BurnSim Wiki - User contributions [en]

Import from CSV

2022-11-17T01:22:56Z

Gregd: Created page with "To import test data into BurnSim from a CSV (Command Delimited text file) it must be in this format Time, Pressure, Thrust Thrust data is optional and can be excluded. A sample data file snippet is given below for an example, which includes only time and pressure data. If thrust data is available, it should be included as a 3rd column in the file. 0,0.00 0.008,7.40 0.017,12.34 0.025,22.20 0.033,32.07 0.042,46.88 ..."

To import test data into BurnSim from a CSV (Command Delimited text file) it must be in this format

Time, Pressure, Thrust

Thrust data is optional and can be excluded. A sample data file snippet is given below for an example, which includes only time and pressure data. If thrust data is available, it should be included as a 3rd column in the file.

0,0.00
0.008,7.40
0.017,12.34
0.025,22.20
0.033,32.07
0.042,46.88
...

2022-11-17T00:46:21Z

Gregd:

Welcome to the BurnSim Wiki! Here you will find the current documentation on how to use the [https://BurnSim.com 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.

<imagemap>
File:BurnSimMain.png|700px|alt=BurnSim Main Window
default [[Main Page|Go to main page]]
rect 2 46 54 76 [[FileMenu|File Menu]]
rect 57 47 118 75 [[ActionMenu|Action Menu]]
rect 126 49 202 74 [[SettingsMenu|Settings Menu]]
rect 206 47 269 77 [[ViewMenu|View Menu]]
rect 272 49 317 75 [[HelpMenu|Help Menu]]
rect 18 136 316 171 [[Grain Types|Grain Type for specified/highlighted grains]]
rect 20 174 317 213 [[Propellant|Propellant for specified grain selected from propellant database]]
rect 18 221 315 262 [[Grain Length|Grain Length]]
rect 20 264 314 297 [[Grain Diameter|Grain Diameter]]
rect 13 302 315 331 [[Grain Core Diameter|Grain Core Diameter]]
rect 20 337 309 372 [[Grain Core Offset|Core Offset, Fin Thickness, etc - this field will change depending on the type of grain selected]]
rect 19 378 313 413 [[Number of Fins|Number 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 selected]]
rect 24 418 310 454 [[Fin Length|Fin Length for finocyl grains - this field will change depending on the type of grain selected]]
rect 18 453 312 494 [[Inhibited Ends|Inhibited Ends - select the number of inhibited ends for the grain(s). Can be 0-2.]]
rect 20 502 94 535 [[Add Grain|Add Grain - this button adds a grain with the specified properties]]
rect 98 500 174 531 [[Delete Grain|Delete Grain - this button will delete any grains selected in the grid]]
rect 181 501 252 538 [[Apply Grain Changes|Update Grain - this button will update any grains selected in the grid with the properties specified.]]
rect 265 502 310 532 [[Move Grain Up|Grain Up - moves the grain up in the motor]]
rect 314 502 389 534 [[Move Grain Down|Grain Down - moves the grain down in the motor]]
rect 324 138 747 491 [[Grain Table|Displayes motor grains and properties]]
rect 760 139 1016 395 [[Grain Cross Section|Image of the selected grain cross section]]
rect 779 440 1004 493 [[Motor Cross Section|Future feature where a longitudinal cross section of the motor will be displayed]]
rect 1 83 42 116 [[Open File|Open a BSX File]]
rect 47 79 83 118 [[New Motor|Start a new motor simulation]]
rect 88 79 128 118 [[Save File|Save current motor disk]]
rect 136 80 172 117 [[ENG Export|Export current motor to ENG file for use in flight simulators]]
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 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 [[Main_Page|Enter this tab for nozzle properties]]
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 1418 167 1504 203 [[Area Button|Not yet implemented]]
rect 1053 166 1389 206 [[Nozzle Throat Diameter|Diameter of nozzle throat]]
