Fuselage Components Layout And Topology Design Of Flapping Wing Micro Air Vehicle

In recent years Flapping Wing Micro Air Vehicle(FWMAV)has become a research hotspot at home and abroad as a new research field.To improve the flight performance of a bionic flapping wing aircraft and to achieve a lightweight design with high integration and high stability,the formulation dealing with the layout and topology optimization design of the multi-component structure fuselage in the bionic micro flapping wing vehicle is proposed.In order to solve this problem,this paper proposes a multi-component structural system layout and topology optimization design method,which includes an explicit description model of embedded component contour and a material interpolation scheme of multi-component structural system.By employing the proposed method,the layout and topology optimization design of the multi-component structure fuselage in FWMAV are solved.The main work and innovation of this work are as follows:Firstly,in order to avoid the redundant and complex description form of mobile embedded components in the multi-component structure system in previous works,this work proposes an explicit description model of movable embedded components contour.This model can accurately represent the geometric and embedded position information of components with general or complex shapes by using P-norm equation and aggregate function form.Then,based on the classical SIMP material interpolation scheme,the sigmoid function and the explicit description model of component contour are used to define a smooth and continuous unified standard material interpolation model in the multi-component structure system.The model can reflect the actual situation of the rigid connection with different materials,which provides a preliminary basis for the layout optimization and topology optimization design of multi-component structure system.Secondly,according to the methods mentioned above,this paper proposes a minimum flexibility optimization model for the multi-component structural systems layout and topology optimization.In this optimization model,the non-overlapping constraints is described by single explicit equation,which effectively reduces the number of constraints.Then the sensitivities of design variables to objective functions and constraints are derived respectively.On this basis,the optimization process and algorithm implementation of the problem are designed.Several numerical cases studies are carried out using MATLAB to verify the efficiency and applicability of the method.Finally,in order to improve the comprehensive mechanical properties of the micro flapping wing vehicle system and achieve the lightweight design with high integration and high stability,the method proposed in this paper is applied to a FWMAV prototype which consists of a multi-component fuselage structure system and a flapping wing mechanism by introducing a system centroid constraint.Combined with the mechanical data provided by the experimental platform of the micro flapping wing vehicle,the optimization results under different system centroid constraints are comparative analyzed.The influence of introducing the system centroid constraint on the optimization process and results is discussed.It is verified that this method can effectively improve the performance of the fuselage multi-component structure system and accurately design the centroid position of the aircraft.