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rect 228 81 269 118 [[Run Simulation|Run simulation]]
rect 228 81 269 118 [[Run Simulation|Run simulation]]
rect 271 80 308 116 [[Nozzle Optimization|Clicking this button will run multiple simulations to find the optimum (highest thrust) nozzle dimensions given the nozzle throat diameter.]]
rect 271 80 308 116 [[Nozzle Optimization|Clicking this button will run multiple simulations to find the optimum (highest thrust) nozzle dimensions given the nozzle throat diameter.]]
rect 1045 124 1167 153 [[Nozzle Tab|Enter this tab for nozzle properties]]
rect 1045 124 1167 153 [[Main_Page|Enter this tab for nozzle properties]]
rect 1185 131 1268 154 [[Propellants Tab|Enter this tab for editing propellants]]
rect 1185 131 1268 154 [[Propellants Tab|Enter this tab for editing propellants]]
rect 1276 131 1337 154 [[Startup Tab|Options for startup transients.  Not currently implemented]]
rect 1276 131 1337 154 [[Startup Tab|Options for startup transients.  Not currently implemented]]

Latest revision as of 16:46, 16 November 2022

Welcome to the BurnSim Wiki!  Here you will find the current documentation on how to use the BurnSim software as well as other subjects related to Experimental Solid propellants including Propellant Characterization, Motor Testing and Data Aquisition, and more!

Hover over or click on various fields in the image below to get more details on each field in BurnSim.

BurnSim Main WindowFile MenuAction MenuSettings MenuView MenuHelp MenuGrain Type for specified/highlighted grainsPropellant for specified grain selected from propellant databaseGrain LengthGrain DiameterGrain Core DiameterCore Offset, Fin Thickness, etc - this field will change depending on the type of grain selectedNumber Of Points when a star grain is selected - this field will change depending on the type of grain selected Number Of Points when a star grain is selected - this field will change depending on the type of grain selectedFin Length for finocyl grains - this field will change depending on the type of grain selectedInhibited Ends - select the number of inhibited ends for the grain(s). Can be 0-2.Add Grain - this button adds a grain with the specified propertiesDelete Grain - this button will delete any grains selected in the gridUpdate Grain - this button will update any grains selected in the grid with the properties specified.Grain Up - moves the grain up in the motorGrain Down - moves the grain down in the motorDisplayes motor grains and propertiesImage of the selected grain cross sectionFuture feature where a longitudinal cross section of the motor will be displayedOpen a BSX FileStart a new motor simulationSave current motor diskExport current motor to ENG file for use in flight simulatorsExport current motor data to CSV for consumption in other applicationsRun simulationClicking this button will run multiple simulations to find the optimum (highest thrust) nozzle dimensions given the nozzle throat diameter.Enter this tab for nozzle propertiesEnter this tab for editing propellantsOptions for startup transients. Not currently implementedNot yet implementedDiameter of nozzle throatUse Nozzle Calculations - when selected this will calculate thrust coefficient based on nozzle dimensionsExit Diameter of the nozzleExpansion Ratio of the nozzleAmbient atmospheric pressureEfficiency - Thrust calculations are based on ideal conditions which are not normally encountered in real life. Select a value here like 90% as needed.Nozzle Erosion - Erosion of the nozzle throat diameter over timeThrust Coefficient - Specify this if you wish to use a given thrust coefficient for thrust calculations instead of calculating from nozzle dimensions.Enter here to view simulation results summaryEnter here to modify colors and turn graph lines on/offEnter here to import test data and view previously imported test dataKn values from the simulation. Kn = ratio of propellant surface area to nozzle throat areaVolume loading percentage of propellant in given motor cylinder volumeRatio of the bottom grain core diameter to the nozzle throat diameterRatio of the nozzle throat diameter to the bottom grain core diameterRatio of propellant core length to diameterMinimum thickness of propellantSimulated motor burn timeLength of all motor grains from top to bottomTotal mass of propellant before burntSimulated total impuseSimulated motor Class DesignationSimulated Delivered ISPSimulated peak max flux of current motorSpecify start value for X axis, useful for zooming in on specific parts of the burnSpecify end value for X axis, useful for zooming in on specific parts of the burnFor motors with a long tail-off, can specify a % of max thrust to designate motor burnout and end the simulationSimulation Results are displayed hereEnter here to view simulation graphNotes tab for recording notes on a motor. Will be saved with the motor.
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