{"id":5042,"date":"2017-03-03T14:12:27","date_gmt":"2017-03-03T13:12:27","guid":{"rendered":"https:\/\/www.italsystemsrl.it\/?p=5042"},"modified":"2024-10-29T09:52:05","modified_gmt":"2024-10-29T08:52:05","slug":"fase-lag-ema","status":"publish","type":"post","link":"https:\/\/www.italsystemsrl.it\/en\/fase-lag-ema\/","title":{"rendered":"FASE-LAG \u2013 EMA"},"content":{"rendered":"

The development of a more electric aircraft represents one of the challenges of the technological transition envisaged for a large part of the primary and auxiliary systems of aircraft and helicopters<\/p>\n

The aircraft industry has initiated numerous studies and developments for electrical actuation, including the use of electro-hydrostatic actuators (EHA), and has started to introduce electromechanical actuators for auxiliary equipment.<\/p>\n

This has necessitated incremental approaches to address hydraulic circuit issues with Power-by-Wire technologies (A320, B777 and Falcon 7X), the introduction of the 2-hydraulic\/2-electric (2H\/2E) power distribution architecture, in which flight control is powered by EHAs using a local hydraulic reservoir (A380, A350XWB) and EMAs for specific systems (spoilers, brakes and engine starters). Thanks also to various research programmes, EMA systems are now considered the best candidate for replacing current hydraulic and mechanical systems.<\/p>\n

This is due to multiple factors :<\/p>\n

- Less complexity due to the absence of a hydraulic system;<\/p>\n

- More energy efficient than hydraulic systems;<\/p>\n

- Easy installation maintenance (no filtration and leaks);<\/p>\n

- Less complex power distribution and management (power is transmitted without mass transfer).<\/p>\n

The PHASE-LAG project, started in 2017, aims to develop an electric drive system for the extension-retraction of the main landing gear of the future SMALL A\/C.<\/p>\n

The main project objectives (FAil-Safe Electro-mechanical actuation for LAnding Gear ) are :<\/p>\n

    \n
  1. Development of an electromechanical actuation system (EMAS) for landing gear characterised by\u00a0reduced size\u00a0<\/strong>and\u00a0weight, higher reliability\u00a0<\/strong>and\u00a0greater safety margins<\/strong><\/li>\n
  2. Testing of the EMAS system for the implementation of the landing system in a dedicated test facility (RIG) to verify the achievement of the target TRL<\/li>\n<\/ol>\n

    To achieve these goals, the solution will include innovative technologies such as:<\/p>\n