by NASA, National Technical Information Service, distributor in [Washington, D.C.], [Springfield, Va .
Written in English
|Other titles||Performance of a low power subsonic arc attachment arcjet thruster.|
|Statement||John M. Sankovic and Darren H. Berns.|
|Series||NASA technical memorandum -- 106244.|
|Contributions||Berns, Darren H., United States. National Aeronautics and Space Administration.|
|The Physical Object|
A subsonic-arc-attachment thruster design was scaled from a 30 kW 's vintage thruster to operate at nominally 3 kW. Performance measurements were obtained over a kW power range using hydrogen as the propellant. Several modes of operation were identified and were characterized by varying degrees of voltage instability. A stability map was developed showing that Cited by: 4. 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. Performance of a low-power subsonic-arc-attachment arcjet by: Performance Computation of a Low-Power Hydrogen Arcjet. The Effects of Swirl on Low Power Arcjet Thruster Flowfield and Heat Transfer Characteristics. 8 June Performance of a low-power subsonic-arc-attachment arcjet thruster. JOHN SANKOVIC and Cited by: A subsonic-arc-attachment thruster design was scaled from a 30 kW 's vintage thruster to operate at nominally 3 kW. Performance measurements were obtained over a kW power range using hydrogen as the propellant. Several modes of operation were identified and were characterized by varying degrees of voltage instability.
Nonequilibrium modeling study on plasma flow features in a low-power nitrogen/hydrogen arcjet thruster 31 March | Plasma Science and Technology, Vol. 19, No. 5 Chemical Nonequilibrium Modeling of Low-Power Nitrogen/Hydrogen Arcjet Thrusters. Performance and preliminary life test of a low power hydrazine engineering design model (EDM) arcjet thruster is carried out to characterize the performance of the thruster operated with different propellants and to demonstrate the life capability of the arcjet thruster accompanied with the power control unit (PCU). performance limitations associated with frozen flow losses in arcjet thrusters. It provides the means of directly measuring the electronic ground state concentrations of molecular hydrogen. Measurements were performed for both cold-flow (see Boyd et al, Appendix C) and arc-heated flow conditions. In the cold-flow studies, experiments were in. Performance of a Miniaturized Arcjet John M. Sankovic Lewis Research Center Cleveland, Ohio and Under the Low Power Arcjet Thruster System (LPATS) program, a kW hydrazine arcjet will be phenomenon documented in subsonic-arc attachment thrusters is due to movement of the anode attachment point
Arcjet thruster specific impulse vs nozzle area ratio for different propellants. Tchamber = K, Pcharnber = 1 MPa. which have some good performance qualities. The results of calculations showed (see Fig. 3) that when employing these gases, s specific impulse could be expected at the thruster chamber tempera- ture T = K. 3. A subsonic-arc-attachment thruster design was scaled from a 30 kW 's vintage thruster to operate at nominally 3 kW. Performance measurements . The thrust was measured by a thrust stand that is developed for low power arcjet thrusters in BUAA, which has three thrust ranges, i.e. 0–10 mN, 0– mN and 0– mN, with an accuracy of 2%.The thrust stand consists of a frame assembly, flexural pivot assembly, movable beam assembly, reactive circuit and feedback force system, capacitor displacement sensor system, electric . An arcjet thruster has a constrictor and nozzle defining an arc chamber. The constrictor has an insulator and an anode. The constrictor defines a subsonic-to-supersonic transition zone axially coextensive with the inculator and anode. The anode is disposed side-by-side with the insulator and located upstream therefrom. A rod defines a cathode spaced from the anode by a gap.