Reliability evaluation method of rocket engine nozzle movable joint structure

Abstract

The invention provides a method for evaluating the reliability of a rocket engine nozzle movable connection structure, which is characterized in that the method comprises the following steps: 1, designing a rocket engine nozzle movable connection structure; 2, carrying out high-altitude simulation commissioning on that condition of the rocket engine; 3, establishing a nozzle live connection reliability evaluation model; 4, carrying out load impact test on that nozzle movable connected simulator; 5, carrying out thermal cycle test on a nozzle movable connection simulator; 6, evaluating that reliability of the nozzle movable connection structure. The invention has the following advantages: 1) reducing the reliability test verification cost of the rocket engine; 2) shortening the developmentcycle of the rocket engine; 3) low-carbon emission reduction and green environment protection.

Description

Technical field [0001] The invention relates to the technical field of spacecraft propulsion systems, in particular to a method for evaluating the reliability of a rocket engine nozzle live connection structure. Background technique [0002] The engine is the heart of spacecraft such as launch vehicles and satellites, and provides power for the spacecraft to change its orbit and attitude. The nozzle is the core component of the rocket engine, which converts the heat energy of the high-temperature gas in the combustion chamber into kinetic energy, so that the engine generates thrust. In order to improve the performance of the rocket engine, it is usually necessary to increase the nozzle area ratio, that is, the nozzle extension section is used. The nozzle live connection structure means that the nozzle extension section is connected with the thrust chamber by the flange structure, which can realize the fastening of the connection structure and the reliable sealing of high-tempera...

AI Technical Summary

Problems solved by technology

Although the multi-sample engine high-altitude simulated thermal test assessment method is beneficial to the adequacy and authenticity of the reliability verification of the joint structure of the nozzle, it has the following disadvantages: 1) The test cost is high; 2) The test cycle is very long; 3) It is easy to introduce low-level quality problems; 4) A large amount of propellant combustion increases atmospheric carbon emissions, which is not conducive to atmospheric environmental protection. For conventional propellants, a large amount of toxic gases will be produced

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