DEVELOPMENT OF A THERMAL ARC ENGINE.
Abstract
The development of a 30 KW electrothermal (arc-jet) engine for space propulsion is described. An experimental 30 KW DC thruster was redesigned to increase life and decrease propellant leakage while maintaining the high level of performance (I sub sp = 1000 sec.; eta > or = 50%) obtained during that research program. Concurrently, other components of the engine, including a hydrogen propellant storage and feed unit, starter and engine controls, and mounting structure were designed, procured or fabricated, and assembled as a demonstration engine. The major accomplishments during this program were (1) operation of a thruster at a nominal specific impulse of 1000 seconds for twenty-five hours with negligible erosion; (2) development of a cryogenic hydrogen propellant storage and feed unit and engine controls suitable for unattended engine stand-by and operation; and (3) demonstration of a high level of thruster performance (efficiency values above 50 percent at a specific impulse of 1000 seconds) in a flight-type thruster. This type of engine is now ready for an advanced development phase, which is necessary to insure the reliability of such a propulsion device during prospective space missions. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- May 12, 1964
- Accession Number
- AD0832211