The invention belongs to the field of aircraft design, and particularly relates to a combined power spray pipe air-entraining type throat adjusting mechanism and an aircraft with the same. A turbine front adjusting plate (7) and a turbine rear adjusting plate (8) are combined to form a nozzle throat, the turbine front adjusting plate (7) is arranged above the rear end of a turbine engine (4) at the abdomen of a fuselage, one end of the turbine front adjusting plate (7) is hinged to the fuselage, the other end of the turbine front adjusting plate (7) overhangs backwards to form a first cantilever tail end, one end of the turbine rear adjusting plate (8) is hinged to the tail of the aircraft, and the other end of the turbine rear adjusting plate (8) overhangs forwards to form a second cantilever tail end. An air entraining channel (10) capable of being opened and closed is formed between the tail end of the first cantilever and the tail end of the second cantilever, at least one of the turbine front adjusting plate (7) and the turbine rear adjusting plate (8) is connected with a driving mechanism so as to drive the turbine front adjusting plate (7) and/or the turbine rear adjusting plate (8) to deflect, and then the opening section of the air entraining channel (10) is adjusted. The temperature of the spray pipe rear adjusting plate can be reduced, the structure is simple, and implementation is easy.

    本申请属于飞机设计领域,特别涉及一种组合动力喷管引气式喉道调节机构及具有其的飞机。由涡轮前调板(7)、涡轮后调板(8)组合形成喷管喉道,涡轮前调板(7)设置在机身腹部的涡轮发动机(4)后端上方,一端与机体铰接,另一端向后悬伸形成第一悬臂末端,涡轮后调板(8)一端铰接飞机尾部,另一端向前悬伸形成第二悬臂末端,第一悬臂末端与第二悬臂末端之间形成能够开闭的引气通道(10),涡轮前调板(7)与所述涡轮后调板(8)中的至少一个连接有驱动机构,以驱动涡轮前调板(7)和/或所述涡轮后调板(8)偏转,进而调节所述引气通道(10)的开口截面。本申请能够降低喷管后调节板的温度,结构简单,易于实现。


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    Titel :

    Combined power spray pipe air-entraining type throat adjusting mechanism and airplane with same


    Weitere Titelangaben:

    一种组合动力喷管引气式喉道调节机构及具有其的飞机


    Beteiligte:
    WANG JUNWEI (Autor:in) / WANG XIAO (Autor:in) / ZHU WEI (Autor:in) / HUA ZHENGXU (Autor:in) / ZHANG CHENLIN (Autor:in)

    Erscheinungsdatum :

    29.12.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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