A 2U space dust sampling CubeSat and sampling method

Abstract

This invention relates to a 2U space dust sampling cubesat and sampling method. The 2U space dust sampling cubesat includes a 2U shell structure, a transparent fixed baffle, a cover plate driving unit, a camera, a lens, an aerogel collection material, a light source, an attitude adjustment component, and an onboard component. The transparent fixed baffle is disposed inside the 2U shell structure and is arranged perpendicular to the length direction of the 2U shell structure. The transparent fixed baffle divides the internal space of the 2U shell structure into a first assembly space and a second assembly space arranged front and rear. The aerogel collection material, attitude adjustment component, and light source are installed in the first assembly space. The cover plate driving unit, camera, lens, and onboard component are installed in the second assembly space. The lens is located in front of the camera and is arranged directly opposite the transparent fixed baffle. The aerogel collection material is located behind the light source and is arranged directly opposite the transparent fixed baffle and lens. A telescopic cover plate is provided on the upper side of the 2U shell structure at a position corresponding to the first assembly space.

Description

Technical Field

[0001] This invention relates to the field of space dust sampling technology, specifically to a 2U space dust sampling cubesat and sampling method. Background Technology

[0002] CubeSats are widely used in space missions due to their small size, light weight, low power consumption, and high degree of autonomy. Furthermore, space dust collection and analysis payloads provide crucial information about the solar system, and in-situ sampling of dust particles supports the acquisition of material information about the origin of debris. However, existing CubeSats are large and heavy, and their dust collection missions are complex to design. Summary of the Invention

[0003] In order to solve one or more technical problems existing in the prior art, the present invention provides a 2U space dust sampling cubesat and sampling method.

[0004] The technical solution of the present invention to solve the above-mentioned technical problems is as follows: A 2U space dust sampling cubesat includes a 2U shell structure, a transparent fixed baffle, a cover plate driving part, a camera, a lens, an aerogel collection material, a light source, an attitude adjustment component, and an onboard component. The transparent fixed baffle is disposed inside the 2U shell structure and is arranged perpendicular to the length direction of the 2U shell structure. The transparent fixed baffle divides the internal space of the 2U shell structure into a first assembly space and a second assembly space arranged front and rear. The aerogel collection material, the attitude adjustment component, and the light source are installed in the first assembly space. The cover plate driving part, the camera, the lens, and the onboard component are installed in the second assembly space. The lens is located in front of the camera and is arranged directly opposite the transparent fixed baffle. The aerogel collection material is located behind the light source and is arranged directly opposite the transparent fixed baffle and the lens. A telescopic cover plate is provided on the upper side of the 2U shell structure at a position corresponding to the first assembly space. The cover plate driving part is connected to the inner side of the telescopic cover plate and drives the telescopic cover plate to expose or cover the aerogel collection material.

[0005] The beneficial effects of this invention are as follows: The 2U space dust sampling CubeSat of this invention utilizes the unique porous structure and ultralight mass of aerogel to effectively capture tiny particles, making the CubeSat highly efficient and accurate in collecting space dust. The CubeSat of this invention, through a rationally designed spatial layout, has a small platform size and simple structure, which reduces launch difficulty, shortens the development cycle, and lowers the cost of space dust collection experiments. The CubeSat of this invention, equipped with a matching camera, can observe and analyze dust collection in orbit, providing possibilities for further scientific research.

[0006] Based on the above technical solution, the present invention can be further improved as follows.

[0007] Furthermore, the first assembly space is provided with a first horizontal partition, a first vertical partition, and a second horizontal partition. The first horizontal partition and the second horizontal partition are arranged horizontally, and the first vertical partition is arranged perpendicularly to the transparent fixed baffle and located between the first horizontal partition and the second horizontal partition. The posture adjustment component is installed on the second horizontal partition, and the aerogel collection material and the light source are installed on the first horizontal partition.

[0008] The beneficial effects of adopting the above-mentioned further solution are: by reasonably setting the first assembly space, the aerogel collection material, light source, and attitude adjustment components can be compactly arranged without affecting sample collection and structural stability.

