Propellants Tab: Difference between revisions

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rect 178 81 219 116 [[CSV Export|Export current motor data to CSV for consumption in other applications]]
rect 178 81 219 116 [[CSV Export|Export current motor data to CSV for consumption in other applications]]
rect 228 81 269 118 [[Run Simulation|Run simulation]]
rect 228 81 269 118 [[Run Simulation|Run simulation]]
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]]
rect 1418 167 1504 203 [[Area Button|Not yet implemented]]
rect 1418 167 1504 203 [[Area Button|Not yet implemented]]
rect 1054 614 1145 641 [[Sim Results Tab|Enter here to view simulation results summary]]
rect 1054 614 1145 641 [[Main_Page|Enter here to view simulation results summary]]
rect 1157 613 1251 637 [[Graph Lines Tab|Enter here to modify colors and turn graph lines on/off]]
rect 1157 613 1251 637 [[Graph Lines Tab|Enter here to modify colors and turn graph lines on/off]]
rect 1266 614 1343 640 [[Test Data Tab|Enter here to import test data and view previously imported test data]]
rect 1266 614 1343 640 [[Test Data Tab|Enter here to import test data and view previously imported test data]]

Latest revision as of 17:01, 16 November 2022

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

BurnSim Main WindowName of the propellantCommon propellant properties, including characterization numbersHere you can specify propellant properties based on chamber pressure. For some propellants, properties change with chamber pressurePropellant NotesC* or Characteristic Exhaust Velocity. This can be calculated in ProPepCharacteristic ISP is simply another representation of C*, aboveBurn Rate Coefficient (A)Burn Rate Coefficient (N)Propellant Density, measured or theoretical from ProPepSpecific Heat Ratio is currently not required, will be used for Startup Transient Simulation in the futureMolar Mass is currently not required, will be used for Startup Transient Simulation in the futureClick this button to add a new propellantClick this button to edit selected propellantClick this button to delete the selected propellantFile 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 simulationEnter this tab for nozzle propertiesEnter this tab for editing propellantsOptions for startup transients. Not currently implementedNot yet implementedEnter 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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