基于后缘线等激波强度楔导乘波舵机鼓包设计方法,以鼓包迎风面后缘线作为设计输入,通过在鼓包迎风面各个纵向截面设置相同的楔角,实现各个纵向截面激波强度相同的设计构想,即实现舵机鼓包迎风面纵向激波沿横向等激波强度设计,与此同时,在楔形流场进行流线追踪生成各条鼓包迎风面流线,楔形流场流线放样生成的鼓包迎风面可以实现激波附体,从而减小气动阻力。本发明由鼓包迎风面后缘线向前生成一种各个纵向截面激波强度相同、力热载荷特性分布均匀、迎风面激波附体的楔导乘波舵机鼓包,并将楔导乘波舵机鼓包与乘波体机身进行一体化设计,从而进一步减小舵机鼓包与乘波体机身组合体的阻力。

    Based on a trailing edge line equal shock wave intensity wedge-guided waverider steering engine bump design method, a bump windward side trailing edge line serves as design input, and the design idea that the shock wave intensity of each longitudinal section is the same is achieved by setting the same wedge angle on each longitudinal section of a bump windward side; the design of equal shock wave strength in the transverse direction of longitudinal shock waves of the bump windward side of the steering engine is achieved, meanwhile, streamline tracking is conducted in the wedge-shaped flow field to generate all bump windward side streamlines, the bump windward side generated through wedge-shaped flow field streamline lofting can achieve shock wave appendages, and therefore aerodynamic resistance is reduced. According to the wedge-guided waverider steering engine bump, the wedge-guided waverider steering engine bump with the same longitudinal section shock wave strength, uniform force thermal load characteristic distribution and a windward side shock wave appendage is generated forwards from the trailing edge line of the windward side of the bump, and the wedge-guided waverider steering engine bump and a waverider body are integrally designed; therefore, the resistance of the steering engine bump and wave rider body assembly is further reduced.


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    Title :

    基于后缘线等激波强度楔导乘波舵机鼓包设计方法


    Publication date :

    2023-03-21


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    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 / B64C AEROPLANES , Flugzeuge