Designing a solid rocket motor requires the simulation of several performance characteristics so that it can be designed to meet the mission requirements. The method of simulation for a solid rocket motor can vary both in the fundamental theories, assumptions, and execution. The theories and assumptions will go into detail later, but Excel was chosen as the program.
In order to gauge performance of the motor, the simulation program outputs a pressure and thrust trace. This enables calculation of other important parameters such as specific impulse, total impulse, max thrust, and more for the given motor. The inputs of the program are the dimensions of the grain, burning surfaces, nozzle geometry, propellant properties, and external environment properties. Tools are also provided within the program to help enable design of the nozzle dimensions and grain dimensions based on more fundamental desired parameters (such as max burning pressure).
Program Outputs:
-Pressure-time trace
-Thrust-time trace
-Specific impulse
-Total impulse
-Max thrust