Atmosphere sampling and storage device for a spacecraft exploring venus

Abstract

This invention discloses an atmospheric sampling and storage device for a Venus probe, relating to the field of atmospheric sampling and storage technology. It includes an air intake duct connecting to the Venusian atmosphere outside the spacecraft, with a cooling and compression device connected to the end of the duct. The cooling and compression device is connected to an unlocking and separation mechanism, the outlet of which is connected to a gas storage duct. A gas storage valve is located at the outlet of the gas storage duct to control the gas entering the corresponding gas storage tank. The system is configured with five sets of gas storage valves and gas storage tanks, enabling the phased collection and independent packaging of gases at different altitudes. Each gas storage tank is equipped with a sensing and regulation device. This invention is applicable to gas sampling and storage during high-speed traversal of the Venusian atmosphere by planetary spacecraft. Through multiple atmospheric entries, it completes the phased collection, graded liquefaction, compression storage, and separate tank sealing of gases at different altitudes. It can withstand the extreme temperature and pressure environment caused by hypersonic flight and effectively maintain the original state of the gas during collection.

Description

Technical Field

[0001] This invention relates to the field of extraterrestrial atmospheric sampling and storage technology, specifically to an atmospheric sampling and storage device for Venus exploration spacecraft. Background Technology

[0002] Venus exploration is at the forefront of planetary science. Obtaining atmospheric samples from different altitudes on Venus and bringing them back to Earth for analysis is of irreplaceable scientific value for studying its evolutionary history, climate characteristics, and even exoplanet analogies. However, the extreme high temperature and pressure environment on the surface of Venus, as well as the intense aerodynamic heating and complex flow field interference encountered by spacecraft when passing through the atmosphere at hypersonic speeds, pose serious challenges to atmospheric sampling technology.

[0003] For Venus sampling, storage, and recovery missions, traditional gasbag sampling methods are insufficient for recovery and analysis. Therefore, a Venus probe is used to repeatedly penetrate the atmosphere to complete multiple sampling, staged liquefaction, compressed storage, and separate container storage. Current planetary atmospheric sampling technologies often employ single containers or simple on / off valve designs, which are insufficient to meet the need for multiple independent samplings of Venusian gas at different altitudes within a single mission. This compromises sample independence and analytical value, severely impacting the accuracy of subsequent analyses.

[0004] Therefore, a dedicated system is needed that can adapt to the extreme environment of Venus and be compatible with Venus probes to achieve multiple, independent, and reliable atmospheric sampling and storage. Summary of the Invention

[0005] The purpose of this invention is to provide an atmospheric sampling and storage device for a Venus exploration spacecraft. This device can accurately and reliably complete multiple independent collections, graded liquefaction, compression processing, state adjustment, and separate packaging and storage of atmospheric samples at different altitudes on Venus under hypersonic flight conditions.

[0006] The technical solution of this invention is: an atmospheric sampling and storage device for a Venus exploration spacecraft, comprising an air intake, a cooling and compression device, an unlocking and separation mechanism, an air storage duct, an air storage valve, an air storage tank, a temperature monitoring module, a pressure monitoring module, a pressure sensor, a temperature regulation module, and a pressure regulation module. The sampling port of the air intake is located on the back of the spacecraft. The air intake outlet is connected to the air inlet of the cooling and compression device, and the air outlet of the cooling and compression device is connected to the front end of the unlocking and separation mechanism. The rear end of the unlocking and separation mechanism is connected to the air storage duct inlet. The air storage valve is installed at the air storage duct outlet and is used to control the opening and closing of the air storage tank. Each air storage valve is connected to a corresponding air storage tank. A total of five air storage duct outlets, air storage valves, and air storage tanks are provided. The temperature monitoring module, pressure monitoring module, pressure sensor, temperature regulation module, and pressure regulation module are integrated into the internal space of the air storage tank shell.

