A device and method for detecting organic components in space dust

Abstract

The present invention discloses a detection device and method for organic components in space dust, the device includes a pyrolysis chamber and an electronics box connected end to end; a transparent window is provided between the pyrolysis chamber and the electronics box, and the front port thereof is provided with an openable and closable front cover plate, on which a silica aerogel plate is inlaid and installed; the electronics box is provided with: a macro magnification camera, an infrared laser unit, an infrared temperature measurement camera, a dual-comb spectrum unit, a main control unit, and a power supply unit. The present invention can effectively capture and collect dust or debris floating in space in the Earth's space orbit or in an environment where asteroids and other celestial bodies are close, and use a high-power infrared laser to heat the captured samples, so that the organic matter and water therein are decomposed and volatilized by heat, and then use a dual-comb spectrometer to carry out qualitative and quantitative analysis of the volatiles, so as to achieve high-precision, high-sensitivity, and high-resolution in-situ detection and analysis of space dust.

Description

Technical Field

[0001] The present invention relates to the fields of space dust detection, asteroid detection and deep space detection, and in particular to a device and method for detecting organic components in space dust. Background Art

[0002] There are a large number of interplanetary dust particles in the Earth's near-Earth orbit environment, which are formed by the collision, disintegration, fragmentation and evaporation of volatiles of small celestial bodies such as planets, their satellites, dust rings, asteroids and comets. These dust particles are transported to the Earth's near-Earth orbit through activities such as solar wind and meteors. Existing studies have found abundant organic matter in meteorites and comets. Although organic components and single-cell life cannot exist under strong ultraviolet radiation in space, if they are wrapped in interstellar dust particles, they are more likely to reach the Earth. Therefore, detecting organic matter in interstellar dust particles is crucial to understanding the origin of life on Earth.

[0003] At the international level, many remote sensing, in-situ measurement or sample return missions have been carried out on the moon, Mars, asteroids and other small celestial bodies. For example, NASA's Stardust probe carried aerogel and mass spectrometer to collect and detect dust from the Wild2 comet; Japan's "Tanpopo" experiment on the International Space Station used amorphous aerogel to collect interstellar dust particles. Due to the small volume of space dust and the small amount of sample captured, existing research has not yet carried out effective in-situ component detection of space dust. Technologies that have been used for deep space in-situ detection, such as visible / infrared imaging spectrometers, laser-induced breakdown spectrometers, Raman spectrometers, X-ray fluorescence / diffraction spectrometers and ultraviolet spectrometers, cannot simultaneously achieve high-resolution, high-sensitivity and high-speed detection of material components.

[0004] As a new type of precision measurement technology, dual-comb spectroscopy technology overcomes the limitations of traditional spectral spatial dispersion separation and mechanical scanning. It can achieve high-precision spectral measurement and has high resolution, high sensitivity and system stability. It can realize high temporal resolution and high spectral resolution in situ measurement of extraterrestrial organic matter.

[0005] Since the working principle of dual-comb spectroscopy technology relies on light transmission, and non-volatile solid organic compounds are opaque and usually do not exist in gaseous form, dual-comb spectroscopy methods cannot be directly applied to these substances.

[0006] Laser pyrolysis technology can be used to vaporize and decompose organic matter encased in space dust (micrometeorites, micrometeoroids and comet dust) into gaseous molecules for subsequent high-precision measurement of dual-comb spectroscopy. Laser pyrolysis is very suitable for space applications due to its precise control, high efficiency, no need for sample pretreatment and selective heating. By locally irradiating the sample with high-energy laser, volatile organic samples can be quickly vaporized, providing a powerful tool for understanding and exploring organic chemical components in space. Summary of the invention

[0007] The present invention provides a device and method for detecting organic components in space dust, which can realize effective in-situ detection of organic components in space dust.

