一种机载超燃冲压发动机压力测量系统

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一种机载超燃冲压发动机压力测量系统

本发明提供了一种机载超燃冲压发动机压力测量系统，主要包括电子压力扫描阀、压力采集控制模块、背压装置和绝压传感器；背压装置为电子压力扫描阀7和8提供参考压力；绝压传感器采集背压装置的压力，电子压力扫描阀的输出信号至压力采集控制模块；所述背压装置由绝压传感器接嘴、背压装置筒和不透钢管组成；背压装置筒里面密封一个当地大气压或抽成真空；绝压传感器接嘴一端连接背压装置筒，另一端连接绝压传感器；不锈钢管一端连接背压装置筒，另一端通过测压管路连接到电子压力扫描阀。本发明体积小，重量轻、精度高，有助于提高有效载荷在飞行器结构中所占比重，为高超声速自主飞行提供一种有效的压力测量手段。

Pressure measuring system for airborne scramjet engine

The invention provides a pressure measuring system for an airborne scramjet engine. The pressure measuring system mainly comprises electron pressure scanning valves, a pressure collecting control module, a backpressure device and an absolute pressure sensor. The backpressure device provides reference pressure for the electron pressure scanning valves 7 and 8. The absolute pressure sensor collects the pressure of the backpressure device. The electron pressure scanning valves output signals to the pressure collecting control module. The backpressure device is composed of an absolute pressure sensor connector, a backpressure device tube and a stainless steel tube. One local atmospheric pressure is sealed in the backpressure device tube, or the backpressure device tube is vacuumized. One end of the absolute pressure sensor connector is connected with the backpressure device tube, and the other end of the absolute pressure sensor connector is connected with the absolute pressure sensor. One end of the stainless steel tube is connected with the backpressure device tube, and the other end of the stainless steel tube is connected to the electron pressure scanning valves through a pressure measuring tube. The pressure measuring system for the airborne scramjet engine is small in size, low in weight and high in precision, can better improve the proportion of effective loads in an aircraft structure, and provides an effective pressure measuring means for hypersonic autonomous flight.