A semi-infinite boundary equivalent target cabin system and an equivalent ground verification test method

Abstract

The present application relates to the technical field of lunar soil ball penetration exploration, in particular to a semi-infinite boundary equivalent target cabin system and an equivalent ground verification test method. The semi-infinite boundary equivalent target cabin system comprises a main body, the main body comprises a raw material cabin and an observation cabin, the raw material cabin is provided with a first containing cavity, a wave absorbing layer is arranged on the inner wall of the first containing cavity, and the raw material cabin is used for loading simulation lunar soil raw materials; the observation cabin is provided with a second containing cavity, the observation cabin is provided with an observation window, and a through hole is arranged at one end of the observation cabin; a walking mechanism is arranged at the bottom of the main body, and the walking mechanism moves on a track. The observation window arranged in the observation cabin is used for monitoring the speed and attitude information of the test piece by using high-speed photography, and the wave absorbing layer is mainly used for absorbing stress waves in the penetration process, so as to make it equivalent to a semi-infinite body.

Description

Technical Field

[0001] This invention relates to the field of lunar regolith penetration exploration technology, specifically to a semi-infinite boundary equivalent target chamber system and an equivalent ground verification test method. Background Technology

[0002] The lunar regolith penetrating exploration mission mode effectively solves the challenges of in-situ exploration of areas inaccessible to the main probe and wide-area distributed network exploration during lunar in-situ exploration. Its main method involves carrying a large number of scientific payloads on a penetrating projectile, using high-speed kinetic energy to penetrate into the lunar subsurface profile. The onboard scientific payloads then conduct in-situ exploration of the uncontaminated subsurface lunar regolith. After exploration is completed, its communication transmission module transmits the data back to a relay satellite. During the development of the penetrating exploration instrument, extensive penetration tests under ground conditions are required to verify the penetrability, payload survivability, and communication reliability of the instrument. Reasonable ground simulation of the lunar regolith profile, providing target objects for penetration tests, is the core and prerequisite for conducting ground verification of the lunar regolith penetrating exploration instrument. The target objects must adhere to three basic principles: Earth-Moon consistency, operational condition coverage, and boundary equivalence. Summary of the Invention

[0003] Therefore, the present invention provides a semi-infinite boundary equivalent target chamber system and an equivalent ground verification test method.

[0004] To address the aforementioned technical problems, this invention provides a semi-infinite boundary equivalent target chamber system, comprising: a main body, the main body including a raw material chamber and an observation chamber, the raw material chamber having a first receiving cavity, the inner wall of the first receiving cavity being provided with a wave-absorbing layer, the raw material chamber being used to carry simulated lunar soil raw materials; the observation chamber having a second receiving cavity, the observation chamber being provided with an observation window, and a through hole being provided at one end of the observation chamber; and a traveling mechanism located at the bottom of the main body, the traveling mechanism moving on a track.

[0005] Furthermore, a connecting plate is provided between the raw material compartment and the observation compartment, and a door is provided on the connecting plate, with the through hole and the door located on the same straight line.

[0006] Furthermore, both the raw material compartment and the observation compartment include a support frame and a plate disposed on the support frame, and the support frame has a three-dimensional structure.

[0007] Furthermore, the absorbing layer is a nylon absorbing liner.

[0008] Furthermore, the observation window is made of double-layered and transparent polycarbonate.

[0009] This invention also provides a ground verification test method for a semi-infinite boundary equivalent of a penetrating explorer, using the aforementioned semi-infinite boundary equivalent target chamber system, including the following steps: 1. Weak extreme condition verification: Using a 300mm caliber balanced gun, since the simulated lunar regolith profile target is relatively loose, a sand rain method combined with a vibratory rod is used to compact it to a density of approximately 1.55g / cm3, and the landing condition with an angle of impact is verified by changing the slope of the impact surface; 2. Nominal condition verification: Using a 155mm caliber air gun, according to the definition of nominal condition, the relative density of the lunar regolith under nominal condition is greater than 90%, i.e., true... With a density greater than 1.8 g / cm3, a 1.5×1.5×3.6m material compartment was used as a container to hold the simulated lunar soil, with a length-to-diameter ratio of approximately 15 to the projectile body; III. Extreme working conditions: Using a 155 caliber air cannon, the simulation of target samples for this type of working condition can be achieved by pre-placing rock blocks with a size of 9 cm and a volume content of approximately 20% on the expected trajectory of the penetrating class; IV. Giant rock working conditions: Using a 155 caliber air cannon, the simulation of target samples for this type of working condition can be achieved by arranging giant simulated lunar rocks with a size greater than 1 m on the projectile-facing surface of the target compartment system or at a depth of 0.5 m.