[0008] The technical solution of the present invention is as follows:

[0009] A device for detecting organic components in space dust, comprising a pyrolysis chamber and an electronics box connected end to end;

[0010] The pyrolysis chamber is open at both ends, a transparent window is provided between the rear port and the electronic box, and a front cover that can be opened and closed is provided at the front port. When the front cover is closed, the pyrolysis chamber forms a closed space;

[0011] A silica aerogel plate for capturing dust particles is inlaid and installed on the side of the front cover plate facing the pyrolysis chamber;

[0012] The electronic box is provided with:

[0013] a macro magnification camera to obtain detailed images of dust particles captured by the silica aerogel plates;

[0014] The infrared laser unit heats the dust particles through infrared lasers, causing the organic components contained in the dust particles to decompose by heat;

[0015] Infrared temperature camera to monitor temperature changes of dust particles;

[0016] A dual-comb spectral unit, whose detection light output optical fiber and receiving optical fiber are respectively connected to the detection light inlet and outlet arranged on the two opposite side walls of the pyrolysis chamber, for obtaining the spectral information of the pyrolysis gas of the organic matter;

[0017] A main control unit communicates with the macro magnification camera, the infrared temperature measurement camera, the infrared laser unit, and the dual-comb spectroscopy unit and outputs corresponding control instructions, and has an inversion model, which classifies and quantitatively predicts the composition of the pyrolysis gas of the organic matter according to the spectral information obtained by the dual-comb spectroscopy unit;

[0018] The power supply unit provides electrical energy to the components in the electronics box.

[0019] The front cover is connected to the pyrolysis chamber through an electric rotating shaft, and is fixed by a door lock when the front cover is closed.

[0020] The silica aerogel sheet is optically transparent.

[0021] The detection device for the organic components of space dust of the present invention needs to be installed on the windward side of the orbit of a space station or a detection satellite. When collecting space dust, drive the electric shaft to slowly open the front cover of the pyrolysis chamber to 180°, which is approximately perpendicular to the direction of movement. Use the silica aerogel installed on the front cover to collect the impacting space dust. The silica aerogel has a low density, so that dust particles can collide with the inside of the aerogel and be preserved; the silica aerogel has a low thermal conductivity, good thermal insulation performance, and is optically transparent, which is very suitable for space applications.

[0022] Preferably, the density of the silica aerogel plate is ≤0.05 g / cm 3 ; Thermal conductivity ≤0.05W / mK.

[0023] The transparent window is made of a material with high transmittance to infrared light. Preferably, the transparent window is made of zinc selenide (ZnSe). Zinc selenide has excellent transmittance in the range of 0.5-22 μm and is widely used in infrared imaging systems, laser optical components (such as lenses, windows) and laser cutting machines.

[0024] Preferably, the center line of the infrared temperature measuring camera window passes through the symmetrical center point of the silica aerogel plate.

[0025] The infrared temperature measuring camera is installed at an angle relative to the transparent window. The performance parameters of the infrared temperature measuring camera are: spectral range 8-14μm, resolution at least 256×192, noise equivalent temperature difference <50mK, and maximum temperature measurement value ≥600℃.

[0026] Preferably, a two-dimensional displacement stage parallel to the front cover is provided in the electronics box, and the macro magnification camera and the infrared laser collimation output head of the infrared laser unit are installed on a slider of the two-dimensional displacement stage.

[0027] Furthermore, the movement range of the slider on the two-dimensional displacement stage is at least 100 mm×100 mm, and the repeatability accuracy is at least 0.1 mm.

[0028] The lens of the macro magnifying camera is 10 mm away from the transparent window and 50 mm away from the front cover of the pyrolysis chamber. The resolution of the macro magnifying camera is at least 560×560, the field of view is at least 15 mm×15 mm, and the closest focusing distance is about 50 mm.

[0029] The infrared laser unit is emitted through a multimode optical fiber and an infrared laser collimation output head, so that the focused light spot is irradiated on the sample for heating. The parameter indicators are wavelength of 1064nm, output power ≥1000mW, output laser divergence angle ≤20mrad, spot size of about 4mm, and power stability <3%.

[0030] The inner diameter of the multimode optical fiber is 400 μm.

[0031] The detection light inlet and outlet on the side wall of the pyrolysis chamber are used to connect to the fiber laser output of the dual-comb spectroscopy unit and receive the emitted laser, respectively. The detection light inlet and outlet are opposite to each other, so that the detection light entering from one side can be emitted from the other side to the receiving optical fiber.

[0032] Preferably, the detection light inlet and outlet interfaces are standard SMA905 interfaces.

[0033] Two optical frequency combs with slightly different repetition frequencies are used to form a dual-comb spectrometer system. The system parameters are as follows: spectral range 1500~1670nm, spectral resolution v ref =100MHz, single sampling time T=1ms, signal-to-noise ratio SNR=735 (total sampling 100s), sensitivity 100ppt.

