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Studies of an extensively axisymmetric rocket based combined cycle (RBCC) engine powered single-stage-to-orbit (SSTO) vehicleThe present comparative performance study has established that rocket-based combined cycle (RBCC) propulsion systems, when incorporated by essentially axisymmetric SSTO launch vehicle configurations whose conical forebody maximizes both capture-area ratio and total capture area, are capable of furnishing payload-delivery capabilities superior to those of most multistage, all-rocket launchers. Airbreathing thrust augmentation in the rocket-ejector mode of an RBCC powerplant is noted to make a major contribution to final payload capability, by comparison to nonair-augmented rocket engine propulsion systems.
Document ID
19890059360
Document Type
Conference Paper
Authors
Foster, Richard W. (Astronautics Corporation of America, Madison, WI, United States)
Escher, William J. D. (NASA Headquarters Washington, DC United States)
Robinson, John W. (Martin Marietta Corp. Astronautics Group, Denver, CO, United States)
Date Acquired
August 14, 2013
Publication Date
July 1, 1989
Subject Category
SPACECRAFT PROPULSION AND POWER
Report/Patent Number
AIAA PAPER 89-2294
Distribution Limits
Public
Copyright
Other