An in-situ lunar soil thermal physical property parameter measuring device and working method

Abstract

The present application relates to the technical field of celestial exploration equipment, and particularly relates to an in-situ lunar soil thermal physical property parameter measuring device, which comprises a shell, a first cavity and a second cavity and a third cavity are sequentially arranged along the extension direction of the shell, and a gas is stored in the second cavity; a primary action mechanism is arranged in the first cavity, the primary action mechanism comprises a heat-driven part, an elastic part and a weak part, the heat-driven part is changed from a compressed state to an initial state, the heat-driven part directly acts on the weak part and makes the weak part break, and then the compressed elastic part is released; a secondary action mechanism is arranged in the third cavity, the secondary action mechanism comprises a heating on-off assembly and a piston, the heating on-off assembly is in communication with the second cavity under the action of heat, the gas enters the third cavity, and the gas drives the piston to move along the extension direction of the third cavity; the in-situ lunar soil thermal physical property parameter measuring device has the characteristics of miniaturization, low power consumption and high power-to-weight ratio under the premise of not increasing the load weight.

Description

Technical Field

[0001] This invention relates to the field of geothermal resource development and utilization technology, specifically to an in-situ lunar soil thermal property parameter measurement device and its working method. Background Technology

[0002] Currently, only a few countries have conducted relevant tests on the lunar surface to measure lunar thermal properties. There are two main ways to measure lunar soil thermal properties: (1) Drilling a probe hole on the lunar surface using a drilling device. After drilling, a thermal property measurement probe is placed in the drill rod, and then the measurement probe is used to measure the lunar soil thermal properties. (2) Penetrating a certain depth into the lunar soil profile using a penetrating method, and measuring the lunar soil thermal properties by deploying heating plates and temperature sensors inside and outside the penetrating bomb.

[0003] The current mainstream technology on the ground involves using a static pressure device to press the probe shell into the soil layer, followed by pneumatic actuation to push the probe out, ensuring full contact between the probe and the soil. However, this pressing process causes significant disturbance to the underlying soil, and in the unknown ground measurement environment, the presence of hard objects such as rocks cannot be ruled out. As the penetration deepens, the likelihood of collisions with these objects increases, easily damaging the probe. Alternatively, this pneumatic approach involves first penetrating to a certain depth and then inflating it using ground equipment. Besides these methods, an electric hammer or drill can be used to drill the drill rod to a certain depth, then inserting the measuring probe inside the drill rod to measure the soil's thermal properties. Because the drilling process causes significant soil disturbance, this method primarily measures the soil inside the drill rod, potentially leading to discrepancies with in-situ soil layer measurements and resulting in higher uncertainty.

[0004] As human scientific advancements continue, space exploration is progressing systematically. Penetrating lunar probes are becoming increasingly feasible, and a key objective of this approach is measuring the thermal properties of lunar regolith. However, current methods, such as lowering a probe into a hollow drill pipe, lack the ability to control its orientation during descent. Furthermore, applying additional loads to the probe to achieve sufficient contact force with the lunar regolith can lead to deviations in measurement results. Deploying heating elements and temperature sensors directly on the surface of the penetrator for thermal property measurement is problematic due to the significant impact overload during penetration, potentially damaging the thermal sensors on the inner and outer walls of the penetrator. Additionally, heating the lunar regolith within the penetrator is limited by the thickness of the penetrator walls, requiring significantly more energy than measurements using small probes. Summary of the Invention

[0005] Therefore, the technical problem to be solved by the present invention is to overcome the problems of the existing technology of measuring lunar soil thermal properties by directly deploying heating plates and temperature sensors on the surface of the penetrating projectile. Due to the large impact overload during the penetrating process into the lunar profile, the thermal measurement sensors on the inner and outer walls of the projectile may be damaged. At the same time, heating the lunar soil inside the penetrating projectile is limited by the thickness of the projectile wall, and the energy consumption required to heat to the same temperature is much higher than that of measuring with a small probe. Therefore, the present invention provides an in-situ lunar soil thermal property measurement device and working method.

