An analysis of the geometry of the burning in both star-cylindrical port interface regions and regions of partially inhibited slots is presented. Some characteristics parameters are defined and illustrated. Methods are proposed for calculating burning areas which functionally depend only on the total distance burned. According to this method, several points are defined where abrupt changes in geometry occur, and these are tracked throughout the burn. Equations are developed for computing port perimeter and port area at pre-established longitudinal positions. Some common formulas and some newly developed formulas are then used to compute burning surface area and port volume. Some specific results are presented for the solid rocket motor committed to the space shuttle project.
Determination of burning area and port volume in complex burning regions of a solid rocket motor
1977-02-01
Report
No indication
English
Automated Approach for 3-D Grain Burning Area Design of Solid Rocket Motor
British Library Conference Proceedings | 1998
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