The invention belongs to the technical field of vibration design of aircraft launching tubes, and particularly relates to a tube opening bias flow device for a unilaterally-perforated airborne launching tube. The unilaterally-perforated airborne launching pipe orifice bias flow device is mounted at the position of an airborne launching pipe orifice and provided with a pipeline concentric with the airborne launching pipe orifice so that a launcher can penetrate through the pipeline, a plurality of flow guide holes are formed in the single side of the unilaterally-perforated airborne launching pipe orifice bias flow device, and the flow guide holes are communicated with the airborne launching pipe orifice. The inclination degrees of the front side pipe wall and the rear side pipe wall of each flow guide hole side wall are different, the front side of each flow guide hole side wall refers to the side far away from the pipe opening of the airborne launching pipe, and the rear side of each flow guide hole side wall refers to the side close to the pipe opening of the airborne launching pipe. According to the unilaterally-perforated airborne launching tube opening bias flow device, flow guide and pressure reduction can be conducted on a flow field in a launching tube opening area, the pressure of the flow field and distribution of shock waves in space are changed, the shock waves and the pressure amplitude near an aircraft equipment cabin are reduced, and therefore the influence of the flow field on fuselage skin and nearby equipment is reduced.

    本申请属于飞机发射管振动设计技术领域,特别涉及一种单侧开孔机载发射管管口偏流装置。所述单侧开孔机载发射管管口偏流装置安装在机载发射管管口处,并具有与所述机载发射管管口同心的管道,以供发射物穿过,所述单侧开孔机载发射管管口偏流装置在单侧设置有多个导流孔,各所述导流孔侧壁的前侧与后侧管壁倾斜度不同,其中,所述导流孔侧壁的前侧是指远离机载发射管管口处的一侧,所述导流孔侧壁的后侧是指靠近机载发射管管口处的一侧。本申请单侧开孔机载发射管管口偏流装置可以对发射管管口区域流场进行导流、减压,改变流场的压力、冲击波在空间的分布,降低飞机设备舱附近的冲击波及压力幅值,从而降低流场对机身蒙皮和附近设备的影响。


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    Titel :

    Bias flow device for pipe orifice of unilaterally-perforated airborne transmitting pipe


    Weitere Titelangaben:

    一种单侧开孔机载发射管管口偏流装置


    Beteiligte:
    WANG YONGQING (Autor:in) / ZHAO MINGSHENG (Autor:in) / ZHOU DONG (Autor:in) / CHEN ZHONGMING (Autor:in) / LI SHUO (Autor:in)

    Erscheinungsdatum :

    2024-01-19


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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