67 results about "Atomic oxygen" patented technology

The present disclosure relates to a method for converting carbon dioxide into carbon monoxide comprising: producing atomic oxygen, providing carbon dioxide to be converted, mixing the carbon dioxide with the atomic oxygen within a mixing area such that the atomic oxygen can interact with the carbon dioxide for forming carbon monoxide within the mixing area through a first CO producing reaction: C02+0→C0+02, supplying the atomic oxygen into the mixing area at a first supply rate and supplying the carbon dioxide into the mixing area at a second supply rate, defining the first supply rate and the second supply rate such that a ratio between the first supply rate and the second supply rate remains within a pre-defined lower and upper threshold, and extracting carbon monoxide from the mixing area. The present disclosure also relates to an apparatus for converting carbon dioxide into carbon monoxide.

Mitigation of erosive effects of atomic oxygen encountered by telescope systems deployed in low earth orbit (LEO is effected by providing an array of multiple very small projections on the interior surface of an open-ended tubular metering shell extending forwardly from a mirror to be protected. The projections are made of material that is geometrically configured to deflect AO atoms one or more times within the shell at angles that ultimately direct the atoms away from the mirror surface and back out through the forward end of the shell.

The invention discloses an atomic oxygen-resistant epoxy resin adhesive and a preparation method thereof, and relates to the technical field of adhesives. The epoxy resin adhesive with atomic oxygen resistance is prepared by introducing autonomously synthesized epoxy-terminated T-type phenyl polysiloxane with fluorine atoms on a side chain as a modifier into an epoxy resin system. A modifier molecule takes a flexible silicon-oxygen-silicon bond as a main chain, and a side chain has rigidity of phenyl and strong stability of trifluoropropyl; epoxy groups at the tail end guarantee the dispersity of the modifier, and tight combination of the components is achieved in a covalent bond chemical bonding mode. A fluorocarbon bond in trifluoropropyl can effectively resist denudation attack of space atomic oxygen by virtue of an extremely high bond, so that the atomic oxygen resistance of the material is optimized; the adhesive has toughness improvement and space environment tolerance on the basis of keeping the inherent strength of epoxy resin, and is suitable for the field of spacecraft structure bonding with strict requirements on reliability and durability.

The invention relates to a cleaning system (100, 200) for cleaning a semiconductor substrate carrier (105, 205) or at least a surface of the carrier (105, 205), comprising: a first chamber (110, 210) and a second chamber (120, 220), where the first chamber (110, 210) and the second chamber (120, 220) are in fluid communication with each other, where the second chamber (120, 220) is configured to receive the carrier (105, 205); an input fluid supply (130, 230) configured to provide an input fluid (135, 235) to the first chamber (110, 210); a radiation source (140, 240) configured to provide radiation of at least one predetermined wavelength within the first chamber (110, 210) and configured to generate a cleaning fluid (145, 245) comprising plasma and / or ozone and / or atomic oxygen by exposing an input fluid (135, 235) in the first chamber (110, 210) to the radiation; a cleaning fluid delivery unit (150, 250) configured to deliver a cleaning fluid from the first chamber (110, 210) to the second chamber (120, 220) to clean the carrier (105, 205) or at least a surface of the carrier (105, 205) disposed in the second chamber (120, 220), and configured to subject the carrier (105, 205) or at least the surface of the carrier (105, 205) to the cleaning fluid in the second chamber (120, 220).

Mitigation of erosive effects of atomic oxygen encountered by telescope systems deployed in low earth orbit (LEO is effected by providing an array of multiple very small projections on the interior surface of an open-ended tubular metering shell extending forwardly from a mirror to be protected. The projections are made of material that is geometrically configured to deflect AO atoms one or more times within the shell at angles that ultimately direct the atoms away from the mirror surface and back out through the forward end of the shell.

