Gas in-situ measurement device for spaceflight exploration

Abstract

The utility model provides a gas in-situ measurement device for spaceflight exploration, the device comprises a gas processing chamber, a gas inlet pipeline, a mass spectrometer, a first gas exhaust pipeline and a second gas exhaust pipeline, a gas pressure detection device is arranged in the gas processing chamber, the mass spectrometer is communicated with the gas processing chamber through a first gas inlet channel, the first gas inlet channel is provided with a first valve, and the second gas exhaust pipeline is provided with a second valve. The first exhaust pipeline is communicated with the mass spectrometer and the external environment, the second exhaust pipeline is communicated with the gas treatment chamber and the external environment, and the second exhaust pipeline is provided with a second valve. The pressure value of the to-be-measured gas in the gas treatment chamber is collected in real time to control opening and closing of each valve, so that the gas path is dynamically adjusted, the situation that the to-be-measured gas with relatively high gas pressure is lifted and directly fed into the mass spectrometer to cause damage to internal components is avoided, the gas measurement precision is ensured, and the environmental adaptability is higher.

Description

Technical Field

[0001] The present application belongs to the technical field of gas composition measurement, and specifically relates to an in-situ gas measurement device for aerospace exploration. Background Art

[0002] During space exploration, gaseous substances such as celestial body atmospheres and cometary ejecta require in-situ detection of gas concentration, composition and other characteristics using gas detection instruments. The data obtained from the detection is the basis for studying important scientific issues such as the formation and evolution of celestial bodies.

[0003] The Viking 1 and Viking 2 landers (Mars exploration missions) each carried a magnetic mass spectrometer (UAMS). The instrument measured atmospheric composition when the landers descended to an altitude between 200 and 120 km above the surface. This instrument used an open-type gas injection system, "pouring" ambient air into the mass spectrometer for analysis. However, open-type gas injections can easily damage the mass spectrometer due to high atmospheric pressure, resulting in measurement accuracy that cannot meet requirements.

[0004] The Galileo (Jupiter exploration) probe carried a quadrupole mass spectrometer (GPMS). To accurately measure the main atmospheric components and isotope ratios, the GPMS was equipped with an injection and vacuum system consisting of four capillary flow restrictors, 13 valves, two enrichment chambers, six getter pumps, three pressure sensors, and an ion pump. However, the probe's complex structure and heft increased its size and weight exponentially, placing a significant cost on the allocation of onboard resources for deep space exploration.

[0005] Therefore, existing gas detectors cannot strike a balance between volume, weight and measurement accuracy.

[0006] Due to the great differences in the content of different types of gases under different environmental conditions, it is necessary to have the ability to detect a wide range of gas content and perform intelligent and autonomous detection during the gas detection process to ensure the normal operation of the equipment and the validity of the detection data. Utility Model Content

[0007] In view of the above technical problems, the present application aims to provide a gas in-situ measurement device for aerospace exploration, which has the advantages of small size and light weight while ensuring measurement accuracy.

[0008] In order to solve the above problems, this application adopts the following technical solutions:

[0009] A gas in-situ measurement device for aerospace detection, comprising:

[0010] A gas processing chamber, wherein a gas pressure detection device for detecting the pressure of the gas to be measured is provided;

[0011] an air inlet pipeline, which delivers the gas to be tested into the gas processing chamber;

[0012] A mass spectrometer for measuring various gas components and isotope contents of the gas to be measured, the mass spectrometer being connected to the gas processing chamber via a first air inlet channel, wherein the first air inlet channel is provided with a first valve and a first flow limiting device in sequence along the air inlet direction;

[0013] a first exhaust pipe, one end of which is connected to the mass spectrometer and is used to discharge the gas inside the mass spectrometer to the external environment from the other end;

[0014] a second exhaust pipeline, one end of which is connected to the gas processing chamber and is used to discharge the gas inside the gas processing chamber from the other end to the external environment when the internal gas pressure is high, and a second valve is provided between the second exhaust pipeline and the gas processing chamber;

[0015] The controller is electrically connected to the air pressure detection device, the first valve, and the second valve, respectively. When the air pressure detection device measures that the pressure value of the gas to be measured in the gas processing chamber is not lower than a first preset value, the controller controls the first valve to close and the second valve to open. When the air pressure detection device measures that the pressure value of the gas to be measured in the gas processing chamber is lower than the first preset value, the controller controls the first valve to open and the second valve to close.

