The disclosed subject matter relates to a radiation shielding apparatus including a cryogenic vessel and a cryogenic hydrogen radiation shielding material capable of providing a radiation shield, the cryogenic hydrogen radiation shielding material including cryogenic hydrogen.

A deployable electromagnetic radiation deflector shield (DERDS) is disclosed. It is used in protecting manned spacecraft or robotic spacecraft flying outside of the Earth's protective magnetic field as well as manned extra-planetary base stations. This DERDS is deployed from the spacecraft during flight and positioned to be between the Sun and the protected spacecraft (or in the case of Jupiter/Saturn missions, transitioning to be between that planet and the spacecraft). It remains in the proper position from the spacecraft by its own sensors and computer controlled gaseous or ion thrusters. It is deployed away from the spacecraft to better deflect incoming solar radiation (or Jovian radiation and the like), and not have its magnetic field affect the protected spacecraft or extra-planetary base station's equipment and astronauts (as in prior art). Its deployment will also prevent any captured radiation in its generated magnetic torus (like Earth's Van Allen radiation belts) from affecting the protected spacecraft or extra-planetary base station. The DERDS has a self-contained superconducting electromagnet that creates a magnetic field to deflect incoming solar radiation, including CMEs (coronal mass ejections) and repositioned for x-ray and gamma ray bursts from distant supernovae. It utilizes a tethered umbilical cord to transmit electrical power and back up commands from the spacecraft or satellite. Another variant or embodiment would be to mount the DERDS on a telescopic/extendable solid mount and remove the need for thrusters within the DERDS as it would move as an attachment to the spacecraft. The source of electrical power in this embodiment is the protected spacecraft's solar arrays, RTG (radioisotope thermal generator), fuel cells, and or batteries. In addition, it can be constructed with these power supplies mounted within the DERDS, as in a self-contained deployed spacecraft/satellite. Another embodiment of the DERDS would be mounted on an ecliptic track wherein the DERDS moves along the track to protect the manned base station.

A system is configured to shield an interior chamber of a structure. The system may include a power source, an outer shield assembly operatively connected to the power source and coupled to an outer wall of the structure, and an inner shield assembly surrounding the internal chamber. The outer shield assembly generates a magnetic field through and around the structure. The inner shield assembly deflects radiation particles away from the interior chamber and re-directs portions of the magnetic field around the interior chamber.

This present invention describes initial sequential methods for constructing and placing into operation a multi-purpose maintenance complex and a space dock in high geosynchronous orbit. This is dual function complex that can provide a orbital platforms to a commercial profitable enterprise or to the Department of Defense (DoD) to enhance their capabilities. A complex will have the capability to fabricate, assemble, test, and place into full operation any size orbital and planetary surface complexes and spacecraft. DoD mission capabilities embracing satellite repairs, research, national security and deterrence, space junk disposal support and other services while in orbit.

A system is configured to shield an interior chamber of a structure. The system may include a power source, an outer shield assembly operatively connected to the power source and coupled to an outer wall of the structure, and an inner shield assembly surrounding the internal chamber. The outer shield assembly generates a magnetic field through and around the structure. The inner shield assembly deflects radiation particles away from the interior chamber and re-directs portions of the magnetic field around the interior chamber.

A pliable multilayer blanket configured as a particle radiation shield, the blanket including multiple layers. A first layer of the multiple layers is composed of a first material and a second layer of the multiple layers is composed of a second material, different from the first material, each layer being less than 20 mils thick. At least one of the first material and the second material is a metal or metal alloy having an atomic number (Z) of at least 29.

The disclosed subject matter relates to a radiation shielding apparatus including a cryogenic vessel and a cryogenic hydrogen radiation shielding material capable of providing a radiation shield, the cryogenic hydrogen radiation shielding material including cryogenic hydrogen.

In some aspects, this disclosure relates to improved Z-grade materials, such as those used for shielding, systems incorporating such materials, and processes for making such Z-grade materials. In some examples, the Z-grade material includes a diffusion zone including mixed metallic alloy material with both a high atomic number material and a lower atomic number material. In certain examples, a process for making Z-grade material includes combining a high atomic number material and a low atomic number material, and bonding the high atomic number material and the low atomic number together using diffusion bonding. The processes may include vacuum pressing material at an elevated temperature, such as a temperature near a softening or melting point of the low atomic number material. In another aspect, systems such as a vault or an electronic enclosure are disclosed, where one or more surfaces of Z-grade material make up part or all of the vault/enclosure.

Radiation shielding performs a range of functions determined by the type and number of layers of materials used, thickness, weight, and structural support afforded by the radiation shielding. A radiation shield laminate stack may be constructed consisting of a plurality of layers of ultra-high molecular weight (UHMW) polyethylene, polyethylene film, and carbon fiber, which is held together with an epoxy. The carbon fiber lay may be coated with nanoparticles of Boron (B) or Boron Nitride (BN), Boron Oxide (B.sub.2O.sub.3) or Boron Carbide (B.sub.4C) or a combination thereof to increase the shielding properties of the laminate stack. The radiation shield is lighter than aluminum, structurally sound, and thus may be used in the space environment to effectively block Galactic Cosmic Rays, atomic oxygen and UV radiation.

The invention relates to a transport system (1) intended to be installed on a space launcher (100) comprising: an aircraft (2) which comprises propulsion means configured to propel the aircraft (2) in a direction of flight, and at least one seat (4) intended to receive a passenger which is movable in rotation about an axis (0) perpendicular to the direction of flight of the aircraft (2), an acceleration sensor being installed on each at least one seat (4) to measure the acceleration of each at least one seat (4); a passenger interface for each at least one seat (4) which comprises a screen intended to display images to the passenger installed on said at least one seat (4), the screen being coupled to said at least one seat (4) so to remain fixed relative to said at least one seat (4); a control unit (6) which is connected to the acceleration sensor and to said at least one seat (4), the control unit (6) being configured to calculate a load factor experienced by the passenger installed on the at least one seat (4) from the acceleration of said at least one seat (4), the control unit (6) being configured to monitor the rotation of the at least one seat (4) during the operation of the transport system (1) in order to maintain the position of the seat (4) fixed relative to the load factor experienced by the passenger throughout the flight.