Abstract
At present, there is little consideration for the overall performance when optimizing the aerodynamic configuration design for hypersonic vehicles. This paper proposes a novel approach for integrated optimal design of overall performance and aerodynamic configuration, taking aerodynamic configuration and overall performance constraints into consideration. First, a geometric parametric model of hypersonic vehicles was established using the quadratic curve method, and three overall performance parameters (aerodynamic properties, volume ratio, and operational stability) of hypersonic vehicles were calculated by engineering estimation. Then, key geometric parameters affecting aerodynamic properties, volume ratio, and operational stability were determined based on parameter influence analysis. Based on that, the aerodynamic configuration optimal for the hypersonic vehicle was achieved using a computational fluid dynamics-based surrogate model optimization method with overall performance parameters as constraints. Finally, the accuracy of an engineering estimation approach and the effectiveness of the optimal design method used were verified by wind tunnel tests. This study provides effective technical means for aerodynamic configuration optimization for hypersonic vehicles.
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