Revisiting the air force project beta two-stage reusable space launch concept: configuration description; performance potential; aerodynamic assessment

摘要

An exploratory study program has been in progress for a number of years at the USAF's Wright Laboratory, investigating the characteristics of a two-stage, fully reusable, horizontal take-off and landing space launch system capable of delivering shuttle class payloads to low earth orbit. The first stage incorporates a high Mach number airbreathing turbofan/ramjet propulsion system augmented by rocket propulsion. The second stage, built around a highly efficient, aerodynamically tailored lifting-body design is powered by a conventional rocket engine. The first stage carries the second stage completely within its mold lines and stages through a lower surface drop mode. Throughout the program, emphasis has been directed towards success-oriented design philosophies incorporating near-term demonstrated technologies and robustness, while avoiding the classical pitfalls usually associated with advanced, high Mach number airbreathing systems. Study results discussed include baseline configuration design and synthesis, performance evaluations and sensitivities, experimental validation, and an assessment of system applicability in light of changing military and civilian roles.