The present invention provides a method for displaying the atomic oxygen erosion effect on a spacecraft surface, relating to the field of spacecraft simulation and computing technology. The method comprises: generating a structured mesh file based on the number of polygonal meshes in each direction within a coordinate system; generating an initial crack file; generating an erosion mesh file; and displaying the atomic oxygen erosion effect on the spacecraft surface based on the data in the structured mesh file, the initial crack file, and the erosion mesh file. Compared with existing technologies, the present invention can intuitively display the atomic oxygen erosion effect on a spacecraft surface, achieving the goal of accurately predicting the erosion of atomic oxygen and the material surface under ultraviolet light. Furthermore, the method is simple in steps and easy to operate.

The invention discloses a manufacturing method of an atomic oxygen prevention external flame-retardant cloth punching multilayer heat insulation assembly, which comprises the following steps: S1, the assembly adopts a five-layer composite structure from top to bottom, and material structures required by a surface layer, a flame-retardant layer, a heat insulation layer, a punching layer and a substrate layer are prepared; s2, performing in-situ growth of a BN nanosheet on the surface of the PI film by adopting laser-induced chemical vapor deposition; s3, a dynamic stirring impregnation method is adopted, and 80 DEG C gradient drying curing is combined; s4, dipping an aluminum silicate fiber skeleton into silicon dioxide sol, and carrying out supercritical CO2 drying and forming; s5, laminating five layers of materials, and sequentially carrying out three-stage hot pressing at 180 DEG C (0.5 MPa), 250 DEG C (1.2 MPa) and 300 DEG C (2.0 MPa); and S6, an ultraviolet laser is selected, and a high-precision positioning system is arranged for laser precision drilling. Through triple innovation of materials, structures and processes, deep synergy of atomic oxygen protection, flame retardance, heat insulation and light weight functions is achieved, the performance of the assembly comprehensively exceeds that of the prior art, and the production cost is reduced by 40%.

The present invention provides a method, device, computer equipment and storage medium for characterizing a space atomic oxygen environment, which belongs to the field of aerospace technology. The method includes obtaining the spatial position coordinates, running speed, running attitude and time parameters of the satellite at the current moment, and then obtaining the atomic oxygen number density data, wind speed data and complex structure data of the spacecraft itself at the real-time on-orbit position during the spacecraft mission according to the running position, speed and attitude, combined with the atomic oxygen environment model and the horizontal wind environment model, and realizing the real-time characterization of the space atomic oxygen environment according to these data, and solving the problem of atomic oxygen effect considering the structure shape of the spacecraft.

The embodiment of the invention provides a method and a device for measuring parameters of a high-enthalpy unbalanced flow field of an atomic oxygen and atomic nitrogen absorption spectrum, and the method comprises the steps: generating a high-enthalpy flow field at an outlet of a high-enthalpy wind tunnel nozzle, a laser absorption spectrum measurement system arranged in a high-enthalpy wind tunnel experiment section is used for carrying out synchronous measurement on the same to-be-measured flow field area of a high-enthalpy flow field, and the Gaussian half width and the integral absorption rate of an atomic nitrogen characteristic spectral line and the Gaussian half width and the integral absorption rate of an atomic oxygen characteristic spectral line are obtained; the effective absorption optical path of the laser penetrating through the high-enthalpy flow field and the pressure of the high-enthalpy flow field are obtained at the same time; setting an initial iteration value of the electron population temperature of the flow field, and based on the initial iteration value, adopting the constructed iteration algorithm to carry out iteration calculation until the temperature parameter converges to obtain a final electron population temperature; and according to the Gaussian half-width of the atomic nitrogen characteristic spectral line and the Gaussian half-width of the atomic oxygen characteristic spectral line, respectively obtaining the translational temperatures of the atomic nitrogen and the atomic oxygen.

The invention discloses a preparation method of an atomic oxygen erosion resistant rigid plastic foam material, which comprises the following steps: preparing a polymer, an initiator, a modifier, a foaming agent, a cross-linking agent and a nucleating agent into a material mixed solution according to a certain mass ratio, carrying out polymerization reaction, and heating and foaming to obtain the atomic oxygen erosion resistant rigid plastic foam material, the polymer is a mixture containing an acrylic acid compound, an acrylonitrile compound and a copolymerization reactant, and the modifier comprises polyhedral oligomeric silsesquioxane. The rigid plastic foam material obtained by the preparation method has good atomic oxygen resistance, and can be applied to the fields of aerospace and atomic oxygen environment resistant materials.

