Abstract: A reusable launch vehicle comprising auxiliary tanks for non-ascent burns, such as orbital maneuver burns, reorientation burns, deorbit burns, or landing burns, and/or power generation. The auxiliary tanks may provide propellants for an orbital maneuvering system, an orbital reaction control system, a reentry reaction control system, and/or a power generation system. The tanks are configured to maintain cryogenic properties of auxiliary fuel and auxiliary oxidizer for the duration of the mission. An auxiliary fuel tank, a main fuel tank, an auxiliary oxidizer tank, and a main oxidizer tank may have various relative positions with respect to each other within the launch vehicle. The auxiliary fuel tank and auxiliary oxidizer tank may comprise insulation to further insulate the cryogenic fluids.

Abstract: A reusable launch vehicle comprising auxiliary tanks for non-ascent burns, such as orbital maneuver burns, reorientation burns, deorbit burns, or landing burns, and/or power generation. The auxiliary tanks may provide propellants for an orbital maneuvering system, an orbital reaction control system, a reentry reaction control system, and/or a power generation system. The tanks are configured to maintain cryogenic properties of auxiliary fuel and auxiliary oxidizer for the duration of the mission. An auxiliary fuel tank, a main fuel tank, an auxiliary oxidizer tank, and a main oxidizer tank may have various relative positions with respect to each other within the launch vehicle. The auxiliary fuel tank and auxiliary oxidizer tank may comprise insulation to further insulate the cryogenic fluids.

Abstract: A cryogenic propellant storage tank system and method are disclosed that thermally couple LO2 and LCH4 tanks together by using either a single tank compartmentalized by a common tank wall or two separate tanks that are coupled together with one or more thermal couplers having high thermal conductivity. Cryogenic cooling equipment may be located only in the LO2 tank while the LCH4 is cooled by the LO2 tank interface. Embodiments of the invention may employ both LO2 and LCH4 liquid acquisition devices (LADs) for low-gravity use. In further embodiments, only the LO2 LADs may be integrated with thermal cooling equipment.