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CN-116986023-B - Small-size disconnect-type penetrator towards planet normal position detection

CN116986023BCN 116986023 BCN116986023 BCN 116986023BCN-116986023-B

Abstract

The invention discloses a small-sized separated penetrator for in-situ detection of a planet, which relates to the technical field of penetrator equipment and comprises an aluminum honeycomb buffer module, wherein the aluminum honeycomb buffer module comprises an external protective shell and an aluminum honeycomb, and the beneficial effects of the invention are as follows: the invention provides a high-speed penetration type in-situ detection for a planet, and discloses a small-sized separation type penetrator, which comprises a star soil penetration module and a star meter detection module, wherein autonomous separation is realized in the impact penetration process, the star meter module can realize star meter detection and communication with a track device, an energy storage device and an impact hammer are arranged in the penetration module, and penetration can be carried out by means of the energy storage device continuously after impact; the star meter module is connected with the penetration module through a flexible wire, and can supply power and transmit signals for the latter, so that the penetrator with modularized characteristics has the in-situ detection capability of the star soil profile, the star detection application mode of the penetrator is expanded, and scientific basis is provided for the research of the star meter structure.

Inventors

  • WANG JINGYUAN
  • FU ZHUORAN
  • WANG ZIHAN
  • HUANG HAN

Assignees

  • 南京航空航天大学

Dates

Publication Date
20260508
Application Date
20230829

Claims (10)

  1. 1. A small split penetrator for in situ satellite detection comprising: an aluminum honeycomb buffer module (1), wherein the aluminum honeycomb buffer module (1) comprises an outer protection shell (11) and an aluminum honeycomb (12), and the aluminum honeycomb (12) is positioned inside the outer protection shell (11); The impact hammer and motor penetration module (2), the impact hammer and motor penetration module (2) is arranged on one side of the aluminum honeycomb buffer module (1), the impact hammer and motor penetration module (2) comprises an impact hammer (21) and a transmission shaft (22), the transmission shaft (22) is arranged on one side of the impact hammer (21), a motor (25) is arranged at one end, far away from the impact hammer (21), of the transmission shaft (22), and the output end of the motor (25) is fixedly connected with the transmission shaft (22); The upper load cabin detection module (3), the lower load cabin detection module (3) is arranged on one side of the impact hammer and motor penetration module (2) away from the aluminum honeycomb buffer module (1), the upper load cabin detection module (3) comprises a lower load cabin (31) and an upper load cabin (32), the lower load cabin (31) is arranged on the outer side of the motor (25), and the upper load cabin (32) is arranged on one end of the lower load cabin (31) away from the impact hammer and motor penetration module (2); The ground surface speed reducing module (4), the ground surface speed reducing module (4) is installed in the upper portion load cabin (32) and keeps away from the one end of lower part load cabin (31), ground surface speed reducing module (4) include afterbody casing (41) and damping spring (42), afterbody casing (41) is installed in the one end that lower part load cabin (31) was kept away from in upper portion load cabin (32), damping spring (42) are installed to the inside bottom of afterbody casing (41).
  2. 2. The small-sized separated penetrator for in-situ satellite detection according to claim 1, wherein a protective housing shell (5) is further installed between the aluminum honeycomb buffer module (1) and the ground surface speed reduction module (4), the protective housing shell (5) comprises a cylindrical pin (51) and a tread baffle (52), the cylindrical pin (51) is arranged on the outer side of the protective housing shell (5), and the tread baffle (52) matched with the lower load cabin (31) is installed on the outer side of the protective housing shell (5) and located on one side of the cylindrical pin (51).
  3. 3. The small-sized separated penetrator for in-situ satellite detection according to claim 1, wherein an energy storage spring (24) is arranged between the impact hammer (21) and the upper and lower load cabin detection modules (3), a gasket (23) is arranged on one side of the energy storage spring (24), and the gasket (23) and the ground surface speed reduction module (4) are sleeved on the outer side of the transmission shaft (22).
  4. 4. The small-sized split type penetrator for in-situ satellite exploration according to claim 1, wherein the lower load compartment (31) is fixedly connected with the motor (25), an electric cable is installed between the lower load compartment (31) and the upper load compartment (32), and one end of the upper load compartment (32) far away from the lower load compartment (31) is fixedly connected with the ground surface speed reducing module (4).
  5. 5. The small-sized split type penetrator for in-situ satellite detection according to claim 1, wherein the tail housing (41) is in a multi-step cylindrical shape, one end of the damping spring (42) is fixedly connected with the tail housing (41), and the other end of the damping spring (42) is fixedly connected with the damping cover (43).
  6. 6. The small-sized split penetrator for in-situ satellite exploration according to claim 1, wherein the outer protective shell (11) has a hollow structure, the aluminum honeycomb (12) is accommodated inside the outer protective shell (11), and a gap is left between the outer protective shell (11) and the aluminum honeycomb (12).
  7. 7. The small-sized separated penetrator for in-situ satellite detection according to claim 2, wherein a spiral groove matched with a cylindrical pin (51) is milled on the outer side of the impact hammer (21), and the impact hammer, the motor penetration module (2) and the upper and lower load compartment detection modules (3) are both positioned in the protective shell (5).
  8. 8. A small-sized separation type penetrator for in-situ satellite exploration according to claim 2, wherein the tail housing (41) is connected with the protective housing (5) through a resin bolt.
  9. 9. The small-sized separated penetrator for in-situ satellite detection according to claim 1, wherein a shock absorbing cover (43) is mounted at one end of the shock absorbing spring (42) far away from the tail shell (41), and a key slot (211) is formed in the impact hammer (21).
  10. 10. The small separated penetrator for in-situ detection of the planet of claim 1, wherein a control chip is arranged in the aluminum honeycomb buffer module (1), a wireless signal transceiver is arranged outside the aluminum honeycomb buffer module (1), and the wireless signal transceiver, the aluminum honeycomb buffer module (1), an impact hammer and motor penetration module (2), an upper load cabin detection module (3), a lower load cabin detection module (4) and a ground surface deceleration module are all electrically connected with the control chip.

