Abstract: This disclosure relates to a system for actively controlling shock train in a high speed, air-breathing propulsion engine. The system includes an isolator, a sensor associated with the isolator, and a shock train fuel injector in electrical communication with the sensor. The sensor is configured to sense changes in pressure generated by a shock train in the isolator. The shock train fuel injector is in electrical communication with the sensor. The shock train fuel injector is configured to modulate fuel flow to the engine to control back pressure produced by the engine in response to predetermined pressure changes in the shock train.

Abstract: The present invention relates to a propulsion system for a vehicle. The propulsion system has an airframe integrated hydrocarbon fueled airbreathing engine, such as a ramjet or a scramjet. The propulsion system further has at least one rocket positioned so as to use the aft body contour of the vehicle directly for flow expansion. In a preferred embodiment, a plurality of rockets are arrayed across the width of the engine nozzle.

Abstract: The present invention relates to a propulsion system for a vehicle. The propulsion system has an airframe integrated hydrocarbon fueled airbreathing engine, such as a ramjet or a scramjet. The propulsion system further has at least one rocket positioned so as to use the aft body contour of the vehicle directly for flow expansion. In a preferred embodiment, a plurality of rockets are arrayed across the width of the engine nozzle.

Abstract: A ramjet engine has an inlet, an outlet, and a gas flowpath from the inlet to the outlet. A pilot recess is along the flowpath. A plurality of struts extend within the flowpath. Each strut has first and second side surfaces extending between leading and trailing ends the trailing end sweeping away from the recess in a downstream direction across from the pilot recess. Each strut has first and second distributed fuel outlets positioned to discharge fuel from the first and second side surfaces respectively.

Abstract: The present invention relates to an improved variable geometry inlet for a scram jet engine having at least one combustor module. The variable geometry inlet comprises each combustor module having two sidewalls. Each of the sidewalls has a central portion with a thickness and a tapered profile forward of the central portion. The tapered profile terminates in a sharp leading edge. The variable geometry inlet further comprises each module having a lower wall and a movable cowl flap positioned forward of the lower wall. The movable cowl flap has a leading edge and the leading edges of the sidewalls intersect the leading edge of the cowl flap.

Abstract: The present invention relates to an improved variable geometry inlet for a scram jet engine having at least one combustor module. The variable geometry inlet comprises each combustor module having two sidewalls. Each of the sidewalls has a central portion with a thickness and a tapered profile forward of the central portion. The tapered profile terminates in a sharp leading edge. The variable geometry inlet further comprises each module having a lower wall and a movable cowl flap positioned forward of the lower wall. The movable cowl flap has a leading edge and the leading edges of the sidewalls intersect the leading edge of the cowl flap.