[0034] The main control unit is an Aarch-Linux architecture development platform based on Rockchip RK3688 main control, with multiple communication interfaces such as GPIO, PWM, SPI, UART and USB to realize communication and control of various components.

[0035] The inversion model in the main control unit is trained by the spectral data of standard gas components.

[0036] The main control unit also includes a temperature-laser power closed-loop control circuit, which is used for closed-loop control of the temperature measured by the infrared temperature measuring camera and the laser power modulation of the infrared laser unit.

[0037] The temperature-laser power closed-loop control circuit adopts a PID algorithm to adjust the infrared laser output power of the infrared laser unit in real time according to the heating temperature of the dust particles, so that the temperature of the heated dust particles rises steadily to 550±10℃.

[0038] The present invention also provides a method for detecting organic components in space dust based on the detection device, comprising the following steps:

[0039] (1) Installing the detection device on the windward side of a space station or detection satellite in low-Earth orbit so that there is no obstruction in front of the detection device; opening the front cover to capture space dust using silica aerogel;

[0040] (2) Use a macro magnification camera to perform morphological observation and visual positioning of the captured dust particles;

[0041] (3) Use an infrared temperature camera to monitor the temperature changes of dust particles;

[0042] (4) Turn on the infrared laser unit and irradiate the captured dust particles with infrared laser to increase their temperature and stabilize it at 550±10°C;

[0043] (5) Turn on the dual-comb spectroscopy unit to monitor the gas composition produced by the thermal decomposition of dust particles in the pyrolysis chamber.

[0044] The present invention can effectively capture and collect dust or debris floating in space in the Earth's space orbit or in the environment of asteroids and other celestial bodies approaching, and use high-power infrared lasers to heat the captured samples, so that the organic matter and water therein are thermally decomposed and volatilized, and then use a dual-comb spectrometer to carry out qualitative and quantitative analysis of the volatiles. The present invention uses the high-precision, high-sensitivity, and high-resolution characteristics of the dual-comb spectrometer to detect the gas components produced by the thermal decomposition of dust particles and search for the characteristic gases produced by the thermal decomposition of organic matter related to life.

[0045] In step (1), the target capture sample is space dust particles rich in organic components such as carbonaceous micrometeorites or comet dust, and the particle diameter is 0.1 to 10 mm.

[0046] Step (2) comprises:

[0047] (2-1) driving the slider of the two-dimensional translation stage to move the macro-magnification camera to scan and photograph the silica aerogel plate containing the captured dust particles to obtain a high-resolution image thereof;

[0048] (2-2) The dust particles are separated from the silica aerogel plate background by threshold segmentation, and then the particle size and shape of the dust particles are obtained by edge detection method through boundary tracking;

[0049] (2-3) The real coordinate position of the dust particles relative to the macro magnification camera is obtained by transforming the pixel coordinates to the real relative camera coordinates.

[0050] In step (2-1), a macro magnifying camera is used to scan and photograph the silica aerogel plate in a row-by-row manner, and the photos are finally synthesized into a complete image to obtain a high-resolution image of the silica aerogel plate.

[0051] Step (3) includes: using an infrared temperature measuring camera to obtain the original infrared frame information of the current field of view, taking the average value of the pixel temperatures in the 3×3 area excluding the maximum and minimum pixels, and finding the highest temperature point in the field of view, which is the temperature of the heated dust particles.

[0052] In the present invention, the captured space dust samples are irradiated and heated using a 1064nm high-power infrared laser that has good penetration and heat absorption efficiency in most materials. The infrared laser passes through a multimode optical fiber and is emitted from a collimator at the end, so that the focused light spot is irradiated on the sample for heating.

[0053] In step (4), the infrared laser output power of the infrared laser unit is adjusted in real time according to the heating temperature of the dust particles, so that the temperature of the heated dust particles rises and stabilizes to 550±10°C.

[0054] At 550±10℃, the thermal decomposition of organic components in space dust may produce trace amounts of water, carbon dioxide, methane, ammonia and other organic-related gas molecules.

[0055] Afterwards, the dual-comb spectroscopy unit is turned on to achieve rapid acquisition of time-domain interferogram signals without a mechanical moving device to restore high-resolution broadband spectra.

