DESIGN AND DEVELOPMENT OF ELECTRO- MECHANICAL ACTUATOR AND RETRACTION CONTROL UNIT FOR AIRCRAFT LANDING GEAR SYSTEM

Abstract

In this research, the detailed literature review was initially performed to replace conventional Hydraulic System Actuator (HAS) in Main Landing Gears (MLGs) with electric based actuators for lightweight aircrafts. The potential benefit was observed in Electro-Mechanical Actuator (EMA) due to its lightweight property, low maintenance and enhanced performance. Different architectures of EMA were proposed by keenly observing the design requirements and design constraints. The subassemblies of EMA were analytically analyzed and then numerically analyzed for their load bearing capability and architectural sizing. Later, the detailed designing was performed to reduced weight and enhance performance. The other geometry parts were also analyzed, and architecture was completed by selecting various joining components which resulted in finalized CAD design of EMA. Then, manufacturing and 3D printing of EMA was performed within budget constraints and Retraction Control Unit (RCU) was modelled by using logic schematic to operate manufactured EMA. The open loop RCU is fully capable to control the retraction and extension of landing gears and display the actuator positioning while operating. The first prototype of EMA is capable to work with desired axial force. Although there are manufacturing and design inefficiencies, the prototype is operating smoothly in well lubricated conditions. The time required for actuation exceeds 1 minutes which was due to the installation of 48W low powered motor. The pre-selected BLDC motors operating at 2490 RPM having 2