A rover can include a spherical shall and an avionics hub. The spherical shell defines a spherical volume and having an inner surface and an outer surface. The avionics hub is disposed within the spherical volume. The avionics hub includes an avionics shell, a data acquisition unit, and a plurality of motortrain assemblies. The avionics shell is disposed with the spherical volume of the spherical shell. The data acquisition unit is disposed within the avionics shell. Each motortrain assembly includes a motorized wheel extending at least partially through the avionics shell and in contact with the inner surface of the spherical shell, the plurality of motortrain assemblies configured to rotate the spherical shell relative to the avionics shell to move the rover.

Systems and methods to remove dust from an extravehicular mobility unit (EMU) worn by an astronaut in a deep space environment involve one or more ionic shower units installed external to an interior volume of a facility. Each ionic shower unit releases positively charged ions and negatively charged ions in a specified direction to neutralize the dust and generate neutralized dust. The interior volume of the facility is defined by an interior hatch that is separated from an exterior hatch by an airlock. One or more collection units is installed external to the interior volume. Each collection unit traps the neutralized dust to prevent the dust from entering the interior volume.

An autonomous mobile mechanically deployed spaceport is disclosed to provide a self-leveling stable landing pad for lunar and Martian descending and ascending spacecraft and which alleviates rocket plume blast effects upon surface soils and volatiles during spacecraft descent and ascent. The autonomous mobile mechanically deployed spaceport is a mechanically deployed unfolding flying landing pad to allow spacecraft to land on the Moon and Mars and alleviates rocket plume blast effects upon surface soils and volatiles.

An autonomous mobile mechanically deployed spaceport is disclosed to provide a self-leveling stable landing pad for lunar and Martian descending and ascending spacecraft and which alleviates rocket plume blast effects upon surface soils and volatiles during spacecraft descent and ascent. The autonomous mobile mechanically deployed spaceport is a mechanically deployed unfolding flying landing pad to allow spacecraft to land on the Moon and Mars and alleviates rocket plume blast effects upon surface soils and volatiles.

A modular, multi-crew life support system and a method of assembling the system involve a fan to draw in ambient air. The system includes one or more assemblies that produce conditioned air from the ambient air, and a housing to support an oxygen source. The system also includes a port configured as an inlet from the oxygen source to augment the conditioned air, and a duct to disperse a result of augmenting the conditioned air as output air to support two or more occupants of an enclosure.

A modular, multi-crew life support system and a method of assembling the system involve a fan to draw in ambient air. The system includes one or more assemblies that produce conditioned air from the ambient air, and a housing to support an oxygen source. The system also includes a port configured as an inlet from the oxygen source to augment the conditioned air, and a duct to disperse a result of augmenting the conditioned air as output air to support two or more occupants of an enclosure.

A method for the safe release of artificial satellite in Earth orbit includes the steps of providing an orbital transport spacecraft able to move at orbital height and comprising a plurality of PODs for releasing satellites transported by the orbital transport spacecraft, housing said orbital transport spacecraft in a space launcher configured to reach an orbital height; generating a release signal and transmitting it to the orbital transport spacecraft to release the orbital transport spacecraft from the space launcher, in case of failure to release the orbital transport spacecraft or in case of breakdown of the orbital transport spacecraft after releasing from the space launcher, activating a safety subsystem of the orbital transport spacecraft to generate a POD activation sequence to release the satellites.

A covering includes an outer material, a plurality of conductive-fibers, and a fastening material. The outer material includes a front surface and a back surface and the conductive-fibers are disposed between the front surface and the back surface. The conductive-fibers are configured to receive a voltage that causes the conductive-fibers to repel and remove dust from the front surface of the outer material. The fastening material is coupled to the back surface of the outer material and facilitates releasably attaching the outer material to an article.

A covering includes an outer material, a plurality of conductive-fibers, and a fastening material. The outer material includes a front surface and a back surface and the conductive-fibers are disposed between the front surface and the back surface. The conductive-fibers are configured to receive a voltage that causes the conductive-fibers to repel and remove dust from the front surface of the outer material. The fastening material is coupled to the back surface of the outer material and facilitates releasably attaching the outer material to an article.

An electromagnetic pulse (EMP) resistant telecommunications system includes core components mounted within and shielded by a Faraday cage. The components include a data source or storage device. An ethernet switch selectively connects the data source or storage device to a primary satellite router and a post-EMP satellite router. Telecommunications signals are output from and input to the core components via low noise blocks (LNBs) and block upconverters (BUCs). A method of resisting EMP interference for a telecommunications system includes the steps of enclosing and shielding core components in a Faraday cage and providing output via LNBs and BUCs to an antenna subsystem.