[0007] Compared with the prior art, the present invention has the following advantages:

[0008] 1. As a mission payload for a planetary exploration spacecraft, the present invention employs a rear-mounted air intake layout. This design effectively avoids the high-intensity shock wave region on the spacecraft's belly and the low-pressure rarefied vacuum region at the tail. The airflow pressure and temperature on the rear of the spacecraft are moderate, and the gas flow is stable, representing the optimal aerodynamic solution suitable for hypersonic flight conditions. Furthermore, the size and layout of the sampling port in this design do not affect the original aerodynamic shape and flight stability of the spacecraft.

[0009] 2. The outer shell of the device of the present invention adopts a compact narrow rectangular parallelepiped configuration, which significantly improves the spatial compatibility and integration of the device in the limited space of the aircraft cabin and effectively avoids spatial interference with other airborne systems of the aircraft.

[0010] 3. The sampling port of the air intake duct of this invention serves as the gas sample capture interface. It employs a 20mm diameter circular inlet configuration. The circular cross-section helps to form a uniform and symmetrical airflow field, effectively reducing flow separation and eddy current generation. Simultaneously, to achieve minimal aerodynamic cost and maximum structural integrity, the sampling port is integrated with the aircraft skin, ensuring a smooth transition and continuous fusion. Its lip line closely matches the fuselage streamline, preventing the sampling port from being exposed as a separate component and increasing additional aerodynamic drag and noise. This ensures that the incoming gas can smoothly enter the sampling channel, improving collection efficiency and maximizing the originality of the sample. Furthermore, the integrated design enhances the overall structural integrity and improves the reliability of the sampling process.

[0011] 4. The sampling port of this invention is integrated upstream of the air intake channel, with a smooth connection between the sampling port and the air intake channel. The air intake channel adopts a constant-diameter circular tube structure, providing sufficient flow area for gas flow and establishing a delivery pipeline with low flow resistance and stable flow characteristics. The sampling port and the air intake channel together constitute an efficient and stable gas capture and delivery system, providing reliable raw gas samples for downstream storage devices.

[0012] 5. This invention incorporates a cooling and compression device at the rear end of the air inlet duct for the graded liquefaction, effective purification, and compression of the captured atmospheric samples. Gas samples directly captured by the air inlet duct are at high temperatures and low pressures, and their main component is carbon dioxide, accounting for over 95% of Venus's atmosphere. Direct storage would occupy a large volume of available space and have limited scientific analytical value. To improve sample storage efficiency and scientific value, this device employs a graded condensation separation technology: after the gas sample enters the cooling container through the air inlet duct, the system controls a liquid nitrogen storage tank to release nitrogen into the cooling container's interlayer, cooling the gas inside the container to below the sublimation point of carbon dioxide (approximately -78°C). At this temperature, the carbon dioxide gas is solidified and separated, stored at the bottom of the container, while the remaining trace but scientifically valuable components remain in a gaseous state. Subsequently, the outlet valve opens, the vacuum pump starts, extracting and pressurizing these enriched precious gas components, and transporting them to the downstream gas storage duct for separate tank packaging. This design significantly increases the effective concentration of the stored gas and reduces the proportion of ineffective storage volume, thereby maximizing the overall scientific value of the sampling mission within a limited payload space.

[0013] 6. This invention incorporates an unlocking and separation mechanism at the junction of the air intake and air storage channels. During sampling, this mechanism provides a rigid connection and sealing between the air intake and air storage channels. After the sealing process is complete, it can be unlocked under controlled instructions, utilizing the driving force of a built-in elastic element to achieve active and safe separation of the air storage module. This facilitates the subsequent ejection and recovery of the air storage module from the machine body. The separation process is rapid and reliable, and the mechanism automatically resets after unlocking, preventing secondary interference with the separated components.

[0014] 7. The gas storage channel structure of this invention adopts a "one-in, multiple-out" tree-like flow distribution structure to achieve the function of multiple sampling and storage. A main gas storage channel receives the total airflow from the inlet channel, and then the airflow is evenly and stably distributed to the branch gas storage channels connecting the various gas storage valves through the flow distribution connectors. This design has a compact layout, clear gas flow path, and efficient distribution, which can realize multiple collections and independent storage of different target samples, and preserve the original atmospheric samples without crossflow, which is conducive to improving the scientific research value of the recovered samples.

