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Arcjet rocket

About: Arcjet rocket is a research topic. Over the lifetime, 1121 publications have been published within this topic receiving 9687 citations. The topic is also known as: Arcjet.


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Journal ArticleDOI
01 Jan 1990
TL;DR: In this paper, the operational performance and the arc structure of a quasisteady magnetoplasmadynamic (MPD) arcjet was made to develop a high-performance accelerator in space.
Abstract: Experimental researches on the operational performance and the arc structure of a quasisteady magnetoplasmadynamic (MPD) arcjet was made to develop a high-performanceaccelerator in space. The results showed that the current pattern, which depended strongly on gas species and discharge current levels, influenced the thruster performance. It was found that the plasma produced in the discharge chamber was compressed radially and that 50% on the input power was consumed in the cathode region. From the plasma potential distribution, a positive voltage slope and mass starvation were found to be present near the anode surface beyond the predicted critical current level.

8 citations

01 May 1989
TL;DR: In this paper, the authors evaluated the performance of five and 10 kW ion and arcjet propulsion systems for a near-term space demonstration experiment and quantified the overall mission performance in terms of the maximum thrusting time, total impulse and velocity increment capability available when integrated onto a generic spacecraft under fixed mission model assumptions.
Abstract: Five and 10 kW ion and arcjet propulsion system options for a near-term space demonstration experiment were evaluated. Analyses were conducted to determine first-order propulsion system performance and system component mass estimates. Overall mission performance of the electric propulsion systems was quantified in terms of the maximum thrusting time, total impulse, and velocity increment capability available when integrated onto a generic spacecraft under fixed mission model assumptions. Maximum available thrusting times for the ion-propelled spacecraft options, launched on a DELTA 2 6920 vehicle, range from approximately 8,600 hours for a 4-engine 10 kW system to more than 29,600 hours for a single-engine 5 kW system. Maximum total impulse values and maximum delta-v's range from 1.2x10 (exp 7) to 2.1x10 (exp 7) N-s, and 3550 to 6200 m/s, respectively. Maximum available thrusting times for the arcjet propelled spacecraft launched on the DELTA 2 6920 vehicle range from approximately 528 hours for the 6-engine 10 kW hydrazine system to 2328 hours for the single-engine 5 kW system. Maximum total impulse values and maximum delta-v's range from 2.2x10 (exp 6) to 3.6x10 (exp 6) N-s, and approximately 662 to 1072 m/s, respectively.

8 citations

01 Apr 1988
TL;DR: In this paper, a laboratory arcjet thruster was used to simulate fully decomposed hydrazine in a vacuum environment with background pressures less than 5 x 10 to the -2 Pa.
Abstract: Electrostatic (Langmuir) probes of both spherical and cylindrical geometry have been used to obtain electron number density and temperature in the exhaust of a laboratory arcjet. The arcjet thruster operated on nitrogen and hydrogen mixtures to simulate fully decomposed hydrazine in a vacuum environment with background pressures less than 5 x 10 to the -2 Pa. The exhaust appears to be only slightly ionized (less than 1 percent) with local plasma potentials near facility ground. The current-voltage characteristics of the probes indicate a Maxwellian temperature distribution. Plume data are presented as a function of arcjet operating condition and also position in the exhaust.

8 citations

Proceedings ArticleDOI
05 Jan 2009
TL;DR: In this paper, a low-density carbon-phenolic ablative material with nominal virgin density of 0.24g/cm3 is heated in arcjet wind tunnels with nitrogen and air as a test gas.
Abstract: Coking phenomenon for low density carbon-phenolic ablative material exposed to aerodynamic heating is examined experimentally. The low density ablators with the nominal virgin density of 0.24g/cm3 are heated in arcjet wind tunnels with nitrogen and air as a test gas. The material in-depth density, in-depth and surface temperatures are measured. The density increase within the char layer is observed for the test specimens heated in the nitrogen arcjet freestream. In contrast, the coking behavior is not clearly seen for the case of air arcjet testing. The present study shows that the nature of the in-depth density distribution is very sensitive to the heating conditions.

8 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
202315
202211
20215
202010
20193
201811