Aerodynamic Shape Optimization Of Hypersonic Vehicles

With the development of aerospace science and technology and the need of national defense science and technology, hypersonic technology has become the focus of attention of the every military power. And hypersonic technology has become the strategic high ground in the field of aerospace science and technology today, because of its unique advantages. In the preliminary design stage of a hypersonic vehicle, we need to optimize its aerodynamic shape quickly, in order to get an excellent optimization scheme. In this paper, a kind of hypersonic vehicle aerodynamic shape optimization program is developed, using genetic algorithm combined with panel method and free-form deformation techniques, to optimize the shape of a hypersonic vehicle. And the whole program is divided into the following three modules:(1) the parametric model, we can use FFD method to achieve the parameterization of aircraft model. Compared to traditional parametric method, FFD method can design parameters more easily, manipulate deformation more flexibility, reduce the difficulty of the parameterization significantly, and can be achieved easily by programming;(2) optimization algorithm module, in this paper, we choose genetic algorithm as the optimization, and introduce treatment methods of constraints, making it can be used in the optimization of aircraft aerodynamic shape;(3) the aerodynamic performance calculation module, the precision of numerical simulation method is high, but it’s time-consuming and inefficient, so in this paper, we select engineering method(panel method) to solve the aerodynamic performance of hypersonic vehicles, it can improve the efficiency of optimization greatly, And its precision can meet the requirements of the preliminary design stage of optimization. We integrate these three modules together to form a hypersonic vehicle aerodynamic shape optimization program. Just by entering the initial aircraft surface panel grid files, distributing control body, designing optimization parameters, and setting up the optimum conditions, we can optimize the aerodynamic shape of the aircraft. The accuracy of calculation meets the requirements of preliminary design, and it can provide favorable conditions for the subsequent fine optimization.