A wafer level solar sail spacecraft capable of detecting space dust and small debris

Abstract

The application discloses a wafer-level solar sail spacecraft capable of detecting space dust and tiny fragments, which comprises a solar sail film, a high-reflection metal electrode coating, double-layer micro metal beam elements, a rigidity-enhancing truss, a limiting frame and a flexible circuit control board. The solar sail film is in the shape of a petal, the center of the front surface of which is an effective payload integration area, and the flexible circuit control board is arranged in the effective payload integration area. An isolation belt is arranged in the middle of the front surface of each petal, and a high-reflection metal electrode coating is coated on the front surface of the petal on the two sides of the isolation belt. The double-layer micro metal beam elements span the isolation belt and are fixed at the two ends of the high-reflection metal electrode coating. The upper metal beam of the double-layer micro metal beam elements is a heat-expansion metal, and the lower metal beam is a heat-shrinkage metal. The back surface of the solar sail film is provided with the rigidity-enhancing truss and a piezoelectric sensor. The flexible circuit control board independently loads different high and low pressures on each high-reflection metal electrode coating.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace technology, in particular, to a wafer-level solar sail spacecraft capable of autonomous attitude adjustment for space dust and small debris detection. BACKGROUND

[0002] Space dust and small debris exist widely in near-earth space and deep space, and are an important threat to human space activities. In recent years, in response to the detection needs of space dust and small debris mass, speed, and spatial distribution, well-known space agencies at home and abroad have carried out a large number of space tests based on piezoelectric space debris detection devices. The surface of such detection devices is a piezoelectric sensor developed using piezoelectric materials. When the piezoelectric sensor collides with space dust and small debris, the piezoelectric sensor can convert its mechanical deformation during the collision into an electrical signal; by analyzing the signal set generated by the piezoelectric effect, important information such as the mass, speed, and spatial distribution of space dust and small debris can be obtained. PVDF piezoelectric film is widely used in the development of piezoelectric space debris detection devices due to its high mechanical strength, impact resistance, and good ultraviolet resistance and thermal stability. However, traditional piezoelectric space debris detection devices are generally installed in a concentrated load form on specific spacecraft, which greatly limits their detection range, and are bulky, heavy, and costly, occupying too much load capacity of the launch vehicle, making it difficult to meet the needs of increasingly complex near-earth space and deep space exploration. SUMMARY

[0003] The technical problem to be solved by the present application is to overcome the problems of existing piezoelectric space debris detection devices, such as relatively fixed detection range, large volume, heavy mass, high cost, and large load capacity occupation, and to provide a wafer-level solar sail spacecraft capable of autonomous attitude adjustment for space dust and small debris detection, which has a wide detection range, is lighter, has higher integration, and occupies less effective payload capacity of the launch spacecraft.

[0004] To achieve the above-mentioned purpose, the technical solution adopted by the present application is:

[0005] A wafer-level solar sail spacecraft capable of detecting space dust and small debris, comprising a solar sail film, a high-reflectivity metal electrode coating, a double-layer micro-metal beam element, a stiffness-enhancing truss, a limiting frame, and a flexible circuit control board.

[0006] The solar sail film is petal-shaped, the center of the front surface is a payload integration area, the flexible circuit control board is arranged in the payload integration area, a separation band is arranged in the middle of the front surface of each petal, a high reflectivity metal electrode coating is coated on the front surface of the petal on both sides of the separation band, the double-layer micro metal beam element spans the separation band and is fixed at both ends on the high reflectivity metal electrode coating, the upper metal beam of the double-layer micro metal beam element is a heat expansion metal, and the lower metal beam is a heat shrinkage metal, the back surface of the solar sail film is provided with a rigidity enhancement truss and a piezoelectric sensor, the piezoelectric sensor is connected with the flexible circuit control board, and the flexible circuit control board independently loads different high and low pressures on each high reflectivity metal electrode coating.

[0007] When the wafer-level solar sail spacecraft capable of autonomously adjusting the attitude for space dust and micro debris detection is released, different high and low pressures are independently loaded on each high reflectivity metal electrode coating by the flexible circuit control board, at this time, the double-layer micro metal beam element has current passing through, thereby generating Joule heat, the lower metal beam shrinks under the heat, and the upper metal beam expands under the heat, thereby causing different degrees of deformation of each petal of the solar sail film, the incident angle of the incident sunlight is changed, thereby obtaining different configuration combinations of the petals, which will cause an asymmetric light pressure distribution, the asymmetric light pressure distribution will generate an asymmetric torque, thereby regulating the attitude of the solar sail, so that the solar sail spacecraft changes the orientation and flies to the target detection area under the push of the solar light pressure.

