Optimizing a liquid propellant rocket engine with an automated combustor design code

by National Aeronautics and Space Administration

A procedure for automatically designing a liquid propellant rocket engine combustion chamber in an optimal fashion is outlined. The procedure is contained in a digital computer code, AUTOCOM. The code is applied to an existing engine, and design modifications are generated which provide a substantial potential payload improvement over the existing design. Computer time requirements for this payload improvement were small, approximately four minutes in the CDC 6600 computer. Hague, D. S. and Reichel, R. H. and Jones, R. T. and Glatt, C. R. Unspecified Center NASA-CR-120856 NAS3-13331 26634 COMBUSTION CHAMBERS; COMPUTER AIDED DESIGN; COMPUTER PROGRAMS; LIQUID PROPELLANT ROCKET ENGINES; ROCKET ENGINE DESIGN; CDC 6600 COMPUTER; DIGITAL DATA; OPTIMIZATION; PROPULSION SYSTEM CONFIGURATIONS

74 pages, Kindle Edition

Published September 26, 2019

About the author

The National Aeronautics and Space Administration (NASA) is an independent agency of the U.S. federal government responsible for the civil space program, aeronautics research, and space research.