The invention provides a hypersonic waverider precursor-inward rotation type air inlet channel integrated design method which comprises the following steps: step 1, designing and obtaining an internal compression reference flow field based on a given air inlet channel inlet design working condition; 2, designing and obtaining an external compression reference flow field based on a given free incoming flow design working condition; step 3, performing viscosity correction on the reference flow fields obtained in the step 1 and the step 2 to obtain a corrected axisymmetric configuration and a non-viscous flow field corresponding to the corrected configuration; 4, designing and obtaining a waverider precursor based on the external compression reference flow field obtained in the step 2 and the non-viscous external compression reference flow field corrected in the step 3; and 5, based on the internal compression reference flow field obtained in the step 1, the non-viscous internal compression reference flow field corrected in the step 3 and the waverider precursor obtained in the step 4, designing to obtain a hypersonic waverider precursor-inward turning type air inlet channel integrated configuration. The aerodynamic performance of the hypersonic waverider front body-inward turning type air inlet channel integrated structure can be effectively improved through the hypersonic waverider front body-inward turning type air inlet channel integrated structure.

    本发明提出一种高超声速乘波前体‑内转式进气道一体化设计方法,包括如下步骤:步骤1:基于给定进气道入口设计工况,设计获得内压缩基准流场;步骤2:基于给定自由来流设计工况,设计获得外压缩基准流场;步骤3:对步骤1和步骤2获得的基准流场进行粘性修正,获得修正后的轴对称构型和相对应修正构型的无粘流场;步骤4:基于步骤2获得的外压缩基准流场和步骤3修正后的无粘外压缩基准流场,设计获得乘波前体;步骤5:基于步骤1所得内压缩基准流场、步骤3修正后的无粘内压缩基准流场和步骤4所得乘波前体,设计获得高超声速乘波前体‑内转式进气道一体化构型。本发明能够有效提高高超声速乘波前体‑内转式进气道一体化构型的气动性能。


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    Titel :

    Integrated design method of hypersonic waverider front body and inward turning type air inlet channel


    Weitere Titelangaben:

    一种高超声速乘波前体-内转式进气道一体化设计方法


    Beteiligte:
    QU FENG (Autor:in) / FU JUNJIE (Autor:in) / SUN DI (Autor:in) / ZHAO QIAN (Autor:in)

    Erscheinungsdatum :

    2024-04-02


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    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 / G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung



    Dual Waverider Concept for the Integration of Hypersonic Inward-Turning Inlet and Airframe Forebody

    You, Y. / Zhu, C. / Guo, J. et al. | British Library Conference Proceedings | 2009


    OSCULATING INWARD TURNING CONE WAVERIDER/INLET (OICWI) DESIGN METHODS AND EXPERIMENTAL STUDY

    Xuzhao, H. / Jialing, L. / Zheng, Z. et al. | British Library Conference Proceedings | 2012




    Aircraft fore-body and internal waverider-derived hypersonic inlet integrated design method

    LI YIQING / YOU YANCHENG / TENG JIAN et al. | Europäisches Patentamt | 2015

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