Abstract: An ion fusion engine for spacecraft having a water vapor ion-based thruster, and a boron vapor injector which injects boron vapor into an exhaust region of the ion thruster causing proton-boron fusion to occur and thereby provide additional afterburner thrust. In addition, a plurality of pulsed lasers are utilized to focus on focal regions of the exhaust region to catalyze boron fusion events, and post exhaust sensors to provide feedback for control systems.

Abstract: An ion fusion engine for spacecraft having a water vapor ion-based thruster, and a boron vapor injector which injects boron vapor into an exhaust region of the ion thruster causing proton-boron fusion to occur and thereby provide additional afterburner thrust. In addition, a plurality of pulsed lasers are utilized to focus on focal regions of the exhaust region to catalyze boron fusion events, and post exhaust sensors to provide feedback for control systems.

Abstract: A modular reusable catalyst system is provided for a bi-propellant rocket engine and adaptable for a monopropellant, wherein a hydrocarbon fuel is combined with one or more catalysts, and can provide an additional convergent-divergent flow in combination with a thruster.

Abstract: An aerospike rocket, engine having individually throttleable thrusters arranged in an annular ring around an aerospike, and a bi-propellant system having a catalyst system for combining a solid propellant and a hydrocarbon fuel, and an additional convergent-divergent flow for each thruster which combine into a main combustion chamber for the aerospike.