RPA: Design Tool for Liquid Rocket Engine Analysis
Ponomarenko, A. - May 2010
The report describes a numerical model and presents equations used for the combustion equilibrium and performance
calculations. Results obtained from implementing these equations will be compared with results from
equilibrium code CEA2.
RPA - Tool for Rocket Propulsion Analysis
Ponomarenko, A. - Conference "Space Propulsion - 2014". Cologne, Germany 2014
This conference paper presents the Rocket Propulsion Analysis tool (RPA) - a multi-platform computational
package intended for use in the conceptual and preliminary design of liquid-propellantrocket
A description of the components and the most important aspects of the physical modeling is
included. It provides details on the following modules: thrust chamber performance analysis,
combustion chamber sizing and nozzle contour design, thrust chamber thermal analysis, engine
cycle analysis and weight estimation. Physical models implemented in RPA enable the analysis of
rocket engines with accuracy sufficient for conceptual and preliminary design studies.
All modules are integrated into executable with user-friendly graphical user interface. Development
tools (set of libraries and documented API) are available, allowing the user to create various custom
applications written in C++.