Propulsion research on the hybrid plume rocket

Technical Report · Sun Jan 01 04:00:00 EST 1989

DOI:https://doi.org/10.2172/5072751· OSTI ID:5072751

Chang-Diaz, F. R. ^[1]; Yang, T. F. ^[2]

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1. National Aeronautics and Space Administration, Houston, TX (USA). Lyndon B. Johnson Space Center
2. Massachusetts Inst. of Tech., Cambridge, MA (USA). Plasma Fusion Center

This report discusses the construction of a tandem mirror plasma propulsion facility, the numerical modelling of the hybrid plume exhaust, and rf heating of the plasma. A preliminary experiment of the ICRH (Ion Cyclotron Resonance Heating) heating of plasma ions was carried out. For 2.0 kW ECRH (Electron Cyclotron Resonance Heating) power injected into the central cell and 10 kW ICRH power into the end cell, the results obtained from the probe in the central cell are: n{sub e} = 2.5 {times} 10{sup 16} m{sup {minus}3} and T{sub e} = 80 eV (928,000 K) in the central cell. The estimated values in the end cell are: n{sub I} = 1.25 {times} 10{sup 17} m{sup {minus}3} and T{sub I} = 500 eV (5,797,000 K). The power conversion efficiency was about 80%. The results from time dependent 3-D three fluid numerical modeling indicate that a boundary layer can be formed. The formation of this layer is strongly dependent on neutral jet geometry and injection angle. The ICRH heating of plasma was modeled numerically and power absorption efficiency is about 50%. Analytical analyses was done on slab geometry. 12 refs., 20 figs., 3 tabs.

• Research Organization: Massachusetts Inst. of Tech., Cambridge, MA (USA). Plasma Fusion Center
• Sponsoring Organization: DOE/ER
• DOE Contract Number: AC02-78ET51013
• OSTI ID: 5072751
• Report Number(s): DOE/ET/51013-T222; PFC/RR--89-15; ON: DE90006759
• Country of Publication: United States
• Language: English

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