|Doctorant - Institut National des Sciences Appliquées de Toulouse (INSA de Toulouse)|
Membre du groupe Modélisation des Systèmes et Microsystèmes Mécaniques (MS2M)
Espace Clément Ader, 3 rue Caroline Aigle
Activités de recherche :
EMA (Electromechanical Actuator) is a technology gathering electrical power with kinetics to create a motion under electrical signal orders. Today, this technology does exist in the field of civil & military aircrafts for auxiliary functions (not critical in terms of safety) and/or back up (case of failure of critical primary functions) and in some industrial sectors for locating a workpiece on machine tools or laboratory’s equipment.
The aeronautics sector changes towards more and more autonomous helicopters. Lots of OPV and UAV projects are starting. The trend on today’s market is a reduction of pilot’s workload and functions’ automatization. The electrification of equipment is necessary and this is even the opportunity to open onto new features installed on board.
Airbus Helicopters is anticipating future evolutions and starts the electrification of flight control system (FbW Fly by Wire) and power system (PbW Power by Wire) on light helicopters (VSR700 project). All the EMA’s interests are here, in the power system. Challenges are even more important: the aim is to reduce mass and overall dimension of structural components with increased performance (resistance to stresses, responsiveness of enslavement) removing issues of plays and vibrations coming from the flight control channel and reducing the complexity of assembly which usually slowers the assembly line operation.
Nevertheless, this technology is not sufficiently developed and handled to take part, from now on, in the helicopter’s critical primary flight control system and guarantee high performances given by severe operating conditions intrinsically brought by the field of rotating blades.
My thesis aims at building key skills in designing at system level the critical EMA technology following 3 research lines: 1. State of the art of the critical EMA and recommendations in the choice of architecture with analysis of measurements from flight profiles, 2. Creation of a tool for multidisciplinary sizing of rotary and linear EMA, then 3. Use of the sizing tool and of a virtual prototype in order to optimize EMA components’ tolerance processes.