A ramjet engine and its combustion chamber performance evaluation method based on the ground direct connection test

Abstract

The invention discloses a performance evaluation method of a ramjet engine and a combustion chamber thereof based on a ground direct connection test, comprising: obtaining a test bench thrust-time curve, a flow parameter and a pressure parameter of a scramjet under the ground direct connection test working condition; Based on the above parameters, the airflow parameters of the engine combustion chamber inlet section and outlet section are obtained; based on the airflow parameters of the engine combustion chamber inlet section and outlet section, the performance evaluation parameters of the engine combustion chamber are obtained; based on the airflow parameters of the engine combustion chamber inlet section and outlet section before and after Simulate the intake port and exhaust pipe of the extended engine and evaluate the engine performance parameters. Only by carrying out a single ground direct connection test, and by measuring the thrust, flow parameters and pressure parameters of the test bench in real time, the real-time performance parameters of the engine and its combustion chamber can be obtained directly, providing a fast, real-time, effective evaluation method.

Description

technical field [0001] The invention relates to the technical field of solid rocket scramjet, in particular to a performance evaluation method of a ramjet and a combustion chamber based on a ground direct connection test. Background technique [0002] The research on solid rocket scramjet belongs to the frontier field of national defense technology. Compared with liquid scramjet, it has the advantages of simple structure, fast response and high reliability. It is one of the ideal power devices for future hypersonic cruise missiles. The structure diagram of solid rocket scramjet engine is as follows figure 1 As shown, its basic working principle is that the oxygen-poor solid propellant is self-sustained combustion in the gas generator, and the high-enthalpy fuel-rich gas generated is injected into the combustion chamber at the speed of sound or supersonic speed, and is compressed by the supersonic speed through the hypersonic inlet port and the isolation section. The flow is...

AI Technical Summary

Problems solved by technology

On the one hand, the current calculation of the cold flow internal resistance of the combustion chamber generally uses three-dimensional high-precision steady-state numerical simulation. One of the disadvantages is that it takes a long time. The real-time status of the engine combustion chamber

On the other hand, in the existing calculation of engine combustion chamber thrust, it is generally necessary to measure the thrust of the heater air test alone first, and then the total thrust of the test bench can be used to obtain the individual thrust of the combustion chamber. One of the disadvantages is that the heater air test cannot be guaranteed. The state of the heater is completely consistent with that of the direct connection test, which leads to invalid test data. Second, the heater flow rate generally fluctuates in a small range during the direct connection test of the engine. In other words, the error that can be caused is relatively large, so it is the most accurate to process the test data if the heater thrust during the test can be used

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