Aluminum Agglomeration and Trajectory in Solid Rocket Motors
Final rept. Aug 2006-Jun 2007
SOFTWARE AND ENGINEERING ASSOCIATES INC CARSON CITY NV
Pagination or Media Count:
Report developed under STTR contract for Topic AF06-T012. The demand for higher performance rocket motors at a reduced cost requires continuous improvements in understanding and controlling propellant combustion. Numerous examples are available where seemingly minor modifications and improvements to existing solid rocket systems have caused previously well performing motors to exhibit unexpected and at times near catastrophic behavior. It is far cheaper to design out problems than fix them during the development or production phases. Various combustion issues have never been modeled in a complete motor prediction model. What is being proposed here has never been successfully done and would greatly increase the design tools available to the motor design community. The overall goal of this innovation is to provide a multi-physics based computer code which will accurately predict the entire flight of aluminum particles from the propellant surface through the nozzle exit plane together with a prediction of the effective properties of the binder, ammonium perchlorate, and aluminum particles which together constitute a solid propellant.
- Computer Programming and Software
- Solid Propellant Rocket Engines
- Solid Rocket Propellants