[0016] The in-situ gas measurement device for aerospace exploration adopts the above-mentioned technical solution, which mainly includes an air intake pipeline, a gas processor, a mass spectrometer and two exhaust pipelines, simplifying the design of the gas measurement device in the existing technology; at the same time, the air pressure detection device is used to judge the air pressure value of the gas to be measured in the gas processing chamber, and the controller controls the direction of the pipeline in which the gas to be measured enters according to the size of the air pressure value, ensuring that the air pressure value of the gas to be measured is within a certain range before the gas to be measured is sent to the mass spectrometer for detection, avoiding damage to the mass spectrometer when the air pressure value is large, and ensuring the accuracy of gas detection to a certain extent.

[0017] In a possible implementation, the device further includes:

[0018] a second air inlet channel, which is used to connect the mass spectrometer and the gas processing chamber, wherein a third valve is provided in the second air inlet channel, and the controller is also electrically connected to the third valve;

[0019] When the gas pressure detection device measures that the pressure of the gas to be measured in the gas processing chamber is lower than a second preset value, the controller controls the first valve to close and the third valve to open, and the second preset value is less than the first preset value.

[0020] In a possible implementation manner, the first valve, the second valve, and the third valve are micro self-locking valves.

[0021] In a possible implementation manner, the air intake line is provided with a first filter.

[0022] In a possible implementation manner, the first exhaust line is provided with a second filter, and the second exhaust line is provided with a third filter.

[0023] In a possible implementation, the second exhaust line is further provided with a second flow limiting device along the exhaust direction before entering the third filter.

[0024] In a possible implementation manner, the first current limiting device and the second current limiting device are metal sheets with micropores.

[0025] In one possible implementation, the mass spectrometer is a quadrupole mass spectrometer.

[0026] In a possible implementation, the air pressure detection device is a vacuum gauge.

[0027] The present application provides a gas in-situ measurement device for space exploration, comprising: a gas processing chamber, which is provided with an air pressure detection device; an air inlet pipeline, which delivers the gas to be measured into the gas processing chamber; a mass spectrometer, which is used to measure various gas components and isotope contents of the gas to be measured, and the mass spectrometer is connected to the gas processing chamber through a first air inlet channel, and the first air inlet channel is provided with a first valve and a first current limiting device in sequence along the air inlet direction; a first exhaust pipeline, which is used to discharge the gas inside the mass spectrometer from the other end to the external environment; a second exhaust pipeline, which is used to discharge the gas inside the gas processing chamber from the other end to the external environment, and a second valve is provided between the second exhaust pipeline and the gas processing chamber; when the air pressure detection device measures that the pressure of the gas to be measured in the gas processing chamber exceeds a first preset value, the controller controls the first valve to close and the second valve to open, and when the air pressure detection device measures that the pressure of the gas to be measured in the gas processing chamber does not exceed the first preset value, the controller controls the first valve to open and the second valve to close. The device controls whether the gas to be tested is sent into the mass spectrometer for measurement according to the pressure range of the gas processing chamber, preventing the gas to be tested with high pressure from directly entering the mass spectrometer and damaging the mass spectrometer components, thereby ensuring that the mass spectrometer can operate normally to detect the composition and isotope content of the gas to be tested, and improving measurement accuracy.

[0028] The in-situ gas measurement device for aerospace detection provided in this application has the advantages of small size, low weight and high structural strength. The molecular mass range it can measure can reach 2 to 150 amu, the resolution is ≤150, and the dynamic range is better than 8 orders of magnitude. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present application and, together with the description, serve to explain the principles of the present application.

[0030] Figure 1 A schematic diagram of the structure of a gas in-situ measurement device for aerospace detection provided in this application Figure 1 ;

[0031] Figure 2 A schematic diagram of the structure of a gas in-situ measurement device for aerospace detection provided in this application Figure 2 ;

[0032] Figure 3 for Figure 2 A circuit control schematic diagram of the illustrated embodiment;

[0033] Figure 4 for Figure 2 Air pressure measurement flow chart of the illustrated embodiment.

