26results about "Spacecraft coatings" patented technology

Disclosed is a satellite which includes an Attitude Determination and Control System (ADCS) and at least one radiative surface, where the orientation of the satellite with respect to the sun is change

A maskless touch up tool having a faceplate and handle. The faceplate is placed on a surface for touching up of a coating on the surface. The surface may be on a rocket body. The faceplate may form a seal around a target region of the surface. The faceplate has an opening configured to receive a touch up coating therethrough for application of the touch up coating to the surface. The handle may extend away from the faceplate and be configured for gripping by a user. The tool may include a reservoir, or an attachment for an external container, configured to collect excess touch up coating from the surface. The tool may be used to touch up the surface coating without the need for masking of the surface.

A space vehicle includes a space vehicle body and a radiator, wherein the space vehicle body includes an interior surface defining an interior of the space vehicle body and an exterior surface opposite the interior surface, and wherein the space vehicle body includes a panel including a sheet metal; wherein the radiator is positioned on the exterior surface of the space vehicle body, wherein the radiator includes a plurality of corrugations, wherein the corrugations are configured such that, when the space vehicle is evaluated under evaluation conditions of: sunlight illuminating Earth in a manner of an equinox date, the space vehicle positioned at a low Earth orbit altitude in an equatorial plane, and an observer positioned on the equator, the plurality of corrugations reflect sufficient sunlight away from the Earth such that a minimum magnitude of the space vehicle is in a range of from 6.5 to 9.5.

A space vehicle includes a space vehicle body and a radiator, the space vehicle body including an interior surface defining an interior of the space vehicle body and an exterior surface opposite the interior surface, wherein at least a portion of the space vehicle body includes a panel including a sheet metal; the radiator being positioned on the exterior surface of the space vehicle body, wherein the radiator includes a plurality of corrugations configured such that, when the space vehicle is evaluated under certain conditions, the corrugations reflect sufficient sunlight away from the Earth such that a reflected sunlight flux is reduced by a reduction factor that is in a range of from 0.1 to 0.2 as compared to a reflected sunlight flux of a comparison space vehicle lacking the plurality of corrugations and otherwise equivalent to the space vehicle, when evaluated under the same conditions

Carbon nanostructure-based composites and methods for making and using the same are described. The carbon nanostructure-based composites can be single-layer or multi-layer composites. Such composites can be useful for shielding radiation, such as that experienced by spacecraft and satellites. Carbon nanostructure-based composites containing low-Z and high-shielding efficiency (e.g., high-Z) materials and having radiation-shielding properties are described herein. A non-limiting exemplary composite is shown in Figure 1.

To provide a system capable of eliminating a complicated function or a high-precision control necessary when a service satellite approaches an outer space non-cooperative object or the like for providing an on-orbit service or removing debris. A cooperative objectification system 1, which cooperatively objectifies an outer space non-cooperative object C existing in an outer space, comprises: a spacecraft S configured to move in the outer space; and a cooperative interface M attached to a surface of the outer space non-cooperative object C by the spacecraft S.

A space vehicle includes a space vehicle body and a radiator, wherein the space vehicle body includes an interior surface defining an interior of the space vehicle body and an exterior surface opposite the interior surface, and wherein the space vehicle body includes a panel including a sheet metal; wherein the radiator is positioned on the exterior surface of the space vehicle body, wherein the radiator includes a plurality of corrugations, wherein the corrugations are configured such that, when the space vehicle is evaluated under evaluation conditions of: sunlight illuminating Earth in a manner of an equinox date, the space vehicle positioned at a low Earth orbit altitude in an equatorial plane, and an observer positioned on the equator, the plurality of corrugations reflect sufficient sunlight away from the Earth such that a minimum magnitude of the space vehicle is in a range of from 6.5 to 9.5.

A radiation shielding material for use in spacecraft comprises boron carbide particles dispersed in an epoxy matrix. In one aspect, the material is formed into modular panels attachable to satellite structures for attenuation of neutron and charged particle radiation. In another aspect, the boron carbide epoxy mixture is applied as a conformal coating to satellite components and cured in place to provide localized shielding. The composite may also be used to pot electronic components within a protective volume. The method of fabrication includes mixing boron carbide with epoxy resin and hardener, stirring until homogeneous, and curing the mixture to form a solid shielding structure. The system provides effective radiation mitigation with reduced weight and form factor compared to traditional metal or high-density polymer shields, and is compatible with aerospace integration and environmental requirements.

To provide a system capable of eliminating a complicated function or a high-precision control necessary when a service satellite approaches space debris or the like for removing the debris. A system 1, which removes a space debris C existing in an outer space, comprises: a first spacecraft S and a second spacecraft R configured to move in the outer space; and a cooperative interface M attached to a surface of the space debris C by the first spacecraft S. The second spacecraft R is configured to approach the space debris C using the cooperative interface M, capture the space debris C, and enter the atmosphere together with the space debris C or release the space debris C at a low altitude.

A maskless touch up tool having a faceplate and handle. The faceplate is placed on a surface for touching up of a coating on the surface. The surface may be on a rocket body. The faceplate may form a seal around a target region of the surface. The faceplate has an opening configured to receive a touch up coating therethrough for application of the touch up coating to the surface. The handle may extend away from the faceplate and be configured for gripping by a user. The tool may include a reservoir, or an attachment for an external container, configured to collect excess touch up coating from the surface. The tool may be used to touch up the surface coating without the need for masking of the surface.