[0010] Furthermore, the specific verification method for the weak extreme working condition is as follows: Based on the density distribution characteristics of lunar regolith, a lunar regolith profile with a relative density of ≈65%, where penetrating probes can easily penetrate and may penetrate too deeply, is defined as a weak extreme working condition. The main implementation method involves using a sand-rain method in conjunction with a vibratory compactor to compact the lunar regolith to a density of approximately 1.55 g / cm³. 3 Similar to the working conditions of a loose profile on the lunar surface, during the test, the explorer test piece was accelerated to the target speed by a 155mm caliber air cannon and then penetrated into the simulated target body of a weak extreme working condition.

[0011] Furthermore, the specific verification method for the nominal working condition is as follows: the working condition that is most likely to occur on the lunar surface and is the main exploration range of the scientific exploration payload is defined as the nominal working condition; for the waterless nominal lunar regolith profile, the main implementation plan is to use four vibration motors with an excitation force of 500 kg at a frequency of 50 Hz to vibrate and compact the loose simulated lunar regolith material in layers. Every 5 tons of simulated lunar regolith material is filled, and vibration and compaction is carried out for 20 minutes to make the relative density of the lunar regolith >95%; for the lunar regolith water ice layer profile containing 3% water content, a secondary equivalent material with similar mechanical properties to the lunar regolith water ice containing 3% water content is placed at a depth of 0.5 m along the trajectory to be used as an equivalent to the lunar regolith profile containing lunar regolith water ice; during the test, the explorer test piece is accelerated to the target velocity by a 155 mm caliber air cannon and then penetrates the nominal working condition simulated target body.

[0012] Furthermore, the specific verification method for the strong extreme working condition is as follows: A profile of lunar regolith with a volume content >20% and small pieces of lunar rock >90mm in size is defined as the strong extreme working condition. This is primarily to verify the reliability of the communication umbilical cable of the penetrating probe. The main implementation plan involves mixing small pieces of rock (90mm-150mm in size) with nominal fine-grained lunar regolith at a ratio of 2:8, then vibrating and compacting it to a relative density >95% according to the nominal working condition preparation process. During the test, the probe test piece is accelerated to the target velocity using a 155mm caliber air cannon before penetrating the simulated target body of the strong extreme working condition.

[0013] Further, the specific verification method for the strong extreme working condition is as follows: The condition of encountering lunar rocks larger than 0.8m on the lunar surface is defined as the strong extreme working condition, primarily to verify the overload resistance of the penetrating exploration instrument. The main implementation plan involves placing rock blocks with a strength >100MPa and a size >1m on the target chamber's anti-ballistic surface, followed by filling with fine-grained lunar regolith with a density >95%, similar to the nominal working condition, to simulate the presence of giant rocks on the lunar surface; or placing rock blocks with a strength >100MPa and a size >1m at a depth of 0.5m along the penetration trajectory, with the remaining portion filled with fine-grained lunar regolith with a density >95%, similar to the nominal working condition. During the test, the exploration instrument prototype is accelerated to the target velocity using a 155mm caliber air cannon before penetrating the target chamber simulating the giant rock condition.

[0014] The technical solution of this invention has the following advantages:

[0015] 1. The semi-infinite boundary equivalent target chamber system provided by the present invention includes: a main body, the main body including a raw material chamber and an observation chamber, the raw material chamber having a first receiving cavity, the inner wall of the first receiving cavity being provided with a wave-absorbing layer, the raw material chamber being used to carry simulated lunar soil raw material; the observation chamber having a second receiving cavity, the observation chamber being provided with an observation window, and a through hole being provided at one end of the observation chamber; and a walking mechanism located at the bottom of the main body, the walking mechanism moving on a track.

