Abstract: An integrated engineering analysis system that determines at least one final output value in response to at least one initial input value. A first subprocesses provides at least one output value in response to the initial input value. A plurality of subprocesses provide a plurality of output values in response to the output values of the first subprocess. The plurality of output values and the output value of the first subprocess are inputted into at least one of the plurality of subprocesses. A command code executes each of the plurality of subprocesses in response to the output values and determines which one of the plurality of subprocesses to run and a final subprocess provides a final output. The final output is the result of a plurality of calculations executed by the plurality of subprocesses and the command code compares the final output with the initial input.

Abstract: A scramjet engine is disclosed which is effective for use in a hypersonic aircraft as an aircraft-integrated scramjet engine. The engine includes a first surface having an aft facing step, and a cowl upper surface spaced from the first surface to define an integrated inlet-combustor therebetween. A method of operating the engine includes injecting fuel into the inlet-combustor at the step for mixing fuel with supersonic airflow for generating supersonic combustion gases in the inlet-combustor. In the preferred embodiment of the invention, the fuel is injected to create a fluid boundary defining a subsonic fuel zone and a supersonic fluid zone. The fluid boundary is variable and eliminates start and unstart problems requiring variable inlet geometry in a conventional scramjet engine.

Abstract: A scramjet engine is disclosed which is effective for use in a hypersonic aircraft as an aircraft-integrated scamjet engine. The engine includes a first surface having an aft facing step, and a cowl upper surface spaced from the first surface to define an integrated inlet-combustor therebetween. Means for injecting fuel into the inlet-combustor at the step are provided for mixing fuel with supersonic airflow for generating supersonic combustion gases in the inlet-combustor. In the preferred embodiment of the invention, the fuel injecting means is effective for injecting fuel to create a fluid boundary defining a subsonic fuel zone and a supersonic fluid zone. The fluid boundary is variable and eliminates start and unstart problems requiring variable inlet geometry in a conventional scramjet engine.

Abstract: A method for feeding an extrudable fuel into a pressurized combustion chamber includes extruding the fuel through a screw extruder and introducing the extruding fuel into the chamber through a passage at the end of the extruder. The passage has reduced cross-sectional area compared to that of the extruder, so that extruded fuel is compacted and provides a pressure seal for the chamber. The compacted fuel is atomized as it is introduced into the combustion chamber, so that the fuel is broken up into particles and dispersed into the chamber. Apparatus for carrying out the invention includes a screw extruder having a helically shaped screw of constant radius affixed to the outer surface of a rotatable shaft. A frusto-conically shaped member is attached to the end of the shaft and disposed through the end of the extruder so that an annular opening is defined between the outer surface of the member and the inner surface of the extruder body.