A space-undetectable harassment device and method

Abstract

The present invention provides a space-based, sensorless harassment device and method, relating to the field of microsatellite technology. The space-based, sensorless harassment device includes a micro-carrier satellite and a force-current multi-field coupling actuator mounted on the micro-carrier satellite. The micro-carrier satellite is used to drive the force-current multi-field coupling actuator toward a target satellite and, by adjusting its attitude, align its jet nozzle with the target satellite's reconnaissance lens. The force-current multi-field coupling actuator is used to spray a harassing liquid from the jet nozzle toward the target satellite's reconnaissance lens under electrostatic pressure, thereby achieving a "blinding" effect on the target satellite's reconnaissance lens. Compared to existing directed energy anti-satellite technologies or parasitic soft-kill methods, the device not only has the advantages of simple structure, low manufacturing cost, and low energy consumption, but can also achieve long-term effective harassment by spraying the harassing liquid toward the target satellite's reconnaissance lens.

Description

Technical Field

[0001] The present invention relates to the field of microsatellite technology, and in particular to a space imperceptible harassment device and method. Background Art

[0002] Satellite "blinding" is an anti-satellite technology, which usually refers to the use of technical means to temporarily or permanently disable the functions of sensitive equipment such as satellite sensors (such as visual sensors), thereby weakening or destroying the satellite's reconnaissance, navigation, communication and other capabilities. This is crucial for satellite defense.

[0003] Existing satellite "blinding" methods primarily include directed-energy anti-satellite (DES) technology and parasitic satellite soft-kill. DES uses directed energy methods such as lasers, particle beams, and microwaves, launched from space or land, to damage various precision instruments in an opponent's space-based systems. Parasitic satellite soft-kill uses microsatellites deployed by a friendly party and capable of attaching to a target satellite. These can, according to the friendly party's instructions, interfere with the target satellite, temporarily disabling it and achieving the purpose of "blinding."

[0004] However, existing directed-energy anti-satellite technologies can directly damage target satellites or disable their sensitive electronic components, but they cannot achieve covert operations. Parasitic satellite soft-kill methods (such as microrobots and electronic jamming) temporarily disable target satellites by interfering with them, but they suffer from long deployment times, high energy consumption, and short strike times. When non-friendly satellite reconnaissance activities occur, they cannot effectively and immediately harass the target satellite for a long period of time. Furthermore, all of these anti-satellite technologies suffer from complex structural control, high manufacturing costs, and high energy consumption. Summary of the Invention

[0005] The problem solved by the present invention is how to achieve low-cost, imperceptible, immediate and long-term effective harassment of a target satellite.

[0006] To solve the above problems, on the one hand, the present invention provides a space-undetectable harassment device, including a micro-carrier satellite and a force-current multi-field coupling driver installed on the micro-carrier satellite. The micro-carrier satellite is used to drive the force-current multi-field coupling driver to approach a target satellite, and adjust the attitude so that the injection nozzle of the force-current multi-field coupling driver is aligned with the reconnaissance lens of the target satellite. The force-current multi-field coupling driver is used to spray harassing liquid from the injection nozzle towards the reconnaissance lens of the target satellite under the extrusion of electrostatic force.

[0007] Optionally, the force-current multi-field coupling driver includes a flexible insulating film, a flexible conductive electrode and a dielectric fluid, the flexible conductive electrode is used to be electrically connected to a power supply device, the dielectric fluid is stored in a cavity formed by the flexible insulating film, and the flexible conductive electrode is coated on the outer surface of the cavity formed by the flexible insulating film.

[0008] Optionally, the force-current multi-field coupling drivers are arranged in multiple rows in parallel.

[0009] Optionally, a drainage tube is further included, and the drainage tube is installed at the top of the cavity.

[0010] Optionally, a film or solid particles are provided on the drainage tube to achieve sealing of the drainage tube.