A space vehicle includes a space vehicle body and a radiator, the space vehicle body including an interior surface defining an interior of the space vehicle body and an exterior surface opposite the interior surface, wherein at least a portion of the space vehicle body includes a panel including a sheet metal; the radiator being positioned on the exterior surface of the space vehicle body, wherein the radiator includes a plurality of corrugations configured such that, when the space vehicle is evaluated under certain conditions, the corrugations reflect sufficient sunlight away from the Earth such that a reflected sunlight flux is reduced by a reduction factor that is in a range of from 0.1 to 0.2 as compared to a reflected sunlight flux of a comparison space vehicle lacking the plurality of corrugations and otherwise equivalent to the space vehicle, when evaluated under the same conditions

The invention relates to a satellite comprising: a satellite body including at least one radiative surface configured to emit satellite heat to space; and an attitude determination and control ‘ADCS’ system for controlling an orientation of the satellite travelling in orbit around Earth, wherein the ADCS system is configured to change the orientation of the satellite with respect to the sun between a first position in which the radiative surface points away from the sun and a second position in which the radiative surface is exposed to the sun. The invention further relates to a method of controlling thermal radiation heat transfer of a satellite.

The present invention relates to a satellite comprising a satellite body including at least one radiation surface configured to radiate heat of the satellite into outer space, and an attitude determination and control (ADCS) system for controlling the orientation of the satellite orbiting around the Earth, wherein the ADCS system is configured to be able to change the orientation of the satellite with respect to the sun between a first position where the radiation surface is away from the sun and a second position where the radiation surface is exposed to the sun. The present invention further relates to a method for controlling heat radiation heat transfer of an artificial satellite.

Techniques for providing a heatshield involve receiving a starting portion of a tape from a tape supply, positioning the starting portion of the tape in contact with a tool structure, and after the starting portion of the tape is positioned in contact with the tool structure, and robotically moving the tool structure and a tape deployment head relative to each other to precisely guide the tape onto the tool structure. Robotically moving the tool structure and the tape deployment head relative to each other includes receiving a set of sensing signals indicating current position of the tool structure and the tape deployment head relative to each other, and based on the set of sensing signals, applying the tape under pressure (e.g., via pressure and temperature control) to form the heatshield.

A maskless touch up tool having a faceplate and handle. The faceplate is placed on a surface for touching up of a coating on the surface. The surface may be on a rocket body. The faceplate may form a seal around a target region of the surface. The faceplate has an opening configured to receive a touch up coating therethrough for application of the touch up coating to the surface. The handle may extend away from the faceplate and be configured for gripping by a user. The tool may include a reservoir, or an attachment for an external container, configured to collect excess touch up coating from the surface. The tool may be used to touch up the surface coating without the need for masking of the surface.

To provide a system capable of eliminating a complicated function or a high-precision control necessary when a service satellite approaches space debris or the like for removing the debris. A system 1, which removes a space debris C existing in an outer space, comprises: a first spacecraft S and a second spacecraft R configured to move in the outer space; and a cooperative interface M attached to a surface of the space debris C by the first spacecraft S. The second spacecraft R is configured to approach the space debris C using the cooperative interface M, capture the space debris C, and enter the atmosphere together with the space debris C or release the space debris C at a low altitude.

A maskless touch up tool having a faceplate and handle. The faceplate is placed on a surface for touching up of a coating on the surface. The surface may be on a rocket body. The faceplate may form a seal around a target region of the surface. The faceplate has an opening configured to receive a touch up coating therethrough for application of the touch up coating to the surface. The handle may extend away from the faceplate and be configured for gripping by a user. The tool may include a reservoir, or an attachment for an external container, configured to collect excess touch up coating from the surface. The tool may be used to touch up the surface coating without the need for masking of the surface.

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.

A spacecraft thermal control system is disclosed that includes a software reconfigurable radiator assembly capable of dynamically switching between high and low absorptance states to regulate thermal load. The system comprises a reflective display layer, such as an electrophoretic material, integrated into a multilayer radiator structure. A controller modulates the thermos-optical properties of the radiator based on pre-programmed or real-time inputs. The system allows for pre-integration into a satellite platform prior to receipt of mission-specific parameters and supports in-orbit thermal reconfiguration. The system can adapt to match changing orbits and mission environments, enabling flexible and responsive thermal management across different phases of operation. Additional features may include heat storage elements and thermal switches to manage payload-specific thermal requirements.

A high temperature thermal protection systems for rockets, and associated methods, is disclosed. A representative system includes a launch vehicle having a first end and a second end generally opposite the first end. The launch vehicle is elongated along a vehicle axis extending between the first and second ends and carries a propulsion system having at least one nozzle positioned at the second end of the launch vehicle. A thermal protection apparatus positioned around the nozzle is used to provide cooling and / or insulation to the nozzle during the flight of the launch vehicle. The thermal protection apparatus can include multiple fabric layers and an insulation layer stacked and stitched together. The fabric layers can include metal alloy fibers. In representative systems, the thermal protection apparatus can further include provisions for water that saturates the insulation layer to provide further insulating and / or cooling effects.

Systems (100) and methods (600) for providing a product with a radiation mitigation feature. The methods comprise: obtaining a composite base layer formed of a fiber-reinforced material; and performing a deposition process to dispose a first coating layer on the composite base layer so as to form the product with a radiation barrier, the first coating layer comprising 35% by mass or less of a metal constituent, at least 65% by mass of a germanium constituent, a zero or substantially zero coating stress, and / or an overall thickness between 2 microns and 8 microns.

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.

A nose tip for a vehicle includes a nose body, an insulative layer that covers at least a portion of the nose body, and an outer skin that covers and encloses the insulative layer. The insulative layer is constructed and arranged to receive a coolant for protecting the nose body from heat during entry of the vehicle into an atmosphere.

Carbon nanostructure-based composites and methods of making and using thereof are described. The carbon nanostructure-based composites may be single-layered or multi-tiered composites. Such composites can be useful for radiation shielding, such as experienced by spacecraft and space satellites.