[0006] To address the aforementioned technical problems, this invention provides an in-situ lunar soil thermophysical parameter measuring device, comprising: a shell, with a first cavity, a second cavity, and a third cavity sequentially arranged along the extending direction of the shell, the second cavity storing gas; a primary actuating mechanism disposed in the first cavity, the primary actuating mechanism including a heated driving component, an elastic component, and a weak component, the heated driving component changing from a compressed state to an initial state, the heated driving component directly acting on the weak component and causing the weak component to break, subsequently releasing the elastic component; a secondary actuating mechanism disposed in the third cavity, the secondary actuating mechanism including a heating on / off assembly and a piston, the heating on / off assembly being heated and communicating with the second cavity, the gas entering the third cavity, the gas pushing the piston to move along the extending direction of the third cavity; and a probe assembly disposed at the end of the piston away from the second cavity, the probe assembly containing a heating component and a temperature sensing component.

[0007] Furthermore, the primary actuation mechanism also includes a tube seat and a wire, the wire being disposed inside the tube seat and connected to the heated drive component.

[0008] Furthermore, the heated driving component is a nickel-titanium alloy component.

[0009] Furthermore, the heating on / off assembly includes: a heat-resistant ring, which is configured to correspond to the vent hole of the second cavity; an annular copper ring, which is disposed on the heat-resistant ring and solder is provided between the heat-resistant ring and the annular copper ring; and a heating element, which is connected to the heating assembly.

[0010] Furthermore, the solder comprises aluminum solder and eutectic solder.

[0011] Furthermore, the second cavity is provided with a gas sealing mechanism, which includes: an arc-shaped boss with an air inlet and a stepped surface on the end face of the arc-shaped boss, with a compression elastic element on the stepped surface; a pressure-bearing pad at the bottom of the arc-shaped boss, with a retaining spring at the bottom of the pressure-bearing pad; and a rubber plug at the top of the arc-shaped boss.

[0012] Furthermore, the rubber stopper is provided with sealant.

[0013] Furthermore, the piston is provided with a sealing ring, which is a fluororubber sealing ring.

[0014] Furthermore, the housing is a titanium alloy shell.

[0015] The present invention also provides an in-situ lunar soil thermal property parameter measuring device, comprising: when the heated driving component is heated, the heated driving component recovers from the compressed state to the initial state and acts on the weak component, the weak component assists the heated driving component in unlocking and releasing the elastic component, since the elastic component is initially compressed at the upper end of the weak component, after the weak component breaks, the elastic component returns to its original state and acts on the top of the secondary actuation mechanism, after the first stage of the push-out process, the elastic component is still in the compressed state and still provides a certain force, after the push-out is completed, the probe assembly is energized, the heating component in one probe assembly starts to work to generate heat, and then the heat diffuses to the soil around the probe assembly, the temperature sensing component in another probe receives the heat energy and transmits relevant data through the signal transmission wire, and after the data transmission is completed, the probe assembly is de-energized;

[0016] After cooling for a period of time, the heating switch component in the secondary actuation mechanism is energized. The heating switch component is heated and connected to the second cavity. The gas enters the third cavity and pushes the piston to move along the extension direction of the third cavity. When the gas pushing force and the penetration resistance reach a balance, the probe assembly stops moving. At this time, the probe assembly is also energized, and the heating component in one probe assembly begins to generate heat. Subsequently, the heat is transferred to another probe through the lunar soil. The temperature sensing component in the other probe assembly receives the heat energy and transmits relevant data through the signal transmission wire.

[0017] The technical solution of this invention has the following advantages:

[0018] 1. The in-situ lunar soil thermal property parameter measuring device provided by the present invention comprises: a shell, wherein a first cavity, a second cavity, and a third cavity are sequentially arranged along the extending direction of the shell, the second cavity storing gas; a primary actuating mechanism disposed in the first cavity, the primary actuating mechanism including a heated driving component, an elastic component, and a weak component, the heated driving component changing from a compressed state to an initial state, the heated driving component directly acting on the weak component and causing the weak component to break, and then releasing the elastic component; a secondary actuating mechanism disposed in the third cavity, the secondary actuating mechanism including a heating switching component and a piston, the heating switching component being heated and communicating with the second cavity, the gas entering the third cavity, the gas pushing the piston to move along the extending direction of the third cavity; and a probe assembly disposed at the end of the piston away from the second cavity, the probe assembly containing a heating component and a temperature sensing component.

