Optimization Of A UAV Composite V-tailstructure

The development prospect of UAV in the modern war field is very broad, due to its wide use, low cost, good cost-effective, zero casualty risk, tenacious survival ability, the advantages of good mechanical performance, convenient use and so on.Advantages and disadvantages of aircraft performance are largely determined by the good or bad design of tail structure, which also has great influence on the result of the whole machine pneumatic elastic quality and fatigue fracture performance. At present, V tail has been paid great attention, because of its stealth ability, considerable weight loss and the low flight resistance.Advanced UAV tail usually uses composite materials overall. First of all, the structure design of a tail contains the layout optimization. Then for the design of composite materials, more design variables which involve the continuous variables and the discrete ones should be considered. All the questions above increase the difficulty in this composite optimization problem.Focusing on the question of the structure optimization of V type composite wing studied in this paper, its stress characteristic was analyzed firstly, and then the preliminary size was designed based on the strength and stiffness criteria. Finishing choosing material, loading and designing layers, the finite element software was utilized to evaluate the mechanical performance index of the initial structure. After that the selected optimization of panels with different length to width ratio was researched, which provides the guidance for the whole structure optimization. Finally, four kinds of design schemes for the panel structure were put forward respectively, and each scheme was designed to reduce weight. Considering the questions that the stiffened panel design contained too much constraints and involved the structural parameters, a comprehensive optimization method of stiffened panel was put forward. This method combined the engineering experience and the finite element, grading the design of strength and stability. To end with, The results of comprehensive optimization method presented in this paper agree with those of traditional finite element methods well, and the panel selection have the same result with the selection of panels with different length to width ratios.