[0011] Optionally, the force-current multi-field coupling driver and the micro-carrier satellite are detachably connected via threaded fasteners or a mortise and tenon structure.

[0012] Optionally, a plurality of cavities formed by the flexible insulating film are arranged side by side, and the flexible conductive electrode is provided on the outer surface of any cavity.

[0013] Optionally, a plurality of the flexible conductive electrodes on the outer surface of the same side of the cavity are connected in series.

[0014] Optionally, it also includes a visual recognition system, a control center and a power control system. The visual recognition system is communicatively connected to the control center, the control center is communicatively connected to the power control, the power control system is used to be electrically connected to the power supply device, the visual recognition system is used to feedback the blinding condition of the reconnaissance lens, and the control center is used to control the output voltage of the power supply device through the power control system according to the feedback from the visual recognition system.

[0015] Compared with the prior art, the space-imperceptible harassment device of the present invention utilizes a force-current multi-field coupling driver installed on a micro-carrier satellite, which can utilize the advantages of light weight and small size of the micro-carrier satellite to reduce the cost of use and achieve imperceptible harassment. The micro-carrier satellite is used to drive the force-current multi-field coupling driver close to the target satellite, and the attitude is adjusted to align the ejection port of the force-current multi-field coupling driver with the reconnaissance lens of the target satellite. The force-current multi-field coupling driver is used to squeeze the target satellite through electrostatic force to spray harassing liquid from the ejection port at the reconnaissance lens of the target satellite, which can achieve a "blinding" effect on the reconnaissance lens of the target satellite. Compared with the existing directed energy anti-satellite technology or parasitic star soft kill method, the space-imperceptible harassment device of the present invention not only has the characteristics of simple structure, low manufacturing cost, low energy consumption, and instantaneousness, but also can achieve long-term effective harassment by spraying harassing liquid at the reconnaissance lens of the target satellite.

[0016] On the other hand, the present invention further provides a space-based harassment method, based on the space-based harassment device as described above, characterized in that it includes the following steps:

[0017] Confirm the target satellite position;

[0018] launching a micro-carrier satellite, wherein the micro-carrier satellite jets toward the target satellite;

[0019] Adjusting the attitude of the micro-carrier satellite so that the ejection port of the force-current multi-field coupling actuator is aligned with the target satellite reconnaissance lens;

[0020] The force-current multi-field coupling driver is powered to spray the harassing liquid toward the reconnaissance lens of the target satellite;

[0021] The force-current multi-field coupling driver is powered off, and the micro-carrier satellite returns.

[0022] Compared with the prior art, the space-undetectable harassment method of the present invention confirms the position of the target satellite; launches a micro-carrier satellite and sprays jets close to the target satellite; enables the micro-carrier satellite to transport the force-current multi-field coupling driver to the position of the target satellite, and adjusts the attitude of the micro-carrier satellite to approach the target satellite's reconnaissance lens; thereby enables the force-current multi-field coupling driver to be aligned with the target satellite's reconnaissance lens, and then powers up the force-current multi-field coupling driver to spray harassing liquid onto the target satellite's reconnaissance lens; the force-current multi-field coupling driver is powered off and the micro-carrier satellite returns, thereby achieving a "blinding" effect on the target satellite's reconnaissance lens, and can achieve an imperceptible, immediate, and long-term effective attack on the opponent's satellite's reconnaissance lens. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 Schematic diagram of the structure of a space-based silent harassment device in an embodiment of the present invention;

[0024] Figure 2 Schematic diagram of the structure of the force-current multi-field coupling driver in an embodiment of the present invention;

[0025] Figure 3 This is a schematic structural diagram of a drainage tube in an embodiment of the present invention in which a thin film is provided at the tube opening;

[0026] Figure 4 This is a schematic structural diagram of a drainage tube in an embodiment of the present invention having solid particles disposed therein;

[0027] Figure 5 is a schematic diagram of the harassing liquid being sprayed in an embodiment of the present invention;

[0028] Figure 6Schematic diagram of a space-based silent harassment device according to an embodiment of the present invention spraying harassing liquid onto a reconnaissance lens of a target satellite;

[0029] Figure 7 Flowchart of a space-based silent harassment method according to an embodiment of the present invention.