rect 1050 211 1272 232 [[Use Nozzle Calculations|Use Nozzle Calculations - when selected this will calculate thrust coefficient based on nozzle dimensions]]
rect 1053 242 1400 270 [[Nozzle Exit Diameter|Exit Diameter of the nozzle]]
rect 1055 276 1388 317 [[Nozzle Expansion Ratio|Expansion Ratio of the nozzle]]
rect 1057 320 1388 356 [[Ambient Pressure|Ambient atmospheric pressure]]
rect 1058 359 1388 393 [[Nozzle Efficiency|Efficiency - Thrust calculations are based on ideal conditions which are not normally encountered in real life. Select a value here like 90% as needed.]]
rect 1054 399 1393 428 [[Nozzle Diameter Erosion|Nozzle Erosion - Erosion of the nozzle throat diameter over time]]
rect 1052 441 1330 511 [[Use Thrust Coefficient|Thrust Coefficient - Specify this if you wish to use a given thrust coefficient for thrust calculations instead of calculating from nozzle dimensions.]]
rect 1054 614 1145 641 [[Sim Results Tab|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 1266 614 1343 640 [[Test Data Tab|Enter here to import test data and view previously imported test data]]
rect 1058 652 1309 727 [[Kn Values|Kn values from the simulation. Kn = ratio of propellant surface area to nozzle throat area]]
rect 1058 731 1310 754 [[Volume Loading|Volume loading percentage of propellant in given motor cylinder volume]]
rect 1060 756 1308 782 [[Port Throat Area Ratio|Ratio of the bottom grain core diameter to the nozzle throat diameter]]
rect 1055 786 1304 804 [[Throat Port Area Ratio|Ratio of the nozzle throat diameter to the bottom grain core diameter]]
rect 1056 810 1300 829 [[Length Diameter Ratio|Ratio of propellant core length to diameter]]
rect 1057 830 1299 855 [[Web Thickness|Minimum thickness of propellant]]
rect 1322 652 1586 676 [[Burn Time|Simulated motor burn time]]
rect 1323 678 1587 701 [[Propellant Length|Length of all motor grains from top to bottom]]
rect 1326 702 1582 726 [[Propellant Mass|Total mass of propellant before burnt]]
rect 1322 728 1581 750 [[Total Impuse|Simulated total impuse]]
rect 1322 758 1589 775 [[Motor Class|Simulated motor Class Designation]]
rect 1326 779 1587 793 [[Delivered ISP|Simulated Delivered ISP]]
rect 1323 805 1598 835 [[Peak Mass Flux|Simulated peak max flux of current motor]]
rect 44 951 286 982 [[X Axis Start|Specify start value for X axis, useful for zooming in on specific parts of the burn]]
rect 320 954 562 980 [[X Axis End|Specify end value for X axis, useful for zooming in on specific parts of the burn]]
rect 648 947 954 987 [[End Sim Percentage|For motors with a long tail-off, can specify a % of max thrust to designate motor burnout and end the simulation]]
rect 23 597 1023 941 [[Results Graph|Simulation Results are displayed here]]
rect 21 561 75 583 [[Graph Tab|Enter here to view simulation graph]]
rect 86 562 134 585 [[Notes Tab|Notes tab for recording notes on a motor. Will be saved with the motor.]]
</imagemap>

{{#tree:
*[[Main_Page|BurnSim WIKI]]
**[[Getting Started with a Basic Simulation]]
**[[Propellant_Characterization]]
**[[Data_Acquisition]]
}}

File:BurnSimTestDataTab.png

2022-11-17T00:45:03Z

Gregd:

2022-11-17T00:05:46Z

Gregd:

File:BurnSimPropellantsTab.png

2022-11-16T23:58:08Z

Gregd:

Propellants Tab

2022-11-16T23:57:21Z

Gregd: Created page with "Hover over or click on various fields in the image below to get more details on each field. <imagemap> File:BurnSimPropellantsTab.png|700px|alt=BurnSim Main Window default Go to main page rect 2 46 54 76 File Menu rect 57 47 118 75 Action Menu rect 126 49 202 74 Settings Menu rect 206 47 269 77 View Menu rect 272 49 317 75 Help Menu rect 18 136 316 171 Grain Types|Grain Type for speci..."