[0034] The above drawings illustrate specific embodiments of the present application, which will be described in more detail below. These drawings and the textual description are not intended to limit the scope of the present application in any way, but rather to illustrate the concepts of the present application to those skilled in the art by reference to specific embodiments.

[0035] Description of reference numerals:

[0036] 1-intake pipe; 11-first filter; 2-gas treatment chamber; 21-air pressure detection device; 3-first intake channel; 31-first valve; 32-first flow limiting device; 4-mass spectrometer; 5-first exhaust pipe; 51-second filter; 6-second exhaust pipe; 61-second valve; 62-second flow limiting device; 63-third filter; 7-second intake channel; 71-third valve; 8-controller. DETAILED DESCRIPTION

[0037] Exemplary embodiments will be described in detail herein, with examples illustrated in the accompanying drawings. In the following description, when referring to the drawings, identical numerals in different figures represent identical or similar elements, unless otherwise indicated. The embodiments described in the following exemplary embodiments are not intended to represent all embodiments consistent with the present application. Rather, they are merely examples of apparatus and methods consistent with certain aspects of the present application, as detailed in the appended claims.

[0038] In the embodiments of the present application, words such as "first" and "second" are used to distinguish between identical or similar items with substantially the same functions and effects. Those skilled in the art will understand that words such as "first" and "second" do not limit the quantity and execution order, and words such as "first" and "second" do not necessarily limit differences. It should be noted that in the embodiments of the present application, words such as "exemplary" or "for example" are used to indicate examples, illustrations or explanations. Any embodiment or design described in this application as "exemplary" or "for example" should not be interpreted as being more preferred or advantageous than other embodiments or design schemes. Specifically, the use of words such as "exemplary" or "for example" is intended to present related concepts in a concrete way. In the embodiments of the present application, "at least one" refers to one or more, and "more" refers to two or more.

[0039] It should be noted that the "at..." in the embodiments of the present application can be the instant when a certain situation occurs, or it can be a period of time after the situation occurs, and the embodiments of the present application do not specifically limit this. In addition, the method provided in the embodiments of the present application is only an example, and the method may also include more or less content.

[0040] To facilitate a clear description of the technical solutions of the embodiments of the present application, some of the terms and technologies involved in the embodiments of the present application are briefly introduced below:

[0041] In space exploration, gaseous substances such as the atmosphere of extraterrestrial bodies and cometary ejecta require in-situ detection of gas concentration, composition and other characteristics using gas detection instruments. The data obtained from the detection is the basis for studying important scientific issues such as the formation and evolution of celestial bodies.

[0042] Existing technology, such as the in-situ detection equipment carried by the Viking 1 and Viking 2 missions used to explore Mars, includes a magnetic mass spectrometer (UAMS). This instrument uses an open inlet to "pour" ambient gas into the mass spectrometer for analysis. The UAMS can analyze small molecules ranging from 1 to 50 amu (amounts of molecular weight) with a resolution of ≤50 and a dynamic range of five orders of magnitude.

[0043] For example, the Galileo probe used to explore Jupiter featured a quadrupole mass spectrometer (GPMS). To accurately measure the main atmospheric components and isotope ratios, the GPMS was equipped with an injection and vacuum system consisting of four capillary flow restrictors, 13 valves, two enrichment chambers, six getter pumps, three pressure sensors, and an ion pump. The GPMS was capable of analyzing small molecules ranging from 2 to 150 amu with a resolution of ≤150 and a dynamic range of greater than seven orders of magnitude.

[0044] Among the above technologies, Viking 1 and Viking 2 use open sampling ports to directly measure gases. For the detection of gases with a wide range of unknown sample concentrations, the single mass spectrometer design cannot achieve dynamic adjustment of the gas path, making it difficult to ensure the continuous normal operation of the equipment and the output of valid detection data. In order to improve the measurement dynamic range, the Galileo measurement device is equipped with an extremely complex sampling system and vacuum system, which causes the volume and weight to increase exponentially, and the cost of resource allocation for deep space exploration is relatively high.