[0019] By placing the primary actuation mechanism within the first cavity, the first cavity provides a mounting position for the primary actuation mechanism. Simultaneously, the heated drive component within the primary actuation mechanism can maintain its initial state at a certain temperature. When heated, the heated drive component returns to its memorized shape, recovering from a compressed state to its initial state. Utilizing the large restoring force of this heated drive component, it acts on the weak component, which assists the heated drive component in unlocking and releasing the elastic component. Since the elastic component is initially compressed at the upper end of the weak component, after the weak component breaks, the elastic component returns to its original shape and acts on the top of the secondary actuation mechanism. After the first stage of the ejection process, the elastic component remains in a compressed state, still providing a certain force. After the ejection is completed, the probe assembly is energized, and the heating component within one probe assembly begins to generate heat. Subsequently, the heat diffuses to the soil surrounding the probe assembly. The temperature sensing component within the other probe receives the heat energy and transmits relevant data via signal transmission wires. After the data transmission is completed, the probe assembly is de-energized.

[0020] After cooling for a period of time, the heating switch component in the secondary actuation mechanism is energized. The heating switch component is heated and connected to the second cavity. The gas enters the third cavity and pushes the piston to move along the extension direction of the third cavity. When the gas pushing force and the penetration resistance reach a balance, the probe assembly stops moving. At this time, the probe assembly is also energized, and the heating component in one probe begins to generate heat. Subsequently, the heat is transferred to the other probe through the lunar soil. The temperature sensing component in the other probe receives the heat energy and transmits relevant data through the signal transmission wire.

[0021] The in-situ lunar soil thermal property parameter measuring device has a simple structure and achieves miniaturization, low power consumption, and high power-to-weight ratio without increasing the load weight. At the same time, the dual-actuation mode can complete two in-situ lunar soil thermal property parameter measurements in one operation.

[0022] 2. The in-situ lunar soil thermophysical parameter measuring device provided by the present invention further includes a tube seat and a wire in the primary actuation mechanism. The wire is disposed inside the tube seat and is connected to the heated driving component. The tube seat provides space for the wire, preventing damage to the wire. Simultaneously, one end of the wire is connected to an external power source, and the other end is connected to the heated driving component, thereby heating the heated driving component.

[0023] 3. The in-situ lunar soil thermophysical parameter measuring device provided by the present invention includes a rubber stopper with sealant. Sealant can be added to the upper end of the rubber stopper until no air bubbles are generated, thus completing the entire sealing process.

[0024] 4. The in-situ lunar regolith thermophysical parameter measuring device provided by the present invention includes a sealing ring on the piston, the sealing ring being a fluororubber sealing ring. Considering the high vacuum environment of the lunar surface, the fluororubber sealing ring possesses good vacuum adaptability and low permeability, exhibiting excellent performance under high vacuum and variable pressure conditions. The aforementioned sealing operation ensures the airtightness of the third chamber.

[0025] The summary section is provided to present the chosen concepts in a simplified form, which will be further described in the detailed description below. The summary section is not intended to identify essential or necessary features of this disclosure, nor is it intended to limit the scope of this disclosure. Attached Figure Description

[0026] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0027] Figure 1 A schematic diagram of the structure of the penetrating projectile provided by the present invention;

[0028] Figure 2 This is a schematic diagram of the in-situ lunar soil thermal property parameter measuring device provided by the present invention.

[0029] Figure 3 A cross-sectional view of the in-situ lunar soil thermal property parameter measuring device provided by the present invention;

[0030] Figure 4 A half-sectional view of the in-situ lunar soil thermal property parameter measuring device provided by the present invention;

[0031] Figure 5 A diagram of the primary action mechanism of the in-situ lunar soil thermal property parameter measuring device provided by the present invention;

[0032] Figure 6 A schematic diagram of the gas sealing mechanism of the in-situ lunar soil thermal property parameter measuring device provided by the present invention;

[0033] Figure 7 A schematic diagram of the weak component of the in-situ lunar soil thermal property parameter measuring device provided by the present invention.

