11results 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 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.

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.

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.

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 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.

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.