An in-situ molecular cleaning and particulate dust removal system for space optical payloads

Abstract

This invention relates to the field of contamination control technology for space optical payloads, specifically providing an in-situ molecular cleaning and particulate dust removal system for space optical payloads. The system includes an electrode array and a multi-mode power controller. The electrode array comprises at least two electrode groups with electrodes in different groups interleaved. The multi-mode power controller is configured to: in a first mode, provide direct current to the electrode array to remove organic molecular contaminants from the surface of the optical payload through high-energy ion bombardment; and in a second mode, provide multiphase alternating current with a phase difference to different electrode groups in the electrode array to push particulate contaminants away from the optical payload surface through a traveling wave electric field. This invention fundamentally solves the problem of combined oil film and particulate contamination that traditional technologies cannot handle.

Description

Technical Field

[0001] This invention belongs to the field of space optical payload pollution control technology, and particularly relates to an in-situ molecular cleaning and particulate dust removal system for space optical payloads. Background Technology

[0002] Space optical payloads (such as remote sensing cameras, laser communication terminals, and star sensors) face extremely severe challenges of "compound contamination" during their on-orbit operation. This contamination mainly consists of two parts: Molecular contaminants: Organic substances (such as silicone oil and phthalates) originating from satellite material venting or propellant plumes can deposit on optical surfaces to form an "oil film" and cross-link and solidify under ultraviolet irradiation, causing the lens to become blurry.

[0003] Particulate contaminants: originating from acoustic and vibrational dust, micrometeorite ejecta, or mechanical wear debris (such as metal shavings and mineral dust) from the launch section.

[0004] For molecular contamination: Existing technologies mainly employ "on-orbit heating (heating)" or "conventional ion cleaning." Heating methods are energy-intensive and prone to thermal deformation of optical components, especially for precision optical devices used for extended periods, affecting their stability. While conventional ion cleaning can remove oil films, it cannot move inorganic particles and may even cause "cold welding" between particles and the substrate due to etching. For particulate contamination: Existing technologies mainly employ "electro-driven dust removal screens (EDS)." This involves processing forked electrodes on the surface and applying multiphase AC high-voltage electricity to generate a traveling wave electric field that pushes particles away. However, existing EDS technology has a fatal flaw: it is only effective for "dry, loose" dust. In actual space environments, particles typically have a layer of molecular contaminants (oil film) at their base, firmly adhering them to the mirror surface (adhesion increases by several orders of magnitude). The electrostatic thrust provided by EDS cannot overcome this strong capillary and van der Waals force, leading to dust removal failure. Furthermore, traditional EDS electrodes are prone to oxidation and failure in the atomic oxygen environment of space, or the DC high voltage can cause electrode material to sputter and contaminate the mirror surface.

[0005] In summary, no single system can currently solve the most challenging complex contamination problem of "oil film adhering to dust." Oil removal equipment cannot remove particles, and dust removal equipment cannot overcome the adhesion of the oil film, resulting in "incomplete removal" or "the more it is removed, the dirtier it becomes." Furthermore, simultaneously installing two independent cleaning systems (one chemical cleaning and one physical dust removal) would significantly increase the satellite's size, weight, and power consumption, and could potentially obstruct the optical aperture. Summary of the Invention

[0006] In view of this, the present invention aims to provide an in-situ molecular cleaning and particulate dust removal system for space optical payloads. By using the same electrode array and timing modulation of the multi-mode power supply, it sequentially realizes two functions: DC high-voltage ion decomposition of organic oil film and AC traveling wave cleaning of particulate contaminants. Without increasing the hardware burden, it utilizes in-situ space resources to completely solve the problem of compound pollution caused by the mixing of oil film and particles.

[0007] To achieve the above objectives, the technical solution created by this invention is implemented as follows: This invention provides an in-situ molecular cleaning and particulate dust removal system for space optical payloads, comprising: An electrode array disposed on the surface of an optical load, the electrode array comprising at least two electrode groups, wherein the electrodes in different electrode groups are staggered. A multi-mode power controller, used to output DC or multi-phase AC power to an electrode array; The multi-mode power controller is configured as follows: In the first mode, the multi-mode power controller provides DC power to the electrode array, which generates an ion acceleration electric field to remove organic molecular contaminants from the surface of the optical payload by high-energy ion bombardment. In the second mode, the multi-mode power controller provides multiphase alternating current with phase difference to different electrode groups in the electrode array. The electrode array generates a traveling wave electric field, which pushes particulate contaminants on the surface of the optical payload away from the optical payload.

