Investigations of an innovative combined cycle nozzle.

摘要

The Rocket Plug Nozzle Combined Cycle (RPNCC) Propulsion System was conceived to alleviate some of the inherent disadvantages of conventional Rocket Based Combined Cycle systems. A rapid, relatively accurate method was needed to model the coaxial jets of the RPNCC system. This thesis describes modification and integration of an empirical base pressure correlation into the Aerospike Design and Performance Tool (ADAPT) to estimate performance of the RPNCC system. Accounting for geometric and flow field effects improved the base pressure prediction to within 10% of existing experimental data. The modified ADAPT code was used in a first-order system comparison of a missile using the RPNCC system to the performance of conventional airbreathing and solid rocket propulsion systems. In this application, the RPNCC system was heavier and reduced overall mission performance. However, this novel concept may be of benefit when replacing conventional liquid rocket or RBCC systems in a space launch vehicle application.