Results 271 to 280 of about 2,580 (293)

15 cm multipole gas ion thruster

12th International Electric Propulsion Conference, 1976
A 15-cm multipole thruster was operated on argon and xenon. The multipole approach used has been shown to be capable of low discharge losses and flat ion beam profiles with a minimum of redesign. This approach employs low magnetic field strengths and flat or cylindrical sheet-metal parts and hence is suited to rapid op. timization and scaling.
Gerald C. Isaacson, Harold R. Kaufman
openaire   +1 more source

Neutralizer-free gridded ion thruster

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, 2014
The first proof-of-concept of a neutralizer-free gridded thruster called NEPTUNE which emits simultaneously ions and electrons producing thrust and high Isp is presented. The NEPTUNE prototype is built and tested in a 1m long beam propagation chamber.
Rafalskyi, D.V., Aanesland, Ane
openaire   +2 more sources

Hall current ion-thruster performance

Journal of Propulsion and Power, 1992
A Hall current ion thruster has been developed to investigate its thruster performance and acceleration processes. Thrust was measured by mounting the thruster on a pendulum-type thrust stand, and internal efficiencies such as propellant utilization, acceleration, and beam energy efficiencies were measured with an ion-beam collector and an ion-energy ...
Kimiya Komurasaki, Yoshihiro Arakawa
openaire   +1 more source

Satellite control mercury ion thruster

10th Electric Propulsion Conference, 1973
Program status is reviewed for development of an 8-cm structurally integrated ion thruster for application to attitude control and stationkeeping of synchronous satellites. The system is designed to achieve a thrust level of 1 and 2 mlb at a beam voltage of 1200 V, a propellant-utilization efficiency of 85%, and electrical efficiency of 75%.
J. HYMAN, JR., R. POESCHEL
openaire   +1 more source

Ion thruster design and analysis

12th International Electric Propulsion Conference, 1976
Questions concerning the mechanical design of a thruster are considered, taking into account differences in the design of an 8-cm and a 30-cm model. The components of a thruster include the thruster shell assembly, the ion extraction electrode assembly, the cathode isolator vaporizer assembly, the neutralizer isolator vaporizer assembly, ground screen ...
S. KAMI, D. SCHNELKER
openaire   +1 more source

Ion Thruster Produced Roll Torque

AIAA Propulsion and Energy 2019 Forum, 2019
Disturbances to the ion engine’s thrust vector will cause a spacecraft to spin about its axis if left unmanaged. Spin about the yaw and pitch axis can be easily handled by a gimbal with enough authority. Spin about the roll axis however must be handled by additional thrusters or reaction wheels.
openaire   +1 more source

Reservoir cathode for ion thrusters

IVESC 2012, 2012
A novel, reservoir-type hollow cathode has been designed, constructed and tested. It provides improved control of the barium dispensation rate to the electron-emitting surface and superior structural integrity relative to previous art. The cathode offers the possibility of much longer life than currently used impregnated dispenser cathodes. This is due
Bernard Vancil, Victor Schmidt, Wayne Ohlinger, James Polk   +3 more
openaire   +1 more source

High-power xenon ion thrusters

21st International Electric Propulsion Conference, 1990
Steady state performance characteristics for a 25-cm diameter laboratory-model xenon ion thruster operating over the power range from 1.8 to 6.8 kW are described. Performance data are also presented for a similar 30-cm diameter thruster operated over the 1.4 to 11.1 kW power range.
J. BEATTIE, J. MATOSSIAN
openaire   +1 more source

40 cm prototype ion thrusters

IEEE Conference Record - Abstracts. PPPS-2001 Pulsed Power Plasma Science 2001. 28th IEEE International Conference on Plasma Science and 13th IEEE International Pulsed Power Conference (Cat. No.01CH37255), 2002
Summary form only given. High-performance 5 to 10 kW class ion propulsion technology has been identified as a key requirement and priority for technology development to support the Exploration of the Solar System (ESS) theme of the Space Science Enterprise.
G.J. Williams, R.F. Roman, J.E. Foster, T.W. Haag, C.D. Carpenter, M.J. Patterson   +5 more
openaire   +1 more source

Emissive Membrane Ion Thruster Concept

Journal of Propulsion and Power, 2007
Experiments conducted on solid-state ionic membranes that convert atoms into ions that can in turn be extracted into energetic beamlets and thereby produce thrust are described. The capability of ionizing and transporting ions is shown to be both rapid (over 10 mA/cm 2 ) and efficient (of order 1 eV/ion).
Paul J. Wilbur, Merrill Wilson, Kent Hutchings, John D. Williams   +3 more
openaire   +1 more source