Four-unit parallel heat testing device for liquid-propellant rocket engine

Abstract

A four-unit parallel heat testing device for a liquid-propellant rocket engine comprises an oxidizing agent pipeline, a fuel pipeline, a cooling agent pipeline and a support. The oxidizing agent pipeline is used for providing an oxidizing agent for a thrust chamber. The fuel pipeline is used for providing fuel for the thrust chamber. The cooling agent pipeline is used for providing a cooling agentfor the thrust chamber for carrying out heat protection on the thrust chamber. The support is used for supporting the oxidizing agent pipeline, the fuel pipeline, the cooling agent pipeline and the tested thrust chamber. The oxidizing agent pipeline further comprises an oxidizing agent adjusting element, and the oxidizing agent adjusting element is used for adjusting the flow and pressure of theoxidizing agent provided by the oxidizing agent pipeline for the tested thrust chamber. The fuel pipeline further comprises a fuel adjusting element, and the fuel adjusting element is used for adjusting the flow and pressure of the fuel provided by the fuel pipeline for the tested thrust chamber. According to the testing device, the development period of the rocket engine can be greatly shortened,the development cost of the rocket engine can be reduced, and the development efficiency of the rocket engine can be improved.

Description

technical field [0001] The invention relates to a four-machine parallel thermal test device for a liquid rocket engine, which belongs to the field of liquid rocket engines. Background technique [0002] The extrusion heat test of the thrust chamber is the main method for the development of the thrust chamber of the liquid rocket engine, and it has the characteristics of many test parameters, many influencing factors, and many design schemes of the test pieces. Extrusion thermal tests of thrust chambers in the prior art are all carried out for a single thrust chamber. In order to optimize design parameters and design schemes, a single research project often needs to do thermal tests ranging from a dozen times to more than 50 times. The test cycle and test cost are very huge, and at the same time consume a lot of labor costs, which are the main factors restricting the rocket engine development cycle and efficiency. At present, in the prior art, there has not been a plan for m...

AI Technical Summary

Problems solved by technology

Extrusion thermal tests of thrust chambers in the prior art are all carried out for a single thrust chamber. In order to optimize design parameters and design schemes, a single research project often needs to do thermal tests ranging from a dozen times to more than 50 times. The test cycle and test cost are very huge, and at the same time consume a lot of labor costs, which are the main factors restricting the rocket engine development cycle and efficiency

At present, in the prior art, there has not been a plan for multiple thrust chambers to carry out thermal tests at the same time. The main problems are: (1) When the test status of multiple thrust chambers is consistent, the entire test device needs to ensure that multiple thrust chambers (2) When the test states of multiple thrust chambers are inconsistent, it is necessary to have the ability to individually adjust the test state of each thrust chamber

Images