The invention belongs to the technical field of aircraft structure design, and particularly relates to a supersonic shock wave nozzle decompression device. The rear end of the device is detachably installed at a supersonic shock wave nozzle, fuselage shielding nozzles (3) and lateral expansion nozzles (4) are arranged on the pipe wall of the supersonic shock wave nozzle pressure reducing device, at least one fuselage shielding nozzle (3) is located on the side, close to an aircraft fuselage, of the supersonic shock wave nozzle pressure reducing device, and the lateral expansion nozzles (4) are located on the pipe wall of the supersonic shock wave nozzle pressure reducing device. The lateral expansion nozzle (4) and the fuselage shielding nozzle (3) are arranged at an interval in the circumferential direction of the pipeline at a set angle, the lateral expansion nozzle (4) and the fuselage shielding nozzle (3) are each provided with an airflow channel (1), and the airflow channels (1) are located at the rear end of the supersonic shock wave nozzle decompression device and communicated with the internal pipeline of the supersonic shock wave nozzle decompression device. The airflow channel (1) is provided with an opening expanding outwards at the rear end of the supersonic shock wave nozzle decompression device. The pressure impact strength of the fuselage side is reduced, and the safety of the fuselage structure and the equipment compartment is guaranteed.
本申请属于飞机结构设计技术领域,特别涉及一种超声速冲击波喷口减压装置。该装置后端可拆卸安装在超声速冲击波喷口处,超声速冲击波喷口减压装置的管壁上设置有机身屏蔽喷嘴(3)及侧向扩张喷嘴(4),其中,至少一个机身屏蔽喷嘴(3)位于超声速冲击波喷口减压装置靠近飞机机身的一侧,侧向扩张喷嘴(4)与机身屏蔽喷嘴(3)沿管道的周向方向间隔设定角度,侧向扩张喷嘴(4)与机身屏蔽喷嘴(3)均具有气流通道(1),气流通道(1)在超声速冲击波喷口减压装置后端与其内部管道联通,气流通道(1)在超声速冲击波喷口减压装置后端具有向外扩张的开口。本申请降低了机身侧的压力冲击强度,保证了机身结构及设备舱的安全。
Supersonic shock wave nozzle decompression device
一种超声速冲击波喷口减压装置
2024-03-15
Patent
Electronic Resource
Chinese
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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