Description

Small-size disconnect-type penetrator towards planet normal position detection Technical Field The invention relates to the technical field of penetrator equipment, in particular to a small-sized separated penetrator for in-situ detection of stars. Background With the development of deep space exploration technology, penetrators have become popular in recent years due to their low energy requirements and low cost. Conventional impact penetrators are embedded within the celestial body in the form of an impact for detecting chemical composition, structural characteristics, temperature changes, etc. below the surface of the celestial body. The penetrator can generate extremely high impact load in the impact process, and in order to enable the penetrator to effectively penetrate a tested medium to a certain depth and ensure that the internal scientific load can effectively work, the protection design and optimization of the internal part of the penetrator are required. The structure buffering technology is a popular research direction. Penetration testing has been successful for many decades for a variety of ground applications, but has been flown only twice as a planetary testing vehicle, many of the planned penetrator testing tasks being cancelled at different stages of development. For the research of penetration technology of penetrators, only Mars penetrators of China space technology institute and lunar penetrators of Shanghai space technology institute have system schemes perfected in China so far. The penetrator in the prior art has the problems of strong vibration, high impact, short detection time, shallow detection depth, large mass and the like, so the invention needs to design a small separated penetrator for in-situ detection of the planet to solve the problems. Disclosure of Invention The invention aims to provide a small-sized separated penetrator for in-situ detection of a planet, which aims to solve the problems of strong vibration, high impact, short detection time, shallow detection depth, large quality and the like of the penetrator in the prior art. In order to achieve the purpose, the invention provides the following technical scheme that the small-sized separated penetrator for in-situ detection of the planet comprises the following components: the aluminum honeycomb buffer module comprises an outer protective shell and an aluminum honeycomb, wherein the aluminum honeycomb is positioned in the outer protective shell; The device comprises an impact hammer and motor penetration module, wherein the impact hammer and motor penetration module is arranged on one side of an aluminum honeycomb buffer module, the impact hammer and motor penetration module comprises an impact hammer and a transmission shaft, the transmission shaft is arranged on one side of the impact hammer, a motor is arranged at one end, far away from the impact hammer, of the transmission shaft, and the output end of the motor is fixedly connected with the transmission shaft; the upper load cabin detection module and the lower load cabin detection module are arranged on one side, far away from the aluminum honeycomb buffer module, of the impact hammer and the motor penetration module, the upper load cabin detection module and the lower load cabin detection module comprise a lower load cabin and an upper load cabin, the lower load cabin is arranged on the outer side of the motor, and the upper load cabin is arranged on one end, far away from the impact hammer and the motor penetration module, of the lower load cabin; The ground surface speed reducing module is arranged at one end, far away from the lower load cabin, of the upper load cabin and comprises a tail shell and a damping spring, the tail shell is arranged at one end, far away from the lower load cabin, of the upper load cabin, and the damping spring is arranged at the bottom end of the tail shell. Preferably, a protective shell is further installed between the aluminum honeycomb buffer module and the ground surface speed reduction module, the protective shell comprises a cylindrical pin and a tread baffle, the cylindrical pin is arranged on the outer side of the protective shell, and the tread baffle matched with the lower load cabin is installed on the outer side of the protective shell and positioned on one side of the cylindrical pin. Preferably, an energy storage spring is arranged between the impact hammer and the upper and lower load cabin detection modules, a gasket is arranged on one side of the energy storage spring, and the gasket and the ground surface speed reduction module are both sleeved on the outer side of the transmission shaft. Preferably, the lower load cabin is fixedly connected with the motor, an electric cable is arranged between the lower load cabin and the upper load cabin, and one end, far away from the lower load cabin, of the upper load cabin is fixedly connected with the ground surface speed reducing module. Preferably, the tail shell is cy