The *dat file is compatible for creating splines in Unigraphics NX, Catia, and SolidWorks. The rocket propulsion system design coordinates are saved to a *dat file which can be used in a CAD program to plot a 3-D model of the rocket propulsion system. Additional design calculations are determined and displayed within the program such as specific impulse, exhaust velocity, propellant weight flow, fundamental instability frequencies, etc.
A 2-D graphical representation of the nozzle and/or chamber is plotted and coordinates of the plotted line are displayed. The program takes the available selections and specifications made by the user and outputs key design parameters calculated from the input variables. Chamber dimensions, propellant selections, and injector selection between doublet or triplet allow for further refinement of the desired rocket system design. The program also allows for the selection of common nozzle profiles including 80% rao, conical, a user selected percentage bell, and a minimum length nozzle (MLN) using method of characteristics (MOC). The program aids in unifying the nozzle, chamber and injector portions of a rocket propulsion system design effort quickly and efficiently using a streamlined graphical user interface (GUI). This document details the functionality of a software program used to streamline a rocket propulsion system design, analysis and simulation effort.
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