Accession Number : ADA601957


Title :   Scientific Research Program for Power, Energy, and Thermal Technologies. Task Order 0001: Energy, Power, and Thermal Technologies and Processes Experimental Research. Subtask: Thermal Management of Electromechanical Actuation System for Aircraft Primary Flight Control Surfaces


Descriptive Note : Interim rept. 20 Jul 2012-1 May 2014


Corporate Author : DAYTON UNIV OH RESEARCH INST


Personal Author(s) : Lammers, Zachary A


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a601957.pdf


Report Date : May 2014


Pagination or Media Count : 237


Abstract : Electromechanical actuation systems (EMAS) are a key component in the more electric aircraft (MEA). EMAS operate on a power- on-demand basis, reducing energy consumption typically required by hydraulic systems to maintain hydraulic pressure. Additionally, EMAS reduce system weight, lessening system maintenance and operating costs. EMAS convert electrical energy to mechanical energy via an electric rotary machine combined with a rotary to linear or rotary to rotary conversion mechanism. Electrical energy required to complete useful mechanical output depends on the efficiency of the system. Therefore, it is important to characterize electrical and thermal loads associated with an EMAS for primary flight control surfaces, such as an aileron. Electric power draw and thermal management are among the most important parameters of research in electromechanical actuation for a primary flight control (PFC) surface. The aim of this thesis was to build an experimental EMAS system and methodology to analyze EMAS performance against realistic duty cycles and mission environments. Thermal energy, in addition to the rate of change of temperature and temperature difference for temperature sensitive components, was used to determine the most thermally malignant profiles and potential thermal design points. It was found that transient missions of an EMAS presented the greatest electric demand of the aircraft electric power supply system, and holding presented the greatest thermal stress of the EMAS, where the EMAS operated at0 percent efficiency and all electric power was converted to heat.


Descriptors :   *ACTUATION , *AERODYNAMIC CONTROL SURFACES , *ELECTROMECHANICAL DEVICES , *TEMPERATURE CONTROL , EFFICIENCY , ELECTRIC POWER , ENERGY CONSUMPTION , FLIGHT CONTROL SYSTEMS , HYDRAULIC EQUIPMENT , HYDRAULIC PRESSURE , THERMAL RADIATION , THERMAL STRESSES


Subject Categories : Air Condition, Heating, Lighting & Ventilating
      Mfg & Industrial Eng & Control of Product Sys
      Thermodynamics


Distribution Statement : APPROVED FOR PUBLIC RELEASE