[0016] The first cavity of the raw material compartment is used to carry simulated lunar soil raw materials. One end of the observation compartment is provided with a through hole to facilitate the smooth entry of the test specimen into the observation compartment. The observation window in the observation compartment is used to monitor the speed and attitude information of the test specimen using high-speed photography. The wave-absorbing layer is mainly used to absorb stress waves during the penetration process, making it equivalent to a semi-infinite body.

[0017] 2. The semi-infinite boundary equivalent target chamber system provided by the present invention includes a connecting plate between the raw material chamber and the observation chamber, and a hatch on the connecting plate, wherein the through hole and the hatch are located on the same straight line. The connecting plate allows the raw material chamber and the observation chamber to be connected as a whole; simultaneously, a hatch can be provided between the raw material chamber and the observation chamber to facilitate communication between them.

[0018] 3. The semi-infinite boundary equivalent target chamber system provided by the present invention includes a support frame and a plate disposed on the support frame, wherein the support frame has a three-dimensional structure. The support frame and the plate together form a load-bearing skeleton, which is mainly used to simulate the weight of lunar soil.

[0019] 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

[0020] 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.

[0021] Figure 1 A schematic diagram of the semi-infinite boundary equivalent target chamber system provided by the present invention;

[0022] Figure 2 A perspective view of the semi-infinite boundary equivalent target chamber system provided by the present invention;

[0023] Figure 3 A schematic diagram of the through hole structure of the semi-infinite boundary equivalent target chamber system provided by the present invention;

[0024] Figure 4 This represents the potential penetration state of the survey instrument under weak extreme working conditions.

[0025] Figure 5 This refers to the possible penetration conditions of the nominal working condition survey instrument;

[0026] Figure 6 This is to describe the possible penetration conditions of the survey instrument under extreme working conditions;

[0027] Figure 7 This describes the possible penetration conditions of the rock-cutting survey instrument.

[0028] Figure 8Method for preparing profiles under weak extreme working conditions;

[0029] Figure 9 Method for preparing nominal working condition profiles;

[0030] Figure 10 Method for preparing profiles under strong extreme working conditions;

[0031] Figure 11 For the penetration acceleration process curves under different boundary conditions;

[0032] Figure 12 The acceleration curves for the penetrating body test are shown.

[0033] Explanation of reference numerals in the attached figures:

[0034] 1. Main body; 2. Raw material compartment; 21. First accommodating cavity; 22. Wave-absorbing layer; 3. Observation compartment; 31. Second accommodating cavity; 32. Observation window; 33. Through hole; 4. Walking mechanism; 5. Track; 6. Connecting plate; 61. Door; 7. Support frame; 8. Plate. Detailed Implementation

[0035] 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.

[0036] 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.

[0037] 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.

[0038] 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.

[0039] 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.

[0040] 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.

[0041] Please see Figures 1 to 11 As shown, the operating conditions of penetrating exploration instruments are mainly defined as weak extreme conditions, nominal conditions, strong extreme conditions, and giant rock conditions.

[0042] Lunar polar penetration exploration will face a harsh and uncertain operating environment. Furthermore, due to its high-speed, transient nature, it cannot be manually intervened online and must rely on its own designed configuration for adaptive penetration operations. Its penetration effectiveness and the high degree of randomness in detecting internal targets further complicate matters. Based on the petrophysical parameter spectrum of lunar regolith profiles at the edge of permanently shadowed craters at the lunar south pole, and constrained by the survivability and detectability of the explorer's scientific payload, this paper classifies and defines the possible operating conditions encountered during the explorer's landing and penetration process, providing input for the system's ground verification.

[0043] The first type is the weak extreme condition: This refers to a surface lunar regolith profile with low bearing capacity and shear strength, but high void ratio and compressibility coefficient. Under this condition, the probe's penetration depth is greater, potentially burying the propulsion stage communication terminal and causing communication failure. Furthermore, low-density lunar regolith is prone to bounce. Therefore, this type of condition should be considered as the upper envelope requirement for propulsion stage drag design and attitude control design.