[0009] Furthermore, the attitude adjustment component includes a magnetometer, a reaction wheel, a three-axis gyroscope, and a GNSS. The magnetometer is installed on the left side of the first vertical partition plate, and the reaction wheel, the three-axis gyroscope, and the GNSS are all installed on the right side of the first vertical partition plate.

[0010] Furthermore, a spaceborne computer is also provided on the lower surface of the second transverse partition.

[0011] Furthermore, the second assembly space is provided with a third horizontal partition and a second vertical partition. The front end and rear end of the third horizontal partition are fixedly connected to the transparent fixed baffle and the second vertical partition, respectively. An electronic component assembly interlayer is formed between the second vertical partition and the rear side of the 2U housing structure. The cover drive unit, camera and lens are installed on the upper side of the third horizontal partition, and the onboard assembly is installed on the lower side of the third horizontal partition.

[0012] The beneficial effects of adopting the above-mentioned further solution are: by rationally setting the structure of the second assembly space, it is convenient to set up the cover plate drive unit, camera, lens and onboard components, resulting in a compact structure and reasonable layout.

[0013] Furthermore, the onboard components include a power control onboard unit, a communication control onboard unit, a data management onboard unit, and an attitude control onboard unit. The power control onboard unit, the communication control onboard unit, the data management onboard unit, and the attitude control onboard unit are stacked and inserted into the lower side of the third transverse partition in the left-right direction.

[0014] Furthermore, a sun sensor is provided at the front end of the four rectangular sides of the 2U shell structure, and a deployable UV antenna is provided on the left rear end of the four rectangular sides of the 2U shell structure.

[0015] Furthermore, the left, right, and bottom surfaces of the 2U shell structure all use body-mounted solar panels as structural plates, while the front, rear, and top surfaces of the 2U shell structure all use metal plates as structural plates.

[0016] The beneficial effect of adopting the above-mentioned further solution is that by setting up a bulk-mounted solar panel as a structural panel, it can provide electrical energy while also serving as a structural panel to ensure structural strength and stability.

[0017] Furthermore, the cover plate drive unit includes a worm gear drive assembly, a lead screw and nut drive assembly, or a cylinder drive assembly.

[0018] A sampling method, implemented using a 2U space dust sampling cubesel as described above, includes the following steps:

[0019] S1, during the CubeSat launch phase, the cover plate drive unit locks the telescopic cover plate, so that the telescopic cover plate, the transparent fixed baffle, and the inner wall of the 2U shell structure form a closed area to protect the aerogel collection material.

[0020] S2. After the CubeSat enters orbit, the attitude adjustment component works with the onboard components to adjust the CubeSat's attitude to a continuously stable state.

[0021] S3, when the CubeSat enters the dust region, the cover plate drive unit drives the telescopic cover plate to open, exposing the aerogel collection material. At the same time, the light source is turned on, and the camera and lens work together to take continuous pictures.

[0022] The beneficial effects of this invention are: the sampling method of this invention has high dust collection efficiency and accuracy. Attached Figure Description

[0023] Figure 1 This is a three-dimensional structural diagram of the 2U space dust sampling cubesat of the present invention;

[0024] Figure 2 This is a three-dimensional structural diagram of the internal structure of the 2U space dust sampling CubeSat of the present invention. Figure 1 ;

[0025] Figure 3 This is a three-dimensional structural diagram of the internal structure of the 2U space dust sampling CubeSat of the present invention. Figure 2 ;

[0026] Figure 4 This is a schematic diagram of the internal structure of the second assembly space of the 2U space dust sampling CubeSat of the present invention.

[0027] The attached diagram lists the components represented by each number as follows:

[0028] 1. Structural frame; 11. Transparent fixed baffle; 12. First horizontal partition; 13. First vertical partition; 14. Second horizontal partition; 15. Third horizontal partition; 16. Second vertical partition; 17. Metal plate; 18. Integral solar panel; 19. UV antenna; 190. Telescopic cover;

[0029] 2. Cover plate drive unit; 21. Worm gear; 3. Camera; 31. Lens; 32. Light source;

[0030] 4. Aerogel collection materials;

[0031] 5. Magnetometer; 51. Reaction wheel; 52. Three-axis gyroscope; 53. GNSS; 54. Sun sensor;

[0032] 6. Power control board onboard; 61. Communication control board onboard; 62. Data management board onboard; 63. Attitude control board onboard;

[0033] 7. Spaceborne computer; 71. Storage battery. Detailed Implementation

[0034] The principles and features of the present invention are described below with reference to the accompanying drawings. The examples given are only for explaining the present invention and are not intended to limit the scope of the present invention.

