Abstract
A cellular-based evolutionary topology optimization scheme over a small curvature big contour wing surface is proposed for the design of an ultralight surface structure. Using this method, a ground-structure technique is first applied to obtain homogeneous mesh generation with a predefined weight value over the design domain. Secondly, the stiffener path’s description is guided by a modified map L system topology method that simulates the growth of the bionic branch, and the structural components are obtained by the specified searching method according to weights of the previous mesh vertexes. Thirdly, an optimal curved stiffener layout is achieved using an agent-based algorithm to create individual instances of designs based on a small number of input parameters. These parameters can then be controlled by a genetic algorithm to optimize the final design according to goals like minimizing weight and structural weakness. A comparison is implemented for long-span panel stiffener layout generation between an initial straight case and a bionic optimal case via our method, thereby indicating the significant improvement of the buckling loads by steering the stiffener’s path. Finally, this bionic method is applied to the wing box structure design and achieves remarkable weight loss at last.
Highlights
Solar-electrically powered fixed-wing unmanned aerial vehicles (UAVs), regarded as a substitute for satellites, have wide applications in communication, disaster relief, supervisory control, and so on.In order to obtain a larger lift-to-drag ratio and solar panel area, this vehicle usually has a high-aspect ratio wing, which requires a large size and very flexible wing-structure
Laminated composite structures with unidirectional glass or carbon fiber reinforced polymer (GFRP/CFRP) materials are usually used as a substrate and are connected together by a resin with solar cell modules to improve their strength and stiffness characteristics [1,2,3]
It is clearly seen that the bionic curved stiffeners increase the critical buckling loads are given in Table 3, and their detailed finite element analysis result are given in Figures 17 and
Summary
Solar-electrically powered fixed-wing unmanned aerial vehicles (UAVs), regarded as a substitute for satellites, have wide applications in communication, disaster relief, supervisory control, and so on. Engineering) concept that implemented to obtain required data for the light optimization uses pre-optimized lightweight structures to widen the design space through the development of various new lightweight solutions to determine the best type of structure [13,14]. These studies have established practical indirect strategies to simulate the characteristics of natural structures by changing their parameters to produce complex design solutions that are high performing, and novel and unexpected.
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