The Stability Analysis And Optimization Design Of Skin Honeycomb Core Plate Structure

Intelligent variant technology has become the research hotspot in the field of aerospace, deformation of wing skin technology is one of the most critical parts,also because of its structural characteristics and ability to adapt to the demanding requirements of flying environment,makes it become a technical difficulty. From the early traditional hard skin with squamous fold type to the current composite material skin structure, skin deformation technology is towards the direction of composite material structure. With the widely application of the honeycomb sandwich structure,the excellent characteristics of the structure performance is more and more prominent. At this point,the concept of flexible mechanism was introduced to the design of the aircraft’s honeycomb sandwich structure, the super elastic skin structure based on the flexible honeycomb structure was proposed,the topology structure of the flexible honeycomb core and size parameters effect on the general properties of the super elastic skin structure was studied. This paper systematically analyzed the honeycomb sandwich plate structure’s domestic and foreign research status and developing trend, gave a preliminary study of the honeycomb sandwich panel structure’s mechanical properties and stability.With the variant aircraft fuselage structure design’s honeycomb core structure to be the research object, based on the Gibson formula and Euler beam theory, in satisfying the aerodynamic characteristics of achieving the wing’s continuous variation, the flexible structure of the honeycomb core parameter optimization model was set up. With the help of intelligent algorithm, specific honeycomb core unit’s selection parameters was designed with multi-objective optimization, the influence law of different structure of the honeycomb core’s selection parameters on the in-plane deformation capacity was got,the selection of the skin structure of the honeycomb core was analyzed, and the deformation drive scheme design of the honeycomb core board structure was carried out.Attention is concentrated as follows:1. The technology of adaptive wing and research status of the honeycombcomposite materials was introduced and summarized,the source and researchsignificance of the thesis was expounded. 2. The free vibration and stability of the honeycomb sandwich structure was analyzed, the bending balance equation and buckling equation of the core board structure was obtained.3. Under the premise of meeting the aerodynamic characteristics of the wing’s continuous variation,the boundary conditions and objective function of the flexible honeycomb core structure’s parameter optimization model was determined,the mathematical model of the honeycomb core structure parameter optimization was given.4. With the help of Genetic algorithm, specific honeycomb core unit’s selection parameters was designed with multi-objective optimization, the influence law of different structure of the honeycomb core’s selection parameters on the in-plane deformation capacity was got,and the selection of the skin structure of the honeycomb core was analyzed.5. Based on the theory and simulation research, the structure design of the flexible honeycomb core elastic skin was carried out.The wing’s skin structure driven design based on the positive and negative poisson’s ratio of honeycomb core board combination was brought up.