[0015] 8. This invention installs a corresponding gas storage valve at each branch outlet of the gas storage channel. When the device is in a normally closed state, the valve is tightly closed, isolating the external environment from the internal environment of the gas storage tank, ensuring the safe standby of the device. During the time window for performing the sampling task, the valve of the gas storage tank corresponding to the current target sample is quickly opened, while the valves of other gas storage tanks remain tightly closed, accurately guiding the airflow into the designated gas storage tank. After sampling is completed, the valve is quickly closed, ensuring the independence of each sampling and the purity of the sample.

[0016] 9. The gas storage tank of the present invention integrates a sample status monitoring system, which consists of a temperature sensor and a pressure sensor. The sensors can sense the temperature and pressure information of the gas sample in the gas storage tank in real time, and can realize real-time monitoring of the status changes of the gas sample in the tank during the mission. The sensor is installed on the top of the gas storage tank, and the flange connector ensures the airtightness of the gas storage tank while realizing the transmission of electrical signals.

[0017] 10. The gas storage tank system of this invention integrates temperature and pressure regulation devices. Temperature regulation employs a TEC semiconductor thermal control chip based on the Peltier effect. By changing the direction of the current, the cooling and heating modes of the thermal control chip can be switched, thereby controlling the temperature of the gas inside the tank to decrease or increase. Heat is transferred between the gas inside the tank and the TEC semiconductor thermal control chip through heat transfer aluminum sheets, improving heat transfer efficiency while preventing direct contact between the thermal control chip and the gas inside the tank, ensuring gas purity. The other end of the thermal control chip exchanges heat with the outside environment through heat transfer aluminum sheets, ensuring stable system operation. Pressure regulation is achieved mechanically by adjusting the volume of the gas storage space inside the tank by changing the extension and retraction length of the corrugated section, thus controlling pressure changes and ensuring the vacuum degree before filling and the sealing performance after filling. Through real-time sensing and autonomous adjustment of the temperature and pressure state of the gas inside the tank by the monitoring and regulation systems, the state correction during gas sample storage and the long-term safety of the gas storage system are ensured. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the module composition of the atmospheric sampling and storage device for a Venus probe spacecraft provided in an embodiment of the present invention;

[0019] Figure 2 This is an overall structural diagram of the atmospheric sampling and storage device for a Venus probe spacecraft provided in an embodiment of the present invention;

[0020] Figure 3 This is a schematic diagram of the unlocking and separation mechanism provided in an embodiment of the present invention;

[0021] Figure 4 This is a diagram of the gas storage tank assembly provided in an embodiment of the present invention;

[0022] Figure 5 This is a schematic diagram of the cooling and compression device design provided in an embodiment of the present invention;

[0023] Figure 6 This is a schematic diagram of the integrated design of the sampling port and the air intake provided in an embodiment of the present invention;

[0024] Figure 7 This is a schematic diagram of the gas storage duct design provided in an embodiment of the present invention.

[0025] Figure 8 This is a simulation result diagram provided by an embodiment of the present invention. Detailed Implementation

[0026] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention. Furthermore, the technical features involved in the various embodiments of this invention described below can be combined with each other as long as they do not conflict with each other. To achieve the above objectives, this invention adopts the following technical solution. Specific implementation method one:

[0028] Combination Figure 1 and Figure 2 This embodiment describes an atmospheric sampling and storage device for a Venus probe. The device is located inside the Venus probe, with the sampling opening located on the back of the probe. The Venus atmospheric sampling and storage device includes an atmospheric acquisition and processing module, an unlocking and separation mechanism 3, and a gas sample storage and encapsulation module. Figure 1 As shown, Venus's atmosphere first enters the intake module, which includes... Figure 2 The air intake duct 1 then enters... Figure 1 The cooling and compression device is also known as Figure 2 The cooling compression device 2, through Figure 1 After the cooling and compression unit enters Figure 1 Unlock the separation mechanism 3, and then enter. Figure 1 The gas storage module, Figure 1 The gas storage module includes Figure 2 The gas storage channel 4, gas storage valve 5, gas storage tank 6, and gas storage box 7. Figure 1 The temperature monitoring module in the middle includes Figure 4 The first flange mounting 17 and temperature sensor 18; the pressure monitoring module includes Figure 4 The second flange mounting component 19 and pressure sensor 20; the temperature control module is also... Figure 4 Temperature regulation system 21; pressure regulation module includes Figure 4 The electric winch 22, pulley 23, pressure control spring 24, and corrugated air storage liner 25 are included.

