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Multi-nozzle rocket jet test system

A test system and multi-nozzle technology, applied in ammunition tests, rocket launchers, offensive equipment, etc., can solve the problems of being unable to guide the engineering design of the rocket body and the ground launch system, unable to reflect the noise environment, and not considering the disturbance effect, etc. , to achieve the effect of ensuring accuracy and credibility, ensuring similarity, and ensuring security

Active Publication Date: 2022-07-29
BEIJING INST OF SPACE LAUNCH TECH +1
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The previous jet flow test system usually only simulates the jet flow noise in the free jet flow state, without considering the disturbance effect of the actual ground launch system on the gas flow or only adding local obstacles. The test data are mostly used for theoretical research and cannot reflect the actual launch process. The noise environment of the rocket body and the ground launch system cannot guide the engineering design of the rocket body and the ground launch system, which has certain limitations.

Method used

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  • Multi-nozzle rocket jet test system

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Embodiment Construction

[0044] The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0045] 1) The outline of the jet test system remains similar to the original launch vehicle and launch support system

[0046] In order to ensure that the gas flow field, the take-off force thermal environment and even the noise field distribution, the noise reduction effect of water spray, and the thermal protection performance of the launch system are consistent with the actual launch vehicle and launch support system, the outline of the jet flow test system should be kept sufficient with the actual product. similarity. At the same time, the water spray flow rate and water spray speed of the water spray noise reduction system should match the test system. Of course, in order to reduce the scale of the jet flow test, on the premise of satisfying the similarity of the gas flow field and the thermal environment of the take-off force, the structure size of th...

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PUM

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Abstract

Multi-nozzle rocket jet test system, including: simulated rocket body, test platform and water spray equipment for reducing noise and protecting the test platform; the outer dimensions of the simulated rocket body and the test platform are designed or carried out in proportion to the actual structural size Linear scaling, the total water spray flow of the water spray equipment is k of the actual total water spray flow 2 The speed of water spray is consistent with the actual product. The simulated arrow body is fixed on the test platform according to the preset test height, and gas is generated during the test. The sensor installed on the simulated arrow body and the test platform collects the test process the temperature, pressure, heat flow and noise; the k is the ratio of the outer dimension of the simulated rocket body and the test platform to the actual structural dimension.

Description

technical field [0001] The invention relates to a multi-nozzle rocket jet flow test system. Background technique [0002] The thermal environment of the launch force of the launch vehicle determines the safety of the launch vehicle. It is also the basis for the design of the comprehensive protection system of the rocket system and its sub-systems, and it is also the basis for the application of new technologies in the launch engineering of the launch vehicle. [0003] The jet flow test system is a special test system specially used to study the thermal environment of the rocket's take-off force before the launch of the launch vehicle. In the past, the jet flow test system usually only simulates the jet flow noise in the free jet state, and does not consider the disturbance effect of the actual ground launch system on the gas flow or only adds local obstructions. The noise environment of the rocket body and the ground launching system under the circumstance cannot guide the ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F41F3/04F42B35/00
CPCF41F3/04F42B35/00
Inventor 陈劲松张筱曾玲芳贾延奎吴新跃王南张国栋平仕良黎定仕翟旺杜小坤
Owner BEIJING INST OF SPACE LAUNCH TECH
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