A framework for unconventional landing gear configuration modelling

In this paper a methodology is presented for the assessment of conventional and unconventional landing gear configurations. A data model is implemented with the aircraft as top-level entity. On that basis the landing gear with its components, the wing and fuselage are described in relation to each other. One focus of the framework is the structural integration of the landing gear into the wing or eventually fuselage structure for possible future aircraft configurations. Therefore, parametrical structural models of the landing gear, wing and fuselage are set up. Each of these three parts demands a preliminary sizing of the structure for the nominal load cases as the effect of landing gear integration can only be assessed afterwards. The proposed method is able to set up models for landing gears and the surrounding aircraft structure to examine the integrational aspects and the effect on the landing gear and aircraft structural mass. A first case study for a fuselage integrated landing is presented, which shows a weight reduction of ~28% compared to a conventional landing gear configuration on landing gear level. First fuselage integration possibilities are discussed as outlook for future studies.