A small detachable penetrator for in-situ exploration of celestial bodies

Abstract

The application discloses a small-sized separated penetrator for in-situ detection of celestial bodies, and relates to the technical field of penetrator equipment, comprising an aluminum honeycomb buffer module, which comprises an external protective shell and an aluminum honeycomb, and has the beneficial effects that the application is provided with in-situ detection of high-speed penetration of celestial bodies, and discloses a small-sized separated penetrator, which comprises a planet soil penetration module and a star table detection module, and realizes autonomous separation in the impact penetration process, the star table module can realize star table detection and communication with an orbiter, the penetration module is internally provided with an energy storage device and an impact hammer, and can continue to penetrate and dive relying on the energy storage device after impact; the star table module is connected with the penetration module through flexible wires, and can supply power and signal transmission to the latter, the technology enables the penetrator with the modular characteristic to have the in-situ detection capability of planet soil profile, aims to expand the application mode of the penetrator for celestial body detection, and provides a scientific basis for the research of star table structures.

Description

Technical Field

[0001] This invention relates to the field of penetrator equipment technology, specifically a small, separate penetrator for in-situ planetary exploration. Background Technology

[0002] With the development of deep space exploration technology, impactors have become a research hotspot in recent years due to their low energy requirements and low cost. Traditional impactors embed themselves into celestial bodies through collisions to detect chemical composition, structural features, temperature changes, and other information below the surface. Impactors generate extremely high impact loads during the impact process. To ensure effective penetration to a certain depth into the measured medium and the efficient operation of the internal scientific payloads, internal protective design and optimization are necessary. Structural buffering technology is a particularly popular research direction.

[0003] For decades, penetrating probes have been successfully used in various terrestrial applications, but they have only flown twice as planetary exploration vehicles, and many planned penetrating probe missions have been cancelled at different stages of development. Regarding research on penetrating probe technology, to date, only the Mars penetrator from the China Academy of Space Technology and the lunar penetrator from the Shanghai Academy of Space Technology have relatively complete system designs in China.

[0004] Existing penetrators suffer from problems such as strong vibration, high impact, short detection time, shallow detection depth, and large mass. Therefore, this invention aims to design a small, separate penetrator for in-situ planetary exploration to solve these problems. Summary of the Invention

[0005] The purpose of this invention is to provide a small, separate penetrator for in-situ planetary exploration, in order to solve the problems mentioned in the background art, such as strong vibration, high impact, short detection time, shallow detection depth, and large mass of existing penetrators.

[0006] To achieve the above objectives, the present invention provides the following technical solution: a small, split-type penetrator for in-situ planetary exploration, comprising:

[0007] An aluminum honeycomb buffer module, comprising an outer protective shell and an aluminum honeycomb, wherein the aluminum honeycomb is located inside the outer protective shell;

[0008] An impact hammer and motor penetration module is installed on one side of an aluminum honeycomb buffer module. The impact hammer and motor penetration module includes an impact hammer and a drive shaft. The drive shaft is installed on one side of the impact hammer, and a motor is installed at the end of the drive shaft away from the impact hammer. The output end of the motor is fixedly connected to the drive shaft.

[0009] The upper and lower load chamber detection module is installed on the side of the impact hammer and motor penetration module away from the aluminum honeycomb buffer module. The upper and lower load chamber detection module includes a lower load chamber and an upper load chamber. The lower load chamber is installed on the outside of the motor, and the upper load chamber is installed on the end of the lower load chamber away from the impact hammer and motor penetration module.

[0010] A ground deceleration module is installed at the end of the upper load chamber away from the lower load chamber. The ground deceleration module includes a tail housing and a shock-absorbing spring. The tail housing is installed at the end of the upper load chamber away from the lower load chamber, and the shock-absorbing spring is installed at the bottom of the inner part of the tail housing.

[0011] Preferably, a protective outer shell is installed between the aluminum honeycomb buffer module and the ground deceleration module. The protective outer shell includes a columnar pin and a trapezoidal baffle. The columnar pin is provided on the outer side of the protective outer shell, and a trapezoidal baffle for use with the lower load chamber is installed on the outer side of the protective outer shell and on the side of the columnar pin.

[0012] Preferably, an energy storage spring is installed between the impact hammer and the upper and lower load chamber detection modules, and a shim is installed on one side of the energy storage spring. The shim and the ground deceleration module are both sleeved on the outside of the drive shaft.

[0013] Preferably, the lower load chamber is fixedly connected to the motor, an electrical cable is installed between the lower load chamber and the upper load chamber, and the end of the upper load chamber away from the lower load chamber is fixedly connected to the ground deceleration module.