The invention relates to the technical field of space environment effect ground tests, and provides a neutralized metal plate sputtering pollution control method and system for an atomic oxygen simulation test. The method comprises the following steps: determining a neutralized metal plate according to a relation curve of sputtering yield and atomic number of target material elements; the generated oxygen plasma is guided to the determined neutralization plate according to the optimized incident angle, the oxygen plasma is neutralized on the surface of the neutralization plate to form atomic oxygen, and the atomic oxygen is guided to the sample to be tested; the bias voltage applied to the neutralization plate is controlled, so that the energy of incident oxygen ions is lower than a sputtering threshold value of the neutralization plate while the energy of atomic oxygen reflected by the neutralization metal plate and the neutralization efficiency are ensured, and sputtering is effectively controlled; the temperature of the neutralized metal plate is controlled to prevent an increase in the sputtering level of the neutralized metal plate. According to the invention, the sputtering pollution of the neutralized metal plate in the test process is effectively controlled.

The present invention provides a method and device for real-time characterization of atomic oxygen inflow and windward surface considering attitude. The method comprises obtaining the spatial position, movement speed and running attitude of an aircraft at each simulation moment, and obtaining the atomic oxygen number density environment and the transverse wind environment in which the aircraft is located according to the position, speed and attitude in combination with an atomic oxygen environment model and a transverse wind environment model, and obtaining the atomic oxygen inflow speed according to the speed of the aircraft and the transverse wind speed in which the aircraft is located, thereby realizing real-time characterization of atomic oxygen on the windward surface in the space atomic oxygen environment of a spacecraft with a complex structure considering the inflow speed and the change of the aircraft's own attitude.

A method of filling a gap on a surface of a substrate is provided. The method may include: (a) placing a substrate on a susceptor within a reaction chamber, the substrate including a gap; (b) a deposition step comprising: flowing a carbon precursor into the reaction chamber; and exposing the carbon precursor to a plasma, wherein the carbon precursor reacts to form a first deposited material; and (c) a processing step including annealing the substrate in an atomic oxygen-containing gas to flow the first deposition material within the gap to form a carbon film.

The present invention provides a simulation method for the ablation effect of spacecraft surface materials in the autonomous acquisition mode, which relates to the technical field of spacecraft simulation calculation. The simulation method realizes the simulation calculation of the ablation effect of materials under the synergistic action of atomic oxygen and ultraviolet by means of autonomously selecting and acquiring the parameters affecting the ablation effect. The parameters affecting the ablation effect include polygon mesh parameters, atomic oxygen parameters, ultraviolet parameters, ablated material parameters and protective layer parameters. Based on the synergistic action of atomic oxygen and ultraviolet, the present invention can realize the acquisition mode of autonomously and freely selecting the parameters affecting the ablation effect, and realize the simulation experiment of the ablation effect of materials under different doses of atomic oxygen and ultraviolet irradiation, which can not only accurately simulate the actual situation, but also accelerate and accurately evaluate the ablation effect of materials under the synergistic action of atomic oxygen and ultraviolet.

A sensor system for a spacecraft comprising: atomic oxygen sensors including graphite strips to provide resistances that increase as the graphite strips ablate away when exposed to atomic oxygen, the atomic oxygen sensors configured to generate first sensor signals indicative of the resistances and, correspondingly, atomic oxygen fluence to which the atomic oxygen sensors are exposed; thermistors to generate second sensor signals indicative of temperature; sensor circuits that are identically configured to each other and that include first sensor circuits to convert the first sensor signals to digitized first signals and second sensor circuits to convert the second sensor signals to digitized second signals; and a controller to process the digitized first signals and the digitized second signals.

