34 results about "Atomic oxygen" patented technology

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 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 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.

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.

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 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 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 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 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.

The invention discloses a CMP cleaning equipment PTFE bearing material anti-wear modification method based on polishing pretreatment, and relates to the technical field of special material surface treatment. According to the invention, the reason of unstable wear-resistant modification of the PTFE bearing material through the atomic oxygen irradiation technology is the state difference of the material surface for the first time, and the roughness of the original surface is controlled through mechanical polishing pretreatment, so that the high consistency of the surface performance of the whole part is successfully ensured after the subsequent atomic oxygen irradiation treatment based on bias regulation and control; according to the modified PTFE material and the preparation method thereof, an oxygen-containing functional group chemical surface and a micro-nano composite rough physical structure are constructed, the wear rate of the obtained modified PTFE material is obviously reduced, the water contact angle is obviously increased, and the modified PTFE material has excellent self-cleaning capacity.

The application provides a simulation method based on material ablation effect under cooperation of atomic oxygen and ultraviolet, and relates to the technical field of spacecraft simulation calculation, and the simulation method comprises the following steps: obtaining atomic oxygen environment influence parameters, wherein the atomic oxygen environment influence parameters comprise spacecraft speed, incoming flow direction and atomic oxygen density; establishing a three-dimensional model of a spacecraft, inputting the atomic oxygen environment influence parameters into the three-dimensional model, and obtaining atomic oxygen flux on the surface of the spacecraft; determining a material ablation reaction coefficient on the surface of the spacecraft according to the cooperation of atomic oxygen and ultraviolet radiation on the surface of the spacecraft; and obtaining the ablation thickness of the material on the surface of the spacecraft through the atomic oxygen flux on the surface of the spacecraft and the material ablation reaction coefficient on the surface of the spacecraft. The simulation method is simple in steps, easy to operate, and accurate in simulation.

The present application relates to the technical field of spraying equipment, and specifically provides a device for spraying anti-atomic oxygen modified layer of special-shaped structural member with integrated dynamic positioning, which adopts a "three-in-one" technical architecture and mainly comprises a device body, a self-adaptive positioning assembly and a cooperative spraying mechanism. The positioning assembly is installed on the device body and is composed of a limiting column, a positioning seat and a supporting seat. The limiting column is located between the positioning seat and the supporting seat, forming a suspended positioning area specially used for placing the special-shaped structural member. The spraying mechanism is connected to the device body and is arranged above the positioning area and can move above the positioning area. To ensure uniform spraying, the spraying mechanism has a highly free spray width adjusting function, and the operator can flexibly adjust the spray width according to the shape and size of the special-shaped member. A multi-axis linkage design is adopted, a high-precision spray gun module is carried by a cantilever type moving platform, and three-dimensional space trajectory movement above the positioning area is realized.

A method of filling a gap on a surface of a substrate is provided. The method may comprise (a) placing a substrate on a susceptor within a reaction chamber, the substrate comprising 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 treatment step comprising: annealing the substrate in an atomic oxygen-containing gas to cause the first deposited material to flow within the gap for forming a carbon film.

The invention relates to an atomic oxygen flux density detection device, a preparation method thereof and an atomic oxygen flux density detection method. The atomic oxygen flux density detection device comprises a polyimide layer, a silver layer, a substrate layer and at least two electrodes, the silver layer is located on the surface of the polyimide layer; the polyimide layer and the substrate layer jointly form a packaging structure, and the silver layer is packaged; one ends of the two electrodes are respectively connected to different positions of the silver layer, and the other ends of the two electrodes extend to the outer side of the packaging structure. The atomic oxygen flux density detection device is high in atomic oxygen flux density detection precision.

A molding process for atomic oxygen-resistant composite materials. This invention belongs to the field of aerospace materials technology. This invention solves the problems of composite materials being susceptible to atomic oxygen in aerospace environments, and the tendency for debonding and air bubbles to form during bonding processes. This invention involves first coating an alloy material and a resin-based carbon fiber composite material separately with adhesive, and then bonding the alloy material and the resin-based carbon fiber composite material together to obtain an atomic oxygen-resistant composite material. The use of pressure rollers in this invention effectively ensures uniform adhesive layer thickness. A uniform adhesive layer allows for better adhesion of the metal protective layer to the surface of the resin-based carbon fiber composite material. The molding process of this invention ensures that the atomic oxygen-resistant composite material does not debond in aerospace environments, effectively extending the service life of aerospace equipment.

Coatings and materials that are atomic oxygen resistant and have an atomically smooth surface that can reduce drag are disclosed. The coatings and materials can be used on at least a portion of a spacecraft intended to operate in harsh environments, such as stable Earth orbits at about 100 km to about 350 km.