[0014] Preferably, the tail housing is a multi-step cylindrical shape, one end of the shock-absorbing spring is fixedly connected to the tail housing, and the other end of the shock-absorbing spring is fixedly connected to the shock-absorbing cover.

[0015] Preferably, the outer protective shell has a hollow structure, the aluminum honeycomb is housed inside the outer protective shell, and a gap is left between the outer protective shell and the aluminum honeycomb.

[0016] Preferably, the outer side of the impact hammer is milled with a helical groove for use with a cylindrical pin, and the impact hammer, the motor penetration module, and the upper and lower load chamber detection modules are all located inside the protective outer shell.

[0017] Preferably, the tail housing and the protective outer housing are connected by resin bolts.

[0018] Preferably, a shock-absorbing cover is installed at the end of the shock-absorbing spring away from the tail housing, and a keyway is provided inside the impact hammer.

[0019] Preferably, a control chip is installed inside the aluminum honeycomb buffer module, and a wireless transceiver is installed outside the aluminum honeycomb buffer module. The wireless transceiver, the aluminum honeycomb buffer module, the impact hammer and motor penetration module, the upper and lower load chamber detection module, and the ground deceleration module are all electrically connected to the control chip.

[0020] Compared with existing technologies, the beneficial effects of this invention are as follows: This invention provides a small, separable penetrating probe for high-speed penetrating in-situ detection of planets, aiming to solve the problems of strong vibration, high impact, and short detection time during the impact of traditional penetrating probes. The penetrating probe includes a regolith penetrating module and a star surface detection module, which achieve autonomous separation during the impact penetration process. The star surface module can realize star surface detection and communication with the orbiter. The penetrating module has a built-in energy storage device and impact hammer, and can continue to penetrate and descend after impact by relying on the energy storage device. The star surface module is connected to the penetrating module through a flexible line, which can provide power and signal transmission to the latter. This technology enables the modular penetrating probe to have the capability of in-situ detection of regolith profiles, aiming to expand the application mode of planetary detection by penetrating probes and provide scientific basis for the study of star surface structures. Attached Figure Description

[0021] Figure 1 This is an exploded view of the overall structure of the present invention;

[0022] Figure 2 This is an exploded view of the aluminum honeycomb buffer module of the present invention;

[0023] Figure 3 This is an exploded view of the impact hammer and motor penetration module of the present invention;

[0024] Figure 4 Exploded view of the upper and lower load chamber modules of the present invention;

[0025] Figure 5 An exploded view of the surface deceleration module of the present invention;

[0026] Figure 6 This is a schematic diagram of the structure of the protective outer shell of the present invention;

[0027] Figure 7 This is a schematic diagram of the aluminum honeycomb structure of the present invention;

[0028] In the picture:

[0029] 1. Aluminum honeycomb buffer module; 11. Outer protective shell; 12. Aluminum honeycomb;

[0030] 2. Impact hammer and motor penetration module; 21. Impact hammer; 211. Keyway; 22. Drive shaft; 23. Shim; 24. Energy storage spring; 25. Motor;

[0031] 3. Upper and lower load chamber detection modules; 31. Lower load chamber; 32. Upper load chamber;

[0032] 4. Ground deceleration module; 41. Tail housing; 42. Shock-absorbing spring; 43. Shock-absorbing cover;

[0033] 5. Protective outer shell; 51. Columnar pin; 52. Trapezoidal baffle. Detailed Implementation

[0034] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0035] Please see Figure 1 and Figure 7 This invention provides a technical solution: a small, split-type penetrator for in-situ planetary exploration, comprising:

[0036] An aluminum honeycomb buffer module 1 includes an outer protective shell 11 and an aluminum honeycomb 12, wherein the aluminum honeycomb 12 is located inside the outer protective shell 11; the outer protective shell 11 has a hollow structure, and the aluminum honeycomb 12 is housed inside the outer protective shell 11 with a gap between the outer protective shell 11 and the aluminum honeycomb 12.

[0037] In this embodiment, during the collision process, the aluminum honeycomb 12 absorbs part of the kinetic energy from the impact hammer-motor penetration module 2 and the upper and lower load chamber detection module 3 through irreversible crushing deformation. The energy generated by the impact will gradually dissipate, and the instantaneous peak values ​​(stress and acceleration) will gradually decrease.

