Topic
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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TL;DR: In this paper, an arcjet discharge device with a rectangular converging and diverging nozzle was developed, which allowed us to optically observe high-density plasma inside the anode nozzle.
Abstract: An arcjet discharge device with a rectangular converging and diverging nozzle was developed, which allowed us to optically observe high-density plasma inside the anode nozzle. Spectroscopic observation along the plasma expansion axis was carried out to examine the characteristics of the arc plasma inside the nozzle. Analyzing intense continuum and line emission spectra, we successfully obtained spatial variations in electron temperature and density. Moreover, we found that two-dimensional optical measurement is highly useful in visualizing the transition from atmospheric thermal plasma to a strongly nonequilibrium recombining plasma due to adiabatic expansion.
6 citations
01 Jan 1992
6 citations
01 Jan 1975
TL;DR: The TSSM described in this report is designed for a broad range of electric propulsion missions requiring from two to ten TSSMs mounted in a 2 by x configuration as mentioned in this paper.
Abstract: Solar Electric Propulsion (SEP) is currently being studied for possible use in a number of near-earth and planetary missions Thruster systems for these missions could be integrated directly into a spacecraft or modularized into a Thruster Sub-System Module (TSSM) A TSSM for electric propulsion missions would consist of a 30-cm ion thruster, thruster gimbal system, propellant storage and feed system, associated Power Processing Unit (PPU), thermal control system and complete supporting structure The TSSM would be wholly self-contained and be essentially a plug-in or strap-on electric stage with simple mechanical, thermal, electrical and propellant interfaces The TSSM described in this report is designed for a broad range of missions requiring from two to ten TSSM's mounted in a 2 by x configuration The thermal control system is designed to accommodate waste heat from the power processor based on realistic efficiencies when the TSSM is operating from 07 to 35 AU's The modules are 061 M (2 ft) wide by 229 M (75 ft) long and have a dry weight including propellant tank of 544 kg (120 lb) The propellant tank will hold 1451 kg (320 lb) of mercury
5 citations
05 Jun 2017
TL;DR: In this paper, a dual-layer carbon phenolic manufactured from a three-dimensional woven substrate was tested in three arcjet facilities over a range of environments up to heat flux of approximately 6'kW/cm2.
Abstract: A new dual-layer carbon phenolic manufactured from a three-dimensional woven substrate was tested in three arcjet facilities over a range of environments up to heat flux of approximately 6 kW/cm2
5 citations
01 Jan 1988
5 citations