Diagnosing whether controllers of internal vehicle systems are the source of failures detected by a system control managing a vehicle such as a spacecraft. Highspeed data is received via at a field programmable gate array (FPGA) embedded in an assembly of the vehicle. The FPGA includes a controller and a digital diagnostic interface. In one embodiment, the diagnostic interface utilizes Very Highspeed Integrated Circuit (VHSIC) Hardware Description Language (VHDL) for performance modeling of a controller configured to control at least one internal system within the vehicle. The VHDL performance models the controller. Upon receiving an indication of a failure, the performance modeling of the controller is used to ascertain whether or not the controller is the source of the failure. Disassembly of the assembly housing the internal system is not required in order to ascertain whether or not the controller is the source of the failure.

Electro oxidation membrane evaporator 1 comprises sweep air handler 60; fluid tank 20 defining a fluid container; fluid contactor/separator 30; oxidation cell 40; and scrubber 80. Electro oxidation membrane evaporator 1 may allow higher percent water recovery from wastewater prior to delivering brine to a brine water recovery system and can allow O.sub.2 from air such as cabin air to continuously diffuse into the wastewater as O.sub.2 is consumed to generate oxidants, helping to eliminate the low oxidant environment at the end of the cycle that causes pH to remain high, and low pH prevents precipitates from forming for longer so more water can be evaporated from the wastewater.

A closed-loop, bioregenerative water purification system including a gravity-independent anaerobic membrane bioreactor capable of operating in the presence and absence of gravity, the bioreactor including an anaerobic bioreactor, a first membrane filtration unit, and a second membrane filtration unit, wherein the anaerobic bioreactor is configured to receive organic waste and hygiene water as inputs and break them down into constituent components using anaerobic microbes, wherein the first membrane filtration unit is configured to receive effluent output from the anaerobic bioreactor, return concentrate to the anaerobic bioreactor, and output permeate to the second membrane filtration unit, and wherein the second membrane filtration unit is configured to receive the permeate output from the first membrane filtration unit, separate biogas from the permeate, and output nutrient-rich water.

A space habitat includes a water processing assembly including a wastewater tank and a water processing section connected to the wastewater tank. The water processing section includes a pump to urge flow of the wastewater, a mostly liquid separator to separate gas from liquid in the wastewater, a catalytic reactor located downstream of the mostly liquid separator, and one or more sensors located downstream of the catalytic reactor to determine if the wastewater is sufficiently processed. A valve directs the wastewater to a water storage tank if the sensors determine that the wastewater is sufficiently processed, and direct the wastewater to the wastewater tank if the one or more sensors determine that the wastewater is not sufficiently processed. The space habitat further includes one or more of a carbon dioxide removal system, a trace contaminant removal system, a temperature and humidity control system or a waste collection system.

A space habitat includes a water processing assembly including a wastewater tank and a water processing section connected to the wastewater tank. The water processing section includes a pump to urge flow of the wastewater, a mostly liquid separator to separate gas from liquid in the wastewater, a catalytic reactor located downstream of the mostly liquid separator, and one or more sensors located downstream of the catalytic reactor to determine if the wastewater is sufficiently processed. A valve directs the wastewater to a water storage tank if the sensors determine that the wastewater is sufficiently processed, and direct the wastewater to the wastewater tank if the one or more sensors determine that the wastewater is not sufficiently processed. The space habitat further includes one or more of a carbon dioxide removal system, a trace contaminant removal system, a temperature and humidity control system or a waste collection system.

A heat rejection system in a vehicle includes a heat exchanger to take in input coolant and to output a warmed coolant, a heat of vaporization device (HVD), and a heat of fusion device (HFD). The heat rejection system also includes a controller to direct the warmed coolant to the HVD or to the HFD based on an input. The input indicates altitude of the vehicle or ambient pressure.

A Space Traffic Management (STM) system comprising a Space Traffic Management System Service Supplier (S3) interface for sending a space conjunction request to a Conjunction Assessment Supplier (CAS) interface, and a Space Situational Awareness Supplier (SSA) interface for receiving and fulfilling space object data requests. The system further comprising the Conjunction Assessment Supplier (CAS) interface for receiving the space conjunction request from the S3 interface, requesting and receiving the space object data from the SSA interface, and generating and sending a conjunction data message to the S3 interface. The system enables coordination of an automated service for spacecraft owner operators to anticipate and avoid a space traffic conjunction using the conjunction data message.

A Space Traffic Management (STM) system comprising a Space Traffic Management System Service Supplier (S3) interface for sending a space conjunction request to a Conjunction Assessment Supplier (CAS) interface, and a Space Situational Awareness Supplier (SSA) interface for receiving and fulfilling space object data requests. The system further comprising the Conjunction Assessment Supplier (CAS) interface for receiving the space conjunction request from the S3 interface, requesting and receiving the space object data from the SSA interface, and generating and sending a conjunction data message to the S3 interface. The system enables coordination of an automated service for spacecraft owner operators to anticipate and avoid a space traffic conjunction using the conjunction data message.

A spacecraft capable of generating an artificial gravity environment comprises frame with a circular track with at least two modules traveling on the track. The two modules are configured to engage the first track opposite the first module to minimize mass imbalance, and a balancing system for the first and second modules configured to mass balance the first and second modules relative to each other. The frame itself does not rotate, and may have other mission supporting structures attached, including storage and supply modules, and observational modules, and spacecraft hangars and spacecraft docking modules. A method of operating a spacecraft to generate artificial gravity in a habitation module comprises operating a frame in space, propelling first and second habitation modules about the frame to generate artificial gravity environments in the modules, and mass balancing the first module relative to the second module to maintain balance of the spacecraft.

A spacecraft capable of generating an artificial gravity environment comprises frame with a circular track with at least two modules traveling on the track. The two modules are configured to engage the first track opposite the first module to minimize mass imbalance, and a balancing system for the first and second modules configured to mass balance the first and second modules relative to each other. The frame itself does not rotate, and may have other mission supporting structures attached, including storage and supply modules, and observational modules, and spacecraft hangars and spacecraft docking modules. A method of operating a spacecraft to generate artificial gravity in a habitation module comprises operating a frame in space, propelling first and second habitation modules about the frame to generate artificial gravity environments in the modules, and mass balancing the first module relative to the second module to maintain balance of the spacecraft.