[0056] The present invention is aimed at the capture of space dust and in-situ detection of organic components. A device and method for detecting organic components in space dust are designed to realize the collection of dust particles such as micrometeorites and comet dust floating in space in an on-orbit environment and the laser pyrolysis detection of their organic components, thereby providing a reference for the development of future on-orbit space dust capture and detection payloads.

[0057] Compared with the prior art, the present invention has the following beneficial effects:

[0058] The detection method of the present invention is mainly used for the capture and detection of space dust in the space environment. Using this method, dust or debris floating in space can be captured and collected in the Earth's space orbit or in the environment of asteroids and other celestial bodies approaching. The captured samples are heated by high-power infrared lasers to decompose and volatilize the organic matter and water therein. Then, a dual-comb spectrometer is used to carry out qualitative and quantitative analysis of the volatiles, thereby realizing high-precision, high-sensitivity, and high-resolution in-situ detection and analysis of space dust. BRIEF DESCRIPTION OF THE DRAWINGS

[0059] Figure 1 Axonometric view of a device for detecting organic components in space dust;

[0060] Figure 2 This is the front view of the schematic diagram of the detection device for organic components in space dust;

[0061] Figure 3 for Figure 2 A right view structural diagram of ;

[0062] Figure 4 for Figure 3 Middle AA section view;

[0063] Figure 5 for Figure 2 Middle DD section view. DETAILED DESCRIPTION

[0064] The present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be pointed out that the embodiments described below are intended to facilitate the understanding of the present invention and do not have any limiting effect on the present invention.

[0065] The present invention provides an embodiment of a device for detecting organic components of space dust, such as Figure 1-Figure 5 As shown, the detection device mainly includes two parts: a pyrolysis chamber 1 and an electronics box 2. The pyrolysis chamber mainly collects space dust, observes samples, heats samples, and allows detection light to enter and exit, thereby providing a closed space for space dust samples from capture to pyrolysis detection. The electronics box 2 mainly provides infrared lasers for heating, detection light for a dual-comb spectrometer, and drive control functions for each component.

[0066] The pyrolysis chamber 1 has a rotatable front cover 3 on the front of the pyrolysis chamber 1, which can ensure that the internal cabin space is in a completely sealed state when closed; the front cover 3 is connected to the pyrolysis chamber 1 through an electric shaft 5; the front cover 3 is fixed by a door lock 6 when closed; eight low-density silica aerogel plates 4 are inlaid and installed on the front cover 3 to capture space dust particles such as micrometeors and comet dust that come from impact; on both sides of the pyrolysis chamber 1 are the inlet and outlet 7 of the dual light comb detection light; the other bottom surface of the pyrolysis chamber 1 opposite to the front cover 3 is a high-transmittance window 8, which is made of a material with high transmittance to infrared light.

[0067] In this embodiment, 8 40×40×15 mm slots are cut out on the front cover plate 3 of the pyrolysis chamber for storing the silica aerogel plates 4. The thickness of the silica aerogel plates 4 is 15 mm and the density is 0.03 g / cm 3 , thermal conductivity is 0.02W / mK, optically transparent. The dual-comb detection light inlet and outlet 7 interfaces on both sides are standard SMA905 interfaces, which are used to access the fiber laser output of the dual-comb spectrometer. The two inlets and outlets are opposite, so that the detection light entering from one side can be emitted into the optical fiber from the other side. The material of the high-transmittance window 8 is zinc selenide (ZnSe), which has excellent transmittance in the range of 0.5-22μm and is widely used in infrared imaging systems, laser optical components (such as lenses, windows) and laser cutting machines.

[0068] The electronics box 2 has an infrared temperature measuring camera 9 outside the high-transmittance window 8; next to the high-transmittance window are a macro magnification camera 10 and an infrared laser collimation output head 11; the macro magnification camera 10 and the infrared laser collimation output head 11 are both installed on a two-dimensional translation stage 12; the two-dimensional translation stage 12 is installed on an electronics box partition 20 of the electronics box 2; the infrared laser 13, the laser driving module 14 and the translation stage driving module 15 are installed on the back of the electronics box partition 20 on which the two-dimensional translation stage 12 is installed; the main control module 16, the power module 17 and the dual-comb spectrometer electronics module 18 and the optical module 19 are installed on the other electronics box partition 20.