[0034] Figure 8 A cross-sectional view of the probe assembly of the in-situ lunar soil thermal property parameter measuring device provided by the present invention;

[0035] Figure 9This is a schematic diagram of the probe assembly of the in-situ lunar soil thermophysical parameter measuring device provided by the present invention.

[0036] Explanation of reference numerals in the attached figures:

[0037] 1. Shell; 2. First cavity; 3. Second cavity; 4. Third cavity; 5. Primary actuation mechanism; 6. Heated drive component; 7. Elastic component; 8. Weak component; 9. Secondary actuation mechanism; 10. Heating on / off assembly; 11. Piston; 12. Probe assembly; 13. Heating assembly; 14. Temperature sensing assembly; 15. Tube seat; 16. Wire; 17. Heat-insulating ring; 18. Vent hole; 19. Annular copper ring; 20. Solder; 21. Heating element; 22. Gas sealing mechanism; 23. Arc-shaped boss; 24. Air inlet; 25. Stepped surface; 26. Compression elastic component; 27. Pressure-bearing gasket; 28. Rubber plug; 29. ​​Sealing compound; 30. Sealing ring; 31. Cable conduit; 32. Penetrating projectile; 33. Snap ring. Detailed Implementation

[0038] In the following description, only certain exemplary embodiments are briefly described. As those skilled in the art will recognize, the described embodiments can be modified in various ways without departing from the spirit or scope of this disclosure. Therefore, the drawings and description are to be considered exemplary in nature and not restrictive.

[0039] In the description of this disclosure, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing this disclosure and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this disclosure. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the stated features. In the description of this disclosure, "a plurality of" means two or more, unless otherwise explicitly specified.

[0040] In the description of this disclosure, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "joint" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections, electrical connections, or connections that allow for communication; they can refer to direct connections or indirect connections through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this disclosure according to the specific circumstances.

[0041] In this disclosure, unless otherwise expressly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0042] The following disclosure provides numerous different embodiments or examples for implementing various structures of this disclosure. To simplify the disclosure, specific examples of components and arrangements are described below. These are merely examples and are not intended to limit the scope of this disclosure. Furthermore, reference numerals and / or letters may be repeated in different examples; such repetition is for simplification and clarity and does not in itself indicate a relationship between the various embodiments and / or arrangements discussed. In addition, various specific examples of processes and materials are provided in this disclosure, but those skilled in the art will recognize the application of other processes and / or the use of other materials.

[0043] The preferred embodiments of this disclosure are described below with reference to the accompanying drawings. It should be understood that the preferred embodiments described herein are for illustration and explanation only and are not intended to limit this disclosure.

[0044] Please see Figures 1 to 9As shown, the present invention provides an in-situ lunar soil thermal property parameter measuring device, which is disposed within a penetrating projectile 32. The in-situ lunar soil thermal property parameter measuring device includes: a housing 1, with a first cavity 2, a second cavity 3, and a third cavity 4 sequentially arranged along the extending direction of the housing 1; the second cavity 3 stores gas; and a primary actuation mechanism 5 disposed within the first cavity 2. The primary actuation mechanism 5 includes a heat-driven component 6, an elastic component 7, and a weak component 8. The heat-driven component 6 changes from a compressed state to an initial state. The gas acts on the weak member 8, causing it to break, and then releases the elastic member 7; a secondary action mechanism 9 is located in the third cavity 4, the secondary action mechanism 9 includes a heating on / off assembly 10 and a piston 11, the heating on / off assembly 10 is heated and connected to the second cavity 3, the gas enters the third cavity 4, the gas pushes the piston 11 to move along the extension direction of the third cavity 4; a probe assembly 12 is located at the end of the piston 11 away from the second cavity 3, the probe assembly 12 is provided with a heating assembly 13 and a temperature sensing assembly 14.

