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Rocket Propulsion Analysis Standard Changelog

What's new in Rocket Propulsion Analysis Standard 2.3.2

Aug 2, 2017
  • Updated tabular properties for CH4(L).
  • Fixed issue in GUI, screen Thermal analysis: on Windows 10, the list of coolant is to small so that the components cannot be selected and edited.

New in Rocket Propulsion Analysis Standard 2.3.1 (Aug 2, 2017)

  • Added support for thermal analysis in scripting utility.
  • Added configuration of injector pressure drop in staged combustion cycle.
  • Fixed issues in thermal and cycle analysis modules.

New in Rocket Propulsion Analysis Standard 2.2.4 (May 4, 2015)

  • Thermal analysis - added support of regenerative cooling segments with two-pass coolant flow
  • Species editor - fixed issue in editor of polynomial properties
  • Scripting utility - added API to design the geometry of combustion chamber and nozzle

New in Rocket Propulsion Analysis Standard 2.2.3 (May 4, 2015)

  • Cycle analysis: improved configuration of Staged Combustion cycle with two turbines

New in Rocket Propulsion Analysis Standard 2.2.2 (May 4, 2015)

  • Modified Scripting Utility API (see User_Manual for more information):
  • Added functions:
  • String sprintf(String format, ...);
  • printf(String format, ...);
  • sscanf(String input, String format, ...);
  • Added objects:
  • File(String name, String mode);
  • File.printf(String format, ...);
  • String File.readLine();
  • File.close();
  • Fixed issues:
  • Performance analysis - fixed improper calculation of propellant density
  • Thrust chamber design - improved calculation of parabolic nozzle contour
  • Cycle analysis - improved estimation of engine performance for gas generator cycle
  • Scripting Utility - function print() prints out the string into default log file

New in Rocket Propulsion Analysis Standard 2.2.1 (May 4, 2015)

  • Fixed issues:
  • Thermal analysis - program crashes when performing analysis of thrust chambers with "coaxial-shells" cooling jackets.

New in Rocket Propulsion Analysis Standard 2.2.0 (May 4, 2015)

  • Thermal analysis - new option to analyze the chamber cooling at specific throttle level of the thrust chamber
  • Thermal analysis - new option to design the cross-section geometry of regeneratively cooling jackets
  • Thermal analysis - improved definition of the cross-section geometry of regeneratively cooling jackets
  • Thermal analysis - cross-section geometry of regeneratively cooling jackets is printed out into the analysis log
  • Nested analysis and Propellant analysis: new column for propellant density in the table with results (only for propellant components with density available in properties file)
  • Performance analysis - propellant density is printed out into the analysis log (only for propellant components with density available in properties file)
  • Fixed issues:
  • Thermal analysis - improved analysis of nozzles with large Ae/At ratio using Ievlev approach

New in Rocket Propulsion Analysis Standard 2.1.5 (May 4, 2015)

  • Cycle analysis - estimation of Isp (SL) as well as engine thrust and thrust-to-weight ratio is supported
  • Fixed issues:
  • Throttled performance with small throttle value ranges is supported
  • Nested and Propellant analyses: improved Isp estimation for off-optimal component ratios
  • Cycle analysis - improved validation of input parameters

New in Rocket Propulsion Analysis Standard 2.1.4 (May 4, 2015)

