Abstract: A hybrid propulsion system for a vehicle comprises a propellant tank for providing a supply of propellant, a propellant heater, and an exhaust nozzle. The propellant tank is in fluid communication with the propellant heater and is configured for providing a flow of propellant to the propellant heater. The propellant heater is in fluid communication with the propellant tank and the nozzle and initially comprises a supply of oxidizer that is configured for reacting chemically with the propellant to produce heat. The propellant heater is further configured for receiving a beam of microwave energy and facilitating transmission of the beam of microwave energy to the propellant. The nozzle is in fluid communication with the propellant heater and is configured for receiving a flow of propellant from the propellant heater, for accelerating the propellant, and for expelling the propellant so as to produce thrust.

Abstract: A system for receiving energy from an electromagnetic energy beam, and for transferring the received energy to a working fluid as thermal energy, comprises a heat exchanger body that defines a path for the working fluid. The heat exchanger body comprising a ceramic matrix composite (CMC) material. A method for configuring a heat exchanger for receiving energy from an electromagnetic energy beam, and for transferring the received energy to a working fluid as thermal energy, includes providing a heat exchanger body, the heat exchanger body comprising a ceramic matrix composite (CMC) material, the CMC material comprising a SiC matrix. The method also includes introducing a concentration of dopant into the SiC matrix, wherein the dopant is selected to facilitate absorption of energy from the electromagnetic energy beam, and wherein the concentration is suitable to achieve a desired rate of energy absorption from the electromagnetic energy beam.

Abstract: A hybrid propulsion system for a vehicle comprises a propellant tank for providing a supply of propellant, a propellant heater, and an exhaust nozzle. The propellant tank is in fluid communication with the propellant heater and is configured for providing a flow of propellant to the propellant heater. The propellant heater is in fluid communication with the propellant tank and the nozzle and initially comprises a supply of oxidizer that is configured for reacting chemically with the propellant to produce heat. The propellant heater is further configured for receiving a beam of microwave energy and facilitating transmission of the beam of microwave energy to the propellant. The nozzle is in fluid communication with the propellant heater and is configured for receiving a flow of propellant from the propellant heater, for accelerating the propellant, and for expelling the propellant so as to produce thrust.