[0030] Description of reference numerals:

[0031] 1-Force-current multi-field coupling driver; 11-Power supply; 12-Flexible insulating film; 13-Flexible conductive electrode; 14-Dielectric fluid; 15-Drainage tube; 151-Solid particles; 2-Micro-carrier satellite; 3-Reconnaissance lens. DETAILED DESCRIPTION

[0032] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, specific embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0033] In the accompanying drawings, the Z-axis represents a vertical position, and the positive direction of the Z-axis (that is, the direction of the arrow on the Z-axis) represents the upper side, and the negative direction of the Z-axis (that is, the direction opposite to the positive direction of the Z-axis) represents the lower side; in the accompanying drawings, the X-axis represents a horizontal position, and the positive direction of the X-axis (that is, the direction of the arrow on the X-axis) represents the right side, and the negative direction of the X-axis (that is, the direction opposite to the positive direction of the X-axis) represents the left side; in the accompanying drawings, the Y-axis represents a front-to-back position, and the positive direction of the Y-axis (that is, the direction of the arrow on the Y-axis) represents the front side, and the negative direction of the Y-axis (that is, the direction opposite to the positive direction of the Y-axis) represents the rear side. It should also be noted that the aforementioned Z-axis, Y-axis, and X-axis are merely for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore should not be understood as limiting the present invention.

[0034] It should be noted that the terms "first," "second," and the like in the description and claims of the present invention and the accompanying drawings are used to distinguish similar objects and are not necessarily used to describe a specific order or precedence. It should be understood that the terms used in this manner are interchangeable where appropriate, such that the embodiments of the present invention described herein can be practiced in an order other than that illustrated or described herein.

[0035] Satellite "blinding" is an anti-satellite technology that generally refers to the use of technical means to temporarily or permanently disable the function of sensitive equipment such as satellite sensors (such as visual sensors), thereby weakening or destroying the satellite's reconnaissance, navigation, and communication capabilities. This is crucial for satellite defense. Existing "blinding" methods mainly include directed energy anti-satellite technology and parasitic satellite soft kill methods. Among them, directed energy anti-satellite technology uses directed energy methods such as lasers, particle beams, and microwaves, launched from space or land, to destroy various precision instruments in the opponent's space-based system. Parasitic satellite soft kill methods use micro-satellites launched by the enemy and capable of attaching to the target satellite. According to the corresponding instructions of the enemy, they can interfere with the target satellite and temporarily disable it, thereby achieving the purpose of "blinding".

[0036] However, while laser technology offers advantages such as high speed, high precision, and zero pollution, the laser beam must travel through the atmosphere before reaching space, resulting in energy attenuation and a decrease in target accuracy. It is also severely affected by weather. Particle beams are unaffected by atmospheric and weather interference, but suffer from the large size of particle accelerators, difficulty focusing, and fire control. Microwaves offer a wide range and long operational range, but their high power makes focusing and control of the microwave beam difficult. Furthermore, directed energy anti-satellite technologies such as lasers, particle beams, and microwaves are unable to achieve covert operations. Parasitic satellites, due to their small size, enable concealed deployment and precise strikes. However, existing soft-kill methods for parasitic satellites (such as microrobots and electronic jamming) temporarily disable target satellites by interfering with them, but suffer from long deployment times, high energy consumption, and short strike times. This makes it impossible to effectively and immediately harass the target satellite in the event of non-friendly satellite surveillance. Furthermore, all of these anti-satellite technologies suffer from complex structural control, high manufacturing costs, and high energy consumption.

