Practical Considerations in the Modelling and Simulation of Electromechanical Actuators (original) (raw)
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In this work, a methodology and an integrated tool framework has been proposed for the preliminary design of electromechanical actuators. An in-house Modelica library has been developed to perform the sizing process. A CAD tool has been integrated with the system simulation software for automatic validation of the geometrical integration of an electromechanical actuator over a specific kinematic. The proposed framework is illustrated with the geometrical validation for an electromechanical actuator of a nose landing gear doors mechanism. Nowadays in Aerospace industry, new generations of systems based on electromechanical actuators technologies are beginning to replace the hydraulics ones [RR1]. This reconfiguration of actuation systems for aircraft can provide a gain in power management, operating mode, reliability and maintainability. This change in technology requires an overall rethinking of the design process and notably the use of multi-physics or multi-domain simulation tools...
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Electromechanical actuator (EMA) is a type of power-by-wire (PBW) actuator that is becoming widely implemented in aerospace industry. Given the application area, designing an EMA is highly constrained in weight, integration space, maintenance costs, dynamic performances, reliability, etc. In order to reduce the EMA’s design time, cost and effort, all these constraints should be considered in the preliminary design stages. The problem is that at such early design stages, system engineers need simple and explicit models. Thus, this communication is attempting to formulate simple relations that account for torque and velocity saturation of the EMA as well as compliances effects on its dynamic performance. The simple and parametric models predict the main impact of the sizing variables on performance.
A Method for the Evaluation of Electromechanical Actuator Systems Using Exergy
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In recent years, aircraft designers have strived to reduce aircraft fuel burn and emissions through the use of more electric aircraft (MEA). In a MEA, heavy systems such as hydraulics are replaced by an electrical system. Although a significant increase in efficiency can be achieved, many design challenges must be addressed. One issue is the high amount of coupling between electrical, mechanical, and thermal management components in a MEA. In order to account for component interactions, a system level design approach is needed. The system level approach will require the evaluation of many different types of components and architectures. In order to achieve this task, a common metric and a technique for rapidly modeling different architectures are required. A modeling environment was created for the evaluation of electromechanical actuation systems which uses exergy as a common metric. Exergy was selected for a figure of merit since it can be used universally with a variety of system...