Experimental device for full-scale nozzle thermal structure of solid-propellant rocket engine

Abstract

The invention puts forward an experimental device for a full-scale nozzle thermal structure of a solid-propellant rocket engine. The experimental device provided by the invention comprises a full-scale nozzle, an experimental engine, a central cone and a central-cone support. Through the design on molded surfaces of a cylindrical section and a tapered section of the central cone, the experimentaldevice has the advantages of fully taking the influences of airflow erosion and high temperature in the experimental process into consideration, realizing that the operating characteristic of the full-scale nozzle in the experimental device is consistent with that of a nozzle in a full-scale engine, and realizing the mini-flow test on the full-scale nozzle, therefore, the experimental device can be used as a flexibly-applied common experimental way.

Description

technical field [0001] The invention belongs to the technical field of solid rocket motor experiments, in particular to an experimental device for the thermal structure of a full-scale nozzle of a solid rocket motor. Background technique [0002] For solid rocket motors, the thermal structure of the nozzle is related to the safety of the engine. How to pass the assessment of the thermal structure of the nozzle of the solid rocket motor is a very important and very complicated issue. At present, the theoretical methods for studying the thermal structure of the nozzle are not mature enough, and most of them are based on numerical simulation of the thermal structure of the nozzle, full-scale engine experiments and simulation tests. Due to many assumptions and simplifications, the numerical simulation research can only be used as a reference, and cannot provide specific quantitative support for the full-scale engine; the full-scale engine experiment period is long, costly, and t...

AI Technical Summary

Problems solved by technology

Due to many assumptions and simplifications, the numerical simulation research can only be used as a reference, and cannot provide specific quantitative support for the full-scale engine; the full-scale engine experiment period is long, costly, and the organization is cumbersome. The cost of organizing a full-scale engine experiment for this single experiment is too high, and if there is a problem, the impact will be bad; the simulation test is still immature, there is a size effect, and it is difficult to solve problems such as the mapping relationship with the full-scale engine

It can be seen that there is currently a lack of convenient, low-risk and low-cost experimental methods for full-scale assessment of the thermal structure of solid rocket motor nozzles

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