[0045] By setting the first-level actuation mechanism 5 inside the first cavity 2, the first cavity 2 provides a setting position for the first-level actuation mechanism 5. At the same time, the heated driving component 6 inside the first-level actuation mechanism 5 can maintain its initial state at a certain temperature. When the heated driving component 6 is heated, it returns to its memory shape. The heated driving component 6 returns from the compressed state to its initial state. Utilizing the large restoring force of the heated driving component 6, it acts on the weak component 8. That is, the weak component 8 assists the heated driving component 6 in unlocking and releasing the elastic component 7. Since the elastic component 7 is initially compressed at the upper end of the weak component 8, after the weak component 8 breaks, the elastic component 7 returns to its original state and acts on the top of the second-level actuation mechanism. After the first stage of the push-out process, the elastic component 7 is still in a compressed state and still provides a certain force. After the push-out is completed, the probe assembly 12 is energized. The heating component 13 inside the probe assembly 12 starts to work and generates heat. Subsequently, the heat diffuses to the soil around the probe assembly 12. The temperature sensing component 14 inside the other probe receives the heat energy and transmits relevant data through the signal transmission wire. After the data transmission is completed, the probe assembly 12 is de-energized.

[0046] After cooling for a period of time, the heating switch component 10 in the secondary actuation mechanism is energized. The heating switch component 10 is heated and connected to the second cavity 3. The gas enters the third cavity 4 and pushes the piston 11 to move along the extension direction of the third cavity 4. When the gas pushing force and the penetration resistance reach a balance, the probe component 12 stops moving. At this time, the probe component 12 is also energized, and the heating component 13 in one probe begins to generate heat. Subsequently, the heat is transferred to the other probe through the lunar soil. The temperature sensing component in the other probe receives the heat energy and transmits relevant data through the signal transmission wire.

[0047] The in-situ lunar soil thermal property parameter measuring device has a simple structure and achieves miniaturization, low power consumption, and high power-to-weight ratio without increasing the load weight. At the same time, the dual-actuation mode can complete two in-situ lunar soil thermal property parameter measurements in one operation.

[0048] The shell 1 is a titanium alloy shell.

[0049] The probe assembly 12 is provided with a cable conduit 31, which contains a signal transmission wire and a power-conducting wire. Both the signal transmission wire and the power-conducting wire are connected to the heating assembly 13 and the temperature sensing assembly 14.

[0050] In some optional embodiments, the primary actuation mechanism 5 further includes a tube seat 15 and a wire 16, the wire 16 being disposed within the tube seat 15 and connected to the heated drive member 6.

[0051] The tube seat 15 provides a space for the wire 16, preventing damage to the wire 16. At the same time, one end of the wire 16 is connected to an external power supply, and the other end is connected to the heated drive 6, thereby heating the heated drive 6.

[0052] In this embodiment, the tube seat 15 is in the shape of a broken line.

[0053] In some optional embodiments, the heated drive component 6 is a nickel-titanium alloy component. This nickel-titanium alloy component has good shape memory effect and superelasticity, and can maintain its initial shape at a certain temperature and recover its memory shape when heated.

[0054] In some optional embodiments, the heating on / off assembly 10 includes: a heat-resistant ring 17, which is disposed corresponding to the vent 18 of the second cavity 3; an annular copper ring 19, disposed on the heat-resistant ring 17, and solder 20 is provided between the heat-resistant ring 17 and the annular copper ring 19; and a heating element 21, which is connected to the heating assembly 13.

[0055] By setting up a heat-insulating ring 17, which is correspondingly set to the vent 18, the heat-insulating ring 17 blocks the vent 18. At the same time, solder 20 is set between the heat-insulating ring 17 and the annular copper ring 19. The heating element 21 heats the annular copper ring 19, causing the solder 20 between the annular copper ring 19 and the heat-insulating ring 17 to melt. This allows the gas in the second cavity 3 to enter the third cavity 4 through the vent 18, thereby achieving communication between the second cavity 3 and the third cavity 4.

[0056] The heat-insulating ring 17 at the upper end of the annular copper ring 19 can also be replaced with a ceramic fiber ring. The ceramic fiber ring is a high-temperature resistant heat insulation material that can be connected to the annular copper ring 19 by welding.

