by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, D.C, Springfield, Va .
Written in English
|Statement||John A. Hamley ... [et al.].|
|Series||NASA technical memorandum -- 107305.|
|Contributions||Hamley, John A., United States. National Aeronautics and Space Administration.|
|The Physical Object|
Get this from a library! NSTAR ion thruster and breadboard power processor functional integration test results. [John A Hamley; United States. National Aeronautics and Space Administration.;]. NSTAR Ion Thrusters and Power Processors The purpose of the NASA Solar Electric Propulsion Technology Applications Readiness (NSTAR) project is to validate ion propulsion technology for use on future NASA deep space missions. This program, which was initiated in September , focused on the development of two sets of flight quality ion thrusters, power processors, and controllers that . All line and load regulation test results show the power supplies to be within the NSTAR flight PPU specified power output of kW. The overall efficiency of the PPU, calculated as the combined efficiencies of the power supplies and controller, at Author: John A. Hamley, Luis R. Pinero, Vincent K. Rawlin, John R. Miller, Kevin C. Cartier, Glen E. Bowers. Development Stares of the NSTAR Ion Propulsion System Power Processor JohnA. Hamley,Luis R. Pinero, , and John R. Miller All line and load regulation test results show the power supplies to be within the NSTAR flight Integration testing of the neutralizer and discharge power supplies with a functional model thruster.
NSTAR Ion Thruster and Breadboard Power Processor Functional Integration Test Results. Article. Full-text available. Sep ; John A. Hamley. Luis R. Pinero. A kW Power Processor for the NSTAR Ion Propulsion (c) American Institute of Aeronautics & Astronautics or Published with Permission of Author(s) and/or Author(s)' Sponsoring Organization. designed to operate the thruster for hours at full power. The LDT was the most successful endurance test of a high-power ion engine ever performed. A total of 8, hours of operation were achieved at an input power of kW with a specific impulse of s before it was voluntarily terminated. A total of 88 kg of xenon propellant was. NSTAR Ion Thruster and Breadboard Power Processor Functional Integration Test Results the reference case of NSTAR ion thruster, which uses Xenon as .
The sub-kilowatt ion propulsion activity included both an in-house hardware development element for the thruster and power processor, as well as a contracted system element. At NASA Glenn, the fabrication and performance assessment of a small ( kW class) laboratory model thruster with an 8-cm beam diameter was completed in test at full power . Subsequent to this test, an engineering model thruster, designated EMT2, was tested for hours at the NSTAR full power point [3,4]. During the execution of this test, two flight thrusters were fabricated by Hughes Electron Dynamics Division; short 0 . NSTAR ion thruster and breadboard power processor functional integration test results / by: Hamley, John A., Published: () NEXT ion thruster performance dispersion analyses by: Soulas, George C. Published: (). Life test results of 21, hours have been obtained with the 13 cm xenon ion thruster and o hours of 25 cm xenon ion thruster life testing have been completed to date.