[0038] Please see Figure 1 , Figure 3 and Figure 7 This invention provides a technical solution: a small, split-type penetrator for in-situ planetary exploration, comprising:

[0039] Impact hammer and motor penetration module 2 is installed on one side of aluminum honeycomb buffer module 1. The impact hammer and motor penetration module 2 includes an impact hammer 21 and a drive shaft 22. The drive shaft 22 is installed on one side of the impact hammer 21. A motor 25 is installed at the end of the drive shaft 22 away from the impact hammer 21. The output end of the motor 25 is fixedly connected to the drive shaft 22. An energy storage spring 24 is installed between the impact hammer 21 and the upper and lower load chamber detection module 3. A shim 23 is installed on one side of the energy storage spring 24. The shim 23 and the ground deceleration module 4 are both sleeved on the outside of the drive shaft 22.

[0040] In this embodiment, the impact hammer 21 is a stepped cylindrical shape, which engages with the protective outer shell 5 via a cylindrical cam, keeping them relatively fixed during impact; its impact surface is the annular surface in the middle. The drive shaft 22 is clearance-fitted with the keyway 211 of the impact hammer 21, ensuring that the axial movement of the impact hammer is not affected when it strikes forward. The energy storage spring 24 is in a compressed state during the first impact on the star table, ensuring that the kinetic energy of the load is transferred to and absorbed by the aluminum honeycomb; a shim 23 is placed at its left end to reduce torsion.

[0041] Please see Figure 1 , Figure 4 and Figure 7 This invention provides a technical solution: a small, split-type penetrator for in-situ planetary exploration, comprising:

[0042] The upper and lower load chamber detection module 3 is installed on the side of the impact hammer and motor penetration module 2 away from the aluminum honeycomb buffer module 1. The upper and lower load chamber detection module 3 includes a lower load chamber 31 and an upper load chamber 32. The lower load chamber 31 is installed on the outside of the motor 25, and the upper load chamber 32 is installed at the end of the lower load chamber 31 away from the impact hammer and motor penetration module 2. The lower load chamber 31 is fixedly connected to the motor 25, and an electrical cable is installed between the lower load chamber 31 and the upper load chamber 32. The end of the upper load chamber 32 away from the lower load chamber 31 is fixedly connected to the ground deceleration module 4.

[0043] In this embodiment, the lower payload compartment 31 contains scientific payloads and tends to move forward upon the initial impact on the satellite surface. Its kinetic energy is absorbed by the energy storage spring 23 and the trapezoidal baffle 52, preventing relative movement with the protective outer shell 5. The upper payload compartment 32 contains communication devices and a power supply, and is fixedly connected to the ground deceleration module 4. After the initial impact, it remains on the satellite surface and releases electrical cables to connect with the lower payload compartment, providing energy for subsequent penetration and exploration.

[0044] Please see Figure 1 , Figure 3 , Figure 4 , Figure 6 and Figure 7 This invention provides a technical solution: a small, split-type penetrator for in-situ planetary exploration, comprising:

[0045] The surface deceleration module 4 is installed at the end of the upper load chamber 32 away from the lower load chamber 31. The surface deceleration module 4 includes a tail housing 41 and a shock-absorbing spring 42. The tail housing 41 is installed at the end of the upper load chamber 32 away from the lower load chamber 31. The shock-absorbing spring 42 is installed at the bottom of the interior of the tail housing 41. The tail housing 41 is in the shape of a multi-step cylindrical structure. One end of the shock-absorbing spring 42 is fixedly connected to the tail housing 41, and the other end of the shock-absorbing spring 42 is fixedly connected to the shock-absorbing cover 43. The shock-absorbing cover 43 is installed at the end of the shock-absorbing spring 42 away from the tail housing 41. The impact hammer 21 has a keyway 211 inside.

[0046] In this embodiment, the tail shell 41 is stepped to increase the penetration resistance and keep it on the star surface; when the shear stress is large enough, the resin bolts of the protective shell 5 break, causing the tail shell 41 to separate from the protective shell 5. The shock-absorbing spring 42 is in a stretched state during penetration, absorbing most of the kinetic energy of the upper load chamber 32, so that it does not move relative to the protective shell 5.

[0047] Please see Figures 1-7 ;

[0048] Furthermore, a protective outer shell 5 is installed between the aluminum honeycomb buffer module 1 and the ground deceleration module 4. The protective outer shell 5 includes a columnar pin 51 and a trapezoidal baffle 52. The columnar pin 51 is provided on the outer side of the protective outer shell 5. The trapezoidal baffle 52, which is used in conjunction with the lower load chamber 31, is installed on the outer side of the protective outer shell 5 and on one side of the columnar pin 51. The outer side of the impact hammer 21 is milled with a spiral groove that is used in conjunction with the columnar pin 51. The impact hammer, the motor penetration module 2, and the upper and lower load chamber detection modules 3 are all located inside the protective outer shell 5. The tail shell 41 is connected to the protective outer shell 5 by resin bolts.