The invention provides a method and a device for evaluating the atomic oxygen resistance of a material. The method comprises the following steps: constructing an initial three-dimensional periodic molecular model of a to-be-evaluated organic material; performing NPT ensemble optimization and geometric optimization on the three-dimensional periodic molecular model to obtain an optimized three-dimensional periodic molecular model; introducing an atomic oxygen molecular beam into reaction molecular dynamics simulation, setting a plurality of atomic oxygen incident angles, and performing atomic oxygen action simulation on the optimized three-dimensional periodic molecular model to obtain atomic oxygen reaction data under each incident angle; processing the atomic oxygen reaction data to obtain an atomic oxygen reaction rate Ey corresponding to each incident angle; and judging the atomic oxygen resistance of the to-be-evaluated organic material according to the atomic oxygen reaction rate Ey. The evaluation method provided by the invention can improve the evaluation efficiency of the atomic oxygen resistance of the material.

The invention discloses a digital twinborn intelligent operation and maintenance system and method for atomic oxygen ground simulation equipment, and the system achieves the process automation of equipment operation, the comprehensive perception of an operation state, intelligent prediction and visual management and control through the construction of high-fidelity virtual mapping of physical equipment and the fusion of multi-source real-time data and mechanism simulation data. Therefore, the efficiency, the accuracy, the safety and the intelligent level of the atomic oxygen ground simulation test are improved.

The invention provides a chemical mechanical polishing solution for metal and metal nitride substrates. The polishing solution includes a solvent and functionalized carbon-based particles having oxygen-containing functional groups. The functionalized carbon-based particles having oxygen-containing functional groups react with a peroxy moiety to increase oxygen to carbon atomic ratio on the functionalized carbon-based particles. The functionalized carbon-based particles contain at least 10 weight percent of an sp3-containing structure, the functionalized carbon-based particles include at least 0.01 atomic percent oxygen and a surface of the functionalized carbon-based particles has an atomic oxygen to carbon ratio of at least 0.01.

The present invention provides a method for displaying the on-orbit operation status of a spacecraft, and relates to the field of spacecraft simulation computing technology. The method includes: parsing an environment file, storing the parsed data information in a memory structure, wherein the data information includes one or more of the spacecraft quaternion, six orbital numbers, atomic oxygen density, incoming flow direction, illumination direction, and longitude and latitude; creating a playback control component, and using the playback control component to realize the display of the windward side, sun-exposed side, and / or running track of the spacecraft during on-orbit operation, wherein the playback control component sets the start and end time range of the playback control component according to the time of the original data in the memory structure to realize playback control of the displayed image. Compared with the prior art, the present invention can achieve the purpose of intuitively displaying the windward side, sun-exposed side, and running track of the spacecraft during on-orbit operation, and the method is simple and the display is accurate.

The application discloses a kind of super low orbit spacecraft aerodynamic configuration optimization method, device, equipment and medium, it is related to spacecraft design field.The method comprises: obtaining target parameter;According to target parameter and NRLMSISE-00 model, calculate real-time atmospheric environment parameter;Based on real-time atmospheric environment parameter, construct multi-objective optimization function;With NSGA-III algorithm, with the minimum drag coefficient, the maximum working medium capture efficiency, the minimum structure weight and the optimal atomic oxygen erosion resistance performance as target, the multi-objective optimization function is solved, and the core geometric parameter of super low orbit spacecraft is obtained;Using constraint condition, core geometric parameter, derivative constraint parameter and material and coating parameter are filtered, and the optimal aerodynamic configuration of super low orbit spacecraft is obtained.The application can realize the rapid optimization of super low orbit spacecraft aerodynamic configuration, and has high reliability and long on-orbit life.