[0037] Combine Figure 1 and Figure 6 As shown, the present invention provides a space-undetectable harassment device, comprising a micro-carrier satellite 2 and a force-current multi-field coupling driver 1 installed on the micro-carrier satellite 2. The micro-carrier satellite 2 is used to drive the force-current multi-field coupling driver 1 close to a target satellite, and adjust its attitude so that the injection nozzle of the force-current multi-field coupling driver 1 is aligned with the reconnaissance lens 3 of the target satellite. The force-current multi-field coupling driver 1 is used to spray a harassing liquid from the injection nozzle toward the reconnaissance lens 3 of the target satellite under the pressure of electrostatic force.

[0038] Specifically, microsatellites are a new generation of satellites with specific purposes. They feature high technological content, a short development cycle (approximately one year), low development costs (in the tens of millions of RMB), and the ability to be further networked. Their light weight and compact size make them important in military applications such as reconnaissance, communications, command, decision-making, logistics, and weaponry. Microsatellite-based harassment devices offer the advantages of concealed deployment, on-demand maneuverability, and controllable intensity, enabling imperceptible harassment of target satellites. Micro-carrier satellite 2 is a microsatellite comprising a recognition camera, antenna, attitude adjuster, star sensor, and thrusters. A force-current multi-field coupling actuator 1 is mounted on micro-carrier satellite 2. The ejection port of micro-carrier satellite 2, carrying force-current multi-field coupling actuator 1, is aimed at the target satellite's reconnaissance lens 3 to spray a harassing liquid at the target satellite's reconnaissance lens 3. Force-current multi-field coupling refers to the coupling of force, electric, and fluid fields. Force-current multi-field coupling actuator 1 is a type of actuator that achieves actuation through the multi-field coupling of force, electric, and fluid fields. Specifically, the position of the target satellite can be confirmed by means of space positioning technology or visual capture. After the position of the target satellite is confirmed, the micro-carrier satellite 2 is launched. The micro-carrier satellite 2 uses its own propulsion system to eject air to approach the target satellite. In the process of approaching the target satellite, the posture of the micro-carrier satellite 2 is continuously adjusted to gradually approach the reconnaissance lens 3 of the target satellite, so that the injection port of the force-current multi-field coupling driver 1 is aligned with the reconnaissance lens 3 of the target satellite. Then, the force-current multi-field coupling driver 1 is powered on, and through the squeezing of electrostatic force, the force-current multi-field coupling driver 1 sprays the harassing liquid onto the reconnaissance lens 3 of the target satellite, as shown in FIG. Figure 6 As shown, after the reconnaissance lens 3 of the target satellite is shielded, the force-current multi-field coupling driver 1 is powered off, and the micro-carrier satellite 2 returns.

[0039] Therefore, in this embodiment, the force current multi-field coupling driver 1 is installed on the micro-carrier satellite 2, which can take advantage of the light weight and small size of the micro-carrier satellite 2 to reduce the cost of use and achieve non-sensing harassment. The micro-carrier satellite 2 is used to drive the force current multi-field coupling driver 1 close to the target satellite, and the attitude is adjusted to align the injection port of the force current multi-field coupling driver 1 with the reconnaissance lens 3 of the target satellite. The force current multi-field coupling driver 1 is used to squeeze the electrostatic force to spray the harassing liquid from the injection port to the reconnaissance lens 3 of the target satellite, which can achieve a "blinding" effect on the reconnaissance lens 3 of the target satellite. Compared with the existing directed energy anti-satellite technology or parasitic star soft kill method, it not only has the characteristics of simple structure, low manufacturing cost, low energy consumption, and instant, but also can achieve long-term effective harassment by spraying the harassing liquid at the reconnaissance lens 3 of the target satellite.

[0040] Optionally, combined Figures 1 to 5As shown, the force-current multi-field coupling driver 1 includes a flexible insulating film 12, a flexible conductive electrode 13 and a dielectric fluid 14. The flexible conductive electrode 13 is used to be electrically connected to the power supply device 11. The dielectric fluid 14 is stored in the cavity formed by the flexible insulating film 12, and the flexible conductive electrode 13 is coated on the outer surface of the cavity.

