John Beasley 3/20/2008 Propulsion Group Contact: Black Boxes and Code Flowchart AAE 450 Spring 2008

Based on figure by Frederick S. Simmons1 Propulsions Black Boxes Injector Nozzle Cooling -directly down port -into pre-combustor Igniter Fuel Grain Geometry Based on figure by Frederick S. Simmons1 AAE 450 Spring 2008 Propulsion Group

Main Propulsion Code Flowchart Format all values for return to main code Return masses, costs, and volumes to main propulsion code Calculate propellant costs and volumes (~) for each stage Calculate masses (`) for each stage, starting with the last stage Calculate mass ratio for each stage Call appropriate staging function (two or three stage) Assign performance and cost characteristics (@) to each stage based on propellant type Receive mission inputs (#) from main code AAE 450 Spring 2008 Propulsion Group

References 1) www.aero.org/publications/simmons/simmons-1.html AAE 450 Spring 2008

Definition of values passed to/from or calculated in main propulsion code #: total delta v, percent of delta v for first two stages, launch type, number of stages, propellant for each stage, payload mass, inert mass fractions, avionics masses @: expansion ratio, characteristic velocity, thrust coefficient, specific impulse, pressure ratio, specific heat ratio, speed of sound, mach number, chamber temperature, equivalence ratio, fuel cost and density, oxidizer cost and density, chamber pressure `: payload, propellant, inert, total masses for each stage ~: fuel cost and volume, oxidizer cost and volume AAE 450 Spring 2008