Monitoring system for carrier-rocket launch fuel-gas flow field

Abstract

The invention discloses a monitoring system for a carrier-rocket launch fuel-gas flow field. The monitoring system includes a first test main array group and a second test main array group, wherein the first test main array group includes an in-diversion-hole fuel-gas flow field test array, a table-board fuel-gas flow field test array and an on-cross-beam fuel-gas flow field test array. The second test main array group includes a near-diversion-trench-entrance fuel-gas flow field parameter test array, a diversion-trench-drainage-guide-face fuel-gas flow field parameter test array, a guide-trench-top fuel-gas flow field parameter test array and a diversion-trench-side-face fuel-gas flow field parameter test array. The test scheme of the carrier-rocket launch fuel-gas flow field is applicable to carrier-rocket launch fuel-gas flow field testing and fuel-gas-flow ablation characteristic assessment and capable of being transplanted conveniently into a shrinkage-scale launch simulation test or fuel-gas flow field testing and fuel-gas ablation characteristic assessment in a special simulation test.

Description

technical field [0001] The invention relates to the field of rocket launch, in particular to the field of gas flow field monitoring for launch of a launch vehicle. Background technique [0002] The impact of rocket launch gas flow on launch system and rocket ablation has always been an issue of concern in the fields of rocket launch technology research and development, launch system special equipment development, rocket special thermal protection and gas flow field control. Research on special thermal protection technology, product principle and verification. A very important task in the related research is to detect and evaluate the flow field parameters of rocket launch gas. For this reason, many simple or systematic detection methods have been proposed to adapt to different technical forms of rocket launch gas. Flow ablative propagation environment. [0003] At present, the monitoring of the rocket launch gas flow field mainly relies on the structural conditions of the l...

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Problems solved by technology

[0003] At present, the monitoring of the rocket launch gas flow field mainly relies on the structural conditions of the launch system of the launch vehicle to carry and arrange limited measuring points on the launch system structure to test the parameters of the gas flow field at special positions. This test is interfered by the structural conditions of the launch system (such as the structural conditions of the launch pad) Due to limitations, the combustion parameters of the test are often difficult to reflect the gas flow field characteristics of the rocket launch gas flow. Under some conditions, due to the structural conditions of the launch system, it is impossible to obtain the actual gas flow field parameters. The sensor is damaged, so the small sample test data can hardly reflect the distribution of the real launch gas flow, so it is impossible to systematically and finely evaluate the impact of the rocket body and the launch system on the gas flow field

[0004] In addition, the current field of gas flow field monitoring is mainly aimed at the gas flow ablation and gas flow field detection and evaluation of single-nozzle rocket launch, while the field of gas flow ablation and gas flow field detection of launch vehicles, especially bundled launch vehicles, is less involved , there are three main reasons: first, the mutual interference effect of the multi-nozzle gas flow of the launch vehicle is obvious, which makes it difficult to test and analyze the gas flow field parameters, especially the gas flow ablation characteristic parameters and gas flow field parameters; the second is that the launch vehicle Different types of engines are often used to meet the requirements of special launch technology capabilities. This is especially prominent in the application of core-stage engines and booster-stage rocket engines of bundled launch vehicles, resulting in gas flow ablation characteristics and gas flow field characteristics tests, Difficult analysis, for example, the research on gas flow ablation mechanism needs to determine the relationship between ablation intensity and incoming flow Reynolds number. Under the condition that the engine gas flow interferes with each other and the incoming gas flow composition is not single, it obviously increases the difficulty of testing and analysis; the third is the carrying The disturbance effect of the rocket launch platform is prominent, and the ablation of the gas flow and the influence of the gas flow field must fully consider the structural disturbance effect of the launch platform

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