[0045] In response to the above technical problems, the inventors discovered that the environmental conditions and gas content of different extraterrestrial bodies vary significantly. Current in-situ gas measurement devices are unable to maintain a highly accurate dynamic measurement range while maintaining a lightweight structure. Based on this, the inventors have improved upon the complex measurement devices. By detecting the pressure of the gas to be measured, the inventors adjust the gas path to feed the gas to the mass spectrometer for measurement only when the pressure meets the required level. This allows the gas detection process to detect a wide range of gas contents, ensuring normal operation of the device while improving the accuracy of the detection data.

[0046] Figure 1 A schematic diagram of the structure of a gas in-situ measurement device for aerospace detection provided in this application Figure 1 .like Figure 1 As shown, an embodiment of the present application provides a gas in-situ measurement device for aerospace exploration, which includes: an air intake pipeline 1, a gas processing chamber 2, a mass spectrometer 4, a first exhaust pipeline 5, a second exhaust pipeline 6 and a controller 8.

[0047] A pressure detection device 21 for detecting the pressure of the gas to be measured is provided inside the gas treatment chamber 2; the air inlet pipe 1 is connected to the gas treatment chamber 2, and is used to deliver the gas to be measured into the gas treatment chamber 2; the mass spectrometer 4 is connected to the gas treatment chamber 2 through the first air inlet channel 3, and is used to measure various gas components and isotope contents of the gas to be measured. A first valve 31 and a first current limiting device 32 are provided in the first air inlet channel 3; one end of the first exhaust pipe 5 is connected to the mass spectrometer 4, and is used to discharge the internal gas of the mass spectrometer 4 from the other end to the external environment; one end of the second exhaust pipe 6 is connected to the gas treatment chamber 2, and is used to discharge the internal gas from the other end to the external environment when the air pressure in the gas treatment chamber 2 is large. A second valve 61 is provided between the second exhaust pipe 6 and the gas treatment chamber 2.

[0048] Controller 8 is electrically connected to air pressure detection device 21, first valve 31, and second valve 61, respectively, and implements dynamic adjustment of the gas path through the following control logic. When air pressure detection device 21 measures the pressure of the gas to be measured in gas processing chamber 2 to be no less than a first preset value, controller 8 controls first valve 31 to close and second valve 61 to open. When air pressure detection device 21 measures the pressure of the gas to be measured in gas processing chamber 2 to be less than the first preset value, controller 8 controls first valve 31 to open and second valve 61 to close.

[0049] It should be noted that, before the gas to be tested is fed into the gas processing chamber 2 , the first valve 31 and the second valve 61 are closed by default.

[0050] If the pressure of the gas to be measured is too high, directly feeding it into the mass spectrometer 4 will likely contain water that can condense within the mass spectrometer 4, which operates at a temperature of 0°C. Therefore, to avoid damaging the internal components of the mass spectrometer by directly feeding the gas to be measured into the mass spectrometer 4 for measurement, the above embodiment first opens the second valve 61 to discharge excess gas from the second exhaust line 6 into the environment outside the cabin. As the gas is discharged, the pressure of the remaining gas to be measured decreases. Only when it falls below a first preset value is the remaining gas to be measured fed into the mass spectrometer 4 for measurement by opening the first valve 31 and closing the second valve 61. This allows the gas to be fed into the mass spectrometer 4 for high-precision measurement even at a high pressure through dynamic adjustment of the gas path. This ensures accurate measurement of the gas over a wide range without damaging the components of the mass spectrometer 4.

[0051] When the pressure of the gas to be measured just drops below the first preset value, the pressure is still too high. In order to prevent a large amount of gas to be measured from entering the cavity of the mass spectrometer 4, a first current limiting device 32 is further provided in the first air inlet channel 3, which can ensure that the gas to be measured slowly enters the mass spectrometer 4, so that the pressure of the gas to be measured entering the mass spectrometer 4 is within the safe working pressure range of the filament and the electron multiplier.

