Patent ID: 7024288

Claim:
A method for developing rocket motor ballistics performance at an output temperature, comprising: receiving input data comprising data from an actual test firing using an input temperature and rocket motor specifications; selecting a coefficient of throat erosion by iteratively solving an expression for rate of throat erosion as a function of said input data until a throat dimension matches a user input value; calculating an array of throat dimension by time increment with the selected coefficient of throat erosion; selecting a reference burn rate by iteratively solving an expression for total web burned as a function of said input data until total linear web burned matches the user input value for web thickness; calculating an array of linear web burned values at the input temperature with the selected reference burn rate; selecting a characteristic velocity by iteratively solving an expression for total propellant weight burned as a function of said input data until a total propellant weight burned matches a user input value; calculating an array of burn surface values at the input temperature with the selected characteristic velocity; and developing data profiles at an output temperature selected by the user.