Solid rocket engine propellant combustion speed measuring method and device

Abstract

The invention discloses a solid rocket engine propellant combustion speed measuring method and device. Firstly, when the axial combustion speed is measured, intermediate frequency signals obtained after frequency mixing of incident signals and reflected signals are analyzed through the Doppler effect, so that the axial combustion speed of a propellant is calculated, the round-trip time of electromagnetic waves in the propellant does not need to be considered, measurement errors are reduced to a large extent, and measurement precision is improved; and secondly, the axial combustion speed and transverse combustion speed of the solid propellant can be measured at the same time, when the transverse combustion speed of the propellant is measured, inversion imaging is conducted on the internal combustion condition of a rocket engine in combination with tomography, the transverse pushing distance of the propellant is obtained, and therefore the transverse combustion speed of the propellant is obtained through calculation, the purpose of multi-layer detection is achieved, the cost can be reduced, and the dynamic, rapid and accurate measurement of the combustion speed of the propellant of the solid rocket engine is realized.

Description

technical field [0001] The invention belongs to the measurement field of solid rocket motors, in particular to a method, a device, a computing platform and a computer-readable storage medium for measuring the burning rate of propellants of solid rocket motors. Background technique [0002] Solid rocket motor technology is the core technology of space launch and missile weapons. The combustion characteristics of solid propellants affect the flight speed and range of the rocket. The burning rate of the combustion surface is the core parameter to characterize the internal ballistic performance of the engine, and it is also a key indicator that needs to be strictly controlled in the design and production of propellant formulations. Therefore, the calculation of the lateral burning rate and axial burning rate of solid propellants is of great significance for discovering the essential laws of propellant combustion, improving the reliability and safety of solid rocket propellant co...

AI Technical Summary

Problems solved by technology

Among them, the target line method and the acoustic emission method can only test the average burning rate under a specific pressure; the optical camera dynamic burning rate test is affected by the smoke deposition when the propellant burns. The observability needs to be filled with nitrogen flow, and the X-ray imaging equipment is huge and radioactive. Limited ultrasound penetration and long measurement times

The time resolution of these methods is low, it is difficult to achieve dynamic real-time measurement of the combustion area, and it is impossible to fully reproduce the entire combustion process, and it is impossible to achieve multi-level detection of the propellant burning rate. The calculation process is relatively complicated, and the overall equipment The cost is high, and there is a large error in the calculated propellant burning rate

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