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

<imagemap>
File:BurnSimPropellantsTab.png|700px|alt=BurnSim Main Window
default [[Main Page|Go to main page]]
rect 2 46 54 76 [[FileMenu|File Menu]]
rect 57 47 118 75 [[ActionMenu|Action Menu]]
rect 126 49 202 74 [[SettingsMenu|Settings Menu]]
rect 206 47 269 77 [[ViewMenu|View Menu]]
rect 272 49 317 75 [[HelpMenu|Help Menu]]
rect 18 136 316 171 [[Grain Types|Grain Type for specified/highlighted grains]]
rect 20 174 317 213 [[Propellant|Propellant for specified grain selected from propellant database]]
rect 18 221 315 262 [[Grain Length|Grain Length]]
rect 20 264 314 297 [[Grain Diameter|Grain Diameter]]
rect 13 302 315 331 [[Grain Core Diameter|Grain Core Diameter]]
rect 20 337 309 372 [[Grain Core Offset|Core Offset, Fin Thickness, etc - this field will change depending on the type of grain selected]]
rect 19 378 313 413 [[Number of Fins|Number 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 selected]]
rect 24 418 310 454 [[Fin Length|Fin Length for finocyl grains - this field will change depending on the type of grain selected]]
rect 18 453 312 494 [[Inhibited Ends|Inhibited Ends - select the number of inhibited ends for the grain(s). Can be 0-2.]]
rect 20 502 94 535 [[Add Grain|Add Grain - this button adds a grain with the specified properties]]
rect 98 500 174 531 [[Delete Grain|Delete Grain - this button will delete any grains selected in the grid]]
rect 181 501 252 538 [[Apply Grain Changes|Update Grain - this button will update any grains selected in the grid with the properties specified.]]
rect 265 502 310 532 [[Move Grain Up|Grain Up - moves the grain up in the motor]]
rect 314 502 389 534 [[Move Grain Down|Grain Down - moves the grain down in the motor]]
rect 324 138 747 491 [[Grain Table|Displayes motor grains and properties]]
rect 760 139 1016 395 [[Grain Cross Section|Image of the selected grain cross section]]
rect 779 440 1004 493 [[Motor Cross Section|Future feature where a longitudinal cross section of the motor will be displayed]]
rect 1 83 42 116 [[Open File|Open a BSX File]]
rect 47 79 83 118 [[New Motor|Start a new motor simulation]]
rect 88 79 128 118 [[Save File|Save current motor disk]]
rect 136 80 172 117 [[ENG Export|Export current motor to ENG file for use in flight simulators]]
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 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 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 1418 167 1504 203 [[Area Button|Not yet implemented]]
rect 1053 166 1389 206 [[Nozzle Throat Diameter|Diameter of nozzle throat]]
rect 1050 211 1272 232 [[Use Nozzle Calculations|Use Nozzle Calculations - when selected this will calculate thrust coefficient based on nozzle dimensions]]
rect 1053 242 1400 270 [[Nozzle Exit Diameter|Exit Diameter of the nozzle]]
rect 1055 276 1388 317 [[Nozzle Expansion Ratio|Expansion Ratio of the nozzle]]
rect 1057 320 1388 356 [[Ambient Pressure|Ambient atmospheric pressure]]
rect 1058 359 1388 393 [[Nozzle Efficiency|Efficiency - Thrust calculations are based on ideal conditions which are not normally encountered in real life. Select a value here like 90% as needed.]]
rect 1054 399 1393 428 [[Nozzle Diameter Erosion|Nozzle Erosion - Erosion of the nozzle throat diameter over time]]
rect 1052 441 1330 511 [[Use Thrust Coefficient|Thrust Coefficient - Specify this if you wish to use a given thrust coefficient for thrust calculations instead of calculating from nozzle dimensions.]]
rect 1054 614 1145 641 [[Sim Results Tab|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 1266 614 1343 640 [[Test Data Tab|Enter here to import test data and view previously imported test data]]
rect 1058 652 1309 727 [[Kn Values|Kn values from the simulation. Kn = ratio of propellant surface area to nozzle throat area]]
rect 1058 731 1310 754 [[Volume Loading|Volume loading percentage of propellant in given motor cylinder volume]]
rect 1060 756 1308 782 [[Port Throat Area Ratio|Ratio of the bottom grain core diameter to the nozzle throat diameter]]
rect 1055 786 1304 804 [[Throat Port Area Ratio|Ratio of the nozzle throat diameter to the bottom grain core diameter]]
rect 1056 810 1300 829 [[Length Diameter Ratio|Ratio of propellant core length to diameter]]
rect 1057 830 1299 855 [[Web Thickness|Minimum thickness of propellant]]
rect 1322 652 1586 676 [[Burn Time|Simulated motor burn time]]
rect 1323 678 1587 701 [[Propellant Length|Length of all motor grains from top to bottom]]
rect 1326 702 1582 726 [[Propellant Mass|Total mass of propellant before burnt]]
rect 1322 728 1581 750 [[Total Impuse|Simulated total impuse]]
rect 1322 758 1589 775 [[Motor Class|Simulated motor Class Designation]]
rect 1326 779 1587 793 [[Delivered ISP|Simulated Delivered ISP]]
rect 1323 805 1598 835 [[Peak Mass Flux|Simulated peak max flux of current motor]]
rect 44 951 286 982 [[X Axis Start|Specify start value for X axis, useful for zooming in on specific parts of the burn]]
rect 320 954 562 980 [[X Axis End|Specify end value for X axis, useful for zooming in on specific parts of the burn]]
rect 648 947 954 987 [[End Sim Percentage|For motors with a long tail-off, can specify a % of max thrust to designate motor burnout and end the simulation]]
rect 23 597 1023 941 [[Results Graph|Simulation Results are displayed here]]
rect 21 561 75 583 [[Graph Tab|Enter here to view simulation graph]]
rect 86 562 134 585 [[Notes Tab|Notes tab for recording notes on a motor. Will be saved with the motor.]]
</imagemap>