[0008] When the wafer-level solar sail spacecraft capable of autonomously adjusting the attitude for space dust and micro debris detection flies to the target detection area under the push of the solar light pressure, when the space dust or micro debris hits the piezoelectric sensor, the piezoelectric sensor will generate an electric signal due to the piezoelectric effect and transmit the electric signal to the flexible circuit control board, the electric signal is conditioned by the signal conditioning circuit on the flexible circuit control board and then transmitted out by the microstrip patch antenna carried on the flexible circuit control board, when the signal receiving device carried on the carrier spacecraft receives the signal transmitted by the microstrip patch antenna, the signal is transmitted to the computer, and the information such as the mass, speed, spatial distribution, material composition, and distribution relationship between the magnetic field and the dust of the space dust or micro debris can be known by analyzing the received signal by the computer.

[0009] As a further technical solution, the flexible circuit control board comprises a solar panel, a micro control unit, a charge amplifier, a voltage amplifier, a digital interface, an AD acquisition module, a high-pass filter, a microstrip patch antenna, a micro battery, a power management module, and a boost converter array.

[0010] The digital code interface is connected with the input end of the micro control unit; the micro control unit is connected with the power management module, the power management module is connected with the solar cell panel, the micro battery and the boost converter array, the boost converter array is connected with the metal electrode coating;

[0011] The piezoelectric sensor is connected with the charge amplifier, the charge amplifier is connected with the voltage amplifier, the voltage amplifier is connected with the high-pass filter, the high-pass filter is connected with the AD acquisition module, the AD acquisition module is connected with the micro control unit, and the micro control unit transmits signals to the patch antenna.

[0012] Further, the boost converter array is composed of eight boost converters corresponding to eight petals respectively.

[0013] As a further technical solution, the high-reflectivity metal electrode coating covers the entire petal outside the isolation band.

[0014] As a further technical solution, on each petal, a plurality of double-layer micro metal beam elements are sequentially arranged along the length direction of the isolation band, the plurality of double-layer micro metal beam elements are different in length and the same in material; the double-layer micro metal beam element located at the middle position of the petal has the longest length, and the double-layer micro metal beam elements located at both ends of the petal have lengths decreasing in turn. That is, four double-layer micro metal beam elements which are the same in material, similar in structure and match the size of the double-layer micro metal beam element deployment area are sequentially arranged on each double-layer micro metal beam element array deployment area.

[0015] Further, the stiffness-enhanced truss is centrally symmetrical, the middle part is a circular ring, and there are trusses corresponding to the double-layer micro metal beam element array deployment area extending outward around the circular ring, which are made of high-strength, lightweight and high-rigidity materials such as carbon fiber and are pasted on the back of the solar sail film through epoxy resin;

[0016] Further, the piezoelectric sensor is a PVDF piezoelectric sensor, which is circular and is matched in size with the central circular ring of the stiffness-enhanced truss and is pasted on the solar sail film through epoxy resin;

[0017] Further, the limiting frame defines a circular effective payload integration area on the front of the solar sail film, and the effective payload integration area is provided with a rectangular flexible circuit control board.

[0018] Further, the limiting frame is made of high-strength, ultra-lightweight and high-rigidity materials such as carbon fiber and is pasted on the central part of the front of the solar sail film through epoxy resin.

[0019] Further, the flexible circuit control board is circular and is pasted on the solar sail film through epoxy resin.

[0020] The present application has the following advantages compared with the prior art:

[0021] 1、The multiple wafer-level solar sail spacecraft for space dust and micro-debris detection with autonomous attitude adjustment can be distributed and clustered in the target area after being launched by a carrier spacecraft, greatly expanding the detection range of space dust or micro-debris.

[0022] 2、The wafer-level solar sail spacecraft for space dust and micro-debris detection with autonomous attitude adjustment can actively adjust the configuration of the solar sail petals according to the space environment and sunlight conditions, change the light pressure distribution on different petals, and adjust the spacecraft to a flight attitude that meets the detection requirements, by using solar sail light pressure regulation technology.