[0049] Furthermore, a control chip is installed inside the aluminum honeycomb buffer module 1, and a wireless signal transceiver is installed outside the aluminum honeycomb buffer module 1. The wireless signal transceiver, aluminum honeycomb buffer module 1, impact hammer and motor penetration module 2, upper and lower load chamber detection module 3, and ground deceleration module 4 are all electrically connected to the control chip.

[0050] In this embodiment, the control chip is used in conjunction with normal data remote management and processing, and the protective housing 5 is installed to ensure normal overall connection and use.

[0051] Specifically, when using this invention, the specific functions that this invention can achieve include:

[0052] 1. Energy absorption and buffering of aluminum honeycomb 12: When the outer protective shell 11 contacts the star table, the penetrator begins to decelerate, and the impact hammer 21-motor 25 structure and the upper and lower load chamber structure move forward relative to the shell. At this time, the aluminum honeycomb 12 begins to be crushed, the shock-absorbing spring 42 is pulled up, and the energy storage spring 24 is compressed. At this time, a peak overload will occur. When the impact hammer 21 moves downward to the maximum depth, the aluminum honeycomb 12 is crushed to the limit, achieving maximum energy absorption.

[0053] II. Separation of the Surface Module: When the penetrator contacts the satellite surface, the resistance on the surface module increases. When the resin pin reaches its cutting limit, it is pulled apart, and the front and rear parts of the penetrator separate. The upper load chamber 32 releases the electrical circuits and remains on the satellite surface with the surface module. It no longer dives, reducing the kinetic energy required for subsequent penetration. At this time, a small overload peak will appear for the rear load.

[0054] III. Penetration and Submersion of Impact Hammer 21: This process consists of the following steps:

[0055] 1. Motor 25 starts, and impact hammer 21 is slowly lifted. During this process, due to the friction of the planetary surface soil, the penetrator as a whole does not move.

[0056] 2. After the impact hammer 21 is raised to the top, it is released instantly, accelerating the impact on the warhead module. Due to the large weight of the shell and the friction between the surface soil and the shell, the shell is displaced upward by a small amount. The impact force generated when impacting the warhead module is much greater than the soil friction force, and the penetrator as a whole is displaced downward by a large amount.

[0057] 3. Through continuous impact, the drill bit achieves drilling. The maximum drilling depth is reached when the underground pressure is too great, the friction between the soil and the outer shell equals the impact force of the outer shell when the impact hammer 21 strikes, or when the electrical cables are exhausted.

[0058] 4. After reaching the predetermined depth, motor 25 reverses slightly, locking the load chamber to facilitate the measurement of seismic data;

[0059] IV. Scientific payload detection: When the penetrator completes its descent, the scientific payload in the lower payload compartment 31 is powered by electrical cables released from the upper payload compartment 32, which remains on the surface, to carry out detection work.

[0060] This invention addresses the issue of high-speed penetrating in-situ planetary exploration by disclosing a small, separable penetrator technology. It aims to solve problems such as strong vibration, high impact, and short detection time during the impact process of traditional penetrators. The penetrator comprises a regolith penetration module and a surface exploration module, which autonomously separate during the impact penetration process. The surface module enables surface exploration and communication with the orbiter. The penetration module has a built-in energy storage device and an impact hammer 21, allowing it to continue penetrating and descending after impact, relying on the energy storage device. The surface module is connected to the penetration module via a flexible wire, providing power and signal transmission to the latter. This technology enables the modular penetrator to possess in-situ detection capabilities for regolith profiles, aiming to expand the application modes of planetary exploration using penetrators and provide scientific basis for the study of surface structures.

[0061] Those skilled in the art will clearly understand that, for the sake of convenience and brevity, the specific working processes of the devices, equipment, and modules described above can be referred to the corresponding processes in the foregoing method embodiments, and will not be repeated here.

[0062] In the embodiments provided in this application, it should be understood that the disclosed devices, systems, and methods can be implemented in other ways. For example, the system embodiments described above are merely illustrative; for instance, the division of modules is only a logical functional division, and in actual implementation, there may be other division methods. For example, multiple modules or units may be combined or integrated into another device, or some features may be ignored or not executed. Furthermore, the coupling or direct coupling or communication connection shown or discussed may be indirect coupling or communication connection through some interfaces, devices, or equipment, and may be electrical, mechanical, or other forms.

[0063] The modules serving as aluminum honeycomb buffers, impact hammers and motor penetration, upper and lower load chamber detection, and surface deceleration may or may not be physically separate. The components displayed as modules may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the units can be selected to achieve the purpose of this embodiment according to actual needs.

