Aerodynamic configuration optimization of a Common Aero Vehicle (CAV) is investigated. A new blended wing-body configuration of CAV is generated by conic lofting design method. The geometry of CAV is parameterized in terms of conic control points and shape parameters. The revised Newtonian Theory and the One-order Panel Method are applied to hypersonic aerodynamic predictions. The aerodynamic configuration is optimized with respect to lift-to-drag ratio and volumetric efficiency given the constraint of longitudinal stability. Pareto solutions are generated by Multi-objective Genetic Algorithm based on niche technique. Combining Physical Programming method with the robust and effective Particle Swarm Optimization Algorithm, the tradeoff Pareto solution of multi-objective optimization can be evaluated effectively. The optimization results indicate that the presented method of CAV configuration design is effective.%研究了通用航空飞行器气动布局设计优化问题.应用基于二次曲线的模线设计方法,实现了通用航空飞行器的参数化外形建模.采用修正的牛顿流理论进行高超声速气动特性计算.在保持纵向稳定性的条件下,以升阻比和容积效率最大化为目标,建立通用航空飞行器气动布局多目标优化模型.应用基于小生境竞争排挤机制的多目标遗传算法求得优化模型的非劣解集.将物理规划设计方法与稳定、高效的粒子群优化算法相结合,有效地求解该优化模型的折衷解.优化结果表明本文的通用航空飞行器气动布局设计优化方法是有效的.
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