[0057] In this embodiment, the solder 20 comprises aluminum solder 20 and eutectic solder 20.

[0058] In some optional embodiments, the second cavity 3 is provided with a gas sealing mechanism 22, the gas sealing mechanism 22 including: an arc-shaped boss 23, the arc-shaped boss 23 having an air inlet 24, and a stepped surface 25 on the end face of the arc-shaped boss 23, the stepped surface 25 having a compression elastic element 26; a pressure-bearing pad 27, located at the bottom of the arc-shaped boss 23, the bottom of the pressure-bearing pad 27 having a retaining spring 33; and a rubber plug 28, located at the top of the arc-shaped boss 23.

[0059] By setting the arc-shaped boss 23 and providing an air inlet 24 on the arc-shaped boss 23, it is convenient to fill the second cavity 3 with gas through the air inlet 24. At the same time, the arc-shaped boss 23 is pressurized, and the arc-shaped boss 23 compresses the compression elastic member 26, so that the air inlet 24 reaches the lower end of the step surface 25, and then enters the second cavity 3 through the air inlet 24.

[0060] After inflation is complete, stop applying pressure to the arc-shaped boss 23. Under the action of the internal and external pressure difference, the gas acts on the lower end face of the arc-shaped boss 23, compressing the sealing ring 30 at the upper end of the arc-shaped boss 23 to achieve a primary seal. Then, screw a rubber plug 28 into the opening at the upper end of the arc-shaped boss 23. The upper diameter of the rubber plug 28 is larger than the diameter of the end face opening, and the expansion of the rubber achieves a secondary seal.

[0061] The rubber stopper 28 is provided with sealant 29. Sealant 29 can be added to the upper end of the rubber stopper 28 until no air bubbles are generated, completing the sealing process. This inflation stage is carried out on the ground, using an external air source for inflation.

[0062] In some optional embodiments, the piston 11 is provided with a sealing ring 30, which is a fluororubber sealing ring 30.

[0063] Two fluororubber sealing rings 30 are provided on the piston 11 for sealing, and the piston 11 has protrusions for positioning the two sealing rings 30. In view of the high vacuum environment of the lunar surface, the fluororubber sealing rings 30 have the characteristics of good vacuum adaptability and low permeability, and can exhibit excellent performance under high vacuum and variable pressure conditions. The above sealing operation ensures the airtightness of the third cavity 4.

[0064] The present invention also provides a method for operating the in-situ lunar soil thermal property parameter measuring device, comprising:

[0065] When the heated drive component 6 is heated, it returns from a compressed state to its initial state and acts on the weak component 8. The weak component 8 assists the heated drive component 6 in unlocking and releasing the elastic component 7. Since the elastic component 7 is initially compressed on the upper end of the weak component 8, after the weak component 8 breaks, the elastic component 7 returns to its original state and acts on the top of the secondary actuation mechanism. After the first stage of the push-out process, the elastic component 7 is still in a compressed state and still provides a certain force. After the push-out is completed, the probe assembly 12 is energized, and the heating component 13 in one probe assembly 12 starts to work and generates heat. Subsequently, the heat diffuses to the soil around the probe assembly 12. The temperature sensing component 14 in another probe receives the heat energy and transmits relevant data through the signal transmission wire. After the data transmission is completed, the probe assembly 12 is de-energized.

[0066] After cooling for a period of time, the heating switch component 10 in the secondary actuation mechanism is energized. The heating switch component 10 is heated and connected to the second cavity 3. The gas enters the third cavity 4 and pushes the piston 11 to move along the extension direction of the third cavity 4. When the gas pushing force and the penetration resistance reach a balance, the probe component 12 stops moving. At this time, the probe component 12 is also energized, and the heating component 13 in one probe component 12 begins to generate heat. Subsequently, the heat is transferred to another probe through the lunar soil. The temperature sensing component 14 in the other probe 12 receives the heat energy and transmits relevant data through the signal transmission wire.

