DESIGN STUDY OF A LARGE UNCONVENTIONAL LIQUID PROPELLANT ROCKET ENGINE AND VEHICLE. VOLUME 5. ADVANCED ENGINE-VEHICLE INTEGRATION STUDY
AEROJET-GENERAL CORP SACRAMENTO CA
Identifiers F-D engines, Thrust vector control, Weight, Bell nozzles.Advanced engine design concepts were studied on the cost performance parameter dollars per pound of payload of a total airborne vehicle and ground support system. Emphasis was placed on use of a 2 million pounds sea level force deflection F-D engine. This engine was used in two basic vehicle configurations a two stage vehicle with a thrust to weight ratio TW of 1.1 and using the F-D engine in both stages operating at Pc of 1000 psi and a single-stage-to-orbit vehicle with a TW of 1.4 and using one F-D engine operating at Pc of 3000 psi. Emphasis was placed on the engine installation, the engine influence on connecting subsystems, and the engine mounting structure.