Calibration Chip for Closed Packaging Structure for In-orbit Analysis of Volatiles in Lunar Soil

Abstract

The present invention discloses a calibration chip for a closed encapsulation structure for in-orbit analysis of volatile substances in lunar soil, which relates to the field of aerospace technology, and solves the problems of opening and closing of passages in different scenarios, as well as the problems that in the existing calibration methods, sample contamination and leakage may occur under the impact during the launch, flight, and landing stages, affecting the analysis results, and the opening and closing of passages in different scenarios. The present invention includes a base, a gland, and a hot melt foil. The gland is installed on the base to form a calibration cavity; a plurality of air holes are provided on the gland, and the hot melt foil covers the air holes. After the hot melt foil is heated and melted, a gas passage is formed between the calibration cavity and the gland through the air holes. The present invention opens the air hole passage by means of induction heating and hot melting, effectively simplifies the structure of the calibration device, and makes the calibration process more accurate and efficient.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and specifically to a calibration chip with a closed encapsulation structure for on-orbit analysis of lunar soil volatiles. Background Art

[0002] Deep space exploration refers to the exploration activities carried out by humans on the moon and more distant celestial bodies or space environments. As an important direction of human space activities and an important way of space science and technology innovation, it is one of the development priorities in the current and future space fields. Deep space exploration is not only a reflection of a country's scientific and technological level, but also a reflection of its comprehensive national strength.

[0003] At present, the main target of human deep space exploration is the only natural satellite of the earth: the moon. The composition of lunar soil on the lunar surface is an important research direction in lunar exploration. However, in the process of in-situ detection of extraterrestrial celestial bodies, it is crucial to eliminate the error of the background in the instrument and the flight process on the detection results, and the calibration of the background needs to be completed in orbit. After the calibration chip is pre-filled with known solid samples on the ground, it needs to be sealed in an encapsulation with a specific configuration to ensure that the samples do not spill during the launch and flight of the detector. At the same time, after the calibration chip is heated in orbit, the volatiles generated inside the heated lunar soil need to be released so that measuring instruments such as mass spectrometers can complete the detection and analysis of the volatiles. Therefore, the calibration chip needs to meet the function of sample encapsulation and retention in the flight stage in terms of structure, and can form a gas passage after heating to realize the detection and analysis of volatile gases by the analysis instrument. Currently, no relevant research has been carried out in China, so it belongs to a new technology. Abroad, the calibration work for in-situ analysis of extraterrestrial celestial bodies has been carried out before, but its method is very different from the principle of the present invention. The foreign calibration method is to cover the sample cavity with soft metal, and the metal is punctured by the movement of the mechanism during work to make the internal gas escape. This method will cause sample pollution and leakage under the impact during the launch, flight, and landing stages, affecting the analysis results. Summary of the Invention

[0004] In order to solve the problem of opening and closing the passage in different scenarios, and the problem that the existing calibration method will cause sample pollution and leakage under the impact during the launch, flight, and landing stages, affecting the analysis results, the present invention hereby provides a calibration chip with a closed encapsulation structure for on-orbit analysis of lunar soil volatiles, which solves the problem of opening and closing the passage in different scenarios, and at the same time avoids the process of forming a gas passage by mechanical damage of the existing calibration method, reduces the overall mass of the device, fills the blank in the design of the calibration object loading structure during in-situ analysis of extraterrestrial celestial bodies in China, and has international advanced nature.

[0005] The present invention provides a calibration chip for a closed encapsulation structure for on-orbit analysis of lunar soil volatiles, which specifically includes a base, a gland, and a hot-melt foil. The gland is installed on the base to form a calibration cavity; several air holes are provided on the gland, and the hot-melt foil covers the air holes. After the hot-melt foil is heated and melted, a gas passage is formed between the calibration cavity and the gland through the air holes.

[0006] Furthermore, two limit blocks and two limit grooves are provided on the base, and the limit blocks and limit grooves cooperate with the calibration device to fix and drive the calibration chip.

[0007] Furthermore, the limit blocks are symmetrically arranged.

[0008] Furthermore, the limit groove is a wedge-shaped groove.

[0009] Furthermore, the base is provided with a first groove, and the gland is installed in the first groove.

[0010] Furthermore, the gland is provided with a second groove, and the second groove and the first groove are relatively buckled to form a calibration cavity.

[0011] Furthermore, several gland fixing pieces are also provided on the base, and the gland fixing pieces fix the gland.

[0012] Furthermore, the gland fixing pieces are evenly distributed on the base.

