Energy Analysis of Electromechanical Actuator under Simulated Aircraft Primary Flight Control Surface Load University of Dayton Research Institute

Format:

Conference/Event

Author/Creator:

Racine, Racine, author.

Contributor:

Barnett, Street

Lammers, Zachary

Leland, Quinn

Murphy, John

Conference Name:

SAE 2014 Aerospace Systems and Technology Conference (2014-09-23 : Cincinnati, Ohio, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 2014

Summary:

AbstractThe 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

Notes:

Vendor supplied data

Publisher Number:

2014-01-2182

Access Restriction:

Restricted for use by site license