[0052] Figure 2 A schematic diagram of the structure of a gas in-situ measurement device for aerospace detection provided in this application Figure 2 .like Figure 2 As shown, this embodiment is in Figure 1 The present embodiment is described based on the embodiment shown. Figure 1 On the basis of the first air inlet channel 3 , a second air inlet channel 7 is added next to the first air inlet channel 3 , whose two ends are respectively connected to the mass spectrometer 4 and the gas processing chamber 2 , and a third valve 71 is provided in the second air inlet channel 7 . At this time, the controller 8 is electrically connected to the third valve 71 .

[0053] If the pressure of the gas to be measured is significantly lower than the first preset value, there is no need to control the flow of gas into the mass spectrometer 4 through the first flow limiting device 32. Instead, the gas to be measured can be directly fed into the mass spectrometer 4. Therefore, when the pressure detection device 21 measures the pressure of the gas to be measured in the gas processing chamber 2 to be lower than the second preset value (the second preset value is lower than the first preset value), the controller 8 controls the closing of the first valve 31 and the opening of the third valve 71, allowing the gas to be measured to enter the mass spectrometer 4 directly from the second air inlet channel 7 for measurement. This embodiment can provide more gas path options to accommodate different pressure values of the gas to be measured, thereby ensuring the measurement accuracy of the gas to be measured.

[0054] In another embodiment, for Figure 2 In the embodiment, the first valve 31, the second valve 61 and the third valve 71 are preferably micro self-locking valves, which can reduce the weight of the device and the power consumption of the valves, wherein the isotropic leakage rate of the micro self-locking valve is preferably less than or equal to 10 -7 Pam 3 / s, which can reduce the leakage of the gas to be measured and ensure measurement accuracy.

[0055] In another embodiment, continue to refer to Figure 2 As shown, since the gas to be tested or the sample gas in the external environment may contain particulate impurities, for example, the gas in the lunar environment contains particles with a diameter greater than 20um, if the air intake pipe 1 is selected as an open pipe, the particulate impurities are very likely to enter the mass spectrometer 4 from the air intake pipe 1 and affect the operation of the internal components. Therefore, this embodiment adds a first filter 11 to the air intake pipe 1, which can filter out particulate impurities in the gas to be tested or the sample gas in the external environment.

[0056] In another embodiment, continue to refer to Figure 2 As shown, particulate matter impurities in the gas to be measured from the external environment can enter the mass spectrometer 4 through the first exhaust line 5 and can also enter the gas to be measured through the second exhaust line 6, thereby affecting measurement accuracy. Therefore, this embodiment provides a second filter 51 in the first exhaust line 5 and a third filter 63 in the second exhaust line 6, respectively, to filter out particulate matter impurities in the gas, ensuring unobstructed internal channels while improving measurement accuracy.

[0057] In another embodiment, continue to refer to Figure 2 As shown, the second exhaust line 6 is further provided with a second flow restrictor 62 before entering the third filter 63 along the exhaust direction. The provision of the second flow restrictor 62 prevents excessive loss of the test gas during exhaust, ensuring a stable outflow of the test gas. Depending on the actual application scenario, the opening size of the second flow restrictor 62 can be adjusted to control the exhaust flow rate, ensuring that sufficient test gas remains for measurement and analysis, meeting the intake measurement standards.

[0058] In another embodiment, in order to further reduce the weight of the device, the first current limiting device 32 and the second current limiting device 62 can be made of metal sheets with micropores.

[0059] In another embodiment, compared to the magnetic mass spectrometers used in Pirates 1 and 2, the mass spectrometer 4 of this embodiment is preferably a quadrupole mass spectrometer, which is more suitable for the application scenario of this embodiment than other mass spectrometers such as magnetic mass spectrometers. The working principle of the quadrupole mass spectrometer is: first, the gas molecules to be measured are ionized in the ion source, and the molecules are converted into charged ions. Then, after the charged ions enter the quadrupole mass analyzer, they are separated under the action of the electric field due to their different mass-to-charge ratios (the ratio of mass to charge). By analyzing the mass of the ions, their chemical nature and isotope ratio can be inferred from their elemental composition. Finally, the number of ions is detected by the detector to obtain the content of various gas components.