[0041] Specifically, the dielectric liquid 14 is the harassing liquid. The dielectric liquid 14 can be a non-transparent liquid such as black ink to physically block the opponent's detection lens 3, or it can be a chemical liquid that can react with the opponent's detection lens 3 to chemically destroy the opponent's detection lens 3. The dielectric liquid 14 is sprayed on the detection lens 3 to "blind" the detection lens 3. The flexible insulating film 12 can be made of any flexible insulating material, and the flexible insulating film 12 is non-conductive and can be deformed. There is no chemical reaction between the flexible insulating film 12 and the dielectric liquid 14. The flexible insulating film 12 can be formed into cavities of different shapes according to needs, such as Figure 5 As shown, the flexible insulating film 12 is formed into a cylindrical structure. The space enclosed by the flexible insulating film 12 forms a cylindrical cavity for storing the dielectric fluid 14 within the cavity. The cavity formed by the flexible insulating film 12 is installed on the micro-launch satellite 2. The flexible conductive electrode 13 can be made of any flexible conductive material. The outer surface of the cavity formed by the flexible insulating film 12 refers to the surface of the flexible insulating film 12 located outside the cavity. The flexible conductive electrode 13 is coated on the outer surface of the cavity (the flexible conductive electrode 13 can also be installed on the outer surface of the cavity by screen printing, electroplating, chemical etching / deposition, or inkjet printing. The shape of the flexible conductive electrode 13 can be adaptively adjusted according to actual needs). Two flexible conductive electrodes 13 are respectively coated on the outer surfaces of the front and rear sides of the cavity, and the two flexible conductive electrodes 13 are not conductive. The power supply device 11 is a power supply device capable of outputting high voltage, including a low-voltage power supply and a high-voltage module (high-voltage amplifier). The positive and negative voltage output ends of the low-voltage power supply are converted into high-voltage outputs by the high-voltage module (high-voltage amplifier), that is, the voltage is boosted from a few volts to several thousand volts and then powered on to the two flexible conductive electrodes 13, so that the positive and negative charges on the two flexible conductive electrodes 13 attract each other to generate electrostatic adsorption force. Under the action of the electrostatic adsorption force, the two flexible conductive electrodes 13 approach each other, causing the cavity to be gradually compressed, causing the dielectric fluid 14 inside the cavity to be ejected.

[0042] In this way, the flexible conductive electrode 13 is used to be electrically connected to the power supply device 11, the dielectric fluid 14 is stored in the cavity formed by the flexible insulating film 12, and the flexible conductive electrode 13 is coated on the outer surface of the cavity. After the power supply device 11 applies high voltage to the flexible conductive electrodes 13, the positive and negative charges on the two flexible conductive electrodes 13 can attract each other to generate electrostatic adsorption force. Under the action of the electrostatic adsorption force, the two flexible conductive electrodes 13 approach each other, so that the cavity formed by the flexible insulating film 12 is gradually compressed, thereby realizing the concentrated spraying of the dielectric fluid 14, so that the dielectric fluid 14 can quickly "blind" the detection lens 3, thereby improving the "blinding" efficiency of the dielectric fluid 14.

[0043] Optionally, combined Figure 1 As shown, the force-current multi-field coupling driver 1 is arranged in multiple rows in parallel.

[0044] Specifically, five force-current multi-field coupling drivers 1 are provided, and the five force-current multi-field coupling drivers 1 are arranged side by side along the length direction of the micro-carrier satellite 2 .

[0045] In this way, by using the force-current multi-field coupling drivers 1 to be arranged in multiple rows in parallel, the detection lens 3 or even multiple detection lenses 3 can be contaminated more thoroughly.

[0046] Optionally, combined Figures 1 to 5 As shown, the force-current multi-field coupling driver 1 further includes a drainage tube 15 , which is installed at the top of the cavity.