[0008] Preferably, the lower surface of the electrode array is provided with an insulating support component, and the electrode array is connected to the optical load surface through the insulating support component.

[0009] Preferably, the electrode array is connected to the insulating support component via a nano-adhesion layer.

[0010] Preferably, an antioxidant layer is deposited on the upper surface of the electrode array to prevent the electrode array from being oxidized by adsorbing atomic oxygen.

[0011] Preferably, the electrode array is a forked conductive array, including phase A electrode group, phase B electrode group and phase C electrode group.

[0012] Preferably, when the optical load is a transmissive optical element, the electrode array uses an ITO transparent conductive film; when the optical load is a reflective optical element, the electrode array uses an ultrathin metal mesh.

[0013] Preferably, in the first mode, the multi-mode power controller provides negative DC power to the electrode array. The electrode array acts as a cathode to adsorb and accelerate oxygen ions. The oxygen ions bombard the organic long chains of organic molecular pollutants on the surface of the optical payload, forming organic fragments. Atomic oxygen oxidizes the organic long chains into gas and removes them.

[0014] Preferably, in the second mode, the multi-mode power controller provides three-phase AC power to the electrode array, and the particulate contaminants on the surface of the optical load are induced to become charged, and are subjected to the combined force of Coulomb force and dielectric force, jumping or sliding along the traveling wave electric field.

[0015] Preferably, a collection groove is provided at the edge of the optical payload for collecting particulate pollutants.

[0016] Preferably, the electrode array is also connected to a bleed resistor. During the in-situ molecular cleaning and particle dust removal process, the multi-mode power controller first executes the first mode, then executes the second mode, and finally the multi-mode power controller stops supplying power and discharges the electrode array to ground through the bleed resistor to eliminate the residual charge on the electrode array.

[0017] Compared with the prior art, the present invention can achieve the following beneficial effects: This invention proposes for the first time a dual-mode synergistic mechanism of "first ion debonding, then traveling wave cleaning". By accelerating oxygen ion bombardment with DC high voltage, the organic oil film at the bottom of the particles is completely decomposed and removed, decoupling the oil film adhesion force on the particles. Then, the AC traveling wave electric field is used to directionally push the particles that have lost their adhesion force away from the optical load. This effectively improves the removal rate of sticky dust mixed with particles and oil film, and fundamentally solves the problem of "oil film + particle" composite pollution that traditional EDS technology cannot handle.

[0018] This invention utilizes a single electrode array, powered by multi-mode power timing modulation, first DC then AC, and first chemical debonding then physical cleaning, achieving the multiplexing of both ion chemical decomposition and physical transport functions. Without increasing the hardware burden, it significantly reduces the resource consumption of space optical payloads in terms of volume, weight, and power consumption, meeting the stringent constraints of spacecraft platforms for payloads.

[0019] This invention features an innovative electrode array design. An anti-oxidation layer effectively resists corrosion from atomic oxygen in space, preventing the oxidation and failure of traditional exposed metal electrodes under DC high-voltage conditions. Furthermore, an insulating support assembly isolates the electrode array from the optical payload surface, ensuring safe operation under the high-voltage electric field while guaranteeing the stability and durability of the electrodes. In addition, suitable electrode arrays are designed for both transmissive and reflective optical payloads.

[0020] This invention utilizes electric field force to remove contaminants in a non-contact manner. Compared with cleaning methods such as mechanical wiping or high-pressure jet cleaning, the electric field cleaning process has no mechanical friction, no risk of scratches, and will not cause any physical damage to precision optical surfaces.

[0021] This invention is not only applicable to space optical payloads, but can also be extended to other scenarios that require in-situ molecular cleaning and particle dust removal. Attached Figure Description

[0022] The accompanying drawings, which form part of this invention, are used to provide a further understanding of the invention. The illustrative embodiments and descriptions of the invention are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings: Figure 1 This is a schematic diagram of the structure of the in-situ molecular cleaning and particulate dust removal system for space optical payloads provided in an embodiment of the present invention; Figure 2 This is a microscopic cross-sectional structure diagram of an antioxidant electrode provided according to an embodiment of the present invention; Figure 3 This is a system operating timing and voltage waveform diagram provided according to an embodiment of the present invention, wherein (a) represents the operating timing and waveform of phase A voltage, (b) represents the operating timing and waveform of phase B voltage, and (c) represents the operating timing and waveform of phase C voltage; Figure 4 This is a schematic diagram illustrating the principle of DC mode ion bombardment for degreasing film provided in an embodiment of the present invention; Figure 5 This is a schematic diagram illustrating the principle of AC mode traveling wave electric field transport of particulate pollutants according to an embodiment of the present invention.

