The invention discloses a configuration for reducing air inlet total pressure distortion of an aircraft tail propulsion system and an aircraft, and belongs to the technical field of hybrid power design, the configuration comprises the tail propulsion system, a fuselage tail end located at the front part of the tail propulsion system and a plurality of airflow direction guiding devices located on the outer surface of the fuselage tail end, and the section of the airflow direction guide device along the fuselage direction is vertical to the outer surface of the tail end of the fuselage. According to the technical scheme, the arrangement scheme design that the airflow direction guiding device is adopted to reduce the air inlet total pressure distortion of the tail propelling system is adopted. The airflow direction guide device is arranged at the tail section of the fuselage in front of the tail propulsion system, and plays a role in disturbing and combing airflow which flows into the tail propulsion system after flowing through the fuselage, so that the total air inlet pressure distortion index of the tail propulsion system is reduced, and the requirement of flight safety for air inlet quality is met.

    本申请公开了一种降低飞机尾部推进系统进气总压畸变的构型和飞机,属于混合动力设计技术领域,所述构型包括:尾部推进系统、位于所述尾部推进系统前部的机身尾端以及位于所述机身尾端的外表面上的多个气流方向引导装置,其中,所述气流方向引导装置沿机身方向的截面垂直于所述机身尾端的外表面。本申请技术方案采用气流方向引导装置降低尾部推进系统进气总压畸变的布置方案设计。气流方向引导装置布置在尾部推进系统前方的机身尾段处,对流经机身后流入尾部推进系统的气流起到干扰梳理作用,帮助降低尾部推进系统的进气总压畸变指数,满足飞行安全对于进气品质的要求。


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    Titel :

    Configuration for reducing air inlet total pressure distortion of aircraft tail propulsion system and aircraft


    Weitere Titelangaben:

    一种降低飞机尾部推进系统进气总压畸变的构型和飞机


    Beteiligte:
    TAN JINGXUE (Autor:in) / WANG KAI (Autor:in) / ZHAO TIHAO (Autor:in) / SUN XUEWEI (Autor:in)

    Erscheinungsdatum :

    02.08.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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