Application of linear motor on artificial satellite fuel pump system

Author

Oyama, Jun ; Higuchi, Tsuyoshi ; Akashi, Hiroto ; Yamada, Eiji ; Nagatomo, N. ; Yoshinaga, Itsuo

Author_Institution

Dept. of Electr. Eng. & Comput. Sci., Nagasaki Univ., Japan

fYear

1992

fDate

4-9 Oct 1992

Firstpage

156

Abstract

The authors propose a new type of fuel pump system with linear motor propulsion, in which two pumps are equipped on both sides of the linear motor and a resonant system with springs is organized to decrease the rated thrust. A pump where the discharge pressure is 21.0 kgf/cm² and the discharge flow rate is 21.25 cm³/s is assumed. A prototype linear pulse motor was designed, built, and tested. The thrust characteristics are estimated using an equivalent magnetic circuit, and it is confirmed that the calculated results agree well with the experimental results

Keywords

aerospace testing; artificial satellites; electric propulsion; equivalent circuits; fuel; linear motors; machine testing; machine theory; magnetic circuits; pumps; stepping motors; artificial satellite fuel pump system; discharge pressure; equivalent magnetic circuit; flow rate; linear motor; machine testing; machine theory; propulsion; pulse motor; resonant system; springs; stepping motors; thrust characteristics; Application software; Artificial satellites; Control systems; Engines; Fuel pumps; Magnetic circuits; Propulsion; Resonance; Satellite broadcasting; Size control;

fLanguage

English

Publisher

ieee

Conference_Titel

Industry Applications Society Annual Meeting, 1992., Conference Record of the 1992 IEEE

Conference_Location

Houston, TX

Print_ISBN

0-7803-0635-X

Type

conf

DOI

10.1109/IAS.1992.244450

Filename

244450