[0044] A1. Low-density lunar soil profile: Based on the minimum relative density of lunar surface soil being approximately 60%, a lunar soil profile with a relative density of 60% is defined as the weak extreme. At this point, the actual density of the lunar soil profile is approximately 1.55 g / cm3, and the penetration depth of the exploration instrument is approximately 2.5–3 m.

[0045] A2. Low-density lunar regolith profile with an angle of impact: The landing environment of the exploration instrument may have a certain angle of impact, and a low-density lunar regolith profile with an angle of impact is more likely to ricochet. Therefore, this condition is designed with a relative density of approximately 60% for the entire profile and an angle of 15° between the impact surface and the exploration instrument test piece.

[0046] The second type is the nominal operating condition: The nominal operating condition refers to the probable distribution state of lunar regolith in the lunar polar regions. This type of operating condition forms the basis for the design and verification of the penetration depth and functional loads of the exploration instrument. Therefore, this type of operating condition will be the primary focus for verifying the functional performance indicators of the entire exploration instrument system and the decoupling verification of the functional performance indicators of each subsystem. Under this operating condition, the penetration depth of the exploration instrument's penetration stage is approximately 1.5m, and all functional loads operate normally. This type of operating condition mainly includes the following two types:

[0047] B1. Dense lunar soil profile: Based on the general distribution pattern of lunar soil on the lunar surface, it is believed that the relative density of lunar soil 20cm below the lunar surface will be greater than 90%. Therefore, when conducting ground tests, we vibrated and compacted the waterless simulated lunar soil to a relative density greater than 90%.

[0048] B2. Water Ice Layer in Lunar Resin with 3% Water Content: Water ice material is likely to be present in impact craters in the lunar polar regions, making it the primary target of the lunar resin penetrating survey instrument. Based on the distribution patterns of water ice material, the first 0.5m of the target in our experiment was set as simulated lunar resin with a relative density greater than 90%, 0.5m to 1m was set as a secondary equivalent material with mechanical properties similar to water ice in lunar resin with 3% water content, and 1m to 3m was set as simulated lunar resin with a relative density greater than 90%.

[0049] The third type is the strong extreme condition: Strong extreme conditions refer to the presence of small fragments of lunar rock with specific scale characteristics in the lunar regolith profile, which the probe has a certain probability of encountering during penetration. This type of condition may cause a small-angle attitude deflection of the probe stage during penetration, resulting in a slightly lower penetration depth and the risk of the communication umbilical cable breaking. Furthermore, it may cause poor contact between some functional probes and the lunar regolith. Therefore, this type of condition is the basis for the design of communication umbilical cable strength and the design of uncertainties in functional probes.

[0050] C1 lunar reef profile containing large-scale particles: Based on the influence of aggregate size on the attitude of the penetrator, a ratio of aggregate size to penetrator diameter of 1 significantly affects the deflection attitude of the penetrator. Furthermore, Apollo data shows that the maximum coarse particle content in the profile is approximately 20%. Therefore, a lunar reef profile containing coarse aggregate with a diameter of approximately 90 mm and a volume content of approximately 20% is defined as a strong extreme condition. Under this condition, the penetration depth of the exploration instrument's penetrator class is greater than 1.2 m, and most functional loads operate normally.

[0051] The fourth type is the giant rock condition: This refers to the encounter of giant rocks larger than 90cm in size on the exploration instrument's penetration trajectory. This condition has an extremely low probability of being encountered during penetration, and it is the upper envelope of the functional detection payload's overload tolerance design. This type of condition is mainly divided into the following three categories:

[0052] D1. Large-scale surface boulder condition: Large-scale boulder refers to a large rock formation located more than 0.5m above the lunar surface with a strength >100MPa, a size >0.8m, and a thickness >0.5m, beneath which lies simulated lunar regolith with a relative density >90%. This type of condition is the most severe that a surveyor may encounter during landing, and the surveyor cannot penetrate it. This type of condition needs to be avoided through remote sensing and other technical means.