[0013] Furthermore, the hot-melt foil is an aluminum foil.

[0014] The beneficial effects of the calibration chip for the closed encapsulation structure for on-orbit analysis of lunar soil volatiles according to the present invention are as follows:

[0015] (1) For the calibration chip for the closed encapsulation structure for on-orbit analysis of lunar soil volatiles according to the present invention, the air hole channel is opened by the hot-melt method of induction heating. This part of the heat energy not only causes the volatiles in the calibration object to volatilize by heating, but also can melt the hot-melt foil to form a gas passage, solving the problem of opening and closing the passage in different scenarios and effectively improving the calibration efficiency;

[0016] (2) For the calibration chip for the closed encapsulation structure for on-orbit analysis of lunar soil volatiles according to the present invention, the air hole channel is opened by the hot-melt method, simplifying the structure of the calibration device and reducing the mass of the payload. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention.

[0018] In the drawings:

[0019] Figure 1 It is a schematic diagram of the overall structure of a calibration chip with a closed packaging structure for on-orbit analysis of lunar soil volatiles according to the present invention;

[0020] Figure 2 It is a schematic top view structure diagram of a calibration chip with a closed packaging structure for on-orbit analysis of lunar soil volatiles according to the present invention;

[0021] Figure 3 It is a calibration chip with a closed packaging structure for on-orbit analysis of lunar soil volatiles according to the present invention Figure 2 The schematic cross-sectional structure diagram at A-A in it;

[0022] Figure 4 It is a calibration chip with a closed packaging structure for on-orbit analysis of lunar soil volatiles according to the present invention Figure 3 The schematic diagram of the local structure in it;

[0023] Figure 5 It is a schematic diagram of the base structure of a calibration chip with a closed packaging structure for on-orbit analysis of lunar soil volatiles according to the present invention;

[0024] Figure 6 It is a schematic diagram of the gland structure of a calibration chip with a closed packaging structure for on-orbit analysis of lunar soil volatiles according to the present invention;

[0025] Wherein: 1-base, 2-gland, 3-thermal melting foil, 4-air hole, 5-limit block, 6-limit groove, 7-first groove, 8-gland fixing piece, 9-second groove. Specific embodiments

[0026] The following further details the specific embodiments of the present invention with reference to the accompanying drawings:

[0027] Specific embodiment one: Refer to Figures 1-6 This embodiment is described. A calibration chip with a closed packaging structure for on-orbit analysis of lunar soil volatiles described in this embodiment specifically includes a base 1, a gland 2 and a thermal melting foil 3. The gland 2 is installed on the base 1 to form a calibration cavity; a plurality of air holes 4 are provided on the gland 2, and the thermal melting foil 3 covers the air holes 4, so that a closed space is formed in the calibration chip before the heating operation. After the thermal melting foil 3 is heated and melted, a gas passage is formed between the calibration cavity and the gland 2 through the air holes 4, and the volatiles generated after the calibration substance in the calibration chip is heated can diffuse into the gas analysis instrument through this gas passage.

[0028] Two limit blocks 5 and two limit grooves 6 are provided on the base 1. The limit blocks 5 and the limit grooves 6 cooperate with the calibration device to realize the fixation and drive of the calibration chip. The limit blocks 5 are symmetrically arranged, and the limit grooves 6 are wedge-shaped grooves.

[0029] The base 1 is provided with a first groove 7, and the gland 2 is installed in the first groove 7.

[0030] The gland 2 is provided with a second groove 9, and the second groove 9 is relatively buckled with the first groove 7 to form a calibration cavity.

[0031] The base 1 is further provided with a plurality of gland fixing pieces 8, and the gland fixing pieces 8 fix the gland 2. The gland fixing pieces 8 are evenly distributed on the base 1. After the base 1 and the gland 2 are assembled, the gland fixing pieces 8 are bent and attached to the gland 2 to realize the fixation of the gland 2.

[0032] The hot-melt foil 3 is selected as aluminum foil, so that the hot-melt foil 3 can melt after the calibration piece is heated to a certain temperature, connecting the inside and the outside of the calibration piece, and at the same time, it will not affect the calibration analysis.