[0029] The atmospheric sampling and processing module includes an air inlet 1, a cooling and compression device 2, and an unlocking and separation mechanism 3. The air inlet 1 and the cooling and compression device 2 are connected, and the outlet of the cooling and compression device 2 is connected to the unlocking and separation mechanism 3. The gas sample storage and packaging module includes a gas storage channel 4, a gas storage valve 5, a gas storage tank 6, and a gas storage box 7. The inlet end of the gas storage channel 4 is connected to the unlocking and separation mechanism 3, and the outlet is connected to the gas storage valve 5. The gas storage valve 5 is connected to the gas storage tank 6. Except for the part of the gas storage channel 4 connected to the unlocking and separation mechanism 3, the entire gas sample storage and packaging module is integrated inside the gas storage box 7. Specific Implementation Method Two:

[0031] Combination Figure 2 , Figure 3 and Figure 6 This embodiment is described below. A schematic diagram of the air intake duct 1 in this embodiment is shown in the figure. Figure 6 As shown, Figure 2 The sampling port of air intake 1 is integrated with the air intake 1 itself. The sampling port adopts a circular capture interface configuration, with the lip line aligned with the streamline of the aircraft. The sampling port is integrated with the aircraft's dorsal skin to reduce airflow separation and turbulence, ensuring the originality of the sample. At the same time, the integrated design enhances the overall structural integrity and improves the reliability of the sampling process. Specific implementation method three:

[0033] Combination Figure 2 and Figure 5 This embodiment describes in detail the structure and operation of the cooling compression device 2. For example... Figure 2 As shown, the device is connected between the air intake duct 1 outlet and the unlocking and separation mechanism 3. Its core function is to perform graded condensation, component separation, purification and pressurization on the captured high-temperature Venusian atmospheric sample.

[0034] The cooling and compression device 2 includes a cooling container 27 and a liquid nitrogen refrigeration subsystem and a gas flow control subsystem connected thereto.

[0035] like Figure 5 As shown, the liquid nitrogen refrigeration subsystem consists of a liquid nitrogen storage tank 30, a liquid nitrogen valve 31, and a nitrogen exhaust valve 32. The liquid nitrogen storage tank 30 is connected to the jacket or internal heat exchanger of the cooling container 27 through the liquid nitrogen valve 31 to provide a precise and controllable cryogenic environment to the cooling container. The exhaust valve 32 is used to discharge the vaporized nitrogen and maintain the system pressure balance.

[0036] Continue to refer to Figure 5 The gas process control subsystem includes an inlet valve 26, an outlet valve 28, and a vacuum pump 29. The inlet valve 26 connects the outlet of the inlet duct 1 to the inlet of the cooling container 27; the outlet valve 28 connects the gas outlet of the cooling container 27 to the inlet of the vacuum pump 29; the outlet of the vacuum pump 29 is connected to the pipeline between the downstream unlocking and separation mechanism 3, which is responsible for extracting the processed enriched gas and pressurizing it to a pressure level suitable for storage.

[0037] The working process of the cooling compression unit 2 is divided into four stages:

[0038] Sample introduction and temporary storage stage: The cooling container 27 is initially in a vacuum state. When the spacecraft enters the sampling area, the inlet valve 26 opens, while the outlet valve 28, liquid nitrogen valve 31, and exhaust valve 32 remain closed. The original Venusian atmosphere from the inlet 1 enters the cooling container 27 under the pressure difference between the inside and outside of the spacecraft, completing the collection and temporary storage of the gas sample.

[0039] Cryogenic and Liquefaction Separation Stage: Just before the spacecraft leaves the sampling area, the air inlet valve 26 closes. The liquid nitrogen valve 31 opens, and nitrogen gas fills the jacket of the cooling container 27, rapidly and uniformly lowering its internal temperature to the sublimation point of carbon dioxide (approximately -78°C) and maintaining it stable. In this cryogenic environment, approximately 95% of the carbon dioxide in the sample is precipitated and solidified, accumulating on the container wall; while high-value trace components remain in a gaseous state, thus achieving effective separation and enrichment.

