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
