Add to ORKGDevelopment of 8 cm ion thruster technology which was conducted in support of the Ion Auxiliary Propulsion System (IAPS) flight contract (Contract NAS3-21055) is discussed. The work included characterization of thruster performance, stability, and control; a study of the effects of cathode aging; environmental qualification testing; and cyclic lifetesting of especially critical thruster components
The Mercury Ion Thruster Technology program was an investigation for improving the understanding of ...
The Ion Auxiliary Propulsion System (IAPS) experiment is designed for launch on an Air Force Space T...
A representative thruster was extensively documented with respect to performance parameters and char...
The performance of the Ion Auxiliary Propulsion System (IAPS) thruster was increased to thrust T = 3...
The technology status of 8 cm diameter electron bombardment ion thrusters is presented. Much of the ...
A slightly modified 8-cm Hg ion thruster demonstrated significant increase in performance. Thrust wa...
The results of extensive testing of two 30-cm ion thrusters which are virtually identical to the 900...
Design analyses showed that an ion thruster of approximately 50 cm in diameter will be required to p...
A program has been conducted in order to improve the performance characteristics of 30 cm thrusters....
This report describes the qualification test of an Engineering-Model 5-mN-thrust 8-cm-diameter mercu...
A structural integrated ion thruster with 8-cm beam diameter (SIT-8) was developed for attitude cont...
A preliminary characterization of the performance capabilities of the 8-cm thruster in order to init...
A 30-cm diameter xenon ion thruster is under development at NASA to provide an ion propulsion option...
A model of ion thruster performance is developed for high flux density, cusped magnetic field thrust...
Engineering model designs and acceptance tests are described for the 800 and 900 series 30 cm electr...
The Mercury Ion Thruster Technology program was an investigation for improving the understanding of ...
The Ion Auxiliary Propulsion System (IAPS) experiment is designed for launch on an Air Force Space T...
A representative thruster was extensively documented with respect to performance parameters and char...
The performance of the Ion Auxiliary Propulsion System (IAPS) thruster was increased to thrust T = 3...
The technology status of 8 cm diameter electron bombardment ion thrusters is presented. Much of the ...
A slightly modified 8-cm Hg ion thruster demonstrated significant increase in performance. Thrust wa...
The results of extensive testing of two 30-cm ion thrusters which are virtually identical to the 900...
Design analyses showed that an ion thruster of approximately 50 cm in diameter will be required to p...
A program has been conducted in order to improve the performance characteristics of 30 cm thrusters....
This report describes the qualification test of an Engineering-Model 5-mN-thrust 8-cm-diameter mercu...
A structural integrated ion thruster with 8-cm beam diameter (SIT-8) was developed for attitude cont...
A preliminary characterization of the performance capabilities of the 8-cm thruster in order to init...
A 30-cm diameter xenon ion thruster is under development at NASA to provide an ion propulsion option...
A model of ion thruster performance is developed for high flux density, cusped magnetic field thrust...
Engineering model designs and acceptance tests are described for the 800 and 900 series 30 cm electr...
The Mercury Ion Thruster Technology program was an investigation for improving the understanding of ...
The Ion Auxiliary Propulsion System (IAPS) experiment is designed for launch on an Air Force Space T...
A representative thruster was extensively documented with respect to performance parameters and char...