[0064] In addition, the functional modules in the various embodiments of the present invention can be integrated into one processing module, or each module can exist physically separately, or two or more modules can be integrated into one module.

[0065] The above are merely preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A small, split-type penetrator for in-situ planetary exploration, characterized in that, include: An aluminum honeycomb buffer module (1) includes an outer protective shell (11) and an aluminum honeycomb (12), wherein the aluminum honeycomb (12) is located inside the outer protective shell (11); Impact hammer and motor penetration module (2), the impact hammer and motor penetration module (2) is installed on one side of aluminum honeycomb buffer module (1), the impact hammer and motor penetration module (2) includes an impact hammer (21) and a drive shaft (22), the drive shaft (22) is installed on one side of the impact hammer (21), the motor (25) is installed at the end of the drive shaft (22) away from the impact hammer (21), and the output end of the motor (25) is fixedly connected to the drive shaft (22); The upper and lower load chamber detection module (3) is installed on the side of the impact hammer and motor penetration module (2) away from the aluminum honeycomb buffer module (1). The upper and lower load chamber detection module (3) includes a lower load chamber (31) and an upper load chamber (32). The lower load chamber (31) is installed on the outside of the motor (25). The upper load chamber (32) is installed at the end of the lower load chamber (31) away from the impact hammer and motor penetration module (2). A ground deceleration module (4) is installed at the end of the upper load chamber (32) away from the lower load chamber (31). The ground deceleration module (4) includes a tail housing (41) and a shock-absorbing spring (42). The tail housing (41) is installed at the end of the upper load chamber (32) away from the lower load chamber (31). The shock-absorbing spring (42) is installed at the bottom of the inside of the tail housing (41).

2. The small, split-type penetrator for in-situ planetary exploration according to claim 1, characterized in that: A protective outer shell (5) is also installed between the aluminum honeycomb buffer module (1) and the ground deceleration module (4). The protective outer shell (5) includes a columnar pin (51) and a trapezoidal baffle (52). The columnar pin (51) is provided on the outside of the protective outer shell (5). The trapezoidal baffle (52) for use with the lower load chamber (31) is installed on the outside of the protective outer shell (5) and on the side of the columnar pin (51).

3. The small, split-type penetrator for in-situ planetary exploration according to claim 1, characterized in that: An energy storage spring (24) is installed between the impact hammer (21) and the upper and lower load chamber detection module (3). A shim (23) is installed on one side of the energy storage spring (24). The shim (23) and the ground deceleration module (4) are both sleeved on the outside of the transmission shaft (22).

4. The small, split-type penetrator for in-situ planetary exploration according to claim 1, characterized in that: The lower load chamber (31) is fixedly connected to the motor (25), and an electrical cable is installed between the lower load chamber (31) and the upper load chamber (32). The end of the upper load chamber (32) away from the lower load chamber (31) is fixedly connected to the ground deceleration module (4).

5. The small, split-type penetrator for in-situ planetary exploration according to claim 1, characterized in that: The tail housing (41) is a multi-step cylindrical shape. One end of the shock-absorbing spring (42) is fixedly connected to the tail housing (41), and the other end of the shock-absorbing spring (42) is fixedly connected to the shock-absorbing cover (43).

6. The small, split-type penetrator for in-situ planetary exploration according to claim 1, characterized in that: The outer protective shell (11) has a hollow structure, and the aluminum honeycomb (12) is housed inside the outer protective shell (11) with a gap between the outer protective shell (11) and the aluminum honeycomb (12).

7. The small, split-type penetrator for in-situ planetary exploration according to claim 2, characterized in that: The impact hammer (21) has a spiral groove milled on its outer side to cooperate with the cylindrical pin (51). The impact hammer, the motor penetration module (2), and the upper and lower load chamber detection module (3) are all located inside the protective outer shell (5).

8. The small, split-type penetrator for in-situ planetary exploration according to claim 2, characterized in that: The tail housing (41) is connected to the protective outer housing (5) by resin bolts.

9. The small, split-type penetrator for in-situ planetary exploration according to claim 1, characterized in that: The shock-absorbing spring (42) is fitted with a shock-absorbing cover (43) at the end away from the tail housing (41), and the impact hammer (21) has a keyway (211) inside.

10. The small, split-type penetrator for in-situ planetary exploration according to claim 1, characterized in that: The aluminum honeycomb buffer module (1) has a control chip installed inside and a wireless signal transceiver installed outside. The wireless signal transceiver, aluminum honeycomb buffer module (1), impact hammer and motor penetration module (2), upper and lower load chamber detection module (3) and surface deceleration module (4) are all electrically connected to the control chip.

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