Main Page

2022-11-16T23:42:20Z

Gregd:

Welcome to the BurnSim Wiki! Here you will find the current documentation on how to use the [https://BurnSim.com 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.

<imagemap>
File:BurnSimMain.png|700px|alt=BurnSim Main Window
default [[Main Page|Go to main page]]
rect 2 46 54 76 [[FileMenu|File Menu]]
rect 57 47 118 75 [[ActionMenu|Action Menu]]
rect 126 49 202 74 [[SettingsMenu|Settings Menu]]
rect 206 47 269 77 [[ViewMenu|View Menu]]
rect 272 49 317 75 [[HelpMenu|Help Menu]]
rect 18 136 316 171 [[Grain Types|Grain Type for specified/highlighted grains]]
rect 20 174 317 213 [[Propellant|Propellant for specified grain selected from propellant database]]
rect 18 221 315 262 [[Grain Length|Grain Length]]
rect 20 264 314 297 [[Grain Diameter|Grain Diameter]]
rect 13 302 315 331 [[Grain Core Diameter|Grain Core Diameter]]
rect 20 337 309 372 [[Grain Core Offset|Core Offset, Fin Thickness, etc - this field will change depending on the type of grain selected]]
rect 19 378 313 413 [[Number of Fins|Number 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 selected]]
rect 24 418 310 454 [[Fin Length|Fin Length for finocyl grains - this field will change depending on the type of grain selected]]
rect 18 453 312 494 [[Inhibited Ends|Inhibited Ends - select the number of inhibited ends for the grain(s). Can be 0-2.]]
rect 20 502 94 535 [[Add Grain|Add Grain - this button adds a grain with the specified properties]]
rect 98 500 174 531 [[Delete Grain|Delete Grain - this button will delete any grains selected in the grid]]
rect 181 501 252 538 [[Apply Grain Changes|Update Grain - this button will update any grains selected in the grid with the properties specified.]]
rect 265 502 310 532 [[Move Grain Up|Grain Up - moves the grain up in the motor]]
rect 314 502 389 534 [[Move Grain Down|Grain Down - moves the grain down in the motor]]
rect 324 138 747 491 [[Grain Table|Displayes motor grains and properties]]
rect 760 139 1016 395 [[Grain Cross Section|Image of the selected grain cross section]]
rect 779 440 1004 493 [[Motor Cross Section|Future feature where a longitudinal cross section of the motor will be displayed]]
rect 1 83 42 116 [[Open File|Open a BSX File]]
rect 47 79 83 118 [[New Motor|Start a new motor simulation]]
rect 88 79 128 118 [[Save File|Save current motor disk]]
rect 136 80 172 117 [[ENG Export|Export current motor to ENG file for use in flight simulators]]
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 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 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 1418 167 1504 203 [[Area Button|Not yet implemented]]
rect 1053 166 1389 206 [[Nozzle Throat Diameter|Diameter of nozzle throat]]
rect 1050 211 1272 232 [[Use Nozzle Calculations|Use Nozzle Calculations - when selected this will calculate thrust coefficient based on nozzle dimensions]]
