Multi-nozzle rocket jet test system

A test system and multi-nozzle technology, which is used in the test of ammunition, rocket launchers, offensive equipment, etc., can solve problems such as inability to guide the engineering design of the rocket body and ground launch system, inability to reflect the noise environment, and ignoring disturbance effects. , to achieve the effect of reducing the layout location and number of layouts, ensuring accuracy and reliability, and ensuring similarity

Active Publication Date: 2019-07-05
BEIJING INST OF SPACE LAUNCH TECH +1
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  • Abstract
  • Description
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  • Application Information

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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
  • Multi-nozzle rocket jet test system
  • Multi-nozzle rocket jet test system

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Embodiment Construction

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

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

[0046] In order to ensure that the gas flow field, the thermal environment of the take-off force and even the distribution of the noise field, 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 fully consistent with the actual product. similarity. At the same time, the water spray flow 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 ...

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Abstract

The invention comprises a multi-nozzle rocket jet test system. The system comprises a simulated rocket body, a test platform and a water spraying device used for reducing noise and protecting the testplatform; the outer contour dimension of the simulated rocket body and the outer contour dimension of the test platform are designed in proportion according to the actual structure size or are subjected to linear scaling, the total water spraying flow of the water spraying device is k<2> times of the total actual water spraying flow, and the water spraying speed of the water spraying device is consistent with that of an actual product; and the simulated rocket body is fixedly installed on the test platform according to a preset test height, and produces fuel gas during a test, temperature, pressure, heat flow and noise in the test process are collected through sensors arranged on the simulated rocket body and the test platform, and the k is the ratio between the outer contour size of thesimulated rocket body and the outer contour size of the test platform to the actual structure size of the same.

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 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 subsystems, and 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 launch. The previous jet flow test system usually only simulates the jet flow noise in the free jet flow state, and does not consider the disturbance effect of the actual ground launch system on the gas flow or only adds 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 un...

Claims

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Application Information

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Patent Type & Authority Applications(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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