This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Energy Analysis of Electromechanical Actuator under Simulated Aircraft Primary Flight Control Surface Load
Technical Paper
2014-01-2182
ISSN: 0148-7191, e-ISSN: 2688-3627
Annotation ability available
Sector:
Language:
English
Abstract
The purpose of this study is to set up a laboratory test apparatus to analyze aircraft flight control EMAS' electrical and thermal energy flow under transient and dynamic flight profiles. A hydraulic load frame was used to exert load to the EMA. The actuator was placed within an environmental chamber which simulates ambient temperature as function of altitude. The simulated movement or stroke was carried out by the EMA. The under test EMA's dynamic load, stroke, and ambient temperature were synchronized through a real time Labview DAQ system. Motor drive voltage, current, regenerative current, and motor drive and motor winding temperature were recorded for energy analysis.
The EMA under test was subjected to both transient and holding load laid out in a test matrix. It was found that the transient missions of EMAS presented the most electric demand on the aircraft electric power supply system while holding presented the most severe thermal stress on the EMAS, where the EMAS operated at 0% efficiency and all the electric power converted to heat.
Recommended Content
Technical Paper | Capabilities and Limitations of Air Cooled Avionic Packages |
Technical Paper | Design Considerations for Aircraft Generator with Start Function |
Technical Paper | Variable Frequency Use in Aerospace Electrical Power Systems |
Authors
Citation
Racine, E., Lammers, Z., Barnett, S., Murphy, J. et al., "Energy Analysis of Electromechanical Actuator under Simulated Aircraft Primary Flight Control Surface Load," SAE Technical Paper 2014-01-2182, 2014, https://doi.org/10.4271/2014-01-2182.Also In
References
- Croke S. and Herrenschmidt J. More electric initiative-power-by-wire actuation alternatives Aerospace and Electronics Conference 1994
- Blanding D. Subsystem Design and Integration for the More Electric Aircraft 5th International Energy Conversion Engineering Conference St. Louis, Missouri, USA 2007
- Moir I. and Seabridge A. Aicraft Systems; Mechanical, Electrical and Avionics subsytems integration West Sussex, England Wiley 2008
- Jensen S. C. J. G. D. R. B. a. D. D. Flight Test Experience with an Electromechanical Actuator on the F-18 Systems Research Aircraft Proceedings of the 19th AIAA Digital Avionics Systems Conference Philadelphia, PA, USA 2000
- Pigg P. R. J. M. R. Energy Optimized Aircraft Modeling, Simulation, and Analysis AIAA Sciences Conference Nashville, TN 2012
- Wells , J. , Amrhein , M. , Walters , E. , Iden , S. et al. Electrical Accumulator Unit for the Energy Optimized Aircraft SAE Int. J. Aerosp. 1 1 1071 1077 2008 10.4271/2008-01-2927
- FedBizOps.Gov Integrated Vehicle Energy Technology (INVENT) Development Program for the 6th Generation Energy Optimized Aircraft (EOA June 2009 https://www.fbo.gov
- U.S. Department of Defense Thermal Design, Analysis and Test Criteria for Airborne Electronic Equipment (MIL-STD-2218) 1992
- Navarro R. Performance of an electro-hydrostatic actuator on the F-18 systems research aircraft 1997 http://www.nasa.gov/centers/dryden/pdf/88524main_H-2210.pdf