[0053] D2. Small-sized surface boulders: Small-sized boulders refer to rocks located on the lunar surface with a strength >100MPa, a size of 0.6-0.8m, and a thickness of 0.3-0.5m, located more than 0.5m above the surface. While penetrating exploration instruments can break these rocks during penetration, the overall penetration efficiency of the instrument is significantly reduced.

[0054] D3. Deeply buried giant rock condition: Shallowly buried giant rock refers to large rocks buried at a depth of 0.5 to 1m on the lunar soil surface, with a size greater than 0.8m and a thickness greater than 0.5m. In this type of condition, the attitude of the penetrating exploration instrument will deflect during the penetration process, and the overload of the exploration instrument will also be at its maximum. This type of condition is the upper envelope of the functional detection load overload-resistant design.

[0055] Please see Figures 1 to 3 As shown, the present invention provides a semi-infinite boundary equivalent target chamber system, comprising: a main body, the main body including a raw material chamber and an observation chamber, the raw material chamber having a first receiving cavity, the inner wall of the first receiving cavity being provided with a wave-absorbing layer, the raw material chamber being used to carry simulated lunar soil raw materials; the observation chamber having a second receiving cavity, the observation chamber being provided with an observation window, and a through hole being provided at one end of the observation chamber; and a walking mechanism located at the bottom of the main body, the walking mechanism moving on a track.

[0056] The first cavity of the raw material compartment is used to carry simulated lunar soil raw materials. One end of the observation compartment is provided with a through hole to facilitate the smooth entry of the test specimen into the observation compartment. The observation window in the observation compartment is used to monitor the speed and attitude information of the test specimen using high-speed photography. The wave-absorbing layer is mainly used to absorb stress waves during the penetration process, making it equivalent to a semi-infinite body.

[0057] In some optional embodiments, a connecting plate is provided between the raw material compartment and the observation compartment, and a door is provided on the connecting plate, with the through hole and the door located on the same straight line. The connection plate makes the raw material compartment and the observation compartment a whole; at the same time, a door can also be provided between the raw material compartment and the observation compartment to facilitate communication between the two compartments.

[0058] In some optional embodiments, both the raw material compartment and the observation compartment include a support frame and a plate disposed on the support frame, the support frame having a three-dimensional structure. The support frame and the plate together form a load-bearing skeleton, which is mainly used to simulate the weight of lunar soil.

[0059] In this embodiment, the absorbing layer is a nylon absorbing liner, which is mainly used to absorb stress waves during the penetration process, making it equivalent to a semi-infinite body.

[0060] The viewing window is made of double-layered, transparent polycarbonate.

[0061] This invention also provides a ground verification test method for a semi-infinite boundary equivalent of a penetrating explorer, using the aforementioned semi-infinite boundary equivalent target chamber system, characterized by comprising the following steps:

[0062] I. Verification under weak extreme conditions: Using a 300mm caliber balanced gun, since the simulated lunar soil profile target is relatively loose, the sand rain method was used in conjunction with a vibratory rod to compact it to a density of approximately 1.55g / cm3, and the landing condition with an angle of impact was verified by changing the slope of the impact surface.

[0063] II. Verification of Nominal Operating Conditions: Using a 155mm air cannon, according to the definition of nominal operating conditions, the relative density of lunar soil under nominal operating conditions is greater than 90%, that is, the actual density is greater than 1.8g / cm3. A raw material tank of 1.5×1.5×3.6m was used as a container to hold the simulated lunar soil, with a length-to-diameter ratio of approximately 15 to the projectile body.

[0064] III. Extreme Working Conditions: Using a 155mm air cannon, the simulation of target samples for this type of working condition can be achieved by pre-placing a rock block with a size of 9cm and a volume content of about 20% on the expected trajectory of the penetrating ballistic missile.

[0065] IV. Giant Rock Condition: Using a 155mm air cannon, the target sample for this type of condition can be simulated by placing a giant simulated lunar rock with a size >1m on the target chamber system's anti-missile surface or at a depth of 0.5m.

[0066] System Verification under Weak Extreme Conditions: Under weak extreme conditions, the exploration instrument faces two main risks: first, the power stage may fail to remain on the lunar surface, causing communication interruption; second, the penetration stage may penetrate too deeply, resulting in the umbilical cable being severed. Therefore, for such conditions, it is crucial to verify the power stage's residence characteristics on the lunar surface and the functional performance characteristics of the damping buffer.

