Determination of Parameters in Arcjet Plume by Tomographic Reconstruction

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概要

• 論文の詳細を見る

• The spatial temperature and atomic number density of the plume generated by a 3-kW-class arcjet thruster are determined with a small number of absorption measurements across the plume based on diode-laser absorption computerized tomography. The maximum temperature and atom number density increase with the massflow rate and discharge current. The increase trend is not always found with the specific input power, although there exists an increasing trend with it at a fixed massflow rate. The development of the plume is studied with the measurements of the plume at different locations. The technique should also be applicable to arcjet or other hypersonic flow systems without much modification.

• 社団法人 日本航空宇宙学会の論文
• 2000-08-04

著者

• Zhang F‐y

  Nagoya Univ. Nagoya Jpn

• Fujiwara T

  Graduate School Of Engineering Nagoya University

• Harada Junya

  Graduate School Of Engineering Nagoya University

• Komurasaki K

  Graduate School Of Engineering Tokyo University

• Fujiwara Toshitaka

  Department Of Aerospace Engineering Nagoya University

• ZHANG Feng-Yuan

  Graduate School of Engineering,Nagoya University

• FUJIWARA Toshitaka

  Graduate School of Engineering,Nagoya University

• KOMURASAKI Kimiya

  Graduate School of Engineering,Tokyo University

• MIYASAKA Takeshi

  Graduate School of Engineering,Nagoya University

• Miyasaka T

  Department Of Aerospace Engineering Nagoya University

関連論文

• Application of Diode-Laser Absorption Technique to the Enthalpy Measurement of an Arc Heater
• Velocity Measurement of Arcjet Plume with a Diode-Laser Absorption Technique
• Suppression of Discharge Current Oscillations in a Hall Thruster
• Discharge Plasma Fluctuations in Hall Thrusters
• Experimental Study of Key Issues on Pulse Detonation Engine Development
• Determination of Parameters in Arcjet Plume by Tomographic Reconstruction
• One-Dimensional Theory Based on a Two-Fluid Nonequilibrium Plasma Model in MPD Thrusters
• Fundamental Characteristics of a Laser Ablation Microthruster
• Effect of Solute Mixing in the Liquid Propellant of a Pulsed Plasma Thruster
• Development of Thrust Stand for Low Impulse Measurement from Microthrusters
• Numerical Analyses of 2-Dimensional Axisymmetric MHD Flows Satisfying Sonic Conditions in an MPD Thruster

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