[0040] Enriched Gas Extraction and Pressurization Stage: The outlet valve 28 opens. The vacuum pump 29 starts, extracting all the enriched precious gas components from the cooling container 27 and compressing and pressurizing them within the pump before delivering them to the downstream gas storage module. The pressurized gas flows through the unlocking and separation mechanism 3 into the gas storage channel 4, completing the separate tank sealing. Afterward, the outlet valve 28 closes, and the vacuum pump 29 stops.

[0041] Exhaust Gas Emission and Reset Phase: After the spacecraft completes its atmospheric reentry and returns to orbit, the system executes the exhaust gas emission and reset procedure. First, the liquid nitrogen supply is completely stopped. Cooling container 27 and its connected air intake duct 1 and gas storage duct 4 are gradually heated above freezing point under space environment or active heating, causing the remaining liquid carbon dioxide inside to completely vaporize. Subsequently, under controlled commands, air intake valve 26 opens, utilizing the residual pressure in gas storage duct 4 and cooling container 27 to exhaust all remaining carbon dioxide and other unsealed gases in the entire gas pipeline (including air intake, cooling container, and gas storage duct) into the space vacuum environment. This process ensures the cleanliness of the sampling system, avoids cross-contamination between samples at different altitudes, and restores the system to its initial vacuum standby state. Air intake valve 26, exhaust valve 28, liquid nitrogen valve 31, and exhaust valve 32 are then closed, preparing the spacecraft for its next Venus atmospheric reentry and sampling mission.

[0042] To further verify the effectiveness of the cooling compression device in this invention for enriching the sampled gas, Figure 8Numerical simulation results are presented based on the actual operating parameters of the device of this invention (sampling port diameter 20mm, gas storage tank volume 5L, cooling temperature -140℃, CO2 sublimation rate 60%, compressor ultimate vacuum 50Pa, etc.), comparing the gas sampling effects of natural intake mode and cooled compression intake mode. Simulations show that a single natural intake can obtain approximately 0.104g of raw atmospheric sample, of which the mass of non-CO2 components is approximately 0.005g, with a concentration of approximately 4.9%; while after cooling compression intake treatment, a single sample actually seals and purifies approximately 0.035g of gas, of which the mass of non-CO2 components is approximately 0.004g, and the concentration can be increased to approximately 11.5%, with an enrichment factor of 2.35 times; after 10 cooling compression accumulations in the same gas storage tank, the mass of non-CO2 components in the total sealed gas can be increased to approximately 0.04g. It is evident that this invention, through staged condensation separation and compression pressurization, significantly increases the relative content of high-scientific-value trace components within a limited gas storage volume, effectively improving sample quality. Specific implementation method four:

[0044] Combination Figure 2 , Figure 5 as well as Figure 7 This embodiment is described below. Before the aircraft reaches the area where the target gas is located, the inlet valve 26 of the cooling compression device 2 and the five gas storage valves 5 are all closed, isolating the external environment from the internal environment of the gas storage tank 6. During the sampling window of the mission, the inlet valve 26 of the cooling compression device 2 is quickly opened, and the gas sample flows through the sampling port after being compressed by the high-pressure gas on the back of the aircraft. Since the initial state inside the cooling container 27 is a vacuum state, the internal pressure is much lower than the gas pressure on the back of the aircraft. The gas is captured by the sampling port and enters the air intake duct 1. The air intake duct 1 adopts a uniform diameter circular tube structure with a smooth inner wall, which is smoothly connected to the sampling port. The gas enters the cooling container 27. When the pressure inside the container and outside the sampling port of the aircraft is balanced, the inlet valve 26 is closed, and the gas in the cooling container 27 is cooled and compressed. After processing, the exhaust valve 28 opens, the vacuum pump 29 starts, and simultaneously, the gas storage valve 5 of the gas storage tank 6 corresponding to the current target sample quickly opens, while other gas storage valves 5 remain closed. The gas is then pressurized by the vacuum pump 29 and flows steadily into the gas storage channel 4. After flowing through the main gas storage channel, it flows through the branch gas storage channel to the target gas storage tank 6 with its gas storage valve 5 open, quickly filling it. The vacuum pump 29 evacuates the cooling container 27 to its highest vacuum level, and then the gas storage valve 5 and vacuum pump 29 quickly close, completing the sample encapsulation and the single sampling task. The precise guidance of the gas by the gas storage channel 4 and the gas storage valve 5 ensures efficient and stable sample collection for each sample, while the independent gas storage tank 6 ensures the independence of the encapsulation and the purity of the sample. The configuration of the gas storage channel 4 is as follows: Figure 7As shown, the gas storage channel 4 adopts an optimized "one inlet and multiple outlet" tree-shaped diversion configuration. A main gas storage channel main pipe receives the total airflow from the inlet channel, and then through a specially designed diversion connector, the airflow is smoothly and evenly distributed to five independent branch gas storage channels, each branch corresponding to a gas storage tank 6.