[0033] The specific use process of the above-mentioned calibration piece of the closed packaging structure for in-orbit analysis of lunar soil volatiles is explained as follows:

[0034] When in-situ testing and analysis are carried out on extraterrestrial celestial bodies, due to the influence of various gases on the payload during the flight stage and the ground transfer stage, it is necessary to use calibration substances to determine the degree of influence of these external influences for quantitative analysis. Therefore, on the ground, calibration substances with known compositions are pre-filled in the calibration piece. During the filling process of the calibration substances, first, the hot-melt foil 3 is loaded into the gland 2 and attached to the bottom of the second groove 9 in the gland 2 to completely cover the air hole 4, then the calibration substances are filled on the aluminum foil, compacted after being filled, and then the base 1 is buckled to the gland 2 to complete the packaging of the calibration substances, and then the calibration piece is turned back, and the filling of the calibration substances is completed.

[0035] When the calibration piece is brought to the surface of the planet, the calibration piece and the calibration substances filled inside the calibration piece are heated by means of induction heating. After being heated by the external alternating magnetic field induction, the wall surface of the calibration piece heats up. When the temperature rises to a certain degree, the hot-melt foil 3 melts to expose the covered air hole 4, making the inside and outside of the calibration piece communicate. At the same time, due to the induction heating method, the calibration piece heats the calibration substances inside. The volatile gases generated by the heated calibration substances diffuse through the air hole 4 to the analysis instrument. Finally, the measured analysis results are compared with the actual composition of the calibration substances, and the difference is the composition error of the payload background, that is, the composition error of the residual gases during the transfer process of the device. In the subsequent lunar soil heating analysis process, the payload background error can be taken into account to obtain a more accurate measurement result of the lunar soil composition.

[0036] Summarizing the above embodiments, for the calibration chip of the closed encapsulation structure for in-orbit analysis of lunar volatiles according to the present invention, the pore channels are opened by the hot melting method of induction heating. This part of the thermal energy not only causes the volatiles in the calibration object to volatilize by heating, but also can melt the hot melt foil 3 to form a gas passage, solving the problem of opening and closing the passage in different scenarios and effectively improving the calibration efficiency. For the calibration chip of the closed encapsulation structure for in-orbit analysis of lunar volatiles according to the present invention, the pore channels are opened by the hot melting method, simplifying the structure of the calibration device and reducing the mass of the payload.

[0037] In the specific embodiments described above, the purpose, technical solutions and beneficial effects of the present invention have been further described in detail. It should be understood that the above are only specific embodiments of the present invention and are not used to limit the invention. It can also be a reasonable combination of the features described in the above embodiments. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A calibration chip for a closed encapsulation structure for in-orbit analysis of lunar regolith volatiles, characterized in that: It includes a base (1), a gland (2) and a hot-melt foil (3). The gland (2) is installed on the base (1) to form a calibration cavity. A number of air holes (4) are provided on the gland (2), and the hot-melt foil (3) covers the air holes (4). After the hot-melt foil (3) is heated and melted, a gas passage is formed between the calibration cavity and the gland (2) through the air holes (4).

2. The calibration chip of the closed encapsulation structure for in-orbit analysis of stardust volatiles according to claim 1, wherein: Two limit blocks (5) and two limit grooves (6) are provided on the base (1), and the limit blocks (5) and the limit grooves (6) cooperate with the calibration device to limit and drive the calibration piece.

3. The calibration chip of the closed encapsulation structure for in-orbit analysis of stardust volatiles according to claim 2, characterized in that: The two limit blocks (5) are symmetrically arranged.

4. The calibration chip of the closed encapsulation structure for in-orbit analysis of stardust volatiles according to claim 3, wherein: The limit groove (6) is a wedge-shaped groove.

5. The calibration chip of the closed encapsulation structure for in-orbit analysis of stardust volatiles according to any one of claims 1, 2, 3 or 4, characterized in that: The base (1) is provided with a first groove (7), and the gland (2) is installed in the first groove (7).

6. The calibration chip of the closed encapsulation structure for in-orbit analysis of stardust volatiles according to claim 5, characterized in that: The gland (2) is provided with a second groove (9), and the second groove (9) and the first groove (7) are relatively buckled to form a calibration cavity.

7. The calibration chip of the closed encapsulation structure for in-orbit analysis of lunar soil volatiles according to any one of claims 1, 2, 3, 4 or 6, characterized in that: A number of gland fixing pieces (8) are also provided on the base (1), and the gland fixing pieces (8) fix the gland (2).

8. The calibration chip of the closed encapsulation structure for in-orbit analysis of stardust volatiles according to claim 7, characterized in that: The gland fixing pieces (8) are evenly distributed on the base (1).

9. The calibration chip of the closed encapsulation structure for in-orbit analysis of stardust volatiles according to any one of claims 1, 2, 3, 4, 6 or 8, characterized in that: The hot-melt foil (3) is an aluminum foil.

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