The invention relates to the technical field of spacecraft propulsion, in particular to a hollow cathode orbit environment gas atmosphere life assessment experiment system which comprises a vacuum chamber, an experiment box, a hollow cathode, an oxygen cylinder, an atomic oxygen generation device, a mixed gas cylinder and a xenon cylinder, and the experiment box is fixed in the vacuum chamber; the hollow cathode is fixed in the experiment box; the atomic oxygen generating device is arranged at the top in the vacuum cabin; the oxygen cylinder is connected with the atomic oxygen generating device through a gas pipeline; the mixed gas cylinder is arranged on one side outside the vacuum cabin and is communicated with the experiment box; and the xenon gas cylinder is arranged at the bottom end outside the vacuum cabin and is communicated with the experiment box. By arranging the vacuum gauge near the hollow cathode, the partial pressure of each component of the gas atmosphere where the hollow cathode is located can be accurately measured, and the atomic oxygen partial pressure, the nitrogen partial pressure and the oxygen partial pressure of the gas atmosphere where the hollow cathode is located can be adjusted.

The invention provides a vacuum in-situ measurement method and device for atomic oxygen flux and atomic oxygen denudation rate. The atomic oxygen flux measurement method comprises the following steps: covering a dielectric material with a known atomic oxygen denudation rate on a resistor; measuring the atomic oxygen flux of the dielectric material covering the resistance piece in an atomic oxygen environment until the dielectric material is completely denudated and the resistance is changed, and measuring the resistance change caused by the reaction of the dielectric material and atomic oxygen to obtain the atomic oxygen flux of the atomic oxygen environment; determining the complete denudation time of the dielectric material according to the start time of the atomic oxygen flux measurement and the end time when the resistance value of the resistor is greater than a specified value; and calculating the atomic oxygen flux of the atomic oxygen environment according to the determined complete denudation time of the dielectric material. The method for measuring the atomic oxygen denudation rate and the atomic oxygen flux, which is convenient, light, low in cost and low in power consumption, can be provided for low-orbit and ultra-low-orbit spacecrafts.

The utility model discloses an atomic oxygen experiment device which comprises a vertical vacuum tank and a vacuumizing system, the vertical vacuum tank comprises a tank body and a top cover, the top cover is used for opening and closing the top of the tank body, and the vacuumizing system is connected with the tank body and used for vacuumizing the tank body. A plurality of hot cathode discharge filaments are arranged on the inner side of the top cover, a multi-pole magnetic field restraint system is arranged on the outer wall of the tank body and used for forming a multi-pole restraint magnetic field in the tank body, an oxygen access port is formed in the tank body, and a test bed is arranged in the tank body. According to the utility model, the hot cathode discharge filament and the multi-pole magnetic field restraint system are respectively arranged inside the top cover and outside the tank body, so that the filament is convenient to maintain and replace.

The embodiment of the invention provides a micro-quality testing device and system for atomic oxygen detection. In one specific embodiment, the device comprises a quartz wafer, a bracket and a controller, electrodes are respectively arranged on two opposite surfaces of the quartz wafer, and the quartz wafer is connected with the bracket through the electrodes; a third plating layer is arranged on the electrode far away from the bracket; the electrode comprises a first plating layer close to the quartz wafer and a second plating layer far away from the quartz wafer; the quartz wafer is used for outputting real-time frequency to the controller through the electrode via the support so that the controller can obtain the real-time frequency output by the quartz wafer and obtain mass change caused by atomic oxygen oxidation erosion of the third coating according to the real-time frequency. The implementation mode can be used for dynamically monitoring the space atomic oxygen erosion state in real time.

The invention relates to the field of satellite energy subsystems, and provides a closed type flexible composite material strain energy rod and a preparation technology thereof.The closed type flexible composite material strain energy rod comprises a flexible strain energy rod body, an atomic oxygen protection layer, a limiting mushroom nail, an unfolding end embedded part and a root embedded part; the atomic oxygen protection layer is arranged on the surface of the outermost layer of the flexible strain energy rod, the unfolding end embedded part and the root embedded part are arranged at the two ends of the flexible strain energy rod respectively, and a plurality of limiting mushroom nails are sequentially arranged in the length direction and the circumferential direction of the flexible strain energy rod at intervals. According to the invention, on-orbit unfolding is realized by utilizing strain energy stored by the device, a hinge and an unfolding driving mechanism are not needed, and the device has the advantages of light weight, small thickness, high rigidity after unfolding, small size after folding, passive self-driving, adjustable unfolding driving torque and the like.