Thermal Structural Design And Optimization Of A Composite Wing On Hign Supersonic Aircraft

High supersonic plane as an important developing direction of aviation industry plays an important role on national defense security.Hypersonic technology has become a national strategy that many powerful nation in aviation military attache great importance to.A high supersonic wing panel with corrugated plate structure is chose as the research object.Because the Mach number of this high supersonic aircraft while cruising is 3.0,serious aerodynamic heating problems arise in the flight phase.Thermal load in the supersonic aircraft structural design must be concerned in the structural design.By using numerical simulation technology,the wing pannel is verified to alleviate the thermal stress on the arrangement direction.It is verified that the corrugated skin structure can effectively reduce the nodal force on the arrangement direction.In order to reduce the structural weight,while thermal buckling eigenvalue is set as constraint,the response surface optimization algorithm code writed by the python is developed to make a structure optimization design to the geometric parameters of corrugated plate.The optimized model’s structural weight compared with the initial wing panel model is reduced by 18.4%.Composite materials have an advantage of lighter weight,higher strength and stiffness.A composite structure can significantly reduce the weight of the wing panel.T300/KH-304 is chose according to the load condition and the working temperature on the wing box.Based on the optimized metal model,a composite wing panel is established to be studied.The thickness of the composite layer is optimized to further reduced the wing structural weight while meeting the requirements of stability.The number of each layer with different angle is obtained.The thermal buckling load of the wing panel is improved after the stacking-sequence is optimized with genetic algorithm.In the end,the static strength of this pannel is checked.