[0069] In this embodiment, the infrared temperature measuring camera 9 is installed at an angle relative to the high-transmittance window 8, so that the center line of the camera window can be extended through the symmetrical center point of the eight silica aerogel plates 4 installed on the front cover plate 3 of the pyrolysis chamber. The performance parameters of the infrared temperature measuring camera 9 are: spectral range 8-14μm, resolution 256×192, noise equivalent temperature difference <50mK, and maximum temperature measurement value 600℃. The macro magnifying camera 10 and the infrared laser collimating output head 11 are both installed on the slider of the two-dimensional displacement stage 12 through mounting parts. The motion range of the two-dimensional displacement stage 12 is 100×100mm, and the repeatability positioning accuracy is better than 0.1mm; wherein the lens of the macro magnifying camera 10 is 10mm away from the high-transmittance window 8 and 50mm away from the front cover plate 3 of the pyrolysis chamber. The resolution of the macro magnifying camera 10 should be 560×560, the field of view range is 15mm×15mm, and the closest focusing distance is about 50mm. The infrared laser is emitted from the infrared laser collimation output head 11 through a multimode optical fiber with an inner diameter of 400μm, so that the focused spot is irradiated on the sample for heating. The parameter indicators are wavelength of 1064nm, output power>1000mW, output laser divergence angle<20mrad, spot size of about 4mm, and power stability<3%. Two sets of optical frequency combs with slightly different repetition frequencies are used to form a dual-comb spectrometer system. The system parameters are as follows: spectral range 1500~1670nm, spectral resolution v ref =100MHz, single sampling time T=1ms, signal-to-noise ratio SNR=735 (total sampling 100s), sensitivity 100ppt. The main control module 16 is an Aarch-Linux architecture development platform based on Rockchip RK3688 main control, with GPIO, PWM, SPI, UART and USB and other communication interfaces for communication and control of various components.

[0070] The present invention also provides an embodiment of a method for detecting organic components in space dust, and the specific implementation methods are as follows:

[0071] 1) The space dust organic component detection device is carried inside a spacecraft or satellite to the space orbit environment, and then the astronauts or space robotic arms install the device on the windward side of the space station or the detection satellite's trajectory. The device is installed in a location without any obstructions, and the front cover 3 of the pyrolysis chamber is likely to be perpendicular to the current running direction to obtain the maximum capture rate of the target sample. The target capture sample is space dust particles rich in organic components such as carbonaceous micrometeorites or comet dust, with a particle diameter of 0.1 to 10 mm.

[0072] 2) Drive the electric shaft 5 to slowly open the front cover 3 of the pyrolysis chamber to 180°, approximately perpendicular to the direction of movement. Use the silica aerogel 4 installed on the front cover to collect the space dust that hits. The density of the aerogel is ≤0.03g / cm 3 , so that dust particles can hit the inside of the aerogel and be preserved. In addition, the excellent thermal insulation performance of aerogel, with a thermal conductivity of ≤0.02W / mK, and the optical transparency are very suitable for space applications.

[0073] 3) Keep the pyrolysis chamber front cover 3 open until the capture mission is completed. Drive the electric shaft 5 again to close the pyrolysis chamber front cover 3 and the door lock 6 to ensure that the pyrolysis chamber 1 is a completely closed environment after closing.

[0074] 4) The two-dimensional translation stage 12 is driven by the main control module 16 and the translation stage driving module 15, so that the macro magnification camera 10 installed on the slider of the two-dimensional translation stage can move in the plane, so as to scan and photograph the silica aerogel 4 installed on the front cover plate 3 of the pyrolysis chamber in a row-first-then-column manner, and the actual area captured by each photo is 15mm×15mm. Finally, all the photos are stitched to obtain detailed images of the space dust particles captured by the silica aerogel 4 with extremely high resolution.

[0075] 5) Based on the high-resolution image of space dust, the particles are separated from the silica aerogel plate background by threshold segmentation, and then the particle size and shape are obtained by boundary tracking using the edge detection method of the Canny operator. The space dust particles with a diameter greater than 0.1 mm are counted, and the real coordinate position of the particles relative to the macro magnification camera 10 is obtained after the pixel coordinates are transformed into the real relative camera coordinates. The two-dimensional translation stage 12 is driven so that the center of the infrared laser collimation output head 11 is aligned with the space dust particle sample position.