[0023] 3、The wafer-level solar sail spacecraft for space dust and micro-debris detection with autonomous attitude adjustment has the advantages of small size, light weight, low cost, and high integration, and can be deployed in large quantities in the target detection area within a specific payload range. BRIEF DESCRIPTION OF DRAWINGS

[0024] The accompanying drawings, which form a part of this application, are included to provide a further understanding of the application and are incorporated in and constitute a part of this application. In the drawings:

[0025] Figure 1 is a plurality of configuration diagrams of the solar sail film of the present application;

[0026] Figure 2 is a three-dimensional structure diagram of the eight-petal solar sail micro-dust debris detection spacecraft of the present application;

[0027] Figure 3 is a front structure diagram of the eight-petal solar sail micro-dust debris detection spacecraft of the present application;

[0028] Figure 4 is a structure diagram of the A-A section in the Figure 3 of the present application;

[0029] Figure 5 is a back structure diagram of the eight-petal solar sail micro-dust debris detection spacecraft of the present application;

[0030] Figure 6 is a payload integration area composition diagram of the micro-dust debris detection spacecraft of the present application;

[0031] Figure 7 is a B-B section structure diagram of the present application;

[0032] Figure 8 is an attitude adjustment flowchart of the present application;

[0033] Figure 9 is a schematic diagram of a solar sail film of the present application;

[0034] Figure 10 is a schematic diagram of a detection workflow of the present application;

[0035] Figure label: 1-solar sail film, 2-array deployment area of double-layer micro metal beam elements, 3-high reflectivity metal electrode coating, 4-isolation belt, 5-double-layer micro metal beam element, 51-thermal expansion metal, 52-thermal contraction metal, 6-rigidity enhancement truss, 7-PVDF piezoelectric sensor, 8-limiting frame, 9-payload integration area, 10-flexible circuit control board, 11-solar cell panel, 12-micro control unit, 13-charge amplifier, 14-voltage amplifier, 15-digital interface, 16-high pass filter, 17-AD acquisition module, 18-microstrip patch antenna, 19-micro battery, 20-power management module, 21-boost converter array. DETAILED DESCRIPTION

[0036] It should be noted that the following detailed description is merely exemplary in nature and is intended to provide further description of the application. Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs.

[0037] It is to be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments consistent with the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises" and / or "comprising," when used in this specification, specify the presence of stated features, steps, operations, elements, components, and / or groups thereof, but do not preclude the presence or addition of one or more other features, steps, operations, elements, components, and / or groups thereof.

[0038] Noun explanation: "high reflectivity" in "high reflectivity metal electrode coating" in this embodiment refers to the reflectivity of sunlight greater than 0.8; in this embodiment, the high reflectivity metal electrode coating is taken as an example of aluminum metal electrode coating with the highest grade reflectivity (i.e. 0.8-0.95).

[0039] The medium-free light pressure propulsion based on solar sail technology has great potential in developing such micro dust and debris detection space systems. As a propulsion device of a solar sail spacecraft, the solar sail can obtain a small but continuous light pressure acceleration by reflecting sunlight, which has a significant advantage in performing long-period, long-distance space micro dust and debris detection tasks. Therefore, the present embodiment discloses a wafer-level solar sail spacecraft capable of detecting space dust and small debris, which has high integration, small volume, light weight, low cost, can be distributed and can actively adjust the attitude.

[0040] The wafer level solar sail spacecraft capable of detecting space dust and small debris provided by the embodiment mainly comprises a solar sail film, a high reflectivity metal electrode coating, a double-layer micro metal beam element, a stiffness enhancement truss, a limiting frame and a flexible circuit control board; the solar sail film is petal-shaped, the front center of the solar sail film is an effective payload integration area, the flexible circuit control board is arranged in the effective payload integration area, a separation belt is arranged in the middle of the front of each petal, a high reflectivity metal electrode coating is coated on the front of the petal on both sides of the separation belt, the double-layer micro metal beam element spans the separation belt and is fixed at both ends on the high reflectivity metal electrode coating; the upper metal beam of the double-layer micro metal beam element is a heat expansion metal, and the lower metal beam is a heat shrinkage metal; the back of the solar sail film is provided with a stiffness enhancement truss and a piezoelectric sensor; the piezoelectric sensor is connected with the flexible circuit control board, and different high and low voltages can be independently loaded on each high reflectivity metal electrode coating through the microcontroller, the power management module and the boost converter array on the flexible circuit control board.

