OPTIMIZATION OF SOLID ROCKET MOTOR IGNITER PERFORMANCE REQUIREMENTS

• Published in: Engineering optimization 1982-01, Vol.6 (1), p.31-38
• Main Authors: FOSTER, WINFRED A., SFORZINI, RICHARD H.
• Format: Article
• Language: English
• ISSN: 0305-215X; 1029-0273
• DOI: 10.1080/03052158208902452

A numerical technique is presented for optimizing a set of solid rocket motor (SRM) ignition control variables to achieve a specific requirement or set of requirements to be used in preliminary design of an SRM igniter. The mathematical model of the igniter transients uses a simplified ignition simulation routine to calculate igniter and SRM performance. The object function to be optimized (minimized) is typically the summation of The absolute values of the differences between the desired and computed thrust values of the SRM at specified times during ignition. Constraints are imposed in the form of limiting values of igniter characteristics, flame-spreading speeds and/or maximum rate of pressure rise in the SRM. Optimization is obtained using a direct pattern search technique to determine the required values of the controlling variables. Examples are presented which illustrate the ability of the technique to meet practical design requirements. Computational results are shown to be consistent with the static test performance of Space Shuttle SRMs. In addition.it is shown that the method is capable of evaluating certain often unknown parameters, such as flame-spreading speed, from test data.