The invention discloses a cross-medium aircraft liner drag separation device which is arranged between an aircraft and a power mechanism and comprises a circular mounting disc fixedly arranged on the bottom end face of the tail of the aircraft and an annular collecting groove formed in the top end face of the power mechanism and vertically corresponding to the circular mounting disc. A plurality of hot melting connecting columns are evenly distributed on the bottom end face of the circular mounting disc, and the bottom ends of the multiple hot melting connecting columns are fixedly connected to the bottom end face of the annular collecting groove. According to the device, when the aircraft is launched, the power mechanism generates strong hot air to melt the hot melting connecting column, reliable separation of the aircraft and the power mechanism in the experiment process of the cross-medium aircraft is achieved, and it is guaranteed that the launch test of the aircraft is conducted smoothly. Melted liquid is guided into a collecting groove formed in the side edge of the power mechanism through an annular collecting groove so as to be reused in the later period.
本发明公开了一种跨介质飞行器胆拖分离装置,所述胆拖分离装置设置在飞行器与动力机构之间,所述胆拖分离装置包括固定设置在飞行器尾部底端面的圆形安装盘以及设置在动力机构顶端面与圆形安装盘上下相对应的环形收集槽,所述圆形安装盘的底端面上匀布有若干热熔连接柱,若干热熔连接柱的底端固定连接在环形收集槽的底端面上。本发明中,在飞行器发射时,动力机构发生强力热空气,将热熔连接柱融化,实现了跨介质飞行器在实验过程中飞行器与动力机构的可靠分离,保证飞行器发射试验的顺利进行。融化后的液体通过环形收集槽导流到动力机构侧边设置的收集槽中,以便后期重复利用。
Liner drag separation device of cross-medium aircraft
跨介质飞行器胆拖分离装置
2024-11-29
Patent
Electronic Resource
Chinese
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