[0035] like Figures 1-4 As shown, a 2U space dust sampling cubeset of this embodiment includes a 2U shell structure, a transparent fixing baffle 11, a cover plate driving part 2, a camera 3, a lens 31, an aerogel collection material 4, a light source 32, an attitude adjustment component, and an onboard component. The transparent fixing baffle 11 is disposed inside the 2U shell structure and is arranged perpendicular to the length direction of the 2U shell structure. The transparent fixing baffle 11 divides the internal space of the 2U shell structure into a first assembly space and a second assembly space arranged front and back. The aerogel collection material 4, the attitude adjustment component, and the light source 32 are installed in the first assembly space. Within the space, the cover plate drive unit 2, camera 3, lens 31, and onboard assembly are installed in the second assembly space. The lens 31 is located in front of the camera 3 and is arranged directly opposite the transparent fixed baffle 11. The aerogel collection material 4 is located behind the light source 32 and is arranged directly opposite the transparent fixed baffle 11 and the lens 31. A telescopic cover plate 190 is provided on the upper side of the 2U shell structure at a position corresponding to the first assembly space. The cover plate drive unit 2 is connected to the inner side of the telescopic cover plate 190 and drives the telescopic cover plate 190 to expose or cover the aerogel collection material 4.

[0036] like Figures 2-4As shown, in a specific embodiment, the first assembly space includes a first horizontal partition 12, a first vertical partition 13, and a second horizontal partition 14. The first horizontal partition 12 and the second horizontal partition 14 are arranged horizontally. The first vertical partition 13 is arranged perpendicularly to the transparent fixed baffle 11 and is located between the first horizontal partition 12 and the second horizontal partition 14. The posture adjustment component is mounted on the second horizontal partition 14, and the aerogel collection material 4 and the light source 32 are mounted on the first horizontal partition 12. By rationally setting the first assembly space, the aerogel collection material, the light source, and the posture adjustment component can be compactly arranged without affecting sample collection and structural stability.

[0037] like Figure 2 and Figure 3 As shown, the attitude adjustment assembly in this embodiment includes a magnetometer 5, a reaction wheel 51, a three-axis gyroscope 52, and a GNSS 53. The magnetometer 5 is installed on the left side of the first vertical partition plate 13, and the reaction wheel 51, the three-axis gyroscope 52, and the GNSS 53 are all installed on the right side of the first vertical partition plate 13. By equipping the CubeSat with the reaction wheel and magnetometer, these efficient attitude control devices ensure that the CubeSat maintains a stable attitude during dust collection.

[0038] like Figure 2 and Figure 3 As shown, the lower surface of the second transverse partition 14 in this embodiment is also provided with a spaceborne computer 7.

[0039] like Figures 2-4 As shown, in a specific embodiment, the second assembly space is provided with a third horizontal partition 15 and a second vertical partition 16. The front end and rear end of the third horizontal partition 15 are fixedly connected to the transparent fixed baffle 11 and the second vertical partition 16, respectively. An electronic component assembly interlayer is formed between the second vertical partition 16 and the rear side of the 2U housing structure. The cover drive unit 2, camera 3, and lens 31 are installed on the upper side of the third horizontal partition 15, and the onboard assembly is installed on the lower side of the third horizontal partition 15. Electronic components such as the battery 71 can be placed in the electronic component assembly interlayer. By reasonably setting the structure of the second assembly space, it is convenient to set up the cover drive unit, camera, lens, and onboard assembly, resulting in a compact structure and reasonable layout.

[0040] like Figure 2 and Figure 3As shown, the onboard components in this embodiment include a power control board 6, a communication control board 61, a data management board 62, and an attitude control board 63. These boards are stacked and inserted into the lower side of the third transverse partition 15 in a left-right direction. By distributing multiple onboard components in a stacked manner, including the communication control board, attitude control board, power management board, and core motherboard, greater space savings and a simplified system architecture are achieved.

