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

2. 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

3. 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

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

5. 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