[0041] When the wafer level solar sail spacecraft capable of autonomously adjusting the attitude and facing space dust and small debris detection is released, different high and low voltages can be independently loaded on each high reflectivity metal electrode coating through the microcontroller, the power management module and the boost converter array on the flexible circuit control board, at this time, the double-layer micro metal beam element will have current passing through, thereby generating Joule heat, the lower metal beam shrinks due to heat, and the upper metal beam expands due to heat, thereby causing different degrees of deformation of each petal of the solar sail film, the incident angle of incident sunlight is also changed, thereby obtaining different configuration combinations of the petal, which will cause asymmetric light pressure distribution, the asymmetric light pressure distribution will generate asymmetric moments, thereby regulating the attitude of the solar sail, so that the solar sail spacecraft changes the direction and flies to the target detection area under the push of the solar light pressure.

[0042] After the wafer level solar sail spacecraft capable of autonomously adjusting the attitude and facing space dust and small debris detection flies to the target detection area under the push of the solar light pressure, when the space dust or small debris hits the piezoelectric sensor, the piezoelectric sensor will generate an electric signal due to the piezoelectric effect and transmit the electric signal to the flexible circuit control board; after the electric signal is conditioned by the signal conditioning circuit on the flexible circuit control board, the electric signal is transmitted out through the microstrip patch antenna carried on the flexible circuit control board; when the signal receiving device carried on the carrier spacecraft receives the signal from the flexible circuit control board, the signal receiving device transmits the signal to a computer, and information such as the mass, speed, spatial distribution, material composition and distribution relationship between the magnetic field and the dust of the space dust or small debris can be known by analyzing the received signal through the computer.

[0043] Specifically, as shown in FIG. 1, the wafer level solar sail spacecraft capable of detecting space dust and small debris provided by the embodiment mainly comprises a solar sail film 1, a high reflectivity metal electrode coating 2, a double-layer micro metal beam element 3, a stiffness enhancement truss 4, a limiting frame 5 and a flexible circuit control board 6. Figures 1-10As shown, the wafer-level solar sail spacecraft capable of detecting space dust and small debris in the embodiment mainly comprises a solar sail film 1, a double-layer micro metal beam element array deployment area 2, a high-reflectivity metal electrode coating 3, an isolation belt 4, a double-layer micro metal beam element 5, a stiffness-enhancing truss 6, a PVDF piezoelectric sensor 7, a limiting frame 8, a payload integration area 9, and a flexible circuit control board 10. The solar sail film 1 is petal-shaped, and the front center thereof is the payload integration area 9. The flexible circuit control board 10 is arranged in the payload integration area 9. An isolation belt 4 is arranged in the middle of the front surface of each petal. A high-reflectivity metal electrode coating 3 is coated on the front surface of each petal on both sides of the isolation belt 4. The double-layer micro metal beam element 5 spans the isolation belt 4 and is fixed at both ends on the high-reflectivity metal electrode coating 3. The upper metal beam of the double-layer micro metal beam element 5 is a heat-expanding metal, and the lower metal beam is a heat-contracting metal. The back of the solar sail film 1 is provided with the stiffness-enhancing truss 6 and the PVDF piezoelectric sensor 7. The PVDF piezoelectric sensor 7 is connected to the flexible circuit control board 10. The flexible circuit control board 10 can independently load different high and low voltages on each high-reflectivity metal electrode coating.

[0044] Further, the surface of the solar sail film 1 in the embodiment can be in various forms, such as Figure 1 As shown, there are four-petal, six-petal, eight-petal, and ten-petal shapes. In addition to the above, there are other shapes of sails. The eight-petal shape is selected as the implementation object of the present application, but the number and shape of the petals of the solar sail film 1 do not limit the protection scope of the present application. Specifically, as shown in Figure 2 and Figure 3 The front surface of each petal of the solar sail film 1 is provided with a double-layer micro metal beam element array deployment area 2. The intersection of all the double-layer micro metal beam element array deployment areas 2, i.e., the central part of the front surface of the solar sail film 1, is provided with a payload integration area 9. In order to enhance the stiffness of the solar sail film 1, a stiffness-enhancing truss 6 is arranged on the back of the solar sail film 1. See Figure 5 for details.

