A ruggedizing apparatus for electronic equipment in a spacecraft is provided that can achieve both a radiation shielding effect and a heat-dissipation effect. The ruggedizing apparatus includes: a pressure vessel that is filled with a coolant and places at least a heat-generating electronic circuit of the electronic equipment within the pressure vessel, wherein the heat-generating electronic circuit is immersed in the coolant; and a forced liquid-flow generator placed within the pressure vessel, wherein the forced liquid-flow generator causes the coolant on the heat-generating electronic circuit to move away from the heat-generating electronic circuit.

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.

A system to create a magnetic field around the outside of a spacecraft to afford human occupants and electronic equipment with protection from cosmic and solar radiation. Using electromagnets to generate magnetic fields placed on the outer surface of the spacecraft, cosmic and solar radiation may be deflected from entering the main body of the spacecraft. In addition, the magnetic field lines are kept away from the human occupants and interior electronic equipment. Side electromagnets are placed on the side outer surface of the spacecraft and separate electromagnetics are positioned in a cross shaped configuration at the front and rear of the spacecraft in alignment with the side electromagnets. Magnetic field lines are channeled around the outside of the spacecraft or centered on the center of quadrupole magnets placed either at the front of rear of the spacecraft.

In a method of facilitating flight operations, a payload is coupled to a spacecraft via a payload interface. The relative alignment of the payload and the spacecraft is dynamically adjusted (e.g., for thrust alignment) while the payload remains coupled to the spacecraft.

The present relates to a quantum communication system for free space quantum key distribution. An emitter and a receiver, the emitter and the receiver are two points distanced by a free space quantum communication channel, the emitter being designed for wirelessly transmitting data to the receiver via said free space optical communication channel. The receiver includes an optical device capable of receiving the data within a predetermined field of view extending from said optical device toward the receiver. The system is characterized in that the emitter further comprises a light protecting device attached on said emitter. The light protecting device is configured to prevent any light coming from the environment beyond the emitter to enter within the field of view of the receiver. The invention further relates to a method for optimizing free space quantum key distribution.

A scalable, extensible, multi-tenancy multi-mission configurable spacecraft system is provided that allows applications to be deployed and managed across many spacecraft. One embodiment includes a plurality of satellites in orbit, where each satellite includes an antenna, a memory configured to store a non-virtualized operating system and one or more software applications, and a processor connected to the antenna and the memory. The processor is configured to run the non-virtualized operating system and to run the one or more software applications. The processors and the applications can be managed by ground terminals or other satellites.

A method includes obtaining a base housing for electronic components. The base housing attenuates radiation entering the base housing by a base amount. An inner volume of the base housing defined by an inner surface of the base housing experiences attenuated radiation. The method also includes affixing one or more inserts to the inner surface of the base housing to further attenuate the attenuated radiation in corresponding one or more areas of the inner volume.

A spacecraft includes a body defining an interior payload region and a particle dispersion layer disposed between the interior payload region and one or more exterior surfaces of the body. The particle dispersion layer is formed of one or more magnets having a persistent magnetic field. The spacecraft including the particle dispersion layer may be manufactured by obtaining a particle dispersion layer having a persistent magnetic field, identifying a directionality of the persistent magnetic field of the particle dispersion layer, and installing the particle dispersion layer between an interior payload region formed by a body of a spacecraft and one or more exterior surfaces of the body according to the identified directionality of the persistent magnetic field.

Disclosed is a micrometeoroid and debris protection system (MDPS) for a thermal control system on a spacecraft. The MDPS comprises a radiator face-sheet, a truss attached to the radiator face-sheet, and a thermally transparent bumper disposed on the truss. The thermally transparent bumper shields the radiator face-sheet from micrometeoroids and debris and enables thermal transfer from the radiator face-sheet through the thermally transparent bumper.

A system to create a magnetic field around the outside of a spacecraft to afford human occupants and electronic equipment with protection from cosmic and solar radiation. Using electromagnets to generate magnetic fields placed on the outer surface of the spacecraft, cosmic and solar radiation may be deflected from entering the main body of the spacecraft. In addition, the magnetic field lines are kept away from the human occupants and interior electronic equipment. Side electromagnets are placed on the side outer surface of the spacecraft and separate electromagnetics are positioned in a cross shaped configuration at the front and rear of the spacecraft in alignment with the side electromagnets. Magnetic field lines are channeled around the outside of the spacecraft or centered on the center of quadrupole magnets placed either at the front of rear of the spacecraft.