K, the temperature uniformity error is less than or equal to +/-5K, and the surface absorption rate of the heat sink structure is more than 0.9.

Cooling time: from normal temperature and pressure to the test working pressure (no-load pressure 10)^-5Pa magnitude), and the required time is less than or equal to 10h when the heat sink temperature is less than or equal to 100K.

Temperature rise time: when the heat sink temperature is returned to normal temperature from 100K and the container is returned to normal pressure, the required time is less than or equal to 10 h;

the maximum working pressure of the heat sink structure is 0.8MPa, and the heat sink structure has the functions of introducing liquid nitrogen into the heat sink, providing a low-temperature cold background of 100K for a test and simulating a cold black environment of outer space. After the test working condition is finished, high-temperature nitrogen is introduced into the heat sink, so that the temperature of the heat sink is restored to be more than 20 ℃, and the container is opened by repressing.

The surface of the whole heat sink structure facing the test piece is coated with special black paint, and the performance indexes of the black paint are as follows: the hemispherical emissivity ε h is more than or equal to 0.88 +/-0.02.

Several Pt100 platinum resistors were arranged on the surface of the entire heat sink structure facing the test piece.

The total leakage rate index requirement of the heat sink structure is as follows: less than 1.3X 10^-6Pa.m³/s。

The above-mentioned embodiments further explain the objects, technical solutions and advantages of the present invention in detail. It should be understood that the above-mentioned embodiments are only examples of the present invention, and are not intended to limit the present invention, and that the reasonable combination of the features described in the above-mentioned embodiments can be made, and any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.