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A measurement system and measurement method for the internal flow field of an engine

An internal flow field and measurement system technology, applied in jet engine testing, gas turbine engine testing, X-ray energy spectrum distribution measurement, etc. Insufficient performance, avoid the effect of internal flow field disturbance

Active Publication Date: 2021-10-08
BEIHANG UNIV
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  • Abstract
  • Description
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  • Application Information

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Problems solved by technology

[0007] In view of this, the present invention provides a measurement system and measurement method for the internal flow field of the engine, which are used to overcome the lack of accuracy of numerical calculation results and avoid the disturbance of the internal flow field by traditional measurement methods

Method used

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  • A measurement system and measurement method for the internal flow field of an engine
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  • A measurement system and measurement method for the internal flow field of an engine

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Embodiment Construction

[0039] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only for illustration and are not intended to limit the present invention.

[0040] A measurement system for the internal flow field of a solid rocket motor provided by the present invention, the top view is as follows figure 1 As shown, it includes: a darkroom 1, a test bench for fixing the solid rocket motor 2 in the darkroom 1, and a plurality of gamma-ray dynamic collectors 3 in the darkroom 1; wherein,

[0041] Such as figure 2 As shown, one side of the darkroom 1 has an opening 4; figure 1 As shown, the solid rocket motor 2 is located on the test bench in the darkroom 1, and the nozzle extension section 5 of the solid rocket motor 2 extends out of the darkroom 1 through the opening, and the darkroom 1 closely fits the n...

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Abstract

The invention discloses a measurement system and a measurement method for the internal flow field of the engine. The powder column of the solid rocket motor is prepared by using radioactive isotope raw materials. Plume, radioactive isotope particles release γ-rays when they flow with the flow field, and use the γ-ray dynamic collector to collect the released γ-rays to measure the dynamic characteristics of the internal flow field of the solid rocket motor. The above-mentioned measurement system uses radioisotopes as tracer particles to realize Compared with the traditional measurement method, the non-contact measurement of the internal flow field of the solid rocket motor does not need to destroy the original structure of the solid rocket motor, and can avoid the disturbance of the internal flow field by the traditional measurement method. Compared with the existing numerical calculation method In comparison, it can overcome the shortcomings of insufficient accuracy of numerical calculation results.

Description

technical field [0001] The invention relates to the technical field of solid rocket motor measurement, in particular to a measurement system and a measurement method for the internal flow field of a solid rocket motor. Background technique [0002] Solid rocket motor is a kind of rocket motor, which has been widely used in the propulsion system of missiles, launch vehicles and space vehicles. [0003] By measuring the internal flow field of the solid rocket motor, it is possible to judge whether the design of the engine is reasonable, whether the charge can burn normally, and whether the charge meets the quality requirements. This is of great significance for optimizing the structural design of the engine and improving the performance of the engine. [0004] Most of the traditional measurement methods measure the internal pressure of solid rocket motors at multiple points to indirectly calculate parameters such as engine thrust, grain burning velocity and flow coefficient. T...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M15/14G01T1/36
CPCG01M15/14G01T1/36
Inventor 任军学袁天楠张金尧吴坤隆胡嘉鑫汤海滨
Owner BEIHANG UNIV
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