Structural Optimization Design Of Composite Wing With Large Aspect Ratio

The high-aspect ratio wing is the main component of long-endurance high-altitude aircraft.Wing is the main part of aircraft to generate lift force,whose weight occupies a large proportion in the aircraft structure weight.Wing performance directly affects the overall performance of the aircraft.The use of designable composite materials in the structure can effectively reduce the weight of the wing structure and improve some performance of the wing.Based on finite element model,the structural design optimization method of a high-aspect ratio composite wing is studied in this paper.The main contents are as follows:1)The design plan of high-aspect ratio composite wing was studied,and the calculation method was determined according to its characteristics.According to the empirical formula,the overall plan of the wing was determined,the aerodynamic model and the structural model were parameterized,the weight of the wing structure was estimated according to the empirical formula,the loading method of the aerodynamic loads on the structure was studied,and the flow model of the aerodynamic structure for the high-aspect ratio wing was built by Isight software.2)The feasibility of applying the equivalent method of composite stiffened plate in the design of high-aspect ratio wing structure was studied.The equivalent method of composite stiffened plate and application in finite element model was studied,the accuracy of equivalent stiffness finite element model in static analysis,modal analysis and flutter analysis was verified,the improvement of the efficiency of optimization calculation by using equivalent stiffness finite element model was confirmed.3)Combined with aerodynamics,structure and other disciplines,the structure optimization platform of high-aspect ratio composite wing was established to rapidly calculate wing performance.The structure optimization of a high-aspect ratio composite wing was carried out to make the wing meet the constraints of statics,dynamics and aeroelasticity,and reduce the weight of the wing structure.