[0076] 6) Turn on the infrared laser 13 and its laser driver module 14, wherein the laser driver module 14 is adjusted to the minimum power output so that the sample can be heated slowly. Turn on the infrared temperature measuring camera 9, which obtains the original infrared frame information of the current field of view, and takes the average value of the pixel temperature in the 3×3 area except for the maximum and minimum in turn, and finds the highest temperature point in the field of view, that is, the temperature of the heated sample point, to obtain the heated temperature of the sample under the current condition. During the heating process, the closed-loop control of temperature detection-laser power modulation adopts the PID algorithm to adjust the output power of the infrared laser 13 in real time, so that the temperature of the heated sample slowly rises to 550±10℃. The organic components contained in the space dust are decomposed by heat to release gas molecules such as water (H2O), carbon dioxide (CO2), methane (CH4) and ammonia (NH3).

[0077] 7) The temperature of the heated sample point is stabilized at 550±10℃, and the optical module 19 and the electronic module 18 of the dual-comb spectrometer are turned on, so that the detection light of the dual-comb enters from the detection light inlet and outlet 7 on both sides of the pyrolysis chamber 1. The detection principle is as follows: The dual-comb spectral detection technology requires two optical combs, Comb 1 (detection comb) and Comb 2 (reference comb). Assume that the zero frequency f of the two optical combs is ceo The positions are the same, then the comb teeth in the frequency domain can be expressed as

[0078] f S =Nf rS +f ceo (1)

[0079] f L =Nf LS +f ceo (2)

[0080] Among them, f S and f L represent the optical comb tooth frequencies of the detection comb and the reference comb, respectively, N is the number of longitudinal modes, and f rS and f rL represent the comb tooth spacing of the two optical combs, f ceo The teeth of the two optical combs are offset in frequency.

[0081] After heterodyning, the two optical combs can generate an interference pattern, which reflects the frequency difference between the detection comb and the reference comb. The detection comb and the reference comb generate equally spaced pulse signals, with the interval time being and Since the repetition frequency f of the two optical combs "S and f "& have tiny differences, resulting in a slight time misalignment between their pulses.

[0082] When the pulse signals of the two optical combs are mixed by heterodyning, the interference signal will generate periodic modulation in the time domain. The modulation period in the interference pattern is the difference Δf between the repetition frequencies of the two optical combs. r =f rS -f rL The time interval of the modulation signal is That is, the modulation period of the interference pattern is much longer than the pulse interval of a single optical comb.

[0083] Dual-comb heterodyne beat frequency detection converts optical frequency information to radio frequency. The corresponding conversion factor K can be expressed in the time domain as

[0084] K=T S / ΔT=T & / ΔT-1 (4)

[0085] Among them, T S and T & are the time intervals between adjacent pulses of the detection comb and the reference comb in the time domain, and T & =T S +ΔT.

[0086] In the frequency domain, the conversion factor K can be expressed as

[0087] K=f "& / Δf " =f "S / Δf " -1 (5)

[0088] In addition, the Nyquist sampling theorem limits the sampling width. Therefore, in order to avoid confusion of heterodyne beat frequency signals in the frequency domain, the detection comb and the reference comb need to be filtered. The filtering bandwidth needs to meet

[0089] Δv / K≤f "& / 2 (6)

[0090] Substituting formula (5) into formula (6),

[0091]

[0092] The detection comb and reference comb are filtered separately. The detection comb will pass through the sample to be tested and carry the sample information. Then, it will perform heterodyne beat frequency detection with the reference comb, which can convert the optical frequency information to the RF comb teeth in the RF domain for detection. The RF comb can obtain the corresponding optical frequency information by multiplying the conversion factor of the dual optical comb, and then obtain the spectral information of the sample by inversion.

[0093] 8) Repeat the above pyrolysis detection process for samples of space dust particles with a particle size greater than 0.1 mm. Finally, use the inversion model trained on the ground using standard gas component spectrum data to classify and quantitatively predict the pyrolysis gas composition on orbit, and look for signature gas components related to life.

