MHD augmented chemical rocket propulsion for space applications

Conference · Wed Jul 01 00:00:00 EDT 1992

OSTI ID:7164485

Schulz, R J; Chapman, J N; Rhodes, R P ^[1]

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1. Tennessee, University, Tullahoma (United States)

A performance analysis is carried out of a magnetohydrodynamic (MHD) augmented chemical thruster (based on a gaseous hydrogen-oxygen system) for space applications such as orbit transfer. The mathematical model used in the analysis is a one-dimensional flow model using equilibrium chemistry for the combustor, choked nozzle, and MHD channel portions of the system, and chemical nonequilibrium kinetics for the high area-ratio gas dynamic nozzle portion of the system. The performance of the chemical-MHD-augmented thruster is compared with that of a pure electric thruster of the same specific impulse level. 13 refs.

• OSTI ID: 7164485
• Report Number(s): AIAA-Paper-92-3001; CONF-9207111-
• Resource Relation: Conference: 23. American Institute of Aeronautics and Astronautics (AIAA) plasma dynamics and lasers conference, Nashville, TN (United States), 6-8 Jul 1992; Other Information: Research supported by University of Tennessee
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
30 DIRECT ENERGY CONVERSION
PROPULSION SYSTEMS
MHD GENERATORS
SPACE VEHICLES
NOZZLES
PLASMA
ROCKET ENGINES
DIRECT ENERGY CONVERTERS
ENGINES
VEHICLES
330000* - Advanced Propulsion Systems
300100 - Direct Energy Conversion- MHD Generators