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.

Disclosed are methods and means of optimizing health of a subject during space travel comprising real time monitoring and intervention guided by automated and/or semiautomated means driven by a machine learning artificial intelligence-based system. In one embodiment the invention discloses the integration of genetic factors, biological properties, microbiome diversity, regenerative activity, and real time physiological changes in order to provide optimum interventions which result in increased health upon return from the space mission, as well as provide ability for said astronaut to endure space travel of increased durations.

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 system, method, and apparatus for a vented launch vehicle adaptor (LVA) for a manned spacecraft with a pusher launch abort system are disclosed. The disclosed LVA provides a structural interface between a commercial crew vehicle (CCV) crew module/service module (CM/SM) spacecraft and an expendable launch vehicle. The LVA provides structural attachment of the module to the launch vehicle. It also provides a means to control the exhaust plume from a pusher-type launch abort system that is integrated into the module. In case of an on-pad or ascent abort, which requires the module to jettison away from the launch vehicle, the launch abort system exhaust plume must be safely directed away from critical and dangerous portions of the launch vehicle in order to achieve a safe and successful jettison.

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 reusable orbital vehicle for a space transport system including a fuselage with a shape splayed in a direction going from a front end of the reusable orbital vehicle as far as a rear end of said fuselage and within which a housing is defined, and a crew-evacuation vehicle housed in said housing while being oriented so as to be extracted from the housing in a direction oriented from said rear end of the fuselage towards said front end of the reusable orbital vehicle.

A seat system for use in a crew escape system of a space transport vehicle comprises a seat having a backrest with a supporting surface. The seat is configured to be installed in a cabin area of the crew escape system so it can rotate about a first axis between a first position where the seat faces a first direction, and a second position where faces a second direction that is opposed to the first direction. The seat system further comprises a control unit configured to control a rotation of the seat at least between the first position and the second position in dependence on at least one signal which is indicative of a trajectory of the crew escape system.