Experimental Study of the Possible Working Pressure Dynamic Control in the Aircraft Hydraulic System

Abstract

Experimental studies were carried out to determine alteration of the nominal working pressure level in the hydraulic system of the integrated test bench designed to develop the aircraft electrohydraulic servovalve actuators and control systems at the Central Aerohydrodynamic Institute (TsAGI). These studies were conducted as part of research of a possibility to limit the aircraft hydraulic subsystems operation time in flight under high pressure to extend the onboard hydraulic system service life. Pressure control according to the flight modes suggests a possibility to reduce power take-off from the aircraft engine, and also significantly simplifies the process of passing to a higher level of nominal working pressure in the hydraulic systems, which could reduce the weight and volume of the aircraft hydraulic equipment. The paper shows that introduction of a special device, i.e., the pressure reduction unit, makes it possible to remotely control the hydraulic supply pressure of the actuators being tested on the bench in a wide range of values using the control system command signals. Device introduction automates the process and expands types of the servovalve actuators experimental studies on the bench, for example, in simulating various flight modes or failure accidents during a seminatural simulation of the aircraft motion dynamics. The paper provides description and operation principle of the pressure reduction unit main elements. Obtained results of the transient processes dynamics in pressure alteration using the pressure reduction unit demonstrates that the control device basic diagram could be introduced not only in bench testing, but also on board the modern and promising aircraft to create intelligent hydraulic systems of the new generation

The work was supported by the Grant from the Russian Science Foundation (project no. 23-19-00464)

Please cite this article in English as:

Erofeev E.V. Experimental study of the possible working pressure dynamic control in the aircraft hydraulic system. Herald of the Bauman Moscow State Technical University, Series Mechanical Engineering, 2024, no. 3 (150), pp. 57--75 (in Russ.).EDN: YFRSAT

References

[1] Matveenko A.M., Zverev I.I. Proektirovanie gidravlicheskikh sistem letatelnykh apparatov [Design of aircraft hydraulic systems]. Moscow, Mashinostroenie Publ., 1982.

[2] Chernenko Zh.S., Lagosyuk G.S., Nikulinskiy G.N., et al. Gidravlicheskie sistemy transportnykh samoletov [Hydraulic systems of transport aircraft]. Moscow, Transport Publ., 1975.

[3] Shumilov I.S. Possible ways to reduce the mass of an aircraft’s rudder control system. Nauka i obrazovanie: nauchnoe izdanie MGTU im. N.E. Baumana [Science and Education: Scientific Publication], 2013, no. 2 (in Russ.). EDN: QABSSB

[4] Boris Yu.A. Pressure forcing in the redundant aircraft hydraulic system in case of its channels failures. Tekhnika vozdushnogo flota, 1991, no. 3, pp. 24--35 (in Russ.).

[5] Matveenko A.M., Dolgushev V.G., Petrovichev V.I., et al. [Improving the efficiency of aircraft on-board hydraulic systems by adapting the operating pressure]. ASTEC’07, 2007, p. 7.

[6] Guo S., Chen J., Lu Y., et al. Hydraulic piston pump in civil aircraft: current status, future directions and critical technologies. Chinese J. Aeronaut., 2020, vol. 33, no. 1, pp. 16--30. DOI: https://doi.org/10.1016/j.cja.2019.01.013

[7] Dolgushev V.G., Ionov V.A., Kun N.V., et al. Development trends of modern aircraft onboard hydraulic systems. Trudy MAI, 2017, no. 95 (in Russ.). Available at: https://trudymai.ru/published.php?ID=84461

[8] Demarchi J., Ohlson J. Flight testing an 8000 psi lightweight hydraulic system. SAE Tech. Pap., 1977, paper 771007. DOI: https://doi.org/10.4271/771007

[9] Robert W.M. High-pressure hydraulics for the A380. Overhand & Maintenance, 2005, vol. 18, no. 6, pp. 43--45.

[10] Zhao Y., Bao Y., Zhang C., et al. Design and analysis of variable pressure control of aircraft hydraulic system. ICMCCE, 2020, pp. 815--819. DOI: https://doi.org/10.1109/ICMCCE51767.2020.00179

[11] Wang Z., Chen B. Characters of future aircraft hydraulic system. SSCAE, 1999, vol. 1, no. 3, pp. 1009--1742.

[12] Aerospace hydraulic pump controls. Aerospace Information AIR5872A. Warren-dale, SAE International, 2017.

[13] Spencer J.E. Development of variable pressure hydraulic systems for military aircraft utilising the "smart hydraulic pump". ImechE, 1993, pp. 101--111.

[14] Matveenko A.M., Peyko Ya.N., Komarov A.A. Raschet i ispytaniya gidravlicheskikh sistem letatelnykh apparatov [Calculation and testing aircraft hydraulic systems]. Moscow, Mashinostroenie Publ., 1974.

[15] Smagin D.I., Pugachev Yu.N., Dolgov O.S. On-board testing of hydraulic systems and their importance in the development of modern aircraft types. Trudy MAI, 2011, no. 44 (in Russ.). Available at: https://trudymai.ru/published.php?ID=25118

[16] Erofeev E., Khaletsky L., Skryabin A., et al. Methodologies and test-rig configurations for experimental improvement of flight control actuation systems. R3ASC, 2018, pp. 109--116.

[17] Sabelnikov V.I., Kolevatov Yu.V., Fadeev Yu.V. Gidrosistema dlya nagruzheniya aviatsionnykh konstruktsiy pri prochnostnykh ispytaniyakh [Hydraulic system for loading aircraft structures at strength tests]. Patent RU 2267759. Appl. 08.01.2004, publ. 10.01.2006 (in Russ.).

[18] Popov D.N. Dinamika i regulirovanie gidro- i pnevmosistem [Dynamics and regulation of hydro- and pneumatic systems]. Moscow, Mashinostroenie Publ., 1987.

[19] Mileti J.A., Lawhead P.M. Controlled pressure pumps for more efficient hydraulic systems. SAE Tech. Pap., 1986, paper 861844. DOI: https://doi.org/10.4271/861844

[20] Wilson T.M., Hasenoehrl T.R., Chin E.C., et al. Engine driven pump (EDP) automatic depressurization system. Patent US 9823670. Appl. 25.11.2014, publ. 21.11.2017.