[0041] like Figure 1 As shown, the front end of the four rectangular sides of the 2U shell structure in this embodiment is provided with a sun sensor 54, and the left rear end of the four rectangular sides of the 2U shell structure is provided with a foldable UV antenna 19.

[0042] like Figure 1 As shown, in a preferred embodiment, the left, right, and bottom surfaces of the 2U shell structure all use body-mounted solar panels 18 as structural plates, while the front, rear, and top surfaces of the 2U shell structure all use metal plates 17 as structural plates. By using body-mounted solar panels as structural plates, power can be provided while also serving as structural plates, ensuring structural strength and stability. Preferably, aluminum plates are used. In this embodiment, the body-mounted solar panels 18, metal plates 17, and telescopic cover 190 are combined with the structural frame 1 to form a 2U shell structure. The entire 2U shell structure has dimensions of 20cm × 10cm × 10cm, exhibiting high structural strength and stable performance. The design of body-mounted solar panels significantly increases the solar energy collection area, thereby acquiring more power within a limited volume, ensuring sufficient power supply for the CubeSat under various operating conditions.

[0043] Optionally, the cover plate driving unit 2 includes a worm gear driving assembly (worm gear 21 structure as follows) Figure 3 (as shown) or a lead screw and nut drive assembly or a cylinder drive assembly.

[0044] In this embodiment, aerogels can be classified according to their appearance, preparation method (synthesis / drying), microstructure, chemical structure, or origin. Transparent aerogels are the optimal choice for capturing and observing tracked particles. Oxide aerogels include SiO2 (silicon dioxide) aerogels, Al2O3 (alumina) aerogels, ZrO2 (zirconia) aerogels, TiO2 (titanium dioxide) aerogels, etc.; organic aerogels, mainly composed of organic matter, include phenolic aerogels, cellulose aerogels, polyimide aerogels, chitosan aerogels, and chitosan / cellulose aerogels, etc.; carbon-based aerogels include carbon nanotube aerogels, graphene aerogels, carbon nanotube-graphene composite aerogels, and polymer-based carbon aerogels, etc.

[0045] The light source used in this embodiment is determined by both the aerogel material and the camera model. Ultraviolet (UV), infrared, and X-ray light sources can be used; the optical transparency of the aerogel allows for internal observation using visible light sources, making them the optimal choice. This includes various options such as incandescent lamps, halogen lamps, fluorescent lamps, and LED lights. The light source illuminates the aerogel, providing the camera with a viewing angle.

[0046] The main objective of this invention lies in the structural layout of the CubeSat. Existing algorithms can be used to implement the onboard computer and the algorithms embedded on the board. For example, deep learning algorithms can be embedded on the core board to achieve edge computing. This allows for rapid analysis of dust image information while reducing the bandwidth used for information downlink, enabling an independent, autonomous, and efficient dust sampling CubeSat. The selection of deep learning algorithms can be flexibly varied according to task requirements, including options such as target classification, target detection, instance segmentation, semantic segmentation, and 3D reconstruction.

[0047] The advantages of this CubeSat layout are as follows: First, the aerogel collection material is used for target capture and storage, while the transparent fixing baffle ensures the stability of the collected material under microgravity or vibration environments. The light source, camera, and lens together form the imaging system, providing high-quality image data for target detection. Second, the flexible stacking of the system functional boards gives the system excellent scalability. Not only can functional boards be added or removed according to mission requirements, but specific functional boards can also be replaced during subsequent upgrades without redesigning the entire system. Simultaneously, the sensors of each system are compactly installed and rationally positioned, facilitating the acquisition of more accurate data information to serve each subsystem. Finally, the main frame and frame aluminum plates provide robust mechanical support, enabling stable installation of each subsystem and providing good vibration resistance.

