Abstract: A rocket engine nozzle includes an aerospike having a plurality of adjustable airfoil vanes distributed around a central longitudinal axis of a rocket engine combustion chamber. The aerospike is integrated on an exit plane at an exit end of the combustion chamber. The adjustable airfoil vanes and an inner perimeter of the combustion chamber define a plurality of apertures which choke an exhaust exiting the combustion chamber and cause the exhaust to expand supersonically along the adjustable airfoil vanes, creating a supersonic jet. An actuator is configured to adjust a position of each of the adjustable airfoil vane relative to each other so as to direct the exhaust exiting the rocket engine combustion chamber as the exhaust expands supersonically over the airfoil vanes without causing a shockwave to be imparted on the supersonic jet that is created. Accordingly, performance of the rocket engine is improved over conventional systems.

Abstract: A rocket engine nozzle includes an aerospike having a plurality of adjustable airfoil vanes distributed around a central longitudinal axis of a rocket engine combustion chamber. The aerospike is integrated on an exit plane at an exit end of the combustion chamber. The adjustable airfoil vanes and an inner perimeter of the combustion chamber define a plurality of apertures which choke an exhaust exiting the combustion chamber and cause the exhaust to expand supersonically along the adjustable airfoil vanes, creating a supersonic jet. An actuator is configured to adjust a position of each of the adjustable airfoil vane relative to each other so as to direct the exhaust exiting the rocket engine combustion chamber as the exhaust expands supersonically over the airfoil vanes without causing a shockwave to be imparted on the supersonic jet that is created. Accordingly, performance of the rocket engine is improved over conventional systems.