Multi-Disciplinary Design of an Aircraft Landing Gear using Concept Design and Optimization Techniques

摘要

In this paper, the CAE-driven design process to achieve a high-performance, lowweight aircraft landing gear design is presented. The process is led by concept design and optimization techniques along with advanced innovative analysis methods. As a result, multidisciplinary design requirements of the landing gear are met and landing gear weight is reduced. This efficient and effective CAE-driven design process is applicable to all practical engineering problems. Aircraft landing gears are designed for landing and taxiing. For the landing event, the objective is to find the optimal damping characteristics of the landing gear such that the dynamic load-stroke curve never exceeds the dynamic load envelope. For this task, a reliable optimum is also sought for using reliability-based optimization method safety margin approach (SMA). In addition to optimizing the damping profile, shape optimization of lugs under dynamic loading is also practiced using Equivalent Static Load Method (ESLM). ESLM is an innovative method for optimizing multi-body dynamics problems that utilize flexible bodies. Taxiing event generate high stresses in the torsion links and lugs. Topology and shape optimization are used for torsion link concept design and shape optimization is used to for lug re-design. The new torsion link weighs 27% less and the re-designed lug stresses are down by 59% to acceptable levels. The allocated time for the project is 6 weeks and it took approximately one-man month to complete it.