[0045] The solar sail film 1 is a material with high heat resistance, radiation resistance, processing flexibility, environmental protection, and excellent mechanical properties, such as polyimide. It is not only conducive to processing into a specific shape, but also can well adapt to complex deep space exploration environments. In order to improve the reflectivity to sunlight and facilitate voltage loading, each double-layer micro metal beam element array deployment area 2 is coated with two corresponding high-reflectivity metal electrode coatings 3, such as a metal aluminum coating. Each high-reflectivity metal electrode coating 3 is half-petal-shaped. Each double-layer micro metal beam element array deployment area 2 has an isolation belt 4 on the middle surface. A plurality of double-layer micro metal beam elements 5 span the isolation belt 4 and are fixed at one end on the high-reflectivity metal electrode coating 3 on one side and at the other end on the high-reflectivity metal electrode coating 3 on the other side (see Figure 2), when different voltages are loaded on the two separated electrode coatings, current and Joule heat will be formed on the array of micro metal beams 5 across the isolation belt 4; on each lobe, a plurality of double-layer micro metal beam elements 5 are arranged along the length direction of the isolation belt, each double-layer micro metal beam element 5 is different in length, similar in structure, and same in material, as shown in Figure 4 Fig. 2, the upper layer metal beam of each double-layer micro metal beam element 5 is a thermal expansion metal 51, such as aluminum, and the lower layer metal beam is a thermal contraction metal 52, such as nickel-titanium alloy. The length of the double-layer micro metal beam element located at the middle of the lobe is the longest, and the length of the double-layer micro metal beam element located at the two ends of the lobe decreases successively; in this embodiment, four double-layer micro metal beam elements which are same in size, similar in structure, and same in material are arranged successively on each double-layer micro metal beam element array arrangement area.

[0046] As shown in Figure 5 Fig. 3, the stiffness enhancement truss 6 in this embodiment is a central symmetric structure, the middle part is a circular ring, and eight trusses corresponding to the number of double-layer micro metal beam element array arrangement areas 2 extend outward around the circular ring. The stiffness enhancement truss 6 is pasted on the back of the solar sail film 1 by epoxy resin, and is made of high-strength, ultra-lightweight, and high-stiffness material, such as carbon fiber, which can effectively enhance the stiffness of the entire spacecraft and further reduce the mass of the entire spacecraft, thereby greatly saving the effective payload capacity of the spacecraft, and correspondingly, the PVDF piezoelectric sensor 7 is also circular and is arranged in the central circular ring of the stiffness enhancement truss 6, and the shapes and sizes of the two are matched.

[0047] On the front of the solar sail film 1, a limiting frame 8 defines a circular effective payload integration area 9, which effectively improves the stiffness of the central part of the solar sail film 1. The limiting frame 8 is made of high-strength, ultra-lightweight, and high-stiffness material, such as carbon fiber, and is pasted on the front central part of the solar sail film 1 by epoxy resin. The circular flexible circuit control board 10, the solar cell panel 11, the micro control unit 12, the charge amplifier 13, the voltage amplifier 14, the digital interface 15, the high-pass filter 16, the AD acquisition module 17, the microstrip patch antenna 18, the micro battery 19, the power management module 20, and the boost converter array 21 are integrated on the flexible circuit control board 10 in the effective payload integration area 9, as shown in Figure 6 and Figure 7 Fig. 4, and the connection relationship of each module is as follows:

[0048] The digital interface 15 is connected to the input end of the micro control unit 12; the micro control unit 12 is connected to the power management module 20, the power management module 20 is connected to the solar cell panel 11, the micro battery 19, and the boost converter array 21, and the boost converter array 21 is connected to the metal electrode coating 3.

[0049] PVDF piezoelectric sensor 7 is connected with charge amplifier 13, charge amplifier 13 is connected with voltage amplifier 14, voltage amplifier 14 is connected with high-pass filter 16, high-pass filter 16 is connected with AD acquisition module 17, AD acquisition module 17 is connected with micro control unit 12, micro control unit 12 transmits signal to microstrip patch antenna 18;

[0050] Further, digital interface 15 has the function of data transmission, and the code for controlling the attitude adjustment of the solar sail can be transmitted to micro control unit 12 through it; micro control unit 12 is small in size and high in integration, and can control the whole system; the role of power management module 20 is to control voltage boost converter array 21 to boost voltage and to convert voltage and current between solar panel 11, micro battery 19 and the whole system, to provide stable and reliable power supply for the whole system, to ensure the normal work of the whole system, and to protect the system from power abnormality; the function of solar panel 11 is to convert solar energy into electric energy for the whole system; micro battery 19 can store the electric energy converted by solar panel 11, and can also stabilize voltage and current to stably supply power for the whole spacecraft system; voltage boost converter array 21 can boost voltage, which is convenient for independently loading high and low voltage on each high reflectivity metal electrode coating 3, and each voltage boost converter array 21 is composed of eight voltage boost converters, which correspond to eight petals respectively; when the petals are six, voltage boost converter array 21 is composed of six voltage boost converters, that is, the number of voltage boost converters is the same as the number of petals of the solar sail film.

