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Test verification of flow stabilizer calculated parameters provided flow stabilization of propellant in wide range of input parameters
- Authors: Beshenev Y.A.1, Volkov A.V.1, Kazankin F.A.1
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Affiliations:
- Research and Development Institute of Mechanical Engineering, Nizhnyaya Salda
- Issue: Vol 11, No 3-1 (2012): Special Issue
- Pages: 385-389
- Section: CONFERENCE MATERIALS
- URL: https://journals.ssau.ru/vestnik/article/view/2142
- DOI: https://doi.org/10.18287/2541-7533-2012-0-3-1(34)-385-389
- ID: 2142
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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 FederationA. 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
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