In the system of the system of the present invention, the detection processing device detects whether there is any target orbiting craft; the acquisition processing device acquires a surface image of said solar panels after detecting the target orbiting craft; the shadow feature data processing device analyzes the acquired surface image of solar panels to detect whether there is any shadow feature data; the trigger processing device triggers starting power ensuring control for the environment control and life support system after detecting the shadow feature data; the matching processing device matches said shadow feature data with the above-mentioned preset shadow feature data cast by the target orbiting craft on said solar panels, and if they match each other, continue to power said experiment cabin to prevent data loss of the experiment cabin, which can effectively avoid unnecessary experimental data loss of the space station.

In the system of the system of the present invention, the detection processing device detects whether there is any target orbiting craft; the acquisition processing device acquires a surface image of said solar panels after detecting the target orbiting craft; the shadow feature data processing device analyzes the acquired surface image of solar panels to detect whether there is any shadow feature data; the trigger processing device triggers starting power ensuring control for the environment control and life support system after detecting the shadow feature data; the matching processing device matches said shadow feature data with the above-mentioned preset shadow feature data cast by the target orbiting craft on said solar panels, and if they match each other, continue to power said experiment cabin to prevent data loss of the experiment cabin, which can effectively avoid unnecessary experimental data loss of the space station.

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.

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.

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.

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.

The automatic control method for preventing experimental data loss of space station includes: presetting shadow feature data cast by said target orbiting craft on said solar panels; detecting whether there is any target orbiting craft; acquiring a surface image of said solar panels after detecting the target orbiting craft; analyzing the acquired surface image of solar panels to detect whether there is any shadow feature data; starting power ensuring control for the environment control and life support system if the shadow feature data is detected; matching said shadow feature data with the above-mentioned preset shadow feature data cast by the target orbiting craft on said solar panels, wherein if they match each other, said experiment cabin is powered continuously to prevent data loss of the experiment cabin, which can effectively avoid unnecessary experimental data loss of the space station.

The automatic control method for preventing experimental data loss of space station includes: presetting shadow feature data cast by said target orbiting craft on said solar panels; detecting whether there is any target orbiting craft; acquiring a surface image of said solar panels after detecting the target orbiting craft; analyzing the acquired surface image of solar panels to detect whether there is any shadow feature data; starting power ensuring control for the environment control and life support system if the shadow feature data is detected; matching said shadow feature data with the above-mentioned preset shadow feature data cast by the target orbiting craft on said solar panels, wherein if they match each other, said experiment cabin is powered continuously to prevent data loss of the experiment cabin, which can effectively avoid unnecessary experimental data loss of the space station.

Establishing and growth of a lunar or planetary surface base involves continuing to use landing spacecraft as docked modules of the base for habitation and work. A first spacecraft is landed at a specified surface site then doubles as first module of the base. A second (and later third and subsequent) spacecraft is landed at the site a safe distance from the existing base modules then moved over the surface into a side-by-side position to dock with selected base modules. At least some of the landing, surface transport, and operational electric power is supplied by micro-fusion using ambient cosmic rays and muons interacting with deuterium-containing particle fuel material to generate energetic reaction products.

Establishing and growth of a lunar or planetary surface base involves continuing to use landing spacecraft as docked modules of the base for habitation and work. A first spacecraft is landed at a specified surface site then doubles as first module of the base. A second (and later third and subsequent) spacecraft is landed at the site a safe distance from the existing base modules then moved over the surface into a side-by-side position to dock with selected base modules. At least some of the landing, surface transport, and operational electric power is supplied by micro-fusion using ambient cosmic rays and muons interacting with deuterium-containing particle fuel material to generate energetic reaction products.