Test verification of flow stabilizer calculated parameters provided flow stabilization of propellant in wide range of input parameters

Abstract

This paper presents a flow stabilizer configuration intended for maintaining regular rated propellants flow through a thruster and also reducing time of transition to steady state mode for any thruster firing in wide range of output parameters.

About the authors

Yu. A. Beshenev

Research and Development Institute of Mechanical Engineering, Nizhnyaya Salda

Author for correspondence.
Email: niimash@list.ru

Low-thrust Rocket Chief Specialist

Russian Federation

A. V. Volkov

Research and Development Institute of Mechanical Engineering, Nizhnyaya Salda

Email: niimash@list.ru
Design-engineer Russian Federation

F. A. Kazankin

Research and Development Institute of Mechanical Engineering, Nizhnyaya Salda

Email: niimash@list.ru
Deputy of Chief Designer Russian Federation

References

Statistics

Views

Abstract: 2947

PDF (Russian): 834

Dimensions

PlumX

Refbacks

  • There are currently no refbacks.

Copyright (c) 2015 VESTNIK of the Samara State Aerospace University

This website uses cookies

You consent to our cookies if you continue to use our website.

About Cookies