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Test Set-up for Electromechanical Actuation Systems for Aircraft Flight Control
Technical Paper
2012-01-2203
ISSN: 0148-7191, e-ISSN: 2688-3627
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English
Abstract
An Electromechanical Actuation System (EMAS) are an important component for an all electric Aircraft. EMAS would be lighter and require less system maintenance and operational costs than hydraulic actuators, typically used in aircraft systems. Also, hydraulic actuation systems require a constant power load to maintain hydraulic pressure, whereas EMAS only use power when actuation is needed. The technical challenges facing EMAS for aircraft primary flight control includes jam tolerance, thermal management, wide temperature range, high peak electric power draw, regenerative power, installation volume limit for thin wings, etc. This paper focuses on a laboratory test setup to simulate EMAS flight control environment to test and evaluate three important performance parameters of EMAS; thermal management, transient peak power draw, and regenerative power.
Authors
Citation
Barnett, S., Lammers, Z., Razidlo, B., Leland, Q. et al., "Test Set-up for Electromechanical Actuation Systems for Aircraft Flight Control," SAE Technical Paper 2012-01-2203, 2012, https://doi.org/10.4271/2012-01-2203.Also In
References
- JENNEY, GAVIN D. 2000 ELECTRICALLY POWERED ACTUATION DESIGN (EPAD) AFRL-VA-WP-TR-2002-3013
- Dawson, David Jenney, Gavin D. Jenson, Steven C. Flight Test Experience With An ElectromechanicalActuator On The F-18 Systems Research Aircraft www.nasa.gov/centers/dryden/pdf/88699main_H-2425.pdf September 2 2011