[0048] This embodiment of the 2U space dust sampling CubeSat utilizes the unique porous structure and ultralight mass of aerogel to effectively capture minute particles, making the CubeSat highly efficient and accurate in collecting space dust. The CubeSat of this embodiment, through a rationally designed spatial layout, has a small platform size and simple structure, reducing launch difficulty, shortening the development cycle, and lowering the cost of space dust collection experiments. The CubeSat of this invention, equipped with a matching camera, can observe and analyze dust collection in orbit, providing possibilities for further scientific research. By utilizing the innovative material aerogel to collect space dust, the efficiency and accuracy of dust collection are improved, and the interference problems existing in traditional dust collection missions are also solved.

[0049] This embodiment also provides a sampling method, which is implemented using a 2U space dust sampling cubes as described above, and includes the following steps:

[0050] S1, during the CubeSat launch phase, the cover plate drive unit 2 locks the telescopic cover plate 190, so that the telescopic cover plate 190, the transparent fixed baffle 11, and the inner wall of the 2U shell structure enclose a closed area to protect the aerogel collection material 4.

[0051] S2. After the CubeSat enters orbit, the attitude adjustment component works with the onboard components to adjust the CubeSat's attitude to a continuously stable state.

[0052] S3, when the CubeSat enters the dust area, the cover plate drive unit 2 drives the telescopic cover plate 190 to open, exposing the aerogel collection material 4. At the same time, the light source 32 is lit, and the camera 3 and lens 31 work together to take continuous pictures.

[0053] Specifically, the dust collection process of the CubeSat is divided into the following stages: During launch, the onboard computer controls the cover drive unit 2 via bus commands to lock the telescopic cover 190. The telescopic cover 190, together with the transparent fixed baffle 11 and the inner wall of the 2U shell structure, forms a closed area. After entering orbit, the sun sensor monitors the sun's azimuth in real time, and the magnetometer provides attitude data of the satellite relative to the Earth's magnetic field. The three-axis gyroscope measures the satellite's angular velocity, providing rotation information. GNSS provides the satellite's position and velocity information to assist in attitude determination. This attitude data is transmitted via bus to the attitude control board, which generates control signals for the reaction wheel. The reaction wheel generates torque by changing its rotation speed, dynamically adjusting the satellite's pointing and maintaining three-axis stability. After adjustment, the sensors continue to collect data, and the attitude control board recalculates the deviation and generates new control signals, forming a closed-loop control to ensure the continuous stability of the satellite's attitude. The power control board is responsible for distributing and regulating the charging and discharging of the battery, stabilizing and filtering unstable voltage and current to convert them into stable voltages suitable for the onboard equipment, and distributing them to other onboard devices and sensors via the bus. When entering the dust region, the onboard computer sends an unfolding command to the cover drive unit, retracting the baffle to expose the aerogel collection material, simultaneously triggering the light source to illuminate and starting continuous shooting by the camera and lens. Image data is transmitted via the bus to the data management board for real-time compression and storage, and then fed back to the onboard computer via the bus. Its built-in deep learning network detects image targets and decides whether to terminate the acquisition. In the later stages of the mission, the onboard computer filters high-quality data and uses communication control onboard modulation signals to drive the deployable UV antenna to transmit scientific data and engineering parameters at regular intervals. The lightweight structure of the main frame and aluminum plate ensures system stability in extreme environments, ultimately achieving a closed-loop control of the entire chain from sensor data acquisition, dynamic attitude control, energy optimization to scientific observation and communication, while simultaneously completing the composite mission objectives of in-situ space dust collection and multi-dimensional observation.

[0054] The sampling method in this embodiment offers high efficiency and accuracy in dust collection. During the sampling process, the CubeSat of this invention can independently and autonomously collect onboard dust and perform in-situ calculations. A centralized management system centered on the onboard computer is employed, with separate subsystems for power management, attitude control, communication control, and data management. Simultaneously, the scientific payload transmits data and commands through the onboard computer, enabling embedded deep learning algorithms to process dust trajectory images. This ensures the selection of valid image information, reduces data downlink bandwidth, and also achieves mission reconfigurability, lowering development costs and shortening the implementation cycle.

