The invention belongs to the field of helicopter fuselage structure strength design, and discloses a tail structure strength design method, and high horizontal tail asymmetric load and vertical tail gas dynamic load distribution have multiple combination states. The tail structure comprises the tail beam and the vertical fin, and different from a traditional design thought, during strength designof the vertical fin and the tail beam, the influence of torque generated by asymmetric loads of the horizontal fin on the strength of the vertical fin and the tail beam is considered, and potential safety hazards, caused by the influence of the asymmetric loads of the horizontal fin, of the tail beam and the vertical fin in the flying process are eliminated.

    本发明属于直升机机身结构强度设计领域,公开了一种尾部结构的强度设计方法,高置平尾非对称载荷与垂尾气动载荷分布存在多种组合状态。尾部结构包含尾梁和垂尾,在垂尾和尾梁的强度设计时,与传统的设计思路不同的是考虑平尾非对称载荷产生的力矩对垂尾及尾梁强度的影响,排除由于平尾非对称载荷影响导致尾梁及垂尾在飞行过程中存在的安全隐患。


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    Titel :

    Tail structure strength design method


    Weitere Titelangaben:

    一种尾部结构的强度设计方法


    Beteiligte:
    YANG CHAN (Autor:in) / ZHA DINGPING (Autor:in) / LYU LEFENG (Autor:in) / WANG YING (Autor:in) / TIAN ZHONGQIANG (Autor:in) / XU CHENGCHENG (Autor:in) / JIAN CHENGWEN (Autor:in)

    Erscheinungsdatum :

    2021-01-05


    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



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