[0051] Further, the role of PVDF piezoelectric sensor 7 is to convert the mechanical signal generated by impact into an electrical signal, which has wide frequency response, impact resistance, toughness and good processing performance, high piezoelectric sensitivity, good thermal stability, outstanding anti-ultraviolet and weathering resistance; charge amplifier 13 can convert weak charge signal into voltage signal that can be read, and voltage amplifier 14 can improve signal voltage; high-pass filter allows frequencies higher than a certain cutoff frequency to pass through, while greatly attenuating lower frequencies, removing unnecessary low frequency parts in the signal; AD acquisition module 17 converts analog signal into digital signal; microstrip patch antenna 18 has low profile, small size, small weight and is easy to install, can be designed as a patch unit of different shapes, and can transmit the conditioned signal.

[0052] As Figure 8As shown, the code for controlling the solar sail to adjust the attitude is transmitted to the micro control unit 12 in advance through the digital interface 15, the micro control unit 12 controls the power management module 20, the power management module 20 controls the voltage boosting converter array 21 to boost the voltage and the voltage and current conversion between the solar cell panel 11, the micro battery 19 and the whole system, the solar cell panel 11 converts the solar energy into electrical energy and then stores it in the micro battery 19, the micro battery 19 stores the electrical energy and also supplies power to the whole system. When the wafer-level solar sail spacecraft capable of autonomous attitude adjustment for space dust and small debris detection is released, the micro control unit 12 controls the power management module 20 and the voltage boosting converter array 21 to boost the voltage, and different high and low voltages are independently loaded on each high reflectivity metal electrode coating 3. At this time, the double-layer micro metal beam element 5 will have current passing through, thereby generating Joule heat, the lower metal beam shrinks due to heat, and the upper metal beam expands due to heat, thereby causing each solar sail film 1 to have different degrees of deformation, the incident angle of the incident sunlight is also changed, thereby obtaining different configuration combinations of eight petal leaves, such as Figure 9 As shown, this is a configuration combination in which four symmetrical petal leaves are deformed and the remaining four petal leaves are not deformed. In addition to this, there are other different configuration combinations, and the present application selects the configuration combination as shown in Figure 9 As shown, this is a configuration combination in which four symmetrical petal leaves are deformed and the remaining four petal leaves are not deformed. In addition to this, there are other different configuration combinations, and the present application selects the configuration combination as shown in

[0053] When the wafer-level solar sail spacecraft capable of autonomous attitude adjustment for space dust and small debris detection flies to the target detection area, as shown in Figure 10As shown, the space dust or small debris in the target area will hit the PVDF piezoelectric sensor 7, which will convert the mechanical signal generated by the impact into an electric charge signal. The electric charge signal is too weak, so it needs to be converted into a voltage signal that can be read by the charge amplifier 13. After conversion, the signal is transmitted to the voltage amplifier 14, which boosts the voltage of the obtained signal to meet the requirements of the digital acquisition circuit. Due to environmental interference, the accuracy of the signal processed by the charge amplifier 13 and the voltage amplifier 14 will be affected. In order to improve the signal-to-noise ratio of the effective signal and remove the interference components brought by the deep space exploration environment, a high-pass filter 16 is used to filter out low-frequency components. The micro control unit 12 has an AD acquisition module 17 inside, but the self-contained AD resolution is low, the precision is not high and the range is limited. In order to accurately collect the effective signal, a dedicated AD acquisition module 17 is used to convert the signal processed by the high-pass filter 16 into a digital signal, which can be collected by the AD acquisition module of the microprocessor. Then the micro control unit 12 implements the transmission function, transmits the collected signal to the microstrip patch antenna 18, and then the microstrip patch antenna 18 transmits the signal back to the carrier spacecraft.

