Method and device for dual-mode measurement of engine propellant flow in pulse working condition for fault identification

Abstract

The invention provides a self-feedback intelligent-fault-recognition pulse-working-condition engine propellant flow two-mode measurement device. A function realization auxiliary unit is used for cooperating with propellant flow measurement, and controlling a flowing pipeline of a propellant. A parameter detection module is used for measuring feature parameters of a propellant in a flowing process,and calculating out and deriving a propellant flow value through the feature parameters. A cylinder body support component includes an outer cylinder body and an inner cylinder body. The outer cylinder body is used for enclosing pressurized gas space. The inner cylinder body is used for storing the propellant. Peripheral components are used for ensuring propellant flow measurement stability performance. The cylinder body support component is connected with the function realization auxiliary unit through a propellant liquid discharging pipe. The propellant flows between the inner cylinder bodyand the function realization auxiliary unit through the propellant liquid discharging pipe. Flow measurement under a propellant pulse working condition is realized, the device has the characteristicsof two-mode measurement, good reliability, high stability, intelligent fault recognition and the like, and high-precision measurement requirements of engines on flow can be satisfied.

Description

technical field [0001] The invention relates to the technical fields of fault identification, sensor technology, measurement control, and high-precision flow measurement of a liquid rocket engine, in particular to a dual-mode measurement method and device for propellant flow of an engine under pulse working conditions for fault identification. Background technique [0002] The propellant flow directly reflects the performance parameters of the engine. Therefore, the propellant flow is an important detection index in the liquid rocket engine test process. At this stage, the propellant pulse flow rate of liquid rocket engines is widely measured by the volumetric tube method. The measurement accuracy is affected by the machining accuracy of the inner diameter of the volumetric tube. The volumetric tube is a slender cylindrical structure, and the high-precision machining of the inner diameter is relatively difficult. The density of the propellant is affected by external factors ...

AI Technical Summary

Problems solved by technology

The above system does not solve the problem of flow instability when the propellant is affected by external factors such as temperature and pressure

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