[0045] Specific Implementation Method Five: Combining Figure 2 and Figure 3 This implementation method is described below. For example... Figure 2 As shown, the unlocking and separation mechanism 3 is installed between the cooling and compression device 2 and the inlet of the gas storage channel 4. During the sampling task, it provides a rigid connection and sealing guarantee for the atmospheric sampling and processing module and the gas sample storage and packaging module. After the packaging task is completed, it is unlocked under controlled instructions to achieve active and safe separation of the gas sample storage and packaging module. Please refer to... Figure 3 The initial state of the unlocking and separation mechanism 3, i.e. the connection state during the sampling task, is as follows: the air inlet connector 8 is connected to the air inlet 1; the air outlet connector 13 is connected to the air storage 4, the air outlet connector 13 is locked by the locking steel ball 11, and the air outlet connector 13 presses against the gasket 14 and the separation spring 15; the slider 9 is pressed against the slider constraint ring 12 by the locking spring 10, which restricts the locking steel ball 11, so that it is at the lowest position of the slot and presses against the air outlet connector 13.

[0046] Continue to refer to Figure 3 The separation steps of the unlocking and separation mechanism 3 are as follows: 1. Pull the slider 9 to the bottom end towards the air inlet 1, reaching the compressed state of the locking spring 10; 2. The locking steel ball 11 leaves the lowest point of the slot and is released into the movable space, releasing the mechanical lock of the air outlet connector 13; 3. While maintaining the state of the slider 9, the separation spring 15 pops open the air outlet connector 13, lifting the locking steel ball 11 during the separation process; 4. The air outlet connector 13 and the air inlet connector 8 are completely separated, the slider 9 is pressed back to its original position by the locking spring 10 and held by the slider constraint ring 12, and the device separation is completed. The unlocking and separation mechanism 3 has a rapid, reliable, and safe separation process, and the mechanism can automatically reset after unlocking, avoiding secondary interference between the fixed body and the separated body.

[0047] Specific Implementation Method Six: Combination Figure 4This embodiment describes a gas storage tank 6 comprising a tank shell 16, an internal sample status monitoring system (i.e., a temperature monitoring system and a pressure monitoring system), and a status regulation system (i.e., a temperature regulation system 21 and a pressure regulation system). The temperature monitoring system includes a first flange mounting component 17 and a temperature sensor 18; the pressure monitoring system includes a second flange mounting component 19 and a pressure sensor 20. The sensors are mounted on the upper surface of the tank shell 16, with appropriately sized holes for mounting the first flange mounting component 17 and the second flange mounting component 19. After secure installation, welding is performed on the external contact surfaces of the gas storage tank 6 to further ensure a tight seal. The sensors are mounted below the first flange mounting component 17 and the second flange mounting component 19, and connected to a power supply and information transmission terminal above them. The internal sample status is sensed by the temperature sensor 18 and the pressure sensor 20. The electrical signals carrying the sensed information are transmitted through the first flange mounting component 17 and the second flange mounting component 19 to a sample information monitoring center outside the tank for storage and analysis.