rect 1053 242 1400 270 [[Nozzle Exit Diameter|Exit Diameter of the nozzle]]
rect 1055 276 1388 317 [[Nozzle Expansion Ratio|Expansion Ratio of the nozzle]]
rect 1057 320 1388 356 [[Ambient Pressure|Ambient atmospheric pressure]]
rect 1058 359 1388 393 [[Nozzle Efficiency|Efficiency - Thrust calculations are based on ideal conditions which are not normally encountered in real life. Select a value here like 90% as needed.]]
rect 1054 399 1393 428 [[Nozzle Diameter Erosion|Nozzle Erosion - Erosion of the nozzle throat diameter over time]]
rect 1052 441 1330 511 [[Use Thrust Coefficient|Thrust Coefficient - Specify this if you wish to use a given thrust coefficient for thrust calculations instead of calculating from nozzle dimensions.]]
rect 1054 614 1145 641 [[Sim Results Tab|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 1266 614 1343 640 [[Test Data Tab|Enter here to import test data and view previously imported test data]]
rect 1058 652 1309 727 [[Kn Values|Kn values from the simulation. Kn = ratio of propellant surface area to nozzle throat area]]
rect 1058 731 1310 754 [[Volume Loading|Volume loading percentage of propellant in given motor cylinder volume]]
rect 1060 756 1308 782 [[Port Throat Area Ratio|Ratio of the bottom grain core diameter to the nozzle throat diameter]]
rect 1055 786 1304 804 [[Throat Port Area Ratio|Ratio of the nozzle throat diameter to the bottom grain core diameter]]
rect 1056 810 1300 829 [[Length Diameter Ratio|Ratio of propellant core length to diameter]]
rect 1057 830 1299 855 [[Web Thickness|Minimum thickness of propellant]]
rect 1322 652 1586 676 [[Burn Time|Simulated motor burn time]]
rect 1323 678 1587 701 [[Propellant Length|Length of all motor grains from top to bottom]]
rect 1326 702 1582 726 [[Propellant Mass|Total mass of propellant before burnt]]
rect 1322 728 1581 750 [[Total Impuse|Simulated total impuse]]
rect 1322 758 1589 775 [[Motor Class|Simulated motor Class Designation]]
rect 1326 779 1587 793 [[Delivered ISP|Simulated Delivered ISP]]
rect 1323 805 1598 835 [[Peak Mass Flux|Simulated peak max flux of current motor]]
rect 44 951 286 982 [[X Axis Start|Specify start value for X axis, useful for zooming in on specific parts of the burn]]
rect 320 954 562 980 [[X Axis End|Specify end value for X axis, useful for zooming in on specific parts of the burn]]
rect 648 947 954 987 [[End Sim Percentage|For motors with a long tail-off, can specify a % of max thrust to designate motor burnout and end the simulation]]
rect 23 597 1023 941 [[Results Graph|Simulation Results are displayed here]]
rect 21 561 75 583 [[Graph Tab|Enter here to view simulation graph]]
rect 86 562 134 585 [[Notes Tab|Notes tab for recording notes on a motor. Will be saved with the motor.]]
</imagemap>

