Results 81 to 90 of about 63,437 (256)
, 1995 " A satellite thruster system capable of creating a high velocity plasma jet is disclosed. The plasma accelerator, or ""railthruster,"" features a high energy current pulse source and a geometrically configured coaxial or parallel dual-rail ignitor system for higher velocity, and thus more fuel efficient, satellite attitude control. A ratio of a length
William F. Weldon, Steven P. Nichols
openaire +2 more sources
Demonstrating a new technology for space debris removal using a bi-directional plasma thruster
Scientific Reports, 2018 Space debris removal from Earth orbit by using a satellite is an emergent technological challenge for sustainable human activities in space. In order to de-orbit debris it is necessary to impart a force to decelerate it, resulting in its atmospheric re ...
Kazunori Takahashi +3 more
semanticscholar +1 more source
A 2000-hour cyclic endurance test of a laboratory model multipropellant resistojet [PDF]
The technological readiness of a long-life multipropellant resistojet for space station auxiliary propulsion is demonstrated. A laboratory model resistojet made from grain-stabilized platinum served as a test bed to evaluate the design characteristics ...
Morren, W. Earl, Sovey, James S.
core +1 more source
All-propulsion design of the drag-free and attitude control of the European satellite GOCE
, 2009 This paper concerns the drag-free and attitude control (DFAC) of the European Gravity field and steady-state Ocean Circulation Explorer satellite (GOCE), during the science phase.
Canuto +18 more
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Direct Thrust Measurement of an Electron Cyclotron Resonance Plasma Thruster
Journal of Propulsion and Power, 2018 Direct thrust measurements of an electron cyclotron resonance plasma thruster are performed with a thrust balance. The thruster performances are deduced, and the influence of power and mass-flow rate is studied.
T. Vialis +3 more
semanticscholar +1 more source
Comparison of thermal analytic model with experimental test results for 30-sentimeter-diameter engineering model mercury ion thruster [PDF]
A thermal analytic model for a 30-cm engineering model mercury-ion thruster was developed and calibrated using the experimental test results of tests of a pre-engineering model 30-cm thruster. A series of tests, performed later, simulated a wide range of
Oglebay, J. C.
core +1 more source
Electrostatic propulsion system with a direct nuclear electrogenerator Patent [PDF]
, 1965 Nuclear electric generator for accelerating charged propellant particles in electrostatic propulsion ...
Low, C. A., Jr., Mickelsen, W. R.
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A dual Stage ion engine for high impulse missions
, 2012 In this paper, the applicability of dual stage ion opticsand in particular of the so-called dual stage ion engine to highpower, high specific impulse missions will be evaluated.
Coletti, M., Gabriel, S.B.
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Low power arcjet thruster pulse ignition [PDF]
An investigation of the pulse ignition characteristics of a 1 kW class arcjet using an inductive energy storage pulse generator with a pulse width modulated power converter identified several thruster and pulse generator parameters that influence ...
Gruber, Robert P., Sarmiento, Charles J.
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Mercury ion thruster technology [PDF]
The Mercury Ion Thruster Technology program was an investigation for improving the understanding of state-of-the-art mercury ion thrusters. Emphasis was placed on optimizing the performance and simplifying the design of the 30 cm diameter ring-cusp ...
Beattie, J. R., Matossian, J. N.
core +1 more source