[0067] Verification of the whole system under nominal working conditions: The nominal working conditions are the working conditions that the exploration instrument will most likely face in the future. Therefore, the verification of this type of working condition mainly involves the following two aspects: First, the penetration of the whole system under different terrain and geomorphological conditions; Second, the functional and performance verification of the scientific detection payload of the whole system.

[0068] Verification of the entire system under severe extreme conditions: Severe extreme conditions refer to the working conditions that the exploration instrument faces. The verification of this type of working condition mainly involves the following two aspects: First, the attitude disturbance of gravel structures with certain sizes and shapes during the penetration process; Second, verifying whether the communication umbilical cable will be damaged due to the disturbance of large-scale gravel during the penetration process.

[0069] In some optional embodiments, the specific verification method for the weak extreme working condition is as follows: Based on the density distribution characteristics of lunar regolith, a lunar regolith profile with a relative density of ≈65%, where penetrating probes can easily penetrate and may penetrate too deeply, is defined as a weak extreme working condition; the main implementation method is to use the sand rain method in conjunction with a vibrator to compact the lunar regolith to a density of approximately 1.55 g / cm³. 3Similar to the working conditions of a loose profile on the lunar surface, during the test, the explorer test piece was accelerated to the target speed by a 155mm caliber air cannon and then penetrated into the simulated target body of a weak extreme working condition.

[0070] In order to effectively eliminate the interference of boundary effects caused by stress wave reflection on the acceleration response of penetrating projectiles, a nylon layer absorbing interface with a wave impedance lower than that of dense simulated lunar soil was added around the semi-infinite boundary equivalent target chamber system.

[0071] In some optional embodiments, the specific verification method for the nominal working condition is as follows: the working condition that is most likely to occur on the lunar surface and is the main exploration range of the scientific exploration payload is defined as the nominal working condition; for the waterless nominal lunar regolith profile, the main implementation scheme is to use four vibration motors with an excitation force of 500 kg at a frequency of 50 Hz to perform layered vibration compaction on the loose simulated lunar regolith material. Every 5 t of simulated lunar regolith material is filled, and vibration compaction is performed for 20 minutes to make the relative density of the lunar regolith >95%; for the lunar regolith water ice layer profile containing 3% water content, a secondary equivalent with similar mechanical properties to the lunar regolith water ice containing 3% water content is arranged at a depth of 0.5 m along the trajectory to be used as an equivalent to the lunar regolith profile containing lunar regolith water ice; during the test, the explorer test piece is accelerated to the target speed by a 155 mm caliber air cannon and then penetrates the nominal working condition simulated target body.

[0072] In some optional embodiments, the specific verification method for strong extreme conditions is as follows: A profile of lunar regolith with a volume content >20% and small pieces of lunar rock >90mm in size is defined as a strong extreme condition. This is primarily to verify the reliability of the communication umbilical cable of the penetrating probe. The main implementation involves mixing small pieces of rock (90mm-150mm in size) with nominal fine-grained lunar regolith at a 2:8 ratio, then vibrating and compacting it to a relative density >95% according to the nominal condition preparation process. During the test, the probe test piece is accelerated to the target velocity using a 155mm caliber air cannon and then penetrates the simulated target body of the strong extreme condition.

[0073] In some optional embodiments, the specific verification method for strong extreme working conditions is as follows: The condition of encountering lunar rocks larger than 0.8m on the lunar surface is defined as a strong extreme working condition, primarily to verify the overload resistance of the penetrating exploration instrument. The main implementation scheme involves placing rock blocks with a strength >100MPa and a size >1m on the target chamber's anti-ballistic surface, followed by filling with fine-grained lunar regolith with a density >95%, similar to the nominal working condition, to simulate the presence of giant rocks on the lunar surface; or placing rock blocks with a strength >100MPa and a size >1m at a depth of 0.5m along the penetration trajectory, with the remaining portion filled with fine-grained lunar regolith with a density >95%, similar to the nominal working condition. During the test, the exploration instrument prototype is accelerated to the target velocity using a 155mm caliber air cannon before penetrating the target chamber simulating the giant rock condition.

