Abstract
Abstract : A mathematical model of a small solid propellant rocket was programmed for use with a Univac Solid State 90 digital computer by means of Fortran I and Fortran II. In addition to calculating the pressure-time and thrust-time transients, the program computes time-averaged pressure, thrust coefficient, thrust, flow rate, and burning rate, as well as total impulse and specific impulse. The report includes the derivation of equations, the method of solution, the program in Fortran I and Fortran II, an example solution compared with experiment, and a recommended procedure for use of the computer program in the design and development of a small solid propellant rocket motor.
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