The invention provides a design method of a wave rider with a controllable three-dimensional leading edge line. A three-dimensional front body front edge line is specified according to the requirement of a supersonic aircraft, a generatrix after rotation of the three-dimensional front edge line serves as a shock wave boundary of an axis pair basic flow field, the shock wave boundary serves as input, and a characteristic line method is adopted to solve a corresponding axial symmetry basic flow field. Then, the three-dimensional front edge line is attached to the axial symmetry basic flow field, and a wave rider profile of the specified three-dimensional front edge line is obtained through streamline tracking from discrete points on the front edge line. The method overcomes the limitation of the wave rider on the three-dimensional space of the leading edge line, expands the design method of the wave rider, and is particularly suitable for some wave rider modeling schemes needing to adopt the three-dimensional leading edge line.
本发明提出了一种三维前缘线可控的乘波体设计方法。其依据超声速飞行器需求指定三维前体前缘线,通过将三维前缘线回转后的母线作为轴对基本流场的激波边界,将激波边界作为输入并采用特征线法求解出对应的轴对称基本流场。然后将三维前缘线贴合到轴对称基本流场中,从前缘线上的离散点出发,通过流线追踪的得到指定三维前缘线的乘波体型面。本发明克服了乘波体对前缘线的三维空间限制,扩展了乘波体的设计方法,特别适用于某些需要采用三维前缘线的乘波体造型方案。
Design method of wave rider with controllable three-dimensional leading edge line
一种三维前缘线可控的乘波体设计方法
2024-05-03
Patent
Electronic Resource
Chinese
IPC: | B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen |
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