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Multi-nozzle rocket dynamic jet test system

A multi-nozzle and rocket technology, which is applied in the test of ammunition, offensive equipment, ammunition, etc., can solve the problems of high cost and unfavorable research development, and achieve the effect of reducing the test cost and the number of jet flow tests.

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

AI Technical Summary

Problems solved by technology

[0004] However, the static jet flow test system also has certain limitations: In order to obtain the gas flow field distribution, noise field distribution, water spray noise reduction effect and take-off force thermal environment at different rocket body heights, it is necessary to process gantry columns of different heights, And prepare a large number of simulated engines
Therefore, in order to find out the actual launch environment, it is necessary to organize and carry out a large number of jet tests, which requires a large cost and is not conducive to the development of research.

Method used

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  • Multi-nozzle rocket dynamic jet test system

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Embodiment Construction

[0051] The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0052] 1) The outline of the jet test system remains similar to the original launch vehicle and launch support system

[0053] 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 ...

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Abstract

Multi-nozzle rocket dynamic 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 in proportion to the actual structural size or For linear scaling, the total spray flow of the water spray equipment is k of the actual total spray flow 2 The speed of water spray is consistent with the actual product. The simulated arrow body is fixed on the test platform through the test tool, and gas is generated during the test. The gas pushes the simulated arrow body along the test tool to achieve height changes; The sensor on the test platform collects the temperature, pressure, heat flow and noise during the test; the k is the ratio of the outer dimension of the simulated arrow body and the test platform to the actual structure size.

Description

technical field [0001] The invention relates to a multi-nozzle rocket dynamic jet 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 order to simplify the operational risk, in most cases, the test is carried out in a static way (simulating the rocket body relative to the launch system to carry out the test in a fixed position). [0004] However, the static jet flow test system also has certain limitations: in order to obtain the gas flow field distribution, noise fiel...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F42B35/02
CPCF42B35/02
Inventor 陈劲松张筱曾玲芳贾延奎吴新跃王南张国栋余佳申鹏杜小坤
Owner BEIJING INST OF SPACE LAUNCH TECH
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