The present invention provides a real-time characterization method for the simulation process of the combined action of space atomic oxygen and ultraviolet radiation, belonging to the field of aerospace technology. When the present invention conducts simulation characterization on an in-orbit space vehicle in the combined environment of space atomic oxygen and ultraviolet radiation to study the ultraviolet and atomic oxygen effects, it characterizes the operating attitude of the vehicle in the form of quaternions, and jointly determines the surface of the vehicle that is subjected to ultraviolet electromagnetic radiation according to the operating attitude of the space vehicle and the incident direction of solar ultraviolet radiation. It characterizes the space position and operating speed of the vehicle, and jointly determines the interaction between the vehicle and atomic oxygen in combination with the operating attitude of the vehicle and the space atomic oxygen environment obtained according to the atomic oxygen calculation model. The present invention comprehensively considers the windward side and sun-facing side of the space vehicle, and can relatively realistically consider the real-time quantitative characterization of the space environment in which the space vehicle is exposed to sunlight and faces atomic oxygen during its in-orbit operation.

The application belongs to the technical field of spacecraft, and particularly relates to a protective-thermal control integrated structure for spacecraft. The integrated structure is composed of a protected object and an inner shield, a protected object and an outer shield, or a protected object and an inner shield and an outer shield. The inner shield is a multifunctional filling layer structure, which is composed of an outer atomic oxygen protection layer, a reflection layer, a heat insulation layer, a crushing layer, a diffusion layer and an inner atomic oxygen protection layer from outside to inside. The atomic oxygen protection layers on the inner and outer surfaces completely cover each surface of the multifunctional filling layer. The outer shield is made of metal and includes a protective outer shield, a plurality of groups of array-distributed connecting ribs and fluid pipelines. The fluid pipelines are arranged along the direction of the cabin body and are welded to the inner side of the protective outer shield through the connecting ribs. The integrated structure can have both protective and thermal control functions, and the mechanical interfaces in the assembly and disassembly processes can be independent of each other, which greatly improves the structural efficiency and simplifies the complexity of the structure.

The present invention provides a calculation method for atomic oxygen or ultraviolet flux based on ray tracing, which relates to the technical field of spacecraft simulation calculation. The calculation method includes: calculating the atomic oxygen flux influence parameter or ultraviolet flux influence parameter of the spacecraft at each point on the orbit according to the orbit parameters of the spacecraft; dividing the spacecraft surface into multiple polygon mesh units, and setting the initial value of atomic oxygen flux or ultraviolet flux for each of the polygon mesh units; calculating the increased value of atomic oxygen flux or ultraviolet flux for each of the polygon mesh units at each point on the spacecraft's motion orbit, and finally obtaining the cumulative value of atomic oxygen flux or ultraviolet flux. Compared with the prior art, the present invention can greatly improve the calculation time efficiency, reduce costs, provide verification data for the calculation results of the Monte Carlo simulation method, and provide an efficient technical means for the rapid screening of spacecraft surface coating materials, having obvious advantages and broad application prospects.

The invention relates to the technical field of space material ground irradiation tests, and provides an acceleration test processing method and system. The method comprises the following steps: based on a first test condition, carrying out a single-factor atomic oxygen irradiation test on a test sample, collecting related data before and after the test, and carrying out data characterization by using at least one spectral analysis mode to obtain a first spectral analysis characterization result; based on a second test condition, performing a single-factor ultraviolet radiation test on the test sample, collecting related data before and after the test, and performing data characterization by using at least one spectral analysis mode to obtain a second spectral analysis characterization result so as to determine an atomic oxygen radiation acceleration flux density interval and an ultraviolet irradiance acceleration interval, the device is used for carrying out an atomic oxygen and ultraviolet comprehensive irradiation test. According to the invention, the selection interval of single-factor atomic oxygen and single-factor ultraviolet radiation accelerated flux is effectively realized, and the ground test effect of a space material is effectively enabled to be closer to a real orbit.

