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.
Optimizing a liquid propellant rocket engine with an automated combustor design code (AUTOCOM)
01.12.1972
Report
Keine Angabe
Englisch
Liquid rocket combustor computer code development
NTRS | 1985
|Propellant Injector Influence on Liquid-Propellant Rocket Engine Instability
Online Contents | 2015
|