@article{oai:jaxa.repo.nii.ac.jp:00031377,
 author = {DOI, Takao and YASUDA, Seiichi and AKIBA, Ryojiro},
 journal = {The Institute of Space and Astronautical Science report},
 month = {Sep},
 note = {The forced evaporation of liquid is employed to produce working fluid for a thermal thruster system called "Spray Thruster." The experimental model of spray thruster has been tested in the wide range of the mass flow rate using Ethyl Ether, Pentane and Furan. The spray thruster is operated well in a vacuum environment without any energy additions. The exhaust stream consists of vapor containing droplets, the mass fraction of which is in the range from 0.8 to 0.9. The Isp reaches 28 seconds at the propellant tank temperature of 20℃ for Ethyl Ether. The analysis of the nozzle flow shows that an equilibrium flow model and partially frozen flow model explain properly the measured thrust performance in the small and large mass flow rate operations, respectively. The effects of chemical properties of propellant, nozzle scale, propellant tank temperature and structural mass of the system on the thrust performance have been investigated in detail to obtain the fundamental design aspects., 資料番号: SA0034977000},
 pages = {1--56},
 title = {An Experimental Study of Spray Thruster},
 volume = {613},
 year = {1984}
}