[0055] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0056] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0057] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0058] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "over," and "on top" of the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0059] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0060] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A 2U space dust sampling cubesat, characterized in that, The device includes a 2U shell structure, a transparent fixing baffle, a cover plate driving unit, a camera, a lens, an aerogel collection material, a light source, an attitude adjustment component, and an onboard component. The transparent fixing baffle is disposed within the 2U shell structure and is arranged perpendicular to the length direction of the 2U shell structure. The transparent fixing baffle divides the internal space of the 2U shell structure into a first assembly space and a second assembly space arranged front and rear. The aerogel collection material, attitude adjustment component, and light source are installed in the first assembly space, while the cover plate driving unit, camera, lens, and onboard component are installed in the second assembly space. The lens is located in front of the camera and faces the transparent fixing baffle, and the aerogel collection material is located behind the light source and faces the transparent fixing baffle and the lens. A telescopic cover plate is provided on the upper side of the 2U shell structure at a position corresponding to the first assembly space. The cover plate driving unit is connected to the inner side of the telescopic cover plate and drives the telescopic cover plate to expose or cover the aerogel collection material.

2. The 2U space dust sampling cubeset according to claim 1, characterized in that, The first assembly space is provided with a first horizontal partition, a first vertical partition, and a second horizontal partition. The first horizontal partition and the second horizontal partition are arranged horizontally, one above the other. The first vertical partition is arranged perpendicularly to the transparent fixed baffle and is located between the first horizontal partition and the second horizontal partition. The posture adjustment component is installed on the second horizontal partition, and the aerogel collection material and the light source are installed on the first horizontal partition.

3. The 2U space dust sampling cubeset according to claim 2, characterized in that, The attitude adjustment assembly includes a magnetometer, a reaction wheel, a three-axis gyroscope, and a GNSS. The magnetometer is installed on the left side of the first vertical partition plate, and the reaction wheel, the three-axis gyroscope, and the GNSS are all installed on the right side of the first vertical partition plate.

4. The 2U space dust sampling cubeset according to claim 2, characterized in that, The lower surface of the second transverse partition is also equipped with a spaceborne computer.

5. The 2U space dust sampling cubeset according to claim 1, characterized in that, The second assembly space is provided with a third horizontal partition and a second vertical partition. The front end and rear end of the third horizontal partition are fixedly connected to the transparent fixed baffle and the second vertical partition, respectively. An electronic component assembly interlayer is formed between the second vertical partition and the rear side of the 2U housing structure. The cover plate drive unit, camera and lens are installed on the upper side of the third horizontal partition, and the onboard assembly is installed on the lower side of the third horizontal partition.

6. The 2U space dust sampling cubeset according to claim 5, characterized in that, The onboard components include a power control onboard unit, a communication control onboard unit, a data management onboard unit, and an attitude control onboard unit. The power control onboard unit, the communication control onboard unit, the data management onboard unit, and the attitude control onboard unit are stacked and inserted into the lower side of the third transverse partition in the left-right direction.

7. A 2U space dust sampling cubeset according to claim 1, characterized in that, A sun sensor is provided at the front end of the four rectangular sides of the 2U shell structure, and a deployable UV antenna is provided on the left rear end of the four rectangular sides of the 2U shell structure.

8. The 2U space dust sampling cubeset according to claim 1, characterized in that, The left, right, and bottom sides of the 2U shell structure all use body-mounted solar panels as structural plates, while the front, rear, and top sides of the 2U shell structure all use metal plates as structural plates.

9. A 2U space dust sampling cubeset according to claim 1, characterized in that, The cover plate drive unit includes a worm gear drive assembly, a lead screw and nut drive assembly, or a cylinder drive assembly.

10. A sampling method, characterized in that, The sampling of space dust using a 2U space dust cubes as described in any one of claims 1 to 9 includes the following steps: S1, during the CubeSat launch phase, the cover plate drive unit locks the telescopic cover plate, so that the telescopic cover plate, the transparent fixed baffle, and the inner wall of the 2U shell structure form a closed area to protect the aerogel collection material. S2. After the CubeSat enters orbit, the attitude adjustment component works with the onboard components to adjust the CubeSat's attitude to a continuously stable state. S3, when the CubeSat enters the dust region, the cover plate drive unit drives the telescopic cover plate to open, exposing the aerogel collection material. At the same time, the light source is turned on, and the camera and lens work together to take continuous pictures.

Images