Conference article

Hydraulic Pressure Fed System Using Helium Gas and Fast Electro-Hydraulic Actuator Applied to Brazilian Sounding Rockets and Microsatellite Launchers

Euler C. M. Gonçalves Barbosa
Aeronautics and Space Institute (DCTA/IAE), São José dos Campos, São Paulo, Brazil

Luiz C. S. Góes
Technological Institute of Aeronautics (DCTA/ITA), São José dos Campos, São Paulo, Brazil

Thiago Scharlau Xavier
Technological Institute of Aeronautics (DCTA/ITA), São José dos Campos, São Paulo, Brazil

Download articlehttp://dx.doi.org/10.3384/ecp181565

Published in: WIEFP2018 – 4th Workshop on Innovative Engineering for Fluid Power, November 28-30, Sao Paulo, Brazil

Linköping Electronic Conference Proceedings 156:2, p. 5-10

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Published: 2018-12-10

ISBN: 978-91-7685-136-4

ISSN: 1650-3686 (print), 1650-3740 (online)

Abstract

This work presents the research and technological development of a hydraulic high Pressure Fed System (named PFS) using Nitrogen/Helium gas and a fast electro-hydraulic actuator (FEHA) applied to movable nozzles for Brazilian sounding rockets and microsatellite launchers. The preliminary control capability analysis to sounding rockets design requires a high performance FEHA, e. g. the bandwidth, to perform the attitude control using the Thrust Vector Control (TVC) strategy. The Thrust Vector Assembly (TVA) consist of the PFS mounted on the EHA that controls the nozzle angular movement, in closed-loop operation. Modeling and simulation results using AMEsim environment show the PFS performance compared to step-unit response obtained from experimental tests. Frequency Response Functions (FRF) are obtained from experimental data using sinusoidal signals of excitation with frequency from 1 to 10 Hz, and the bandwidth Bw is accessed. Equipment to the PFS includes a pressure regulator to the helium gas in order to pressurize the hydraulic fluid with a constant pressure of 200 bar. A high performance electro-valve controls the oil flow in the hydraulic cylinder and a real-time digital controller is implemented to stabilize the closed loop. The results are of very interest if compared to the European actuator flight model of the Brazilian satellite launcher vehicle VLS-1. Details and improvements are discussed in order to obtain best bandwidth in the next FEHA engineering model, e.g. the digital flow control technique to the servo-valve.

Keywords

Pressure system, electro-hydraulic actuator, control system

References

[1] Ettl, et al, Development of the VS-50 as an intermediate step towards VLM-1, European Space Agency, 22nd ESA Symposium on European Rocket and Balloon Programmers and Related Research, ESA SP-730, 2015.
[2] A. L. Greensite, Control Theory: Analysis and Design of Space Vehicle Flight Control Systems, Spartan Books, 1970.

[3] Merrit, H., Hydraulic Control Systems,John Wiley & Sons, Inc., New York, 1967.

[4] M. Jelali and A. Kroll, Hydraulic servo-systems. Springer, 2003.

[5] Karnopp, D., Margolis, D., & Rosenberg, R., System Dynamics: A Unified Approach, 1990.

[6] Barbosa, E. C. M. B., Wekerle, T., Batagini, C. M., Brazilian Thrust Vector Control System Development: Status and Trends, Propulsion and Energy Forum, July 25-27, Salt Lake City, UT, http://arc.aiaa.org | DOI: 10.2514/6.2016- 4909. 52nd AIAA/SAE/ASEE, 2016.

[7] Barbosa, E. C. M. B., Wekerle, T., Batagini, C. M., Closed-loop actuator identification for Brazilian Thrust Vector Control development. In: International Federation of Automatic Control, 2016, Shrebrok. 20th IFAC Symposium on Automatic Control in Aerospace - ACA 2016. Toronto: IFAC, 2016. v. 12. p. 233-243.

[8] Barbosa, E. G., Modeling via Bong Graphs of a flexible structure controlled by a hydraulic actuation, Technological Institute of Aeronautics - ITA, Master Dissertation, 2001.

[9] G. P. Sutton and O. Biblarz. Rocket Propulsion Elements 8 th ed. John Wiley & Sons, Inc., Hoboken, New Jersey, 2010. ISBN 978-0-470-08024-5

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