This page discusses the details of the Setup Tab in the Rocket Motor Simulation Module.
On the left hand side of the Setup tab are the Analysis Control Parameters and the 3 Sigma Prediction Parameters of the Rocket Motor Simulation. On the right hand side is the Output Control Parameter inputs required for program execution:
Under the Analysis Control Parameters are inputs for:
- The Empty Propellant Chamber Vol. is the total volume of the combustion chamber.
- The Atmos. Pressure is the atmospheric pressure at the nozzle outlet.
- The Integration Time Step is the incremental time between computational steps for the rocket motor simulation. An appropriate integration time step for each motor will vary depending on the physical size of the motor.
Under the 3 Sigma Prediction Parameters are the following inputs:
- The % of Burn Rate Change is the expected percent change in Burn Rate (mm/sec or in/sec) of the Rocket Motor Booster material.
- The Lower Temp Bound is the Temperature below which Rocket Motor Burn rate will be reduced by % of Burn Rate Change.
- The Upper Temp Bound is the Temperature above which Rocket Motor Burn rate will be increased by % of Burn Rate Change. .
Under the Output Control Parameters are the following inputs:
- # Time Steps Before Print is the required number of integration time steps prior to printing the first output data.
- # Time Steps Before Print Change is the required number of integration time steps prior to changing print increments.
- Second Print Increment is the print increment after the Print Change has occurred.
- 2nd # of Time Steps Before Print Change is an additional break-point for output printing.
- Special Print Time is a time beyond which an additional line of output data will be printed.
- Print Cut-Off Pressure is the lowest pressure desired by the user for printed output.
- Web Limit for Press Print is the grain web size beyond which the maximum and minimum pressures will not be printed.
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