[0048] The temperature control system 21 is a TEC semiconductor temperature control system, comprising a TEC semiconductor thermal control chip and heat transfer aluminum plates at both ends. The TEC semiconductor thermal control chip operates based on the Peltier effect. When a direct current flows through a circuit composed of two different semiconductor materials, in one direction of the current, one junction absorbs heat (cools down), while the other junction releases heat (heats up). This principle allows the thermal control chip to switch between cooling and heating modes by changing the direction of the direct current flowing through it, thus controlling the temperature of the gas inside the tank. Heat is transferred between the gas inside the tank and the TEC semiconductor thermal control chip through the heat transfer aluminum plates. The other end of the thermal control chip exchanges heat with the outside environment through the heat transfer aluminum plates. The main function of the heat transfer aluminum plates is to improve the heat transfer efficiency of the TEC thermal control chip while preventing direct contact between the thermal control chip and the gas inside the tank, thus avoiding the generation of contaminated gas.

[0049] The pressure regulation system includes an electric winch 22, pulleys 23, a pressure control spring 24, and a corrugated gas storage liner 25. Pressure regulation is mechanical; the volume of the internal gas storage space of the gas tank 6 is adjusted by changing the extension and retraction length of the corrugated section of the corrugated gas storage liner 25 to control pressure changes, ensuring the vacuum degree of the gas tank 6 before filling and its sealing performance after filling. The electric winch 22 is the drive device for the pressure regulation system, installed above the gas tank shell 16. The rope is perforated at the top, passes through the space between the corrugated gas storage liner 25 and the gas tank shell 16, and then passes downwards around two pulleys 23 at the bottom of the corrugated gas storage liner 25 and a fixed circular hole in the middle of the bottom surface. The rope is then fixed upwards to the inside of the top surface of the gas tank shell 16. The pressure control spring 24 is installed in the space between the bottom surface of the gas tank shell 16 and the bottom surface of the corrugated gas storage liner 25. A tension spring is selected, and it is in a compressed state when no force is applied. The pressure regulation system uses an electric winch 22 to pull a rope, compressing the corrugated gas storage liner 25 and increasing the pressure inside the tank. When the electric winch 22 is in the unloaded state, the tension generated by the pressure control spring 24 stretches the corrugated gas storage liner 25, reducing the pressure inside the tank. In its original length state, the corrugated gas storage liner 25 is subjected to the upward tension of the rope and the downward tension of the pressure control spring 24, at which point the device is in force balance.

[0050] By monitoring and regulating the temperature and pressure of the gas in the gas storage tank 6 in real time, the system ensures the state correction during the gas sample storage process and the long-term safety of the gas storage system.

Claims

1. An atmospheric sampling and storage device for a Venus exploration spacecraft, characterized in that, The atmospheric sampling and storage device includes an atmospheric acquisition and processing module, an unlocking and separation mechanism (3), and a gas sample storage and packaging module; wherein, The atmospheric sampling and processing module includes an air intake (1), a cooling and compression device (2), and an unlocking and separation mechanism (3). The air intake (1) and the cooling and compression device (2) are connected, and the outlet of the cooling and compression device (2) is connected to the unlocking and separation mechanism (3). The gas sample storage and packaging module includes a gas storage channel (4), a gas storage valve (5), a gas storage tank (6), and a gas storage box (7). The front end of the gas storage channel (4) is connected to the unlocking and separation mechanism (3), and its outlet is connected to the gas storage valve (5). The gas storage valve (5) is connected to the gas storage tank (6). Except for the gas storage channel connected to the unlocking and separation mechanism (3), the entire gas sample storage and packaging module is integrated inside the gas storage box (7).

2. The atmospheric sampling and storage device for a Venus exploration spacecraft according to claim 1, characterized in that, The sampling port of the air intake (1) is located on the back of the aircraft, and the air intake (1) is integrated with the aircraft skin.

