Patent Application
20240117501
The present disclosure relates to fuel generation, and more particularly to solid organic waste to methane fuel generation for use in spacecraft propulsion such as for deep space missions such as those for the Artemis Program for deep space exploration and for commercial spacecraft such as the Orbital Reef.
Deep space missions involve distances from Earth to the Moon, Mars, and beyond. Crewed space missions to the Moon take about three days travel time from Earth to the Moon. Space missions to Mars take about seven months travel time from Earth to Mars. Due to long travel times, supplies of fuel to propel and maneuver spacecraft is needed for support of deep space missions.
The conventional techniques have been considered satisfactory for their intended purpose. However, there is an ever-present need for improved systems and methods for fuel supplies for deep space missions and the like. This disclosure provides a solution for this need.
A system includes a combustion reactor configured to receive solid organic waste and O2, and to output a combined stream of H2O and CO2. A separator is configured to receive the combined stream of H2O and CO2 from the combustion reactor and to separately output a stream of CO2 and a stream of H2O. A Sabatier reactor is operatively connected to receive CO2 from the separator and to receive H2 from an H2 source, and to output CH4.
A mixer can be operatively connected to receive a portion of the O2 diverted from a supply line supplying the O2 to the combustion reactor, and to receive CO2 scrubbed air, and to output a mixture of the diverted O2 and the CO2 scrubbed air.
A water electrolyzer can be operatively connected to receive H2O from the separator through a water supply line, to output the H2 to the Sabatier Reactor through an H2 supply line, and to output the O2 to the supply line supplying the O2 to the combustion reactor and to the mixer, for oxidizing the solid organic waste with pure O2 in the combustion reactor. A thermal amine scrubber (TAS) can be configured to receive cabin air that includes CO2 and to output the CO2 scrubbed air to the mixer in a scrubbed air line.
A CO2 accumulator can be connected to a first CO2 line to receive CO2 from the TAS. The CO2 accumulator can be connected to a second CO2 line to receive CO2 from the separator. The CO2 accumulator can be connected to a third CO2 line to supply CO2 from the CO2 accumulator to the Sabatier reactor.
A spacecraft can include a thruster operatively connected to receive CH4 from the Sabatier reactor for combustion to generate thrust. The spacecraft can include a cabin configured to receive O2 enriched air from the mixer and to supply CO2 to the TAS for scrubbing.
A method of producing fuel includes combining CO2 from a spacecraft cabin and from solid organic waste, and supplying the CO2 to a Sabatier reactor to produce CH4 fuel. The method includes generating H2 and supplying it to the Sabatier reactor for use in generating the CH4 fuel, wherein generating H2 includes producing O2, at least some of which is supplied to the spacecraft cabin for life support.
The method can include mixing CO2 scrubbed air with the O2 which is supplied to the cabin for life support. The CO2 from solid organic waste can be produced by reacting the organic waste with O2. Reacting the organic waste with O2 can include combusting the organic waste and O2 into combustion products including CO2 and H2O.
The method can include separating CO2 from the combustion products for use in the Sabatier Reactor and separating H2O from the combustion products. The method can include electrolyzing the H2O from the combustion products into O2 and H2 and supplying the H2 to the Sabatier reactor. The method can include recycling H2O from the Sabatier reactor to be electrolyzed. The method can include scrubbing CO2 from the spacecraft cabin for use in the Sabatier reactor. The method can include combusting the CH4 in a thruster of the spacecraft.
These and other features of the systems and methods of the subject disclosure will become more readily apparent to those skilled in the art from the following detailed description of the preferred embodiments taken in conjunction with the drawings.
So that those skilled in the art to which the subject disclosure appertains will readily understand how to make and use the devices and methods of the subject disclosure without undue experimentation, preferred embodiments thereof will be described in detail herein below with reference to certain FIGURES, wherein:
Reference will now be made to the drawings wherein like reference numerals identify similar structural features or aspects of the subject disclosure. For purposes of explanation and illustration, and not limitation, a partial view of an embodiment of a system in accordance with the disclosure is shown in
The system 100 can include or be incorporated in a crewed spacecraft 102. The system includes an oxidative combustion reactor 104 configured to receive solid organic waste and O2, and to output a combined stream of H2O and CO2, as indicated by the arrows pointing into and out of the reactor 104 in
A mixer 110 is operatively connected to receive a portion of the O2 diverted from a supply line 112 supplying the O2 to the combustion reactor 104, and to receive metabolic CO2 scrubbed air, e.g. from the thermal amine scrubbers (TAS) described below, and to output a mixture of the diverted O2 and the metabolic CO2 scrubbed air, e.g. to the crewed cabin 114 for breathing air for the spacecraft crew members.
A water electrolyzer 116 is operatively connected to receive H2O from the separator 106 through a water supply line 118, to output the H2 gas to the Sabatier Reactor 108 through an H2 supply line 120, and to output the O2 to the supply line 112 supplying the O2 to the oxidative combustion reactor 104 and to the mixer 110, e.g., for oxidizing the solid organic waste with pure O2 in the oxidative combustion reactor. A thermal amine scrubber (TAS) 122 is configured to receive cabin air that includes metabolic CO2 and to output the CO2 scrubbed air to the O2/air mixer 110 in a scrubbed air line 124.
A CO2 accumulator 126 is connected to a first CO2 line 128 to receive CO2 from the TAS 122. The CO2 accumulator 126 is connected to a second CO2 line 130 to receive CO2 from the separator 106. The CO2 accumulator 126 is connected to a third CO2 line 132 to supply CO2 from the CO2 accumulator 126 to the Sabatier reactor 108.
The spacecraft 102 includes a thruster 134 operatively connected to receive CH4 from the Sabatier reactor 108, as indicated by the arrow out of the Sabatier reactor 108 in
A method of producing fuel includes combining CO2 from a spacecraft crew cabin, e.g. cabin 114, and from solid organic waste, and supplying the CO2 to a Sabatier reactor, e.g. Sabatier reactor 108, to produce CH4 fuel. The method includes generating H2 and supplying it to the Sabatier reactor for use in generating the gaseous CH4 fuel, wherein generating H2 includes producing O2, at least some of which is supplied to the spacecraft crew cabin for life support.
The method includes mixing metabolic CO2 scrubbed air with the O2 which is supplied to the cabin for life support. The CO2 from solid organic waste oxidative combustion is produced by reacting the organic waste with O2, e.g. in the reactor 104. Reacting the organic waste with O2 includes combusting the organic waste and O2 into combustion products including gaseous CO2 and water vapor H2O.
The method includes separating CO2 from the oxidative combustion products for use in the Sabatier Reactor and separating H2O from the combustion products, e.g., in a separator 106. The method includes electrolyzing the H2O from the combustion products into O2 and H2 and supplying the H2 to the Sabatier reactor, e.g. using an electrolyzer 116. The method includes recycling H2O from the Sabatier reactor to be electrolyzed, e.g. using the water recycle line 136 feeding into line 118. The method includes scrubbing CO2 from the spacecraft crew cabin for use in the Sabatier reactor, e.g. using the TAS 122. The method includes combusting the CH4 in a thruster, e.g., thruster 134, of the spacecraft. Some of the O2 generated from the water electrolyzer 116 can be used to combust CH4 in the thruster to propel the spacecraft 102.
The methods and systems of the present disclosure, as described above and shown in the drawings, provide for production of fuel from solid organic waste such as for use during deep space missions. While the apparatus and methods of the subject disclosure have been shown and described with reference to preferred embodiments, those skilled in the art will readily appreciate that changes and/or modifications may be made thereto without departing from the scope of the subject disclosure.