[0023] The reference numerals in the figures include: Optical payload 1, electrode array 2, A-phase electrode group 21, B-phase electrode group 22, C-phase electrode group 23, multi-mode power controller 3, collection tank 4, anti-oxidation layer 5, nano-adhesion layer 6, insulating support component 7. Detailed Implementation

[0024] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only for explaining the invention and do not constitute a limitation thereof. Similar elements in different embodiments are referred to by associated similar element reference numerals. In the following embodiments, many details are described to facilitate a better understanding of the invention. However, those skilled in the art will readily recognize that some features may be omitted in different situations, or may be replaced by other elements, materials, or methods. In some cases, some operations related to the invention are not shown or described in the specification. This is to avoid obscuring the core parts of the invention with excessive description. For those skilled in the art, detailed description of these related operations is not necessary; the relevant operations can be fully understood based on the description in the specification and general technical knowledge in the art.

[0025] It should be noted that, unless otherwise specified, the embodiments and features described in this invention can be combined to form various implementations. Furthermore, the order of the steps or actions in the method description can be changed or adjusted in a manner readily apparent to those skilled in the art. Therefore, the various orders in the specification and drawings are merely for the clear description of a particular embodiment and do not imply a mandatory order, unless otherwise stated that a particular order must be followed.

[0026] 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," and "counterclockwise," etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are 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, and therefore should not be construed as a limitation on this invention. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, features defined with "first," "second," etc., may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0027] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; 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; and they can refer to the internal connection of two components. Those skilled in the art will understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0028] The invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0029] Please see Figure 1 In one embodiment of the present invention, an in-situ molecular cleaning and particulate dust removal system for space optical payloads is provided, comprising: An electrode array 2 is disposed on the surface of the optical load 1. The electrode array 2 includes at least two electrode groups, and the electrodes in the different electrode groups are staggered. A multi-mode power controller 3 is used to output DC power or multi-phase AC power to the electrode array 2; The multi-mode power controller 3 is configured as follows: In the first mode, the multi-mode power controller 3 provides DC power to the electrode array 2, and the electrode array 2 generates an ion acceleration electric field to remove organic molecular contaminants from the surface of the optical payload 1 by high-energy ion bombardment. In the second mode, the multi-mode power controller 3 provides multi-phase alternating current with phase difference to different electrode groups in the electrode array 2. The electrode array 2 generates a traveling wave electric field, which pushes particulate contaminants on the surface of the optical payload 1 away from the optical payload 1.

[0030] The electrode array 2 is directly attached to the surface of the optical payload 1, employing a finger-shaped conductive array, and is powered by a multi-mode power controller 3. The electrode array 2 includes three electrode groups: phase A electrode group 21, phase B electrode group 22, and phase C electrode group 23, with the electrodes in these groups arranged in an alternating pattern. The multi-mode power controller 3 is connected to the electrode array 2 and features dual output modes: "high-voltage DC" and "multi-phase high-voltage AC." It can switch between these modes sequentially according to cleaning requirements, achieving both molecular cleaning and particulate dust removal. In the multi-phase high-voltage AC power supply mode, phase A electrode group 21, phase B electrode group 22, and phase C electrode group 23 are respectively connected to different output terminals of the multi-mode power controller 3.

[0031] Different electrode arrays 2 need to be designed for optical payloads 1 with different optical properties. When the optical payload 1 is a transmissive optical element, the electrode array 2 needs to have high transmittance to avoid affecting the performance of the optical payload 1. Specifically, an ITO transparent conductive film can be prepared on the surface of the transmissive optical payload 1 by magnetron sputtering, and then a forked pattern, i.e., the electrode array 2, can be etched on the ITO transparent conductive film by photolithography. Each electrode in the electrode array 2 has a width of 5-20 micrometers, an electrode spacing of 100-500 micrometers, and a transmittance of greater than 90%.

