The invention relates to an aircraft active load reduction structure based on a cavitator. A gas injection flow channel is designed in the head of an aircraft, and gas flow injection holes are designed in the outer side face of the aircraft. A cavitator is designed at the top end of the head of the aircraft, the cavitator is of a disc-shaped structure with an acute angle edge, and ventilation is conducted through airflow jet holes behind the acute angle structure to form supercavitation bubbles surrounding an object. A gas injection on-off valve is located behind the interior of the head of the aircraft, is connected with an injection flow channel and a high-pressure gas bottle and is directly controlled by an aircraft gas injection control system to control on-off of air flow. And the high-pressure gas cylinder is positioned at the rear part of the gas injection on-off valve and stores all high-pressure gas required for generating the supercavity. High-pressure compressed air serves as a ga source, and compared with fuel gas injection load reduction, the system is more compact and smaller and is more suitable for being applied to small and medium-sized underwater vehicles.
本发明涉及一种基于空化器的航行器主动降载结构,航行器头部内部设计有气体喷射流道,外边面设计有气流喷射孔。航行器头部的顶端设计有空化器,空化器为一个带锐角边缘的圆盘状结构,在锐角结构之后通过气流喷射孔通气,可形成包围物体的超空泡。喷气通断阀位于航行器头部内的后方,连接着喷射流道和高压气瓶,受航行器喷气控制系统的直接控制,控制着气流的通断。高压气瓶位于喷气通断阀的后部,储存着产生超空泡所需要的全部高压气体。本发明以高压压缩空气作为气源,相比于燃气喷气降载,系统更为紧凑小巧,更适合应用于中小型水下航行器。
Aircraft active load reduction structure based on cavitator
一种基于空化器的航行器主动降载结构
26.06.2020
Patent
Elektronische Ressource
Chinesisch
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