[0074] The verification method first uses numerical simulation to analyze the influence of the boundary during the penetration process. For example... Figure 10 The curves shown are acceleration curves under three working conditions: iron bucket + nylon, pure iron bucket, and no reflective boundary. Figure 10 As can be seen, the boundary acceleration of the pure iron barrel exhibits significant fluctuations due to the influence of boundary conditions, primarily caused by the reflection and transmission of stress waves. By adding a nylon absorbing layer between the iron barrel and the target chamber system, the acceleration curve almost perfectly matches that under non-reflective boundary conditions. This effectively demonstrates that the nylon interlayer effectively absorbs stress waves and also indirectly reflects that by adding a nylon absorbing interlayer, the equivalent semi-infinite body boundary of a target with finite dimensions can be effectively utilized.

[0075] The boundary effect of the target is mainly manifested in the fluctuation of the acceleration curve during the penetration process. When the boundary of the target affects the penetration mechanical response of the projectile, its acceleration curve has obvious characteristic fluctuation peaks. Conversely, when the characteristic fluctuation peaks do not appear on the acceleration curve, it can be considered that the boundary has no significant effect on the mechanical response of the penetration process. At this time, it can be considered that the condition is equivalent to the semi-infinite body boundary condition on the lunar surface.

[0076] To verify the semi-infinite boundary equivalence of the target chamber system, we conducted penetration tests using a 155mm air cannon against a 90mm reconnaissance projectile prototype equipped with an acceleration recording module. The test setup diagram is shown below. Figures 1 to 3 As shown, we obtained the acceleration curves of a nominal working target with dimensions of 1.5m × 1.5m × 3m under both conditions: with and without a target chamber system and an internal absorbing layer. Figure 12 As shown in the figure, the acceleration curves show obvious characteristic fluctuation peaks caused by the boundary when no nylon absorbing layer is added, while no obvious characteristic fluctuation peaks are seen when the absorbing layer material is added. This indicates that the method proposed in this invention can effectively reduce the interference of the target boundary effect on the projectile penetration load response, thereby achieving the experimental objective of using a finite-size target to replace a semi-infinite target.

[0077] 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. A semi-infinite boundary equivalent target chamber system, characterized in that, include: The main body includes a raw material compartment and an observation compartment. The raw material compartment has a first receiving cavity, and the inner wall of the first receiving cavity is provided with a wave-absorbing layer. The raw material compartment is used to carry simulated lunar soil raw materials. The observation chamber has a second receiving cavity, an observation window is provided on the observation chamber, and a through hole is provided at one end of the observation chamber; A walking mechanism is located at the bottom of the main body, and the walking mechanism moves on a track; The absorbing layer is a nylon absorbing liner.

2. The semi-infinite boundary equivalent target chamber system according to claim 1, characterized in that, A connecting plate is provided between the raw material compartment and the observation compartment, and a door is provided on the connecting plate. The through hole and the door are located on the same straight line.

3. The semi-infinite boundary equivalent target chamber system according to claim 2, characterized in that, Both the raw material compartment and the observation compartment include a support frame and a plate disposed on the support frame, and the support frame has a three-dimensional structure.

4. The semi-infinite boundary equivalent target chamber system according to claim 3, characterized in that, The viewing window is made of double-layered, transparent polycarbonate.

5. A ground verification test method for a penetrating explorer with a semi-infinite boundary equivalent, using the semi-infinite boundary equivalent target chamber system as described in any one of claims 1-4, characterized in that, Includes the following steps: I. Verification under weak extreme conditions: Using a 155mm balanced gun, since the simulated lunar soil profile target is relatively loose, the sand rain method was used in conjunction with a vibratory rod to compact it to a density of approximately 1.55g / cm3, and the landing condition with an angle of impact was verified by changing the slope of the impact surface. II. Verification of Nominal Operating Conditions: Using a 155mm air cannon, according to the definition of nominal operating conditions, the relative density of lunar soil under nominal operating conditions is greater than 90%, that is, the actual density is greater than 1.8g / cm3. A 1.5×1.5×3.6m material tank was used as a container to hold the simulated lunar soil, with a length-to-diameter ratio of approximately 15 to the projectile body. III. Extreme Working Conditions: Using a 155mm air cannon, the simulation of target samples for this type of working condition can be achieved by pre-placing a rock block with a size of 9cm and a volume content of about 20% on the expected trajectory of the penetrating ballistic missile. IV. Giant Rock Condition: Using a 155mm air cannon, the target sample for this type of condition can be simulated by placing a giant simulated lunar rock with a size >1m on the target chamber system's anti-missile surface or at a depth of 0.5m.