[0032] When the optical payload 1 is a reflective optical element, the electrode array 2 adopts an ultra-thin metal mesh. The material of the ultra-thin metal mesh is gold or platinum, and the electrode linewidth in the ultra-thin metal mesh is less than 5 micrometers to ensure that the imaging quality is not affected.

[0033] As an optional embodiment, such as Figure 2 As shown, to ensure safe operation under high voltage and guarantee the stability and durability of the electrodes, in this embodiment of the invention, the electrode array 2 is connected to the surface of the optical load 1 via an insulating support component 7. The insulating support component 7 is made of a flexible insulating material, such as PI or PET. The electrode array 2 is connected to the insulating support component 7 via a nano-adhesion layer 6, which can be made of Cr or Ti.

[0034] As an optional embodiment, when the multimodal power controller 3 operates in the first mode (molecular cleaning mode), the electrode array 2 is subjected to a negative DC high voltage. At this time, the electrodes act as cathodes, attracting and accelerating oxygen ions (O2) in the space environment. + The electrode surface is exposed to atomic oxygen. If the electrode surface is directly exposed to atomic oxygen, conventional metals or transparent conductive oxides are prone to oxidation, leading to an increase in the resistivity of the electrode array 2. In severe cases, this may cause secondary contamination of the optical surface or electrode failure. To address this, this invention proposes for the first time to deposit a dense platinum (Pt) or iridium (Ir) layer with a thickness of 5-10 nm on the surface of the electrode array 2 as an anti-oxidation layer 5. Platinum and iridium can form an extremely thin, self-limiting oxide layer in an atomic oxygen environment. This oxide layer is dense and stable, effectively preventing further diffusion of atomic oxygen inward, thereby protecting the underlying electrode array 2 from oxidation and corrosion.

[0035] The multi-mode power controller 3 includes a DC module and an AC module. The DC module outputs adjustable DC power from -200V to -1000V and features a constant current limiting function of <1mA to ensure the operational stability of the electrode array 2. The AC module outputs three-phase AC power with an amplitude of 500V to 1000V, specifically capable of outputting multi-phase square waves or sine waves with frequencies from 1Hz to 100Hz to generate a traveling wave electric field for particulate matter removal. The control timing of the multi-mode power controller 3 is as follows: Figure 3 As shown, where Figure 3 (a) shows the operating timing and waveform of phase A voltage. Figure 3 (b) shows the operating timing and waveform of phase B voltage. Figure 3 (c) shows the operating timing and waveform of the C-phase voltage. The first mode in the figure is the DC high-voltage mode (T1), in which oxygen ions are adsorbed and charged. The multi-mode power controller 3 provides negative high voltage to the A-phase electrode group 21, B-phase electrode group 22, and C-phase electrode group 23. The second mode is the three-phase AC pulse mode (T2). The multi-mode power controller 3 provides three-phase AC power with phase difference to the A-phase electrode group 21, B-phase electrode group 22, and C-phase electrode group 23. The traveling wave electric field formed on the surface of the optical load 1 has a repulsive effect on charged particles, realizing the directional transport of particulate pollutants. Furthermore, the multi-mode power controller 3 also integrates microampere-level current limiting protection and soft-start function to prevent destructive breakdown in a vacuum plasma environment.

[0036] When optical payload 1 performs in-situ molecular cleaning and particle removal, multimodal power controller 3 is configured to execute the first mode first, and then the second mode. The specific workflow and timing are as follows: First, when the satellite reaches an orbital segment with a high atomic oxygen flux and the onboard monitoring system detects a decrease in the performance of optical payload 1, it is considered that the surface of optical payload 1 on the satellite is contaminated, resulting in a decrease in imaging quality. At this time, the satellite platform or payload controller sends a start command to the multi-mode power controller 3 of this embodiment of the invention, and the system enters the cleaning state.

