Add to ORKGControl logic functions were established for three automatic modes of operation of a 30-cm thruster using a power conditioner console with flight-like characteristics. The three modes provide: (1) automatic startup to reach thermal stability, (2) steady-state closed-loop control, and (3) the reliable recycling of the high voltages following an arc breakdown to reestablish normal operation. Power supply impedance characteristics necessary for stable operation and the effect of the magnetic baffle on the reliable recycling was studied
The design of ion optics for bombardment thrusters strongly influences overall performance and lifet...
Some space flight missions require advanced ion thrusters which operate at conditions much different...
The major objective was to define the exact role of an onboard spacecraft computer in the control of...
The vaporizer dynamic control characteristics of a 30-cm diameter mercury ion thruster were determin...
A prototype electric power management and thruster control system for a 30 cm ion thruster is descri...
Development and tests of flight prototype power conditioner for 20 cm mercury bombardment electric t...
Electrical breakdowns have been observed during ion thruster operation. These breakdowns, or arcs, c...
The technology development of the 30 centimeter J series mercury ion thruster for prime propulsion a...
The results of extensive testing of two 30-cm ion thrusters which are virtually identical to the 900...
A two grid 30 cm diameter mercury ion thruster was operated with only six power supplies over the ba...
Performance tests of critical components on mercury electron bombardment thruste
NASA LeRC is developing a 30 cm diameter xenon ion thruster for auxiliary and primary propulsion app...
A 2000-hour durability test of a modified Hughes SIT-5 (Structurally Integrated Thruster, 5 cm) was ...
The initial development and demonstration of power supplies with an order of magnitude reduction in ...
Recent improvements in overall thruster performance have imposed new constraints on neutralizer perf...
The design of ion optics for bombardment thrusters strongly influences overall performance and lifet...
Some space flight missions require advanced ion thrusters which operate at conditions much different...
The major objective was to define the exact role of an onboard spacecraft computer in the control of...
The vaporizer dynamic control characteristics of a 30-cm diameter mercury ion thruster were determin...
A prototype electric power management and thruster control system for a 30 cm ion thruster is descri...
Development and tests of flight prototype power conditioner for 20 cm mercury bombardment electric t...
Electrical breakdowns have been observed during ion thruster operation. These breakdowns, or arcs, c...
The technology development of the 30 centimeter J series mercury ion thruster for prime propulsion a...
The results of extensive testing of two 30-cm ion thrusters which are virtually identical to the 900...
A two grid 30 cm diameter mercury ion thruster was operated with only six power supplies over the ba...
Performance tests of critical components on mercury electron bombardment thruste
NASA LeRC is developing a 30 cm diameter xenon ion thruster for auxiliary and primary propulsion app...
A 2000-hour durability test of a modified Hughes SIT-5 (Structurally Integrated Thruster, 5 cm) was ...
The initial development and demonstration of power supplies with an order of magnitude reduction in ...
Recent improvements in overall thruster performance have imposed new constraints on neutralizer perf...
The design of ion optics for bombardment thrusters strongly influences overall performance and lifet...
Some space flight missions require advanced ion thrusters which operate at conditions much different...
The major objective was to define the exact role of an onboard spacecraft computer in the control of...