Email this article PROCESS MODELING ELECTRO-HYDRAULIC CONTROL SYSTEM CANCELED OR RE-LAUNCH ROCKET ENGINE SOLID FUEL
- Authors: Bachurin A.B.1, Strelnikov E.V.1, Tselischev V.A.1
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Affiliations:
- Ufa State Aviation Technical University Ufa, Ul. K. Marksa, 12 Russia, 450000
- Issue: Vol 2, No 2 (2015)
- Pages: 6-15
- Section: Articles
- URL: https://dynvibro.ru/dynvibro/article/view/2939
- DOI: https://doi.org/10.18287/2409-4579-2015-2-2-6-15
- ID: 2939
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Abstract
Within the framework of the contemporary problem solving serial use of solid propulsion in space industry related disabilities deep traction control module and multiple on-off setting, proposed the introduction of a combined system of governance. The article provides a diagram of a controlled rocket propulsion system, equipped with a dual-circuit electrohydraulic control system, and describes how to control laid down in its foundation.The analysis of transients in a rocket engine solid fuel in separate and combined use of control subsystems responsible for the extinction of the engine and preparing to re-launch.
About the authors
A. B. Bachurin
Ufa State Aviation Technical UniversityUfa, Ul. K. Marksa, 12 Russia, 450000
Email: bachurinsasha1987@mail.ru
кандидат технических наук, старший преподователь кафедры Прикладной Гидромеханики ФГБОУ ВПО УГАТУ
Russian FederationE. V. Strelnikov
Ufa State Aviation Technical UniversityUfa, Ul. K. Marksa, 12 Russia, 450000
Author for correspondence.
Email: e_strelnikov@mail.ru
аспирант кафедры Прикладной Гидромеханики ФГБОУ ВПО УГАТУ
Russian FederationV. A. Tselischev
Ufa State Aviation Technical UniversityUfa, Ul. K. Marksa, 12 Russia, 450000
Email: pgl.ugatu@mail.ru
доктор технических наук, профессор, заведующий кафедрой Прикладной Гидромеханики ФГБОУ ВПО УГАТУ
Russian FederationReferences
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