6. The ground verification test method for the semi-infinite boundary equivalent of the penetrating explorer according to claim 5, characterized in that, The specific verification method for weak extreme working conditions: Based on the density distribution characteristics of lunar regolith, a lunar regolith profile with a relative density of ≈65%, where penetrating probes can easily penetrate and may penetrate too deeply, is defined as a weak extreme working condition; the main implementation plan is to use the sand rain method in conjunction with a vibratory tamper to compact the lunar regolith to a density of approximately 1.55 g / cm³. 3 Similar to the working conditions of a loose profile on the lunar surface, the probe test piece was accelerated to the target speed by a 155 mm caliber air cannon and then penetrated into the simulated target body of a weak extreme working condition.

7. The ground verification test method for the semi-infinite boundary equivalent of the penetrating explorer according to claim 6, characterized in that, The specific verification method for the nominal working condition is as follows: The working condition that is most likely to occur on the lunar surface and is the main exploration range of the scientific exploration payload is defined as the nominal working condition. For the waterless nominal lunar regolith profile, the main implementation plan is to use four vibration motors with an excitation force of 500 kg to vibrate and compact the loose simulated lunar regolith material in layers at a frequency of 50 Hz. Every 5 tons of simulated lunar regolith material is filled and vibrated and compacted for 20 minutes to make the relative density of the lunar regolith >95%. For the lunar regolith water ice layer profile with 3% water content, a secondary equivalent with similar mechanical properties to the 3% water content lunar regolith water ice is placed at a depth of 0.5 m along the trajectory to be used as an equivalent to the lunar regolith profile containing lunar regolith water ice. During the test, the explorer test piece is accelerated to the target velocity by a 155 mm caliber air cannon and then penetrates the nominal working condition simulated target body.

8. The ground verification test method for the semi-infinite boundary equivalent of the penetrating explorer according to claim 6, characterized in that, Specific verification methods for strong extreme operating conditions: The lunar regolith profile containing small lunar rocks larger than 90 mm and a volume content greater than 20% in the lunar regolith layer on the lunar surface is defined as a strong extreme working condition. This is mainly to verify the reliability of the communication umbilical cable of the penetrating probe. The main implementation plan is to mix small rocks with a size of 90 mm to 150 mm with nominal fine-grained lunar regolith at a ratio of 2:8, and then vibrate and compact it to a relative density of >95% according to the nominal working condition preparation process. During the test, the probe test piece is accelerated to the target speed by a 155 mm caliber air cannon and then penetrates the simulated target body of the strong extreme working condition.

9. The ground verification test method for the semi-infinite boundary equivalent of the penetrating explorer according to claim 6, characterized in that, The specific verification method for the giant rock test is as follows: The test condition of lunar rocks larger than 0.8m in size appearing on the lunar surface is defined as a strong extreme test condition, mainly to verify the overload resistance of the penetrating exploration instrument. The main implementation plan is to place rock blocks with a strength >100MPa and a size >1m on the target surface of the target chamber, and then fill it with fine-grained lunar soil with a density >95% similar to the nominal test condition to simulate the test condition of giant rocks appearing on the lunar surface; or place rock blocks with a strength >100MPa and a size >1m at a depth of 0.5m along the penetration trajectory, and fill the remaining part with fine-grained lunar soil with a density >95% similar to the nominal test condition; during the test, the exploration instrument test piece is accelerated to the target velocity by a 155 mm caliber air cannon and then penetrates into the giant rock test simulation target.

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