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.

Space Propulsion Applications of Helium Arcjets

Abstract: : With currently available space electric power systems, the optimum specific impulse for electrically propelled satellite transfers from low Earth orbit to geosynchronous Earth orbit appears to be in the 1000 to 1200 second range. Arcjets operating with helium as a propellant may be the most efficient electric thruster capable of operating in this specific impulse range. This work reports on a recent set of experiments which examined the effects of arcjet configuration, and propellant composition and flow rates, on arcjet performance. In these tests, it was found that increasing the cathode-anode gap over that normally used with hydrogen or ammonia propellants increased arc stability and significantly improved specific impulse and electrical efficiency. Hydrogen seeding was found to improve arc stability, particularly at smaller cathode gaps, but it had a very small effect on overall performance of the arcjet. The primary variable which affected arcjet performance was found to be propellant flow rate. The efficiency of the helium arcjet was found to increase with increasing propellant flow rate up to the maximum flows available for the current set of experiments.

Radial Profiles of Arcjet Flow Properties Measured with Laser-Induced Fluorescence of Atomic Nitrogen

Abstract: Radial profile measurements of absolute atomic nitrogen density, temperature, and velocity using two photon laser-induced fluorescence in the NASA Ames Aerodynamic Heating Facility (AHF) are reported. Improvements in experimental technique and calibration procedure significantly reduced measurement uncertainties compared to previous efforts. The addition of a traversing system within the AHF test cabin permitted, for the first time, radial measurements of the three flow properties during a single arcjet run. Typical measurement uncertainties are 12% for absolute N density, 10-30% for temperature, and 3% for velocity. Details of the measurement technique, optical configuration, data analysis procedures, and results of two repeated demonstration runs in air/Ar flows are presented.

Applications of Microthrusters for Satellite Missions and Formation Flights Scenarios

Abstract: Low thrust engines (e.g. ion thrusters, arcjet engines, magneto‐plasmadynamic systems) with high specific impulses became important tools for recent space missions (SMART 1, Hayabusa 1 …). Although in particular ion thrusters demonstrated high reliability and long term stability, their performance is not sufficient for satellite systems requiring drag‐free, high precision attitude and orbit control. An increasing number of missions for geodetic purposes or astronomic science goals as well as formation flight scenarios with precise distance control between single satellites require much better propulsion systems enabling thrust control down to the sub‐μN level. Micropropulsion systems must be able (i) to compensate disturbing forces preventing the spacecraft from flying on an ideal geodetic orbit and (ii) to balance tidal forces and spacecraft dynamics in formation flight scenarios. Recent developments (e.g. Field Emission Electric Propulsion—FEEP) are promising but so far not sufficient approaches, wherefore laser induced ablative thrusters are completely new concepts still under study.

Spectroscopically Measured Velocity Profiles of an MPD Arcjet

Abstract: : The plasma jet was investigated with respect to the Doppler shift of spectral lines resulting from macroscopic velocities in axial and rotational directions. (Author)