[0054] After the signal receiving device carried on the carrier spacecraft receives the signal transmitted by the microstrip patch antenna 18, it transmits the signal to the computer for processing. By analyzing the signal through the computer, the mass, speed, spatial distribution, material composition, and distribution relationship between the magnetic field and the dust of the space dust or small debris in space can be obtained.

[0055] The above only describes the preferred embodiments of the present application and is not intended to limit the present application. Those skilled in the art can make various modifications and changes to the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application shall be included in the protection scope of the present application.

Claims

1. A wafer-level solar sail spacecraft capable of detecting space dust and micro-debris, characterized in that, This includes solar sail films, high-reflectivity metal electrode coatings, double-layer micro-metal beam elements, stiffening trusses, limiting frames, and flexible circuit control boards; The solar sail film is petal-shaped, with a payload integration area at the center of its front side. The flexible circuit control board is located in the payload integration area. An isolation strip is set in the middle of the front side of each petal. A high-reflectivity metal electrode coating is coated on the front side of the petals on both sides of the isolation strip. The double-layer micro-metal beam element spans the isolation strip and is fixed at both ends to the high-reflectivity metal electrode coating. The upper metal beam of the double-layer micro-metal beam element is thermally expandable metal, and the lower metal beam is thermally contractible metal. A stiffness-enhancing truss and a piezoelectric sensor are provided on the back side of the solar sail film. The piezoelectric sensor is connected to the flexible circuit control board, which independently applies different high and low pressures to each high-reflectivity metal electrode coating.

2. The wafer-level solar sail spacecraft capable of detecting space dust and micro-debris as described in claim 1, characterized in that, The flexible circuit control board includes a solar panel, a microcontroller unit, a charge amplifier, a voltage amplifier, a digital interface, an AD acquisition module, a high-pass filter, a microstrip patch antenna, a micro battery, a power management module, and a boost converter array. The digital interface is connected to the input terminal of the microcontroller unit; the microcontroller unit is connected to the power management module, which is connected to the solar panel, the micro battery and the boost converter array, and the boost converter array is connected to the metal electrode coating. The piezoelectric sensor is connected to a charge amplifier, which is connected to a voltage amplifier. The voltage amplifier is connected to a high-pass filter, which is connected to an AD acquisition module. The AD acquisition module is connected to a microcontroller unit, which transmits signals to the patch antenna.

3. The wafer-level solar sail spacecraft capable of detecting space dust and micro-debris as described in claim 2, characterized in that, The boost converter array consists of multiple boost converters, and the number of boost converters is the same as the number of lobes on the solar sail film.

4. The wafer-level solar sail spacecraft capable of detecting space dust and micro-debris as described in claim 1, characterized in that, The high-reflectivity metal electrode coating covers the entire front of the outer side of the isolation strip.

5. The wafer-level solar sail spacecraft capable of detecting space dust and micro-debris as described in claim 1, characterized in that, On each lobe, multiple double-layer micro-metal beam elements are sequentially arranged along the length of the isolation strip. The lengths of the multiple double-layer micro-metal beam elements are different, but the materials are the same. The double-layer micro-metal beam element located in the middle of the lobe is the longest, and the lengths of the double-layer micro-metal beam elements located at both ends of the lobe decrease sequentially.

6. The wafer-level solar sail spacecraft capable of detecting space dust and micro-debris as described in claim 1, characterized in that, The stiffness-enhancing truss is centrally symmetrical, with a circular ring in the middle. A truss corresponding to the deployment area of ​​the double-layer micro-metal beam element array extends outward around the circular ring and is attached to the back of the solar sail film with epoxy resin.

7. The wafer-level solar sail spacecraft capable of detecting space dust and micro-debris as described in claim 6, characterized in that, The piezoelectric sensor is a PVDF piezoelectric sensor, which is circular and placed inside the central ring of the stiffness-enhancing truss. The two are matched in size and are attached to the solar sail film with epoxy resin.

8. The wafer-level solar sail spacecraft capable of detecting space dust and micro-debris as described in claim 1, characterized in that, It also includes a limiting frame that defines the payload integration area on the front side of the solar sail film.

9. The wafer-level solar sail spacecraft capable of detecting space dust and micro-debris as described in claim 1, characterized in that, The limiting frame is attached to the center of the front side of the solar sail film with epoxy resin.

10. The wafer-level solar sail spacecraft capable of detecting space dust and micro-debris as described in claim 1, characterized in that, The flexible circuit control board is circular and is attached to the solar sail film with epoxy resin.

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