[0094] The embodiments described above provide a detailed description of the technical solutions and beneficial effects of the present invention. It should be understood that the above are only specific embodiments of the present invention and are not intended to limit the present invention. Any modifications, supplements and equivalent substitutions made within the scope of the principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A device for detecting organic components in space dust, characterized in that: It includes a pyrolysis chamber and an electronics box connected end to end; The pyrolysis chamber is open at both ends, a transparent window is provided between the rear port and the electronic box, and a front cover that can be opened and closed is provided at the front port. When the front cover is closed, the pyrolysis chamber forms a closed space; A silica aerogel plate for capturing dust particles is inlaid and installed on the side of the front cover plate facing the pyrolysis chamber; The electronic box is provided with: a macro magnification camera to obtain detailed images of dust particles captured by the silica aerogel plates; The infrared laser unit heats the dust particles through infrared lasers, causing the organic components contained in the dust particles to decompose by heat; Infrared temperature camera to monitor temperature changes of dust particles; A dual-comb spectral unit, whose detection light output optical fiber and receiving optical fiber are respectively connected to the detection light inlet and outlet arranged on the two opposite side walls of the pyrolysis chamber, for obtaining the spectral information of the pyrolysis gas of the organic matter; A main control unit communicates with the macro magnification camera, the infrared temperature measurement camera, the infrared laser unit, and the dual-comb spectroscopy unit and outputs corresponding control instructions, and has an inversion model, which classifies and quantitatively predicts the composition of the pyrolysis gas of the organic matter according to the spectral information obtained by the dual-comb spectroscopy unit; The power supply unit provides electrical energy to the components in the electronics box.

2. The device for detecting organic components in space dust according to claim 1, characterized in that: The front cover is connected to the pyrolysis chamber through an electric rotating shaft, and is fixed by a door lock when the front cover is closed.

3. The device for detecting organic components in space dust according to claim 1, characterized in that: The density of the silica aerogel plate is ≤0.05g / cm 3 ; Thermal conductivity ≤0.05W / mK.

4. The device for detecting organic components in space dust according to claim 1, characterized in that: A two-dimensional displacement stage parallel to the front cover is arranged in the electronics box, and the macro magnification camera and the infrared laser collimation output head of the infrared laser unit are installed on a slider of the two-dimensional displacement stage.

5. The device for detecting organic components in space dust according to claim 1, characterized in that: The inversion model in the main control unit is trained by the spectral data of standard gas components.

6. The device for detecting organic components in space dust according to claim 1, characterized in that: The main control unit also includes a temperature-laser power closed-loop control circuit, which is used for closed-loop control of the temperature measured by the infrared temperature measuring camera and the laser power modulation of the infrared laser unit.

7. A method for detecting organic components in space dust based on the detection device according to any one of claims 1 to 6, characterized in that: The following steps are involved: (1) The detection device is installed on the windward side of a space station or a detection satellite in a low-Earth orbit so that there is no obstruction in front of the detection device; Open the front cover to capture space dust using silica aerogel; (2) Use a macro magnification camera to perform morphological observation and visual positioning of the captured dust particles; (3) Use an infrared temperature camera to monitor the temperature changes of dust particles; (4) Turn on the infrared laser unit and irradiate the captured dust particles with infrared laser to increase their temperature and stabilize it at 550±10°C; (5) Turn on the dual-comb spectroscopy unit to monitor the gas composition produced by the thermal decomposition of dust particles in the pyrolysis chamber.

8. The method according to claim 7, characterized in that Step (2) comprises: (2-1) driving the slider of the two-dimensional translation stage to move the macro-magnification camera to scan and photograph the silica aerogel plate containing the captured dust particles to obtain a high-resolution image thereof; (2-2) The dust particles are separated from the silica aerogel plate background by threshold segmentation, and then the particle size and shape of the dust particles are obtained by edge detection method through boundary tracking; (2-3) The real coordinate position of the dust particles relative to the macro magnification camera is obtained by transforming the pixel coordinates to the real relative camera coordinates.

9. The method according to claim 7, characterized in that: Step (3) includes: using an infrared temperature measuring camera to obtain the original infrared frame information of the current field of view, taking the average value of the pixel temperatures in the 3×3 area excluding the maximum and minimum pixels, and finding the highest temperature point in the field of view, which is the temperature of the heated dust particles.

10. The method according to claim 7, characterized in that In step (4), the infrared laser output power of the infrared laser unit is adjusted in real time according to the heating temperature of the dust particles, so that the temperature of the heated dust particles rises and stabilizes to 550±10°C.

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