[0067] Obviously, the above embodiments are merely illustrative examples for clear explanation and are not intended to limit the implementation. Those skilled in the art will recognize that other variations or modifications can be made based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. However, obvious variations or modifications derived therefrom are still within the scope of protection of this invention.

Claims

1. An in-situ lunar soil thermophysical parameter measuring device, characterized in that, include: The shell (1) is provided with a first cavity (2), a second cavity (3), and a third cavity (4) in sequence along the extension direction of the shell (1). The second cavity (3) stores gas. The first-level action mechanism (5) is located in the first cavity (2). The first-level action mechanism (5) includes a heat-driven component (6), an elastic component (7), and a weak component (8). The heat-driven component (6) changes from a compressed state to an initial state. The heat-driven component (6) acts directly on the weak component (8) and causes the weak component (8) to break. Then the elastic component (7) is released to realize the first stage of ejection. The secondary action mechanism (9) is located in the third cavity (4). The secondary action mechanism (9) includes a heating switch assembly (10) and a piston (11). The heating switch assembly (10) is heated and connected to the second cavity (3). Gas enters the third cavity (4) and pushes the piston (11) to move along the extension direction of the third cavity (4). The probe assembly (12) is located at the end of the piston (11) away from the second chamber (3). The probe assembly (12) is provided with a heating assembly (13) and a temperature sensing assembly (14). The heat-driven component (6) is a nickel-titanium alloy component; The heating on / off assembly (10) includes: A heat-insulating ring (17) is provided corresponding to the vent (18) of the second cavity (3); An annular copper ring (19) is disposed on a heat-insulating ring (17), and solder (20) is provided between the heat-insulating ring (17) and the annular copper ring (19). Heating element (21) is located at the bottom of the annular copper ring (19) and is used to heat solder (20). When solder (20) melts, gas in the second cavity (3) enters the third cavity (4) through the vent (18), thus realizing the connection between the second cavity (3) and the third cavity (4).

2. The in-situ lunar soil thermal property parameter measuring device according to claim 1, characterized in that, The primary action mechanism (5) also includes a tube seat (15) and a wire (16), the wire (16) being located inside the tube seat (15) and connected to the heated drive component (6).

3. The in-situ lunar soil thermophysical parameter measuring device according to claim 2, characterized in that, Solder (20) consists of aluminum solder and eutectic solder.

4. The in-situ lunar soil thermophysical parameter measuring device according to claim 3, characterized in that, The piston (11) is provided with a sealing ring (30), which is a fluororubber sealing ring (30).

5. The in-situ lunar soil thermophysical parameter measuring device according to claim 3, characterized in that, The shell (1) is a titanium alloy shell.

6. A method for operating the in-situ lunar soil thermal property parameter measuring device according to any one of claims 1-5, characterized in that, include: When the heated drive component (6) is heated, the heated drive component (6) returns from the compressed state to the initial state and acts on the weak component (8). The weak component (8) assists the heated drive component (6) in unlocking and releasing the elastic component (7). Since the elastic component (7) is initially compressed on the upper end of the weak component (8), after the weak component (8) breaks, the elastic component (7) returns to its original state, realizing the first stage of ejection. After the first stage of ejection, the elastic component (7) is still in the compressed state and still provides a certain force. After the ejection is completed, the probe assembly (12) is powered on. The heating component (13) in one probe assembly (12) starts to work and generates heat. Then the heat diffuses to the soil around the probe assembly (12). The temperature sensing component (14) in another probe receives the heat energy and transmits relevant data through the signal transmission wire. After the data transmission is completed, the probe assembly (12) is powered off. After cooling for a period of time, the heating switch component (10) in the secondary actuation mechanism is energized. The heating switch component (10) is heated and connected to the second cavity (3). Gas enters the third cavity (4). The gas pushes the piston (11) to move along the extension direction of the third cavity (4). When the gas pushing force and the penetration resistance reach equilibrium, the probe component (12) stops moving. At this time, the probe component (12) is also energized. The heating component (13) in one probe component (12) begins to generate heat. Subsequently, the heat is transferred to another probe through the lunar soil. The temperature sensing component in the other probe component (12) receives the heat energy and transmits relevant data through the signal transmission wire.

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