[0060] In another embodiment, the air pressure detection device 21 may be a general pressure sensor. In this embodiment, a vacuum gauge is used to detect the air pressure of the gas to be measured in the gas processing chamber 2. Taking a hot cathode vacuum gauge as an example, its operating principle is that the thermal emission electrons generated during operation ionize the gas to be measured, and the magnitude of the ion flow is proportional to the number density of gas molecules. The air pressure value is thus obtained by measuring the ion flow.

[0061] The in-situ gas measurement device for space exploration provided in the above-mentioned embodiments of this application has the advantages of small size, low weight, and reliable structural strength. Furthermore, the device utilizes a small-diameter pipe welding process for each pipeline, and each valve utilizes a micro-self-locking valve, which is leak-resistant and has an equidirectional leakage rate of less than or equal to 10⁻⁷ Pamin³ / s.

[0062] Figure 3 for Figure 2 The circuit control diagram of the embodiment shown is as follows. Figure 3 As shown, the controller 8 is connected to the pressure detection device 21, the first valve 31, the second valve 61, and the third valve 71 respectively. Among them, the pressure detection device 21 collects the pressure value of the gas to be measured in the gas processing chamber 2 in real time and sends it to the controller 8. The controller 8 controls the closing and opening of the first valve 31, the second valve 61, and the third valve 71 according to the relationship between the pressure value and the first preset value and the second preset value, thereby realizing dynamic adjustment of the gas path and ensuring that the mass spectrometer 4 can measure the gas at a safe pressure. In order to complete the exhaust process after the gas measurement is completed, the controller 8 is also connected to the mass spectrometer 4. When the mass spectrometer 4 completes the measurement work, the controller 8 can control the exhaust operation.

[0063] Figure 4 for Figure 2 The measurement flow chart of the embodiment shown below. Figures 2 to 4The measurement flow chart of the gas in-situ measurement device for space exploration will be specifically described.

[0064] S401: Open the first valve 31, the second valve 61 and the third valve 71 to discharge the gas in the device, measure the background gas and close all valves;

[0065] The background gas can reflect the background in the device. Measuring the parameters of the background gas facilitates the subsequent correction of the measurement structure of the gas to be measured.

[0066] In some embodiments, the interior is evacuated and then a standard gas is injected for measurement, the purpose of which is also to calibrate the measurement results of the gas to be measured later.

[0067] S402: The gas to be measured collected at the front end is sent to the gas processing chamber 2 through the gas inlet pipe 1 of the device to enter the measurement process;

[0068] The process of collecting the gas to be tested in the external environment is not realized by this device, but is processed by an independent device at the front end of the air intake pipe. After collection, it is sent into this device through the air intake pipe for measurement.

[0069] S403: The gas pressure value P of the gas to be measured in the gas processing chamber 2 is measured in real time by the gas pressure detection device 21, and the pressure value P is sent to the controller 8;

[0070] Before measurement, a first preset value P1 and a second preset value P2 need to be pre-set in the controller 8 , where the first preset value is greater than the second preset value. The first preset value and the second preset value are reasonably adjusted according to the specific device.

[0071] S404: Determine in real time the relationship between the air pressure value P and the first preset value P1 and the second preset value P2. If P≥P1, jump to step S405; if P2≤P<P1, jump to step S406; if P<P2, jump to step S407;

[0072] S405: The controller 8 controls the first valve 31 to close, the second valve 61 to open, and the third valve 71 to close;

[0073] In this step, the states of the first valve 31, the second valve 61 and the third valve 71 are kept unchanged, and the air pressure value P will continue to decrease. It is determined in real time whether the air pressure value P is lower than P1. If the air pressure value P is lower than P1, jump to step S406.

[0074] S406: The controller 8 controls the first valve 31 to open, the second valve 61 to close, and the third valve 71 to close;

[0075] In this step, the states of the first valve 31, the second valve 61, and the third valve 71 remain unchanged, and the gas pressure value P continues to decrease. At this time, the mass spectrometer 4 measures the incoming gas to be tested, and after the measurement is completed, the process jumps to step S408. It should be noted that although in this step, as the gas to be tested is continuously fed into the mass spectrometer 4 for measurement, the gas pressure value P within the gas processing chamber 2 continues to decrease, even falling below P2, this step does not jump to step S407 at this time, but instead jumps directly to step S408 after the measurement.

