Verification of flutter method for the purposes of building a very flexible wing generative model

First step of aircraft design is calculation of initial parameters, based on assumptions determining flight parameters which designed aircraft should meet. During these calculations, it is possible to pre-detect structure instability called a flutter. These calculations are made based on the geometric parameters assumed in the first conceptual drawings of the flying vehicle. Assumed masses and speeds allow for preliminary analysis of forces acting on the structure. The next step is to determine the displacements and deformations occurring in the structure of the aircraft in different phases of flight and under different conditions. The article presents all the stages of wing analysis for a proposed stratospheric drone with a highly flexible wing structure. This analysis, after integration with CAD software, will allow for the preparation of a comprehensive generative model. The basic assumptions of the designed aircraft are: flight altitude, wings area, very extended or unlimited flight time, approximate flight speed, climbing time, hull parameters, rudder size and placement, wing profile and mass of the structure. These assumptions made it possible to carry out a preliminary analysis of loads, wing pressure distribution, lift force and total resistance force. The goal of the research is to develop a methodology of preliminary flutter analysis which can be easily integrated in the form of calculation backgound for generative model. This methodology has been developed to determine displacements, structure stability and critical vibration frequencies. CAD software after integration with constantly optimizing calculation software will allow the generation of optimal shape and structure rigidity for given initial assumptions.