Preliminary Design of the Landing Gear for a CESTOL Aircraft FAR 23

Abstract

Objective: Design the landing gear for a CESTOL type aircraft according to FAR 23 using: (i) the conceptual designs of the nose and main gear and (ii) evaluate the structural strength of the design by means of finite element analysis at a stage of landing. Materials and methods: The initial requirements for the theoretical development of a preliminary landing gear design are used as a case study. The aircraft’s structure is taken as a base for the different design stages. This analysis is according to a static and level landing condition selected on each gear with a side and supplementary load. Additionally, calculations of geometric parameters and mechanical resistance with preselecting materials for the component analysis to determine and compare theoretical results with finite elements to evaluate the reliability of the design approach. Results and discussion: It is determined to move the main landing gear backward near the cargo area. That allows for better aircraft performance, placing the GC in front of the main gear and avoiding an overturn. However, this load percentage changes in proportion to the longitudinal stability criterion, where it generates an increase in the contribution to the mechanical stress in the structure of the gear. Conclusions: Results obtained about stability, controllability, and structural analysis are acceptable for the regulations of FAA Part 23 with standards associated with airworthiness, being corroborated with theoretical analysis and combined loads.