Abstract :
The main wheel brakes fitted to existing aircraft are generally controlled by hydraulic actuators. There is currently considerable interest in the concept of the `all- or more electric aircraft´, where traditional technologies such as hydraulic actuators are being replaced by their electro-mechanical counterparts. Adoption of electro-mechanical technology in braking systems can offer potential benefits. These include: improved safety, by reducing the risk of brake fire, through the removal of flammable hydraulic fluid from the brake vicinity; improved reliability and maintainability, by removing the possibility of hydraulic leakage and associated maintenance tasks; potentially improved efficiency through better control of braking torque; and reduced system mass when considered in the context of the `more electric aircraft´, with the removal of hydraulic pumps, reservoirs and valves. The work described in the paper covers the design of the electro-mechanical actuator, which forms part of a wider two year feasibility study of the development of the whole electro-mechanical braking system, including the Wheel/Brake and Electronic Brake Control System design/integration. The specific focus of this work has been to improve braking performance in relation to the existing hydraulic system and to incorporate novel methods for failure management. The paper discusses the dominant actuator design drivers, being: system availability, dynamic performance, and thermal environment
Keywords :
aircraft; EABSYS; Electronic Brake Control System; aircraft; all-electric aircraft; brake fire risk reduction; brake vicinity; braking performance improvement; braking torque control; dynamic performance; electrically actuated braking system; electro-mechanical braking system; flammable hydraulic fluid; maintainability; more electric aircraft; reliability; safety; system availability; thermal environment; wheel brakes;