  • New examples included into distribution package
  • Updated User_Manual included into distribution package
  • Additional problem types are available in Scripting Utility and RPA Wrapper - VT=const, VU=const, and VS=const
  • Modified Scripting Utility API (see User_Manual for more information):
  • Removed functions:
  • Reaction.setP(Number p, String p_unit);
  • Reaction.setT(Number T, String T_unit);
  • Reaction.setH(Number H, String H_unit);
  • Reaction.setS(Number S, String S_unit);
  • Added functions:
  • Reaction.setPT(Number p, String p_unit, Number T, String T_unit);
  • Reaction.setPH(Number p, String p_unit, Number H, String H_unit);
  • Reaction.setPS(Number p, String p_unit, Number S, String S_unit);
  • Reaction.setVT(Number v, String v_unit, Number T, String T_unit);
  • Reaction.setVU(Number v, String v_unit, Number U, String U_unit);
  • Reaction.setVS(Number v, String v_unit, Number S, String S_unit);
  • Reaction.getU(String U_unit);
  • Provided examples have been updated correspondingly
  • Modified RPA Wrapper API:
  • Removed functions:
  • void equilibriumSetP(void* equilibriumPtr, double p, const char* p_units);
  • void equilibriumSetT(void* equilibriumPtr, double T, const char* T_units);
  • void equilibriumSetH(void* equilibriumPtr, double H, const char* H_units);
  • void equilibriumSetS(void* equilibriumPtr, double S, const char* S_units);
  • Added functions:
  • void equilibriumSetPT(void* equilibriumPtr, double p, const char* pressureUnits, double T, const char* temperatureUnits);
  • void equilibriumSetPH(void* equilibriumPtr, double p, const char* pressureUnits, double H, const char* enthalpyUnits);
  • void equilibriumSetPS(void* equilibriumPtr, double p, const char* pressureUnits, double S, const char* entropyUnits);
  • void equilibriumSetVT(void* equilibriumPtr, double v, const char* volumeUnits, double T, const char* temperatureUnits);
  • void equilibriumSetVS(void* equilibriumPtr, double v, const char* volumeUnits, double S, const char* entropyUnits);
  • void equilibriumSetVU(void* equilibriumPtr, double v, const char* volumeUnits, double U, const char* energyUnits);
  • double equilibriumGetU(void* equilibriumPtr, const char* energyUnits);
  • Provided examples have been updated correspondingly
  • Fixed issues:
  • Thermodynamic database editor: fixed issue while saving the user database
  • Cycle Analysis module: improved convergence of solution for staged-combustion cycles
  • Cycle Analysis module: improved convergence of solution for cycles with booster pumps

New in Rocket Propulsion Analysis Standard 2.1.3 (May 4, 2015)

  • Chamber Geometry module: added option to design the nozzle with truncated ideal contour (TIC) which produces max thrust at fixed length
  • Chamber Geometry module: improved model for obtaining efficiency of truncated ideal contour (TIC)
  • Chamber Geometry module: when using nozzle with truncated ideal contour (TIC), chamber performance, propellant mass flow rate and chamber geometry may be obtained using nozzle efficiency calculated for TIC; as result, the numbers may differ from that obtained in Performance Analysis module
  • Thermal Analysis module: improved model of film cooling
  • Thermal Analysis module: added option to specify the relative thickness of the wall layer
  • Updated properties of CH4(L) which makes it possible to use this component as a coolant in Thermal Analysis and propellant component in Cycle Analysis.
  • Nested Analysis and Propellant Analysis: added columns "M" (molecular weight), "gamma" (ratio of specific heats) and "k" (isentropic exponent)
  • Fixed issues:
  • Thermal Analysis module obtains correct value of heat transfer coefficient for chambers with Ac/At > Ae/At

New in Rocket Propulsion Analysis Standard 2.1.2 (May 4, 2015)

  • Fixed issues:
  • Improved convergence of solution for metalized solid propellants

New in Rocket Propulsion Analysis Standard 2.1.1 (May 4, 2015)

  • Updated user manual includes the chapter for the Cycle Analysis.
  • Fixed issues:
  • Could not solve some cycle analysis problems for staged combustion cycle with a high chamber pressure (for instance, example problem RD-170.cfg available in distribution package)

New in Rocket Propulsion Analysis Standard 2.1.0 (May 4, 2015)

  • Added cycle analysis tool to estimate operational parameters of following engine cycles:
  • Staged Combustion cycle (SG)
  • Full Flow Staged Combustion cycle (FFSG)
  • Gas Generator cycle (GG)
  • Added estimation of engine performance for Gas Generator cycle
  • Added estimation of engine dry weigth
  • Fixed issues:
  • When ambiguous design parameters are specified, Chamber Geometry module obtains correct geometry of combustion chamber automatically adjusting parameters L* or L'
  • Thermal Analysis module obtains correct value of radiation heat transfer coefficient for chambers with ambiguous design parameters
  • Thermal Analysis module works properly with several regenerative cooling sections
  • Thermal Analysis module obtains correct parameters (density, thermal conductivity and viscosity) of coolant which consists of several individual components
  • Improved stability of Thermal Analysis module

New in Rocket Propulsion Analysis Standard 1.2.0 (Feb 25, 2011)

  • scripting module to solve user's own problems, extending standard capabilities of the program
  • propellant analysis tool to evaluate different propellant compositions, with stepwise replacement of one component with another one
  • determination of combustion chamber size for given thrust, propellant mass flow rate, or throat diameter
  • designing parabolic or MOC TIC nozzle contour with capability to export the resulting contour to DXF file
  • producing publication-quality plots (in raster or vector format)