Burton et al. (1982) have discussed the theory of the Pulsed Electrothermal (PET) thruster, a device which in principle can operate with 70 percent efficiency at a specific impulse of 1000 seconds and higher. It is pointed out that this level of performance would be particularly attractive for orbit raising of large satellites and other near-earth missions, which cannot be easily accomplished by chemical propulsion. The present investigation is concerned with two PET thruster operating modes. A PET thruster was built and tested on a thrust stand. Exhaust velocities for polyethylene propellant vary from 20 to 27 km/sec. Single pulse specific impulse and efficiency measurements based on ablated mass show a thruster efficiency of 37-56 percent in the time range from 1000 to 1750 seconds. It is believed that an improved design with a thruster efficiency in the range from 70 to 80 percent might be possible.
Experimental investigation of the pulsed electrothermal (PET) thruster
1984-06-01
Conference paper
No indication
English
Investigation of a pulsed electrothermal thruster system
NTRS | 1984
|Theory of the pulsed electrothermal thruster
AIAA | 1982
|Initial development of a pulsed electrothermal thruster
AIAA | 1991
|Initial development of a pulsed electrothermal thruster
NTRS | 1991
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