[0076] S407: The controller 8 controls the first valve 31 to close, the second valve 61 to close, and the third valve 71 to open;

[0077] In this step, the states of the first valve 31 , the second valve 61 and the third valve 71 are kept unchanged, and the mass spectrometer 4 is used to measure the gas to be tested. After the measurement is completed, the process jumps to step S408 .

[0078] S408: Exhaust the gas to be tested through the first exhaust pipeline 5 and the second exhaust pipeline 6.

[0079] When controller 8 receives notification that mass spectrometer 4 has completed measurement, it controls second valve 61 to open, and then exhausts the primary gas to be measured from mass spectrometer 4 through first exhaust line 5, and exhausts the primary gas to be measured from gas processing chamber 2 and other pipelines through second exhaust line 6. The exhaust process can be powered by a vacuum pump.

[0080] It should be understood that the present application is not limited to the exact structure described above and shown in the drawings, and that various modifications and changes may be made without departing from the scope thereof. The scope of the present application is limited only by the appended claims.

Claims

1. A gas in-situ measurement device for aerospace exploration, characterized in that: include: A gas processing chamber (2) is provided with a gas pressure detection device (21) for detecting the pressure of the gas to be measured; An air inlet pipe (1) for delivering the gas to be measured into a gas processing chamber (2); A mass spectrometer (4) is used to measure various gas components and isotope contents of the gas to be measured, wherein the mass spectrometer (4) is connected to the gas processing chamber (2) via a first air inlet channel (3), wherein the first air inlet channel (3) is provided with a first valve (31) and a first flow limiting device (32) in sequence along the air inlet direction; a first exhaust pipe (5), one end of which is connected to the mass spectrometer (4) and is used to discharge the internal gas of the mass spectrometer (4) to the external environment through the other end; a second exhaust pipe (6), one end of which is connected to the gas processing chamber (2) and is used to discharge the gas inside the gas processing chamber (2) from the other end to the external environment when the internal gas pressure is relatively high; a second valve (61) is provided between the second exhaust pipe (6) and the gas processing chamber (2); A controller (8) is electrically connected to the air pressure detection device (21), the first valve (31) and the second valve (61), respectively. When the air pressure detection device (21) measures that the pressure value of the gas to be measured in the gas processing chamber (2) is not lower than a first preset value, the controller (8) controls the first valve (31) to close and the second valve (61) to open. When the air pressure detection device (21) measures that the pressure value of the gas to be measured in the gas processing chamber (2) is lower than the first preset value, the controller (8) controls the first valve (31) to open and the second valve (61) to close.

2. The device according to claim 1, characterized in that Also includes: a second air inlet channel (7) for connecting the mass spectrometer (4) and the gas processing chamber (2); a third valve (71) is provided in the second air inlet channel (7); and the controller (8) is also electrically connected to the third valve (71); When the gas pressure detection device (21) measures that the pressure value of the gas to be measured in the gas processing chamber (2) is lower than a second preset value, the controller (8) controls the first valve (31) to close and the third valve (71) to open, and the second preset value is smaller than the first preset value.

3. The device according to claim 2, characterized in that The first valve (31), the second valve (61) and the third valve (71) are micro self-locking valves.

4. The device according to claim 1, characterized in that The air intake pipeline (1) is provided with a first filter (11).

5. The device according to claim 1, characterized in that The first exhaust pipe (5) is provided with a second filter (51), and the second exhaust pipe (6) is provided with a third filter (63).

6. The device according to claim 5, characterized in that The second exhaust pipe (6) is further provided with a second flow limiting device (62) along the exhaust direction before entering the third filter (63).

7. The device according to claim 6, characterized in that The first current limiting device (32) and the second current limiting device (62) are made of metal sheets with micropores.

8. The device according to claim 1, characterized in that The mass spectrometer (4) is a quadrupole mass spectrometer (4).

9. The device according to claim 1, characterized in that The air pressure detection device (21) is a vacuum gauge.

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