[0047] Specifically, in conjunction with the foregoing, drainage tube 15 is located at the upper end of the cavity formed by flexible insulating film 12. Drainage tube 15 communicates with the cavity, and the upper end of drainage tube 15 serves as the injection port of force-current multi-field coupling actuator 1. Thus, by vertically mounting drainage tube 15 at the top of the cavity, it can guide the injection of dielectric fluid 14, thereby improving injection accuracy.

[0048] Optionally, combined Figure 3 and Figure 4 As shown, a film or solid particles 151 is provided on the drainage tube 15 to achieve sealing of the cavity formed by the flexible insulating film 12 .

[0049] Specifically, a thin film can be provided at the connection between the drainage tube 15 and the cavity formed by the flexible insulating film 12. When not spraying, the thin film seals the cavity formed by the flexible insulating film 12. During spraying, the harassing liquid can flush the thin film open, allowing spraying. Alternatively, solid particles 151 can be provided within the drainage tube 15. When not spraying, the solid particles 151 seal the cavity formed by the flexible insulating film 12. During spraying, the harassing liquid can flush the solid particles 151 out of the interior of the drainage tube 15, allowing spraying.

[0050] In this way, a film or solid particles 151 is provided on the drainage tube 15 to achieve the sealing of the cavity formed by the flexible insulating film 12, so that when there is no need to spray the harassing liquid, the film or solid particles 151 can seal the cavity formed by the flexible insulating film 12, thereby improving the stability of the harassing liquid stored in the cavity formed by the flexible insulating film 12.

[0051] Optionally, the force-current multi-field coupling driver 1 and the micro-carrier satellite 2 are detachably connected.

[0052] Specifically, for example, the force-current multi-field coupling driver 1 and the micro-launch satellite 2 are connected by threaded fasteners such as bolts made by 3D printing or a mortise and tenon structure.

[0053] In this way, the detachable connection between the force-current multi-field coupling driver 1 and the micro-carrier satellite 2 can not only improve the stability of the connection between the force-current multi-field coupling driver 1 and the micro-carrier satellite 2, but also facilitate the replacement of the force-current multi-field coupling driver 1.

[0054] Optionally, combined Figure 1 As shown, a plurality of cavities formed by the flexible insulating film 12 are arranged side by side, and a flexible conductive electrode 13 is provided on the outer surface of each cavity.

[0055] It should be noted that, when a plurality of cavities formed by the flexible insulating film 12 are arranged side by side, the drainage tube 15 may be provided on only one cavity located in the middle.

[0056] Specifically, five cavities formed by the flexible insulating films 12 are arranged side by side, and the cavities formed by the five flexible insulating films 12 are lined up along the width direction of the micro-carrier satellite 2. The cavities formed by the five flexible insulating films 12 are connected in sequence, and the flexible conductive electrodes 13 on the two front cavities and the flexible conductive electrodes 13 on the two rear cavities are symmetrical about the axis of the drainage tube 15, so that the dielectric fluid 14 in the four front and rear cavities flows toward the middle cavity.

[0057] In this way, multiple cavities formed by the flexible insulating film 12 are arranged side by side, and a flexible conductive electrode 13 is provided on the outer surface of each cavity, which can increase the carrying capacity of the dielectric liquid 14, thereby being able to more thoroughly contaminate the detection lens 3 or even contaminate multiple detection lenses 3.

[0058] Optionally, combined Figure 1 and Figure 5 As shown, the flexible conductive electrodes 13 on the outer surfaces of the same side of the multiple cavities are connected in series.

[0059] Specifically, in combination with the foregoing, the flexible conductive electrodes 13 on the outer surface of the same side of the five cavities (the five flexible conductive electrodes 13 on the left side of the five cavities are connected in series, and the five flexible conductive electrodes 13 on the right side of the five cavities are connected in series) can be connected in series in sequence through wires.