3. An atmospheric sampling and storage device for a Venus exploration spacecraft according to claim 2, characterized in that, The cooling and compression device (2) includes an inlet valve (26), a cooling container (27), an outlet valve (28), a vacuum pump (29), a liquid nitrogen storage tank (30), a liquid nitrogen valve (31), and an exhaust valve (32). The outlet of the inlet channel (1) is connected to the inlet of the cooling container (27) through the inlet valve (26); the gas outlet of the cooling container (27) is connected to the inlet of the vacuum pump (29) through the outlet valve (28); the outlet of the vacuum pump (29) is connected to the front end pipeline of the unlocking and separation mechanism (3); the liquid nitrogen refrigeration circuit connection is as follows: the liquid nitrogen storage tank (30) is connected to the interlayer inlet of the cooling container (27) through the liquid nitrogen valve (31); the interlayer exhaust port of the cooling container (27) is connected to the exhaust valve (32).

4. An atmospheric sampling and storage device for a Venus exploration spacecraft according to claim 3, characterized in that, The unlocking and separation mechanism (3) includes an air inlet connector (8), a slider (9), a locking spring (10), a locking steel ball (11), a slider constraint ring (12), an air outlet connector (13), a gasket (14), and a separation spring (15); wherein, the air inlet connector (8) is connected to the air inlet channel (1); the air outlet connector (13) is connected to the air storage channel (4), and the slider (9) and the slider constraint ring (12) are sequentially sleeved on the outer periphery of the air inlet connector (8), the slider (9) can slide along the axial direction, and the slider constraint ring (12) is fixedly positioned; the locking spring (10) is installed Between the shoulder or housing of the slider (9) and the inlet connector (8), the slider (9) is pushed towards the slider constraint ring (12); the locking steel ball (11) is installed in the radial through hole of the inlet connector (8), and its radial inner and outer positions are controlled by the inner surface of the slider (9); the outlet connector (13) is inserted into the inlet connector (8) from the axial direction, and its outer circumferential groove engages with the locking steel ball (11) for positioning; the separation spring (15) and the washer (14) are installed between the mating end faces of the inlet connector (8) and the outlet connector (13) to maintain the compressed energy storage state.

5. An atmospheric sampling and storage device for a Venus exploration spacecraft according to claim 4, characterized in that, The gas storage channel (4) of the gas sample storage and packaging module includes a main gas storage channel and five branch gas storage channels; the gas sample storage and packaging module includes five gas storage units, each of which includes a gas storage valve (5) and a gas storage tank (6).

6. An atmospheric sampling and storage device for a Venus exploration spacecraft according to claim 5, characterized in that, The gas storage tank (6) includes a gas storage tank shell (16), a sample status monitoring system inside the tank, and a gas storage tank status adjustment system; wherein, the sample status monitoring system inside the tank includes a temperature monitoring system and a pressure monitoring system, and the gas storage tank status adjustment system includes a temperature adjustment system (21) and a pressure adjustment system.

7. An atmospheric sampling and storage device for a Venus exploration spacecraft according to claim 6, characterized in that, The temperature monitoring system includes a first flange mounting component (17) and a temperature sensor (18), and the pressure monitoring system includes a second flange mounting component (19) and a pressure sensor (20).

8. An atmospheric sampling and storage device for a Venus exploration spacecraft according to claim 7, characterized in that, The temperature regulation system (21) is a TEC semiconductor temperature control system, including a TEC semiconductor thermal control chip and heat transfer aluminum sheets at both ends of the TEC semiconductor thermal control chip.

9. An atmospheric sampling and storage device for a Venus exploration spacecraft according to claim 6, characterized in that, The pressure regulation system includes an electric winch (22), pulleys (23), a pressure control spring (24), and a corrugated gas storage liner (25). The electric winch (22) is installed above the gas tank shell (16). The rope is opened at the top, passes through the space between the corrugated gas storage liner (25) and the gas tank shell (16), and goes down around the two pulleys (23) at the bottom end of the corrugated gas storage liner (25) and the fixed round hole in the middle of the bottom surface. The rope is fixed upward to the inside of the top surface of the gas tank shell (16). The pressure control spring (24) is installed in the space between the bottom surface of the gas tank shell (16) and the bottom surface of the corrugated gas storage liner (25).

10. An atmospheric sampling and storage device for a Venus probe spacecraft according to claim 9, characterized in that, The pressure control spring (24) is a tension spring, which is in a compressed state when it is not under force.

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