Modelling and Optimization of Strut Configurations in Aircraft Landing Gear Assembly for Effective In-Service Duty Cycle

Abstract

The landing gear configuration system is one of the most critical systems, subjected to intense dynamic loads and failure during landing and taxiing operations. The optimization of this system is of key importance to the aviation industry, with clear and direct effects ranging from integrity, safety, and fuel efficiency to maintenance dynamics. The present study focuses on the modelling and optimization of strut configurations in an aircraft landing gear assembly for an effective in-service duty cycle. Two strut configurations, consisting of a conventional single strut and an optimized dual strut, were modelled and comparatively analyzed using parametric CAD tools as well as Finite Element Analysis (FEA) within the SolidWorks simulation environment. The modelling and simulation involve the load and stress analysis of critical components, ranging from the main strut, retraction mechanisms, torque links, torque bars, and wheels to the actuator and main support. This approach was geared towards the premise of analyzing and optimizing the landing gear system by achieving weight reduction without compromising structural integrity. This was achieved through FEA of the design model. The simulation results showed that achieving a conservative 5% reduction in weight would translate into a decrease of approximately 1,045 kg in the aircraft's operating empty mass, which further translates into a reduction in the aircraft's energy consumption during its in-service duty cycle. The results further revealed that the developed model can effectively support the prediction and analysis of the mechanical behaviour of the landing strut.