Accession Number : AD0474103


Title :   High Specific Impulse Thermal Arc Jet Thrustor Technology


Descriptive Note : Interim rept. 1 Apr-30 Sep 1965


Corporate Author : XEROX ELECTRO-OPTICAL SYSTEMS PASADENA CA


Personal Author(s) : Cann, G L ; Moore, R A ; Jacobs, P F ; Gallagher, L R


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/474103.pdf


Report Date : Sep 1965


Pagination or Media Count : 77


Abstract : A thrustor was tested in a high vacuum (.0000001 torr) with lithium as a propellant, an identical thrustor was evaluated with potassium as the propellant with a wide variation of operating parameters, and improvements were made to the alkali metal feed system and the thrust measurement system. The high-vacuum tests essentially duplicated the performance of the lithium thrustor (Isp = 5000 sec, eta sub T = 53%) measured at the higher pressure of .001 torr during a 10-hour endurance test. The efficiency and maximum specific impulse of the thrustor with potassium were lower than with lithium.


Descriptors :   *ARC JET ENGINES , *PLASMA JETS , ACCELERATION , ALKALI METALS , ANODES , ATTACHMENT , CAPTIVE TESTS , CATHODES , ELECTROMAGNETIC FIELDS , HALL EFFECT , HEAT TRANSFER , LITHIUM , OPERATION , PERFORMANCE(ENGINEERING) , POTASSIUM , POWER , PRESSURE , SPECIFIC IMPULSE , THRUST , TIME , VACUUM


Subject Categories : Electric and Ion Propulsion


Distribution Statement : APPROVED FOR PUBLIC RELEASE