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)
1972-12-01
Report
No indication
English
Liquid rocket combustor computer code development
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