Studies of an extensively axisymmetric rocket based combined cycle (RBCC) engine powered single-stage-to-orbit (SSTO) vehicle

Conference · Sun Jan 01 00:00:00 EST 1989

OSTI ID:5419674

Foster, R W; Escher, W J.D.; Robinson, J W

The 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. 16 refs.

• OSTI ID: 5419674
• Report Number(s): AIAA-Paper-89-2294; CONF-8907118-
• Resource Relation: Conference: 25. American Society of Mechanical Engineers joint propulsion conference, Monterey, CA (USA), 10-13 Jul 1989
• Country of Publication: United States
• Language: English

Related Subjects

42 ENGINEERING
33 ADVANCED PROPULSION SYSTEMS
PROPULSION SYSTEMS
PERFORMANCE
ROCKETS
COMPARATIVE EVALUATIONS
DESIGN
ENGINES
RAMJET ENGINES
ROCKET ENGINES
SUPERSONIC FLOW
FLUID FLOW
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
420200* - Engineering- Facilities
Equipment
& Techniques
330000 - Advanced Propulsion Systems