Abstract
Nozzle throat erosion is inherently present in high performance solid rocket motors because of high operative pressures and long combustion times. Whereas for large SRM boosters, operating in atmosphere, it does not represent a strong limit to obtain high performance, for upper stage SRMs it brings to relevant losses in the speci c impulse and, hence, less e cient design of the solid rocket motor due to the nozzle throat erosion e ects on both the operative pressure and speci c impulse. This paper discusses the e ects on the performance of an upper stage SRM of di erent kinds of aluminized propellants, compared to the baseline propellant HTPB 1912. The reference con guration is Ze ro 9A, third stage of the European launcher VEGA, recently quali ed with its rst maiden ight. The analysis is performed with the use of the complete coupling of the following models: a 3D grain burnback model, GREG, a full Navier-Stokes simulation of the nozzle throat erosion and a Q1D model of the SRM internal ballistic.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