The invention discloses a method for analyzing atomic oxygen erosion resistance of a Ti3C2Tx / polyimide film through molecular dynamics, which comprises the following steps: firstly, establishing a polyimide film model through a polyimide monomer model by using molecular dynamics modeling software, establishing a Ti3C2Tx film model through a Ti3C2Tx monomer model, and establishing a Ti3C2Tx film model through a Ti3C2Tx film model; then a layered structure Ti3C2Tx / polyimide film model and a layered-coating structure Ti3C2Tx / polyimide film model are constructed, and then the models are subjected to structure optimization; the method comprises the following steps of: firstly extending in a Z direction by using molecular dynamics simulation software, then carrying out relaxation, and finally carrying out simulation calculation on an atomic oxygen erosion model through molecular dynamics simulation based on a ReaxFF force field to obtain a dynamic evolution condition of the model in an atomic oxygen erosion process. And the component composition of the model at the end of erosion and the mass change of the model in the erosion process are counted to obtain the atomic oxygen erosion mechanism of the Ti3C2Tx / polyimide film model with the layered structure and the Ti3C2Tx / polyimide film model with the layered-coating structure.

The present invention provides a Monte Carlo simulation method of atomic oxygen or ultraviolet flux on the surface of a spacecraft, and relates to the technical field of spacecraft simulation calculation. The method comprises: creating a main thread and a sub-thread, wherein the main thread unifies the random experimental parameters on each motion trajectory point of the spacecraft into the body coordinate system, and then divides a plurality of polygonal mesh units of the spacecraft surface into a first structural unit and a second structural unit according to the structural relationship of the spacecraft components, and assigns simulation tasks to each sub-thread; each sub-thread obtains the position coordinates and relative motion direction of the simulated particle according to the simulation task, and calculates the polygonal mesh unit touched by each simulated particle through the first structural unit and the second structural unit; the main thread obtains the atomic oxygen flux or ultraviolet flux on the surface of the spacecraft according to the calculation results of each sub-thread. The present invention can reduce the time of Monte Carlo simulation and improve the calculation accuracy and efficiency.

The application belongs to the technical field of space lubricating materials, and particularly relates to a MoS2-WS2-based composite film and a preparation method and application thereof. The preparation method of the MoS2-WS2-based composite film provided by the application comprises the following steps: after a base material is ion-bombarded and cleaned, non-equilibrium magnetron sputtering is performed on the base material by using a MoS2 target and a WS2 target, or a MoS2 target, a WS2 target and a metal Ti target, so as to form a MoS2-WS2-based composite film; and according to an atomic percentage, the MoS2-WS2-based composite film contains 0-13.5% Ti, 13.0-27.3% W, 14.4-38.4% Mo and a balance of S and impurity elements. MoS2 and WS2 with similar crystal structures are combined together by using non-equilibrium magnetron sputtering, and the obtained composite film has excellent tribological properties in a vacuum environment, and still has a relatively low friction coefficient and a relatively long wear life after being irradiated by atomic oxygen.

The application discloses an atomic oxygen conversion method and an air-breathing electric propulsion filtering system. The atomic oxygen is ionized and then recombined to generate oxygen, so that high-speed and controllable oxygen conversion is realized, and the reaction efficiency is high. The air-breathing electric propulsion filtering system comprises an air inlet section, a contraction section and a straight section. The air-breathing electric propulsion filtering system is provided with a central electrode and a side wall electrode, so that the atomic oxygen in the super-low orbit atmosphere is pre-ionized, and is pushed to a side wall thickening area under the action of an electric field. The atomic oxygen ion obtains electrons from the metal material of the side wall thickening area, and then re-generates atomic oxygen. A high-concentration atomic oxygen aggregation area is generated, so that the recombination rate of the atomic oxygen is greatly improved. The generated oxygen molecules are rectified by a rectifying mechanism, and then replace the original strong corrosive atomic oxygen to enter an ion thruster, so that the corrosion of the atomic oxygen in the super-low orbit atmosphere to key components of the ion thruster is effectively avoided.

The invention discloses a flexible packaging film, the surface of the flexible packaging film is provided with an anti-atomic oxygen layer, and the anti-atomic oxygen layer is deposited on the surface of the flexible packaging film through a solution method or a vacuum deposition method. The flexible packaging thin film material prepared by the invention can solve the problems of ultraviolet radiation aging, atomic oxygen corrosion, optical performance degradation, insufficient mechanical stability and the like of the existing packaging material in a space environment, so that the on-orbit service life of the solar cell is prolonged, and the efficiency stability of the solar cell is improved.