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ROCket Combustor Interactive Design (ROCCID)

Performance and combustion stability analysis for liquid rocket engines


Sierra Engineering has maintained and enhanced the ROCket Combustor Interactive Design (ROCCID) and analysis computer model since 2000. ROCCID provides a standardized methodology using state-of-the-art codes and procedures for the analysis of a liquid rocket engine combustor's steady state combustion performance and combustion stability. ROCCID also includes an interactive design capability for liquid propellant combustors. The most current version of ROCCID is the 2013 release.


Year - $3500
Month - $700
Week - $250
Day - $150
Initiation Fee - $200
Export controlled
ROCCID is currently capable of analyzing mixed element injector patterns containing impinging like doublet or unlike triplet, showerhead, shear coaxial and swirl coaxial elements as long as only one element type exists in each injector core, baffle, or barrier zone. Real propellant properties of oxygen, hydrogen, methane, propane, RP-1, ethylene, and space storables are included in ROCCID. The properties of other propellants can be easily added.
The analysis models in ROCCID can account for the influences of acoustic cavities, helmholtz resonators and radial thrust chamber baffles on combustion stability. ROCCID also contains the logic to interactively create a combustor design that will meet input performance and stability goals.
A preliminary design results from the application of historical correlations to the input design requirements. The steady state performance and combustion stability of this design is evaluated using the analysis models, and ROCCID guides the user as to the design changes required to satisfy the user's performance and stability goals, including the design of stability aids.

Output from ROCCID includes a formatted input file for the standardized JANNAF engine performance prediction procedure.

Our current proprietary release, ROCCID 2013, includes numerous enhancements and improvements over the original verions of ROCCID. ROCCID 2003 included integrated EXCEL plotting and enhanced combustion response modelling capabilities. ROCCID 2006 included the capability to analyze the stability characteristics of some rectangular cross-section combustors. ROCCID 2010 included modifications to account for the presence of multiple exhaust nozzles, e.g. a turbine inlet, and liquid-liquid coaxial injectors. ROCCID 2010 also included additional options for injection and burning response modelling.

The current ROCCID 2013 release includes modeling of gas-gas injection elements (impinging and coaxial), gas-centered swirl coaxial injection elements and improved treatment of staged combustion propellant inlets.