A bumper is provided on an outer side of a structural body of a spacecraft with a predetermined gap between the bumper and the structural body. The bumper includes: a first layer that is provided on the outer side and that is formed from an impact resistant material; a second layer that is provided on an inner side being on a side of the structural body with respect to the first layer, the second layer having holes; and a third layer that is provided on the inner side with respect to the second layer, the third layer including a resin.

A bumper is provided on an outer side of a structural body of a spacecraft with a predetermined gap between the bumper and the structural body. The bumper includes: a first layer that is provided on the outer side and that is formed from an impact resistant material; a second layer that is provided on an inner side being on a side of the structural body with respect to the first layer, the second layer having holes; and a third layer that is provided on the inner side with respect to the second layer, the third layer including a resin.

A pressurized structure panel for forming a pressurized space pressurized inside includes a panel structure having a panel body to receive the pressure, a rib provided in the panel body, and a hollow part formed by the panel body and the rib, a radiation shielding material provided in the hollow part, and a debris bumper provided outside the panel structure and provided spaced apart from the panel structure by a certain spacing. The radiation shielding material includes a material containing hydrogen atoms in molecules.

A pressurized structure panel for forming a pressurized space pressurized inside includes a panel structure having a panel body to receive the pressure, a rib provided in the panel body, and a hollow part formed by the panel body and the rib, a radiation shielding material provided in the hollow part, and a debris bumper provided outside the panel structure and provided spaced apart from the panel structure by a certain spacing. The radiation shielding material includes a material containing hydrogen atoms in molecules.

This invention relates to technology used for creating an enhanced artificial magnetosphere or electromagnetic shield for use in both manned and unmanned spacecraft. The invention includes an Interference Generating Pattern (IGP) which is tuned to the high-frequency radiation of X-rays and gamma rays and a conformal magnetic field. This technology will reduce the exposure of astronauts or other space travelers, as well as radiation-sensitive equipment, to the environmental hazards present therein. The net result will be reduced flux intensity in order to create a space radiation-free environment as to render space travel safe.

This invention relates to technology used for creating an enhanced artificial magnetosphere or electromagnetic shield for use in both manned and unmanned spacecraft. The invention includes an Interference Generating Pattern (IGP) which is tuned to the high-frequency radiation of X-rays and gamma rays and a conformal magnetic field. This technology will reduce the exposure of astronauts or other space travelers, as well as radiation-sensitive equipment, to the environmental hazards present therein. The net result will be reduced flux intensity in order to create a space radiation-free environment as to render space travel safe.

A method and a device for deorbiting artificial satellites from Earth orbit, the artificial satellite having multilayer insulation, at least partially detaches at least one layer of the multilayer insulation from the artificial satellite. Due to detachment of the layer, the underlying satellite structure is exposed to environmental influences. This exposure accelerates the self-disintegration of the artificial satellite, and thereby reduces the mass and increases the ballistic coefficient. Splaying out the layer augments its cross-sectional area and leads due to energy reduction to a premature re-entry into Earth's atmosphere. A number of layers can be arranged here so that regardless of a rotation of the satellite, at least one surface is always directed against the aerodynamic flow.

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 spacecraft panel includes a first skin, a second skin spaced apart from the first skin, and a first truss structure connecting the first skin to the second skin. The first truss structure includes a plurality of truss members, and each truss member is integral with the first skin and the second skin, such that the first skin, the second skin, and the first truss structure collectively form a single monolithic joint-free structure.

Solar collectors can provide power for electricity, thermal propulsion, and material processing (e.g., mining asteroids). In one aspect, an apparatus for collecting solar energy and simultaneously protecting against damage from a resulting energy beam includes a solar energy collection system including at least one concentrator and a target configured to use, store, or convert the solar energy, the collection system configured to cause solar energy to focus on the target, at least one sensor configured to detect misalignment of the concentrator by determining that some or all of the collected solar energy is offset from the target, and a safety system configured to redirect the energy or interpose a safety structure for shielding other non-target systems from receiving too much solar energy from the collection system.