Conceptual Design, Material, and Structural Optimization of a Naval Fighter Nose Landing Gear for the Estimated Static Loads

The Naval Nose Landing Gear (NLG) structural assembly consists of components with complex structural geometry and critical functionalities. The landing gear components are subjected to high static and dynamic loads, so they must be appropriately designed, dimensioned, and made by materials with mechanical characteristics that meet high strength, stiffness, and less weight requirements. This article contributes to the shape, size, and material optimization for the NLG of a supersonic naval aircraft for the estimated static loads. The estimated modal frequency values of the NLG assembly using Finite Element Analysis (FEA) software were compared with available Ground Vibration Test data of an aircraft to literally prove the accuracy and suitability of finite element (FE) model that can be used for any further analysis. Static structural analysis was performed for the critical landing load cases, and the Reserve Factor (RF) values of the landing gear components were calculated to determine their static strength capacity. Iterations including shape, size, and material optimization were done in the NLG to reduce the mass with the required strength characteristics.