{{#tree:
*[[Main_Page|BurnSim WIKI]]
**[[Getting Started with a Basic Simulation]]
**[[Propellant_Characterization]]
**[[Data_Acquisition]]
}}

Main Page

2022-11-16T23:31:13Z

Gregd:

Welcome to the BurnSim Wiki! Here you will find the current documentation on how to use the [https://BurnSim.com 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.

<imagemap>
File:BurnSimMain.png|700px|alt=BurnSim Main Window
default [[Main Page|Go to main page]]
rect 2 46 54 76 [[FileMenu|File Menu]]
rect 57 47 118 75 [[ActionMenu|Action Menu]]
rect 126 49 202 74 [[SettingsMenu|Settings Menu]]
rect 206 47 269 77 [[ViewMenu|View Menu]]
rect 272 49 317 75 [[HelpMenu|Help Menu]]
rect 18 136 316 171 [[Grain Types|Grain Type for specified/highlighted grains]]
rect 20 174 317 213 [[Propellant|Propellant for specified grain selected from propellant database]]
rect 18 221 315 262 [[Grain Length|]]
rect 20 264 314 297 [[Grain Diameter|]]
rect 13 302 315 331 [[Core Diameter|]]
rect 20 337 309 372 [[Core Offset|Core Offset, Fin Thickness, etc - this field will change depending on the type of grain selected]]
rect 19 378 313 413 [[Number of Fins|Number 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 selected]]
rect 24 418 310 454 [[Fin Length|Fin Length for finocyl grains - this field will change depending on the type of grain selected]]
rect 18 453 312 494 [[Inhibited Ends|Inhibited Ends - select the number of inhibited ends for the grain(s). Can be 0-2.]]
rect 20 502 94 535 [[Add Grain|Add Grain - this button adds a grain with the specified properties]]
rect 98 500 174 531 [[Delete Grain|Delete Grain - this button will delete any grains selected in the grid]]
rect 181 501 252 538 [[Apply Grain Changes|Update Grain - this button will update any grains selected in the grid with the properties specified.]]
rect 265 502 310 532 [[Move Grain Up|Grain Up - moves the grain up in the motor]]
rect 314 502 389 534 [[Move Grain Down|Grain Down - moves the grain down in the motor]]
rect 324 138 747 491 [[Grain Table|Displayes motor grains and properties]]
rect 760 139 1016 395 [[Grain Cross Section|]]
rect 779 440 1004 493 [[Motor Cross Section|]]
rect 1 83 42 116 [[Open File|]]
rect 47 79 83 118 [[New File|]]
rect 88 79 128 118 [[Save File|]]
rect 136 80 172 117 [[ENG Export|]]
rect 178 81 219 116 [[CSV Export|]]
rect 228 81 269 118 [[Run Simulation|]]
rect 271 80 308 116 [[Nozzle Optimization|]]
rect 1045 124 1167 153 [[Nozzle Tab|Enter this tab for nozzle properties]]
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 1418 167 1504 203 [[Area Button|]]
rect 1053 166 1389 206 [[Nozzle Throat Diameter|Diameter of nozzle throat]]
rect 1050 211 1272 232 [[Use Nozzle Calculations|Use Nozzle Calculations - when selected this will calculate thrust coefficient based on nozzle dimensions]]
rect 1053 242 1400 270 [[Nozzle Exit Diameter|]]
rect 1055 276 1388 317 [[Nozzle Expansion Ratio|]]
rect 1057 320 1388 356 [[Ambient Pressure|]]
rect 1058 359 1388 393 [[Nozzle Efficiency|Efficiency - Thrust calculations are based on ideal conditions which are not normally encountered in real life. Select a value here like 90% as needed.]]
rect 1054 399 1393 428 [[Nozzle Diameter Erosion|Nozzle Erosion - Erosion of the nozzle throat diameter over time]]
rect 1052 441 1330 511 [[Use Thrust Coefficient|Thrust Coefficient - Specify this if you wish to use a given thrust coefficient for thrust calculations instead of calculating from nozzle dimensions.]]
rect 1054 614 1145 641 [[Sim Results Tab|]]
rect 1157 613 1251 637 [[Graph Lines Tab|]]
rect 1266 614 1343 640 [[Test Data Tab|]]
rect 1058 652 1309 727 [[KN Values|]]
rect 1058 731 1310 754 [[Volume Loading|]]
rect 1060 756 1308 782 [[Port Throat Area Ratio|]]
rect 1055 786 1304 804 [[Throat Port Area Ratio|]]
rect 1056 810 1300 829 [[Core Length Diameter Ratio|]]
rect 1057 830 1299 855 [[Web Thickness|]]
rect 1322 652 1586 676 [[Burn Time|]]
rect 1323 678 1587 701 [[Propellant Length|]]
rect 1326 702 1582 726 [[Propellant Mass|]]
rect 1322 728 1581 750 [[Total Impuse|]]
rect 1322 758 1589 775 [[Motor Class|]]
rect 1326 779 1587 793 [[Delivered ISP|]]
rect 1323 805 1598 835 [[Peak Mass Flux|]]
rect 44 951 286 982 [[X Axis Start|]]
rect 320 954 562 980 [[X Axis End|]]
rect 648 947 954 987 [[End Sim Percentage|]]
rect 23 597 1023 941 [[Results Graph|]]
rect 21 561 75 583 [[Graph Tab|]]
rect 86 562 134 585 [[Notes Tab|]]
</imagemap>

