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This paper presents an advanced single stage-to-orbit (SSTO) design concept based on our understanding of Russian AJAX technologies. The concept brings together a unique set of subsystem components to enhance the performance of an advanced combined cycle engine powered SSTO design concept. A magnetohydrodynamic (MHD) generator-accelerator energy bypass system is used to maintain subsonic flow in the engine combustion chamber. And, an electromagnetic drag reduction system is used to reduce wave and base drag during ascent and reentry. The performance of the advanced highly reusable SSTO is compared to a reference advanced air-breathing rocket-based combined cycle ejector ram-scramjet powered SSTO design concept. The results indicate an approximate 15% performance increase compared to the reference design.

In the parametric optimization of an accelerator or a cruise vehicle for hypervelocity missions, five elements of the analysis relate to (i) vehicle configuration, (ii) weights, (iii) trajectory, (iv) propulsion and (v) control. A scheme for the overall system optimization is described. Considering weights, the concept of fixed weight growth factor in relation to gross weight is developed to illustrate the implications of technology development and staging. The analysis of the propulsion system must be based on both energy and energy availability considerations in order to assure not only the highest thrust and propulsive efficiency but also the least dependence on obtaining each component to operate at the highest achievable mechanical efficiency. A few propulsion schemes have been analyzed to illustrate methodology and benefits.

On the Thermodynamic Spectrum of Airbreathing Propulsion - Insights from 1958 are valid guidelines yet in 1988 - Paul Czysz. Staff Manager, McDonnell Douglas Fellow. McDonnell Douglas Corporation