Automated thermovacuum firing test facility for testing and research of workflow in low-thrust rocket engine on hypergolic propellants

Abstract

The paper presents a description and the technical characteristics of newly created and upgraded systems of automated thermovacuum fire stand for testing and research of the workflow of liquid rocket thrusters (small thrust jet engines) working on hypergolic propellant components. The stand allows to determine the energy and dynamic characteristics of small thrust jet engine with thrust from 0.1 to 100 N in the continuous and pulsed operating modes; to explore the intrachamber workflows; to study kinetic properties of gasified liquid intermediates of liquid-phase interaction of hypergolic propellants; to explore the thermal state of the engine under high altitude conditions; to provide research of the power, heat and polluting impacts of small thrust jet engine jet on elements of structure surface of the spacecraft; to explore of diagnostic methods of the small thrust jet engine functioning and others. Automated measuring and information system of the stand provides small thrust jet engine management on a given cyclogram; carrying out the calibration of channels for measurement of parameters of small thrust jet engine: thrust, flow rate of components, pressure, temperature, etc.; collecting information from the measuring channels of the stand during tests and information storage on the hard disk; processing of measurement results on the computer during the test and their representation in the required form (protocols, characteristics, charts and tables); formation of database of engines studied. For measuring the temperature of the outer surface of the chamber of small thrust jet engine is used contactless method using an infrared thermal imaging system. Complex work for improvement of element base and systems of automated thermovacuum fire stand for testing and research of workflow of small thrust jet engine working on hypergolic fuel components was expanded the opportunities of stand in the field of new tasks statement for workflow working off and increase the accuracy of the main parameters measurement for the engines.

About the authors

R. N. Galperin

Samara State Aerospace University

Author for correspondence.
Email: ke_src@ssau.ru

Senior research fellow, research center of cosmic energy

Russian Federation

Y. S. Ivashin

Samara State Aerospace University

Email: ke_src@ssau.ru

Candidate of Science (Engineering)

Senior research fellow, research center of cosmic energy

Russian Federation

V. E. Nigodjuk

Samara State Aerospace University

Email: ke_src@ssau.ru

Candidate of Sciencs (Engineering)

Associate professor of the department of aircraft engines theory

Russian Federation

V. V. Ryzhkov

Samara State Aerospace University

Email: ke_src@ssau.ru

Candidate of Science (Engineering)

Research supervisor of the Research center of space power

Russian Federation

A. V. Sulinov

Samara State Aerospace University

Email: ke_src@ssau.ru

Candidate of Science (Engineering)

Associate professor of the department of aircraft engines theory and senior research fellow, research center of cosmic energy

Russian Federation

References

  1. Ageenko Y.I., Galperin R.N., Ivashin Y.S., Nigodyuk V.E., Ryzhkov V.V., Sulinov A.V. Research of influence of the thermal stream from the mid-flight liquid rocket engine on parameters of operating liquid rocket engines of small draught in the conditions of perspective razgonnogo's propulsion system of the block // Vestnik of the Samara State Aerospace University. 2012. No. 3(34), part 3 P. 251-259. (In Russ.)

Statistics

Views

Abstract: 3766

PDF (Russian): 2024

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