Change Log

RPA v.1.2.5

Standard Edition

• fixed mistake in calculation of thermal transport properties for off-optimum component ratios
• fixed mistake in calculation of nozzle exit condition for reaction products with "liqud-solid" phase transition

Lite Edition

Note that RPA Lite Edition v.v.1.2.2 - 1.2.4 have never been released.

• fixed mistake in calculation of nozzle exit condition for reaction products with "liqud-solid" phase transition
• improved filter functionality in species dialog window (ported from RPA SE 1.2.4)

RPA v.1.2.4

Standard Edition

• added export of nozzle contour to ASCII file
• improved filter functionality in species dialog window

RPA v.1.2.3

Standard Edition

• added possibility to define combustion chamber length by either L* or L'
• added calculation of estimated delivered altitude performance
• added calculation of estimated delivered performance of throttled engine

RPA v.1.2.2

Standard Edition

• added possibility to define initial parabola angle for paraboloc nozzles
• fixed mistake in chamber sizing module that allowed definition of L* in SI units only ignoring other selected units (in, ft, mm)
• fixed mistake in parabolic nozzle calculation for nozzles with low area ratio Ae/At

RPA v.1.2.1

Standard Edition

• calculation of thermal transport properties
• fixed mistake that caused program crash when loading configuration file with defined diameter of nozzle throat

Standard and Lite Edition

• improved performance estimation for solid propellants
• fixed mistake in calculation of sonic velocity at nozzle throat section for reaction products with condensed phase

RPA v.1.2.0

Standard Edition

• 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)

Lite Edition

• Minor improvements and bug fixes.

RPA v.1.1.x Lite Edition

1.1.4 (December 20, 2010)

• Bugfix: null pointer usage
• Bugfix: the program can crash when condensed species experience phase transition "liquid"-"solid"
• Estimated correction factor is calculated taking into account the quantity of the condensed phase in reaction products
• Optimum propellant mixture ratio is calculated taking into account the estimated/specified correction factors
• Nested analysis is performed taking into account the estimated/specified correction factors

1.1.3 (December 08, 2010)

• Bugfix: the program can crash due to memory leak in nested analysis module
• Additional distribution package for Linux i386

1.1.2 (November 12, 2010)

• Bugfix: results of multi-parameter nested analysis could not be plotted correctly

1.1.1 (November 08, 2010)

• Bugfix: crash at very off-optimal component ratios
• Plotting function for nested analysis implemented

1.1.0 (November 03, 2010)

• Improved thermodynamic analysis algorithm
• Output in SI units or U.S. customary units
• Improved Graphical User Interface
• Added Command-Line Interface utility
• Improved software installation process
• Installation package for Windows x86-64 (XP/Vista/7)
• Installation package for Mac OS X 10.5+ (universal binary for Intel x86 and x86-64)

1.0.10 (September 10, 2010)

• Initial temperature and/or pressure of the propellant components can be specified.
• Thermodynamic database editor is available. Now you can specify new or change existing propellant components, and immediately use it in your analysis.
• Import of data for propellant components from PROPEP library file is implemented.
• Improved calculation of chamber efficiency.

1.0.09 (August 10, 2010)

• Fixed mistake in nested analysis that caused the application to crash.
• Updated thermodynamic data library (see Thermodynamic data).

1.0.09 (May 11, 2010)

• The temperature of the components can be specified explicitly.

1.0.08

• Added nested analysis, stepping of four independent variables.
• Fixed mistake in calculation of nozzle exit conditions at low temperature and pressure for stoichiometric propellant composition.

1.0.07

• Fixed mistake in calculation log.
• Saving the empty project is now allowed.

1.0.06

• Improved installation procedure.

1.0.05

• Added express analysis view.
• Implemented application session settings (window sizes and positions, recent files, last opened file).

1.0.04

• Fixed application crash while starting analysis on MS Windows Vista or MS Windows 7.
• Reaction products not displayed on the list of available species while adding component to propellant.

1.0.03

• Fixed wrong calculation of amount of condensed species in combustion composition.
• Fixed memory corruption during analysis under certain circumstances.

1.0.02

• Improved model of engine efficiency.

Last modified: May 9, 2012