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Detection system for single-jet-pipe rocket launch water-spray cooling noise-reduction effect

A rocket launch, water spray cooling technology, applied in the direction of measuring devices, machine/structural component testing, instruments, etc., can solve the problem of powerlessness in theoretical fine-grained evaluation

Active Publication Date: 2014-04-09
BEIJING INST OF SPACE LAUNCH TECH +1
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Problems solved by technology

Since the theoretical and refined evaluation of the actual effect of water spray cooling and noise reduction technology is relatively powerless, it is necessary to use a professional testing system to determine the actual effect of water spray cooling and noise reduction

Method used

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  • Detection system for single-jet-pipe rocket launch water-spray cooling noise-reduction effect
  • Detection system for single-jet-pipe rocket launch water-spray cooling noise-reduction effect
  • Detection system for single-jet-pipe rocket launch water-spray cooling noise-reduction effect

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Embodiment Construction

[0027] see Figure 1-Figure 3 , The detection system used in the present invention mainly consists of gantry 1, simulated rocket 2, rocket positioning adjustment equipment 5, water spray device 6, noise detection equipment, gas flow field and gas flow ablation intensity detection equipment, etc.

[0028] The gantry 1 is mainly composed of two uprights and the upper hanging beam. During the test, the two uprights of the gantry 1 are placed parallel and vertically on the foundation 9, and cooperate with the upper hanging beam to safely and reliably fix the rocket and other above-mentioned equipment.

[0029] The simulated rocket 2 is used as a test rocket, which is mainly used to generate the gas flow medium and gas flow noise sound source conditions required for the test. In order to cooperate with the evaluation of the gas flow field, gas flow ablation intensity and jet flow noise law, the thrust chamber of the simulated engine needs to Place pressure and temperature sensors. ...

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Abstract

The invention discloses a detection system for a single-jet-pipe rocket launch water-spray cooling noise-reduction effect. The system includes a portal frame, a simulating rocket, a rocket positioning and adjustment device, a water-spray device, a noise detection device and a fuel-gas flow field and fuel-gas-flow ablation intensity detection device. The water-spray device is installed around an engine jet pipe of the simulating rocket. The noise detection device includes a noise test array frame installed around the simulating rocket and noise array sensors installed on the noise test array frame. The fuel-gas flow field and fuel-gas-flow ablation intensity detection device includes a jet-flow field and ablation intensity test board installed under the simulating rocket and a jet-flow field and ablation intensity sensor array installed on the jet-flow field and ablation intensity test board. Based on the system, researches of a rocket launch water-spray cooling noise-reduction mechanism and effect evaluation can be carried out and a reference is also supplied to the water-spray cooling noise-reduction effect of follow-up complete simulating rocket launch technical conditions.

Description

technical field [0001] The invention relates to the field of rocket launching, in particular to a detection system for the effect of water spraying, cooling and noise reduction for single-nozzle rocket launching. Background technique [0002] At present, all countries in the world are promoting the application of water spray cooling and noise reduction technology in the field of rocket launch technology. On the one hand, the mixture of water flow and high-temperature, high-speed, high-condensation phase gas flow exchanges momentum and energy to reduce the temperature and scouring speed of the gas flow. In order to solve the problem of high temperature, high speed and high condensed phase gas flow ablation of the launch system, especially the launch platform and diversion tank, on the one hand, through the intense infiltration of water flow and gas flow, the high-speed atomization of water flow suppresses the high sound intensity of the launch gas flow Noise generation, at th...

Claims

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Application Information

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IPC IPC(8): G01M99/00
Inventor 陈劲松曾玲芳贾延奎王明华
Owner BEIJING INST OF SPACE LAUNCH TECH
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