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Electro-hydraulic actuation of primary flight control surfaces

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5 Author(s)
P. M. Churn ; Dept. of Electron. & Electr. Eng., Sheffield Univ., UK ; C. J. Maxwell ; N. Schofield ; D. Howe
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Increasingly demanding performance and certification requirements for next-generation aircraft flight control systems, together with a continuous development effort within the industry towards `all/more electric' aircraft, have fostered the need to replace traditional hydraulic actuation systems by electric and/or electro-hydraulic technology. Digitally controlled brushless permanent-magnet drive systems with integrated power electronics, offer one possibility for rationalising the drive-train architecture of such aircraft actuation and control systems. The paper will discuss key issues pertinent to actuation systems based on electro-hydraulic actuators for large aircraft. Specifically, it considers an actuation system which has been developed for a primary control surface, viz. the rudder, for which aircraft aerodynamic loadings combined with environmental conditions require a high performance drive-train

Published in:

All Electric Aircraft (Digest No. 1998/260), IEE Colloquium on

Date of Conference:

17 Jun 1998