{{#tree:
*[[Main_Page|BurnSim WIKI]]
**[[Getting Started with a Basic Simulation]]
**[[Propellant_Characterization]]
**[[Data_Acquisition]]
}}

2022-11-16T22:16:40Z

Gregd:

Main Page

2022-11-16T22:14:02Z

Gregd:

File:BurnSimMain.png

2022-11-16T22:13:11Z

Gregd:

Main Form in BurnSim

Main Page

2022-11-16T21:30:33Z

Gregd:

Main Page

2022-11-15T20:07:31Z

Gregd:

Data Acquisition

2022-11-15T18:22:31Z

Gregd: /* Analog / Digital Converter */

Collecting data from test motors is less complicated than it may seem. There are many options to go about collecting motor test data spanning using a few inexpensive components all the way up to dedicated data collection devices. The process outlined here is intended as a starting point and has many options for expansion. There are dedicated motor testing data collection devices that combine all the below components into a single device.

There are 2 types of data most often collected when motor testing, chamber pressure and thrust. Other data may also be collected, such as case temperature, burn through wires, etc.

Chamber pressure is the most relevant data in a motor test, as it is needed for propellant characterization as well as confirming simulation results on a motor being tested. Further, thrust can be calculated from pressure using nozzle dimensions. [[Calculating Thrust From Presssure Data|BurnSim will do these calculations for you when importing pressure test data]].

== Equipment ==
Basic equipment needed for measuring chamber pressure includes a pressure transducer, analog/digital converter, a laptop and a power source. The laptop does not need to be anything special.