[0060] In this way, by connecting the flexible conductive electrodes 13 on the outer surfaces of multiple cavities in series, only one power supply device 11 is needed to achieve synchronous compression of multiple cavities, thereby significantly improving the flow efficiency of the dielectric fluid 13 and further improving the injection efficiency of the harassing liquid.

[0061] Optionally, the space-undetectable harassment device also includes a visual recognition system, a control center, and a power control system. The visual recognition system is communicatively connected to the control center, and the control center is communicatively connected to the power control. The power control system is used to be electrically connected to the power supply device 11. The visual recognition system is used to feedback the blinding condition of the detection lens 3, and the control center is used to control the output power of the power supply device 11 through the power control system according to the feedback from the visual recognition system.

[0062] Specifically, the visual recognition system identifies the image after the dielectric liquid covers the detection lens 3, and transmits the image to the control center. The control center controls the output voltage of the power supply device 11 according to the image transmitted by the visual recognition system. For example, according to the image, the dielectric liquid does not completely cover the detection lens 3, the control center increases the output voltage of the power supply device 11 through the power control system, thereby achieving further compression of the cavity, that is, spraying more dielectric liquid to cover the uncovered area on the detection lens 3; or, according to the image, the dielectric liquid has completely covered the detection lens 3, the control center reduces the output voltage of the power supply device 11 through the power control system until it is zero, that is, the power supply device 11 no longer applies high voltage to the flexible conductive electrode 13 to reduce energy waste.

[0063] In this way, the visual recognition system is connected to the control center through communication, and the control center is connected to the power control communication. The power control system is used to be electrically connected to the power supply device 11. The visual recognition system is used to feedback the blinding situation of the detection lens 3. The control center is used to control the output voltage of the power supply device 11 through the power control system according to the feedback from the visual recognition system. The visual recognition system can capture and feedback the situation of the dielectric fluid covering the detection lens 3 in time, so that the control center can easily regulate the output voltage of the power supply device 11 through the power control system, thereby realizing the adjustable output voltage of the power supply device 11. It can not only improve the flexibility of use of the power supply device 11, but also reduce energy waste when the dielectric fluid completely covers the detection lens 3.

[0064] Combine Figure 7 As shown, an embodiment of the present invention further provides a space-sensing harassment method, based on the above-mentioned space-sensing harassment device, comprising the following steps:

[0065] Step 1: Confirm the target satellite position;

[0066] Step 2: launching the micro-carrier satellite 2, which jets towards the target satellite;

[0067] Step 3: Adjust the attitude of the micro-carrier satellite 2 so that the ejection port of the force-current multi-field coupling driver 1 is aligned with the target satellite reconnaissance lens 3;

[0068] Step 4: Powering up the force-current multi-field coupling driver 1 to spray the harassing liquid toward the reconnaissance lens 3 of the target satellite;

[0069] Step 5: The force-current multi-field coupling driver 1 is powered off and the micro-launch satellite 2 returns.

[0070] Specifically, the position of the target satellite can be confirmed through space positioning technology or visual capture. After the position of the target satellite is confirmed, the micro-carrier satellite 2 is launched. The micro-carrier satellite 2 uses its own thrusters and other means to jet to approach the target satellite. In the process of approaching the target satellite, the attitude of the micro-carrier satellite 2 is continuously adjusted to gradually approach the reconnaissance lens 3 of the target satellite. Then, the force-current multi-field coupling driver 1 is powered on, and the harassing liquid is sprayed onto the reconnaissance lens 3 of the target satellite. After the reconnaissance lens 3 of the target satellite is blocked, the force-current multi-field coupling driver 1 is powered off, and the micro-carrier satellite 2 returns.

