3 edition of Evaluation of the communications impact of a low power arcjet thruster found in the catalog.
Evaluation of the communications impact of a low power arcjet thruster
by National Aeronautics and Space Administration, For sale by the National Technical Information Service in [Washington, DC], [Springfield, Va
Written in English
|Statement||Lynnette M. Carney.|
|Series||NASA technical memorandum -- 100926.|
|Contributions||United States. National Aeronautics and Space Administration.|
|The Physical Object|
use on low-power hydrogen arcjet thrusters and xenon-propelled electric thrusters. In the case of low power hydrogen arcjets, these laser induce fluorescence measurements constitute the first complete set of data that characterize the velocity and temperature field of such a device. The research performed under the auspices of this NASA grant includesFile Size: 7MB. In work sponsored by INTELSAT, Rocket Research has designed ~nd is fabricating a 2.O-N thruster designed to operate at an exhaust velocity of x ~ms-~ and a power of kW. This thruster will be tested in (Smith, ). Low power (arcjet development in the U.S. was discontinued in Cited by: 1.
Digital control power supply to electric power was developed in order to convert low, and to miniaturize and lighten the arc-jet thruster. As a result, discharge starting reproducibility with single power supply was good and we succeeded in stable arc discharge in the low electric current territory. Session:Arcjet Thrusters. In a conventional Resistojet, the amount of energy added to the ﬂow (and in consequence the speciﬁc impulse) is limited by the maximum working temperature of the materials used in its construction: the walls of the device are directly heated by an electric source and is through contact with these walls that the ﬂow increases its Size: KB.
ArcJet Systems is a factory Location in the Western area of The Commonwealth. It is located to the East of the Federal Ration Stockpile, and West of the Rocky. The invention provides an arcjet thruster capable of improving operation stability. The arcjet thruster comprises a cathode, a sealing piece, an insulating piece, a metal sleeve and an anode spraying pipe which are sequentially connected. The cathode, the sealing piece and the insulating piece are fixedly connected in sleeving mode in : 潘文霞, 吴承康, 孟显.
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A low power arcjet thruster is currently being developed as a high per-formance alternative for auxiliary propulsion applications such as north-south stationkeeping on communications satellites (refs.
1 and 2). When operated with storable propel 1 ants at power levels. AIREX: Evaluation of the communications impact of a low power arcjet thruster The interaction of a 1 kW arcjet thruster plume with a communications signal is evaluated.
A two-parameter, source flow equation has been used to represent the far flow field distribution of the arcjet plume in a realistic spacecraft configuration.
Get this from a library. Evaluation of the communications impact of a low power arcjet thruster. [Lynnette M Carney; United States. National Aeronautics and Space Administration.]. The interaction of a 1 kW arcjet thruster plume with a communications signal is evaluated.
A two-parameter, source flow equation has been used to represent the far flow field distribution of the arcjet plume in a realistic spacecraft : Lynnette M. Carney. the low-power DC arcjet thruster performance.
In the present study, arc voltage, thrust and other important pa-rameters of arcjet thruster are measured for various mass flow rates of argon, nitrogen, nitrogen/ammonia mixtures simulating hydrazine, while the arc current of the arcjet thruster is fixed constant (i.e.
I=10 A), so that the effects. A low power arcjet‐thruster of 1 kW‐class with gas mixture of H2–N2 or pure argon as the propellant is fired at a chamber pressure about 10 Pa.
The nozzle temperature is detected with an infrared pyrometer; a plate set perpendicular to the plume axis and connected to a force sensor is used to measure the thrust; a probe with a tapered head is used for measuring the impact pressure in the Author: Wenxia Pan, Xian Meng, Heji Huang, Chengkang Wu.
Application of hollow cathode in arcjet propulsion at low and average power Evaluation of the communications impact of a low power arcjet thruster The interaction of a 1 kW arcjet thruster. Arcjet thruster development. The Effects of Swirl on Low Power Arcjet Thruster Flowfield and Heat Transfer Characteristics.