=== Pressure Transducer ===
Chamber pressure is measured with a pressure transducer. While there are different types of pressure transducers, the type most useful here is one with a range suitable for measuring motor chamber pressure (typically in the 1000-2000 psi range) and 3 wires with an output in the 5V range. The 3 wires are Ground, Excitation Voltage, and output. These can be purchased on ebay for relatively cheap, as well as other sources.

=== Analog / Digital Converter ===
An Analog / Digital converter does exactly what the name implies. It takes an analog signal and converts it into a digital signal suitable for recording on a computer. Inexpensive A/D converters are available from [https://www.dataq.com/data-acquisition/starter-kits/ www.Dataq.com] for as little as $50. Their least expensive starter kit includes free software and is suitable for our purposes here.

=== Laptop ===
A laptop is used to record the data from the a/d converter, running the free software that comes with the Dataq unit. Nothing special is required here other than a USB port and the capability to run a recent version of windows. There may also be linux versions of the software available, although i've not tried that myself.

=== Pressure Transducer Calibration Manifold (optional) ===
This is an optional component but recommended for getting the most accurate data. Pressure transducers come with specifications and their output voltage correlates to a range of measured pressures. You can generally rely on this to be correct, but a calibration manifold allows you to confirm your numbers are accurate.

The calibration manifold consists of a block of aluminum with a threaded port each for a pressure gauge, grease gun, the pressure transducer as well as a pressure bleeding screw. A grease gun is used to create pressure, and a pressure gauge is used to show actual pressure being generated.

[image needed]

=== Power Source ===
A 9v battery is suitable to power the pressure transducer, although anything that provides the appropriate voltage will work.

== Putting it All Together ==
Once you have all the equipment listed above its time to put it all together.

First, install the dataq software on the laptop and follow all instructions there.

Connect the transducer output to the positive (+) input for channel one on the a/d converter. Connect both the pressure transucer ground and the negative (-) input for channel one on the a/d converter to the negative side of the voltage source (battery). Connect the positive side of the battery to the exitation input of the pressure transducer. Connect the a/d converter to your laptop.
[[File:ADConverter Connections.jpg|thumb|Example of a pressure transducer, battery, and A/D converter connected for pressure data collection]]

At this point you should be able to see the dataq software showing 1 volt (or zero volts depending on the transducer).

=== Testing and Calibration ===
If you have a calibration manifold, connect the pressure transducer to the manifold along with the gauge and the grease gun. Skip forward to the next section if you do not have a test manifold.

The manifold should be filled with grease by pumping the grease gun until grease comes out of the bleeding port. Then close the bleeding port and you should be able to pump up the pressure with the grease gun and see that pressure reflected on the gauge. If it does not hold steady, you need to bleed all air out of the manifold. You may need to loosen the pressure gauge and pump in grease until the air escapes and then tighten the gauge back up. The same process may be required on the pressure transducer.. If everything is working correctly, you'll see the voltage rise in the Dataq software as you pump up the pressure with the grease gun. It will hold steady until you release pressure with the pressure bleeding screw.

If you are successful in making the data rise and fall by increasing the pressure and releasing it with the bleeding screw, you can confirm the calibration of your pressure transducer. For example, if the data sheet that came with your transducer specifies output as 5v at 1000psi, you can pump the test manifold up to 1000psi and confirm the voltage in the dataq software.

[TBD process for calibration and setting units in dataq software]

== Running a motor test ==
'''NOTE''' Testing rocket motors is '''DANGEROUS.''' Always do so in a safe location, and observe from a safe distance not in clear sight of the motor being tested. You should always assume the absolute worst will happen, and that should not cause any serious problems. For example, you should assume the motor being tested will fail catastrophically, and your testling location/setup should allow for that possibility without potential for injury.

When you are ready to test an actual motor, the pressure transducer should be connected to a pressure port on the motor and connected to your a/d converter. A long usb cable can be used to attach the recording laptop and have it located some distance from the actual test motor. Utilize a remote firing system.

TBD more details to come...

2022-11-15T02:39:26Z

Gregd:

Example output of the propellant characterization spreadsheet