[0071] In this way, by confirming the position of the target satellite; launching the micro-carrier satellite 2, and jetting close to the target satellite; the micro-carrier satellite 2 can transport the force-current multi-field coupling driver 1 to the position of the target satellite, and adjust the attitude of the micro-carrier satellite 2 to approach the target satellite reconnaissance lens 3; thereby, the force-current multi-field coupling driver 1 can be aimed at the reconnaissance lens 3 of the target satellite, and then the force-current multi-field coupling driver 1 is powered on, and the harassing liquid is sprayed to the reconnaissance lens 3 of the target satellite; the force-current multi-field coupling driver 1 is powered off, and the micro-carrier satellite 2 returns, thereby achieving a "blinding" effect on the reconnaissance lens 3 of the target satellite, and being able to achieve an imperceptible, immediate, and long-term effective attack on the opponent's satellite reconnaissance lens.

[0072] Although the present disclosure is disclosed as above, the protection scope of the present disclosure is not limited thereto. Those skilled in the art may make various changes and modifications without departing from the spirit and scope of the present disclosure, and these changes and modifications will fall within the protection scope of the present invention.

Claims

1. A space-sensing harassment device, characterized in that: The invention comprises a micro-carrier satellite (2) and a force-current multi-field coupling driver (1) installed on the micro-carrier satellite (2), wherein the micro-carrier satellite (2) is used to drive the force-current multi-field coupling driver (1) to approach a target satellite, and adjust the attitude so that the ejection port of the force-current multi-field coupling driver (1) is aligned with the detection lens (3) of the target satellite, and the force-current multi-field coupling driver (1) is used to eject a harassing liquid from the ejection port to the detection lens (3) of the target satellite under the pressure of electrostatic force; the force-current multi-field coupling driver (1) comprises a flexible insulating film (12 ), a flexible conductive electrode (13) and a dielectric liquid (14), wherein the flexible conductive electrode (13) is used to be electrically connected to the power supply device (11), the dielectric liquid (14) is stored in the cavity formed by the flexible insulating film (12), and the flexible conductive electrode (13) is coated on the outer surface of the cavity formed by the flexible insulating film (12); and further comprising a drainage tube (15), wherein the drainage tube (15) is installed at the top end of the cavity; and a film or solid particles (151) are provided on the drainage tube (15) to achieve sealing of the cavity formed by the flexible insulating film (12).

2. The space-undetectable harassment device according to claim 1, characterized in that: The force-current multi-field coupling driver (1) is arranged in multiple rows in parallel.

3. The space-undetectable harassment device according to claim 1, characterized in that: The force-current multi-field coupling driver (1) and the micro-carrier satellite (2) are detachably connected.

4. The space-undetectable harassment device according to claim 1, characterized in that: A plurality of cavities formed by the flexible insulating film (12) are arranged side by side, and the flexible conductive electrode (13) is provided on the outer surface of any cavity.

5. The space-undetectable harassment device according to claim 4, characterized in that: The flexible conductive electrodes (13) on the outer surface of the same side of the cavity are connected in series.

6. The space-undetectable harassment device according to claim 1, characterized in that: The system further comprises a visual recognition system, a control center and a power control system, wherein the visual recognition system is in communication connection with the control center, the control center is in communication connection with the power control system, the power control system is used to be electrically connected to the power supply device (11), the visual recognition system is used to feedback the blinding condition of the detection lens (3), and the control center is used to control the output voltage of the power supply device (11) through the power control system according to the condition fed back by the visual recognition system.

7. A space-based harassment method, based on the space-based harassment device according to any one of claims 1 to 6, characterized in that: The steps include: Confirm the target satellite position; launching a micro-carrier satellite (2), wherein the micro-carrier satellite (2) jets toward the target satellite; Adjusting the attitude of the micro-carrier satellite (2) so that the ejection port of the force-current multi-field coupling driver (1) is aligned with the target satellite reconnaissance lens (3); The force-current multi-field coupling driver (1) is powered to spray the harassing liquid toward the reconnaissance lens (3) of the target satellite; The force-current multi-field coupling driver (1) is powered off, and the micro-carrier satellite (2) returns.

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