[0037] To address the challenge of handling complex contamination with a single technology, the multi-modal power controller 3 of this invention is configured with two modes: DC power supply followed by AC power supply, and chemical debinding followed by physical cleaning. Without increasing hardware burden, it utilizes in-situ space resources to thoroughly resolve the problem of complex contamination caused by the mixing of oil film and particles. Specifically, as shown... Figure 4 As shown, the multi-mode power controller 3 is first configured in the first mode, and its output is switched to DC output mode. The multi-mode power controller 3 short-circuits the A-phase electrode group 21, the B-phase electrode group 22, and the C-phase electrode group 23 and applies a uniform negative DC high voltage (e.g., -500V). Under this voltage, the electrode array 2 acts as the cathode, and the electrostatic field it generates extends to the space plasma sheath layer on the surface of the optical payload 1. Under the action of the ion acceleration electric field, it adsorbs and accelerates oxygen ions (O2) in the environment. + High-energy oxygen ions bombard the optical surface of optical payload 1 with a certain kinetic energy. The energy of the high-energy oxygen ions is sufficient to break the carbon-carbon bonds (C-C bonds) in the molecular chains of organic contaminants (i.e., organic oil film) covering the bottom of dust particles, causing the oil film to break or carbonize. Subsequently, the highly oxidizing atomic oxygen reacts with the organic fragments generated by the bombardment of the oil film by high-energy oxygen ions, oxidizing them into gaseous products and releasing them. The organic oil film that acts as "glue" to adhere the particles to the surface of optical payload 1 is completely removed by high-energy ion bombardment. The bonding force between the particles and the surface of optical payload 1 is significantly reduced from the initial strong adhesion state (micro Newton level) to a weak physical contact state (nano Newton level), creating the preconditions for subsequent particle removal.

[0038] like Figure 5As shown, the multi-mode power controller 3 is then configured in a second mode, switching its output to AC output mode. The multi-mode power controller 3 sequentially outputs three-phase AC high voltage (phase difference 120°) with a fixed phase difference to the A-phase electrode group 21, B-phase electrode group 22, and C-phase electrode group 23. In the figure, A represents the electrode in the A-phase electrode group 21, B represents the electrode in the B-phase electrode group 22, and C represents the electrode in the C-phase electrode group 23. At this time, the electrode array 2 generates a traveling wave potential well on the surface of the optical load 1, which moves directionally along the electrode arrangement direction. Particulate contaminants on the surface of the optical load 1 are induced to become charged in the traveling wave electric field, thus experiencing the combined force of Coulomb force and dielectric electrophoresis (DEP). This combined force propels the particulate contaminants to jump or slide along the traveling wave propagation direction. By rationally designing the electrode arrangement direction in the electrode array 2, loose particulate contaminants can be directionally pushed into the pre-set collection groove 4 at the edge of the optical load 1. The geometry of the collection groove 4 effectively captures and accommodates the particulate contaminants, preventing them from drifting back to the optical load 1.

[0039] After completing in-situ molecular cleaning and particle dust removal, the multimodal power controller 3 resets and shuts off the voltage output. To eliminate residual charge on the electrode array 2, a bleed resistor is also connected to the electrode array 2. After the operation is completed, the electrode array 2 is grounded through the bleed resistor to discharge, eliminating residual charge and preventing the Coulomb force of the residual charge from attracting new dust, which would cause the optical surface of the optical payload 1 to be contaminated again.

[0040] The in-situ molecular cleaning and particulate dust removal system for space optical payloads in this invention, without increasing hardware burden, utilizes in-situ space resources to completely solve the problem of complex contamination caused by the mixing of oil film and particles. Compared to traditional EDS technology, the system in this invention improves the removal rate of sticky dust from less than 10% to more than 95%. This system has been verified through simulation and ground experiments. During the simulation verification process, a multiphysics model was established using COMSOL Multiphysics. The simulation results show that in the presence of an oil film, the adhesive force (~100 nN) on the particles is much greater than the electric thrust (~10 nN) provided by EDS. Therefore, traditional EDS technology cannot effectively remove the oil film + particle composite contamination on the surface of optical payload 1. When cleaning is performed using the in-situ molecular cleaning and particle dust removal system of the space optical payload, after simulating oil film removal in DC mode, the adhesive force of the particle contaminants drops to <5 nN, and the particles are instantly removed in AC mode.

[0041] During ground-based experiments, quartz glass coated with silicone oil and sprinkled with JSC-1A simulated lunar dust was tested in a vacuum environment simulation device. A control group was set up using only EDS dust removal: the dust removal rate was less than 10%, and a large number of particles remained. The experimental group of this invention first used DC mode to decompose the oil film, then used AC mode for dust removal. After 20 minutes of DC cleaning, AC dust removal was activated, and the particulate matter was rapidly removed, achieving a dust removal rate of 98.5%, and the spectral transmittance recovered to over 99% of its initial value.

[0042] As an optional embodiment, for scenarios where directional conveying is not required (such as vertically mounted lenses), the AC mode of the multi-mode power controller 3 can use a single-phase standing wave, utilizing the bouncing effect in conjunction with microgravity to remove dust.

