• more-electric aircraft
• modeling and simulation
• landing gear actuation
• electromechanical actuator
• electro-hydraulic actuator
• power absorption
• preliminary design

In a context where the flight control actuation is moving towards more electric solutions, there is no longer reason to employ the conventional hydraulic system for landing gear actuation, which is the largest user of hydraulic power in civil transport aircraft.
This thesis aims to provide the designer with models able to asses landing gear actuation by means of an Electro-Mechanical Actuator and an Electro-Hydraulic Actuator. In this way the designer will be able to make top-level decisions between competing solutions based on a greater and deeper knowledge of the system.
To achieve this goal, the models of a landing gear, an EMA and an EHA were developed using Modelica language. At the same time, an automatized user-Modelica interface has been implemented using Java language, in order to make the models re-usable for a rapid exploring and assessment of different architectures.