The Development of Japanese 20N Thruster Valve for a Spacecraft Propulsion System

Paper number

IAC-06-C4.P.3.10

Author

Dr. Taiichi Nagata, Japan Aerospace Exploration Agency (IAT/JAXA), Japan

Coauthor

Mr. kenichi kushiki, Japan Aerospace Exploration Agency (IAT/JAXA), Japan

Coauthor

Mr. kenichi kajiwara, Japan Aerospace Exploration Agency (IAT/JAXA), Japan

Coauthor

Mr. yoshiharu sugimura, Japan

Coauthor

Mr. masayuki kobayashi, Japan

Coauthor

Mr. hiroyasu itoh, Japan

Year

2006

Abstract

The 20N-class thruster valve is currently being developed by MOOG Japan and Japan Aerospace Exploration Agency (JAXA).

 We aim to develop this valve of the high reliability and the robust design and manufacturing methods. The GD3 method, TOYOTA motor company qualification control method, has been applied to design and development process of this valve on trial.
 
 The required specifications have been set, and the preliminary valve design was completed [1]. The feature of this valve is follows.

1) Solenoid type operation: This thruster valve is the solenoid type valve.

2) Suspended armature configuration : The armature (plunger) is suspended by “S-Spring”, which is a king of leaf spring, not with coil spring. There is no friction surface between armature and casing. This design may contribute to long life performance.

3) Control orifice: The control orifice is not an area that is formed by an armature stroke but rather an area of the nozzle that prevents degradation of the flow caused by the seal swelling. In addition, it is available for application of thruster valves of various sizes by adjusting the area of the nozzle [2].

 The Bread board model (BBM) has been developed and the performance tests have been done. Based on these results, we are improving the valve design now. The elemental tests and the qualification test will be performed in near future.
  
 We can provide the results of these tests and the overview of our development status.

REFERENCES

[1] Kushiki, K. et al., “Development of a 20N Thruster Valve for A Spacecraft Propulsion System”, Proc. of On-Board Energetic Equipment, Avignon, 2004.

[2] Howell, G. W., and Weathers, T. M., “Aerospace Fluid Component Designers Handbook,” Vol.1, RPL-TDR-64-25, 1970.

Abstract document

IAC-06-C4.P.3.10.pdf

Manuscript document

IAC-06-C4.P.3.10.pdf (🔒 authorized access only).

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