[0043] As an alternative embodiment, for infrared loads, electrode array 2 may employ carbon nanotubes (CNTs) or graphene films to obtain better infrared transmittance.

[0044] In summary, the above description is merely a preferred embodiment of this specification and is not intended to limit the scope of protection of this specification. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this specification should be included within the scope of protection of this specification.

[0045] The systems, apparatuses, modules, or units described in one or more of the above embodiments may be implemented by a computer chip or entity, or by a product having a certain function. A typical implementation device is a computer. Specifically, a computer may be, for example, a personal computer, a laptop computer, a cellular phone, a camera phone, a smartphone, a personal digital assistant, a media player, a navigation device, an email device, a game console, a tablet computer, a wearable device, or any combination of these devices.

[0046] It should also be noted that the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0047] The various embodiments in this specification are described in a progressive manner. Similar or identical parts between embodiments can be referred to interchangeably. Each embodiment focuses on describing the differences from other embodiments. In particular, the system embodiments are basically similar to the method embodiments, so the description is relatively simple; relevant parts can be referred to the descriptions in the method embodiments.

Claims

1. A space optical payload in-situ molecular cleaning and particulate dust removal system, characterized in that, include: An electrode array disposed on the surface of an optical load, the electrode array comprising at least two electrode groups, wherein the electrodes in different electrode groups are staggered. A multi-mode power controller for outputting direct current or multiphase alternating current to the electrode array; The multimode power controller is configured to: In the first mode, the multi-mode power controller provides DC power to the electrode array, which generates an ion-accelerating electric field to remove organic molecular contaminants from the surface of the optical payload by high-energy ion bombardment. In the second mode, the multi-mode power controller provides multiphase alternating current with phase difference to different electrode groups in the electrode array. The electrode array generates a traveling wave electric field, which pushes particulate contaminants on the surface of the optical payload away from the optical payload.

2. The in-situ molecular cleaning and particulate dust removal system for space optical payloads according to claim 1, characterized in that, The lower surface of the electrode array is provided with an insulating support component, and the electrode array is connected to the optical load surface through the insulating support component.

3. The in-situ molecular cleaning and particulate dust removal system for space optical payloads according to claim 2, characterized in that, The electrode array is connected to the insulating support component via a nano-adhesion layer.

4. The in-situ molecular cleaning and particulate dust removal system for space optical payloads according to claim 1, characterized in that, An antioxidant layer is deposited on the upper surface of the electrode array to prevent the electrode array from being oxidized by adsorbing atomic oxygen.

5. The in-situ molecular cleaning and particulate dust removal system for space optical payloads according to claim 1, characterized in that, The electrode array is a forked conductive array, including phase A electrode group, phase B electrode group and phase C electrode group.

6. The in-situ molecular cleaning and particulate dust removal system for space optical payloads according to claim 5, characterized in that, When the optical load is a transmissive optical element, the electrode array uses an ITO transparent conductive film; when the optical load is a reflective optical element, the electrode array uses an ultrathin metal mesh.

7. The in-situ molecular cleaning and particulate dust removal system for space optical payloads according to claim 1, characterized in that, In the first mode, the multimode power controller provides negative DC power to the electrode array, which acts as a cathode to adsorb and accelerate oxygen ions. The oxygen ions bombard the organic long chains of organic molecular pollutants on the surface of the optical payload, forming organic fragments. Atomic oxygen oxidizes the organic long chains into gas and removes them.

8. The in-situ molecular cleaning and particulate dust removal system for space optical payloads according to claim 7, characterized in that, In the second mode, the multi-mode power controller provides three-phase AC power to the electrode array. The particulate contaminants on the surface of the optical load are induced to become charged and are subjected to the combined force of Coulomb force and dielectric force, jumping or sliding along the traveling wave electric field.

9. The in-situ molecular cleaning and particulate dust removal system for space optical payloads according to claim 1, characterized in that, The optical payload is provided with a collection groove at its edge for collecting particulate pollutants.

10. The in-situ molecular cleaning and particulate dust removal system for space optical payloads according to claim 1, characterized in that, The electrode array is also connected to a bleed resistor. During the in-situ molecular cleaning and particle dust removal process, the multi-mode power controller first executes the first mode, then executes the second mode, and finally the multi-mode power controller stops supplying power and discharges the electrode array to ground through the bleed resistor to eliminate the residual charge on the electrode array.

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