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Procedure of designing a pilot operated gas pressure regulator for launch vehicle fuel tanks
- Authors: Gimadiev A.G.1, Sverbilov V.Y.1, Stadnik D.M.1
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Affiliations:
- Samara National Research University
- Issue: Vol 15, No 4 (2016)
- Pages: 33-46
- Section: AIRCRAFT AND SPACE ROCKET ENGINEERING
- URL: https://journals.ssau.ru/vestnik/article/view/3299
- DOI: https://doi.org/10.18287/2541-7533-2016-15-4-33-46
- ID: 3299
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Abstract
The paper presents a calculation procedure based on the mathematical model of a pilot operated gas pressure regulator. The model takes into account the parameters of the feedback channel, the gas damper, the flow force at the main valve poppet and the dynamics of the fuel tank pressurization system of a launch vehicle. We analyzed the influence of the gas damper incorporated in the pressure relief valve on the pressure control system performance. Stability domains in the space of the regulator parameters are calculated. We assessed the control system stability margin for varying gas damper parameters. The proposed procedure of regulator design ensures the required stability margin of the gas pressure control system. The static accuracy of the system remains unchanged.
About the authors
A. G. Gimadiev
Samara National Research University
Author for correspondence.
Email: gimadiev_ag@mail.ru
Doctor of Science (Engineering)
Professor of the Department of Power Plant Automatic Systems
V. Ya. Sverbilov
Samara National Research University
Email: v.sverbilov@mail.ru
Candidate of Science (Engineering)
Assistant Professor of the Department Power Plant Automatic Systems
D. M. Stadnik
Samara National Research University
Email: sdm-63@bk.ru
Candidate of Science (Engineering)
Assistant Lecturer of the Department of Power Plant Automatic Systems
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