8 June Overview of thermal arcjet thruster development. Aircraft Engineering and Aerospace Technology, Vol. 90, No. by: Departures from thermal, chemical equilibrium of a plasma flow in a low-power arcjet thruster with a nitrogen/hydrogen mixture as the working gas have been studied by axisymmetric numerical.
ARCJET ENGINE PERFORMANCE- EXPERIMENT AND THEORY. Performance gains of a regeneratively cooled low power arcjet thruster.
17 August Effect of nozzle and cathode configuration on arcjet performance. 23 May | Journal of Propulsion and Power, Vol. 6, No. 3 Low power arcjet by: broad range of power and with various propellants. Many electric propulsion systems are currently proposed for spacecrafts as Hall effect thruster, gridded ion thruster, plasma pulsed thruster, field electron emission plasma source, micro-wave source, and arc-jet .
The choice of aFile Size: KB. Carney, L. M., "Evaluation of the Communications Impact on a Low Power Arcjet Thruster," AIAA PaperJuly Ling, H., et al. "Near Field Interaction of Microwave Signals with a Bounded Plasma Plume," Final by: 5.
High Power Arcjet Thruster Experiments T. Gilz, M. Auweter-Kurtz, H. Kurtz, and H. Schrade Institut fur Raumfahrtsysteme Universilat Stuttgart Abstract A water cooled laboratory model of a high power thermal arcjet was designed and built at the Institut far Raumfahrtsysteme (IRS).
The thruster was designed for the kW power level. Also summarized are the results of spacecraft between the arcjet and the spacecraft and found them impact evaluation testing carried out using to be benign or even beneficial.
The arcjet system development hardware. These evaluation tests, described herein is in fact a subsystem at the. Discussion on the simulation of thermodynamic properties across the thruster can be viewed here.
Discussion on the effect of material selection on cathode erosion can be found here. Early research paper from Arcjet Development project can be found here.
Abstract. 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 breakdown voltage including pulse Author: Charles J.
Sarmiento and Robert P. Gruber. mass, it should also be the highest power Hall thruster that is expected to be used for GEO stationkeeping. • An even number of thrusters should be clustered, in opposite magnetic polarity, to cancel out the Hall thruster torques. • The unit thruster power should be sufficiently low so as to allow testing in current ground test facilities.
The High Power Arcjet thruster is investigated with respect to the effects of constrictor diameter, cathode gap, and cooling mechanism on specific impulse and general engine performance.
The thruster is mounted on a thrust balance and integrated into a stainless steel vacuum chamber, and cathodes with 5-,and mm diams and varying tip configurations are by: 5. Near term flight applications of arcjet and ion thruster satellite station-keeping systems as well as development activities in Europe, Japan, and the United States are reviewed.
At least two arcjet and three ion propulsion flights are scheduled during the - period. Fundamentals of Electric Propulsion: Ion and Hall Thrusters March The research described in this publication was carried out at the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration.
Reference herein to any specific commercial product, process, or service. A power supply for a thruster for space applications (e.g., an arcjet thruster) comprises a series/parallel resonant converter wherein the load quality (Q) factor of the resonant tank circuit inherently varies with arc voltage so as to accommodate changes in arc voltage from initiation thereof through steady-state operation.
Effectively, the resonant tank circuit acts as a ballast by matching Cited by: Arcjet Thruster Operated With Different Propellants Abstract: As a simple and reliable propulsion system, arcjet thrusters have been used in multiple satellite missions.
The performance of an arcjet thruster is controlled by the characteristics of the arc-discharge behavior and the arc-electrode interactions to a large by: 2.An arcjet rocket or arcjet thruster is a form of electrically powered spacecraft propulsion, in which an electrical discharge (arc) is created in a flow of propellant (typically hydrazine or ammonia).
This imparts additional energy to the propellant, so that one can extract more work out of each kilogram of propellant, at the expense of increased power consumption and (usually) higher cost.