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Flame-radiation-based combustion measuring apparatus and measuring method for solid rocket propellant

A flame radiation and measurement device technology, applied in the direction of measurement devices, instruments, etc., can solve the problem that the measurement device cannot realize multi-parameter testing, and achieve the effect of easy maintenance

Active Publication Date: 2017-03-08
ELECTROMECHANICAL ENG INST OF SICHUAN AEROSPACE +1
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Problems solved by technology

[0005] The purpose of the present invention is to address the deficiencies of the prior art, to provide a solid rocket propellant combustion measurement device and measurement method based on flame radiation, to solve the problem that the existing measurement device cannot realize multi-parameter testing

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  • Flame-radiation-based combustion measuring apparatus and measuring method for solid rocket propellant
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  • Flame-radiation-based combustion measuring apparatus and measuring method for solid rocket propellant

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[0025] In order to make the purpose, technical solution and advantages of the present application clearer, the present application will be further described in detail below in conjunction with the accompanying drawings and specific embodiments. For simplicity, some technical features known to those skilled in the art are omitted from the following description.

[0026] The solid rocket propellant combustion measurement device based on flame radiation is used to test the combustion temperature, radiation rate and burning speed of the medicine rod 103 in the combustion device 1, such as figure 1 As shown, it includes a light converging part 2, a plurality of spectral measurement parts 3, a control part 4, a signal processing part 5 and an ignition device.

[0027] The combustion device 1 is an airtight container, and the pressure in the airtight container can be adjusted to carry out tests under specific experimental conditions. The combustion device 1 comprises a combustion ch...

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Abstract

The invention provides a flame-radiation-based combustion measuring apparatus for a solid rocket propellant. The apparatus comprises a light convergence part, a plurality of spectral measurement parts, an ignition device, a control part, and a signal processing part. The light convergence part is formed by a plurality of light convergence devices arranged at the same straight line; the light convergence devices corresponding to the spectral measurement parts one by one; and the light convergence devices and the corresponding spectral measurement parts are connected by fibers. The control part is connected with the ignition device, the signal processing part, and the plurality of spectral measurement parts electrically. In addition, a measuring method based on the measuring apparatus is characterized in that temperature and radiance parameters are obtained by fitting of a flame radiation, so that the measuring precision of the optical radiation measuring method can be improved. And with combination of the array arrangement method, a combustion speed parameter can be obtained. For propellant combustion testing, multi-parameter simultaneous on-line non-contact measurement is realized; processing on a medical stick is avoided; and the apparatus is easy to repair.

Description

technical field [0001] The invention belongs to the technical field of solid rocket propellant testing, in particular to a flame radiation-based solid rocket propellant combustion measurement device and measurement method. Background technique [0002] The combustion temperature, radiation rate and burning rate parameters of solid rocket propellants are important parameters to characterize the burning rate performance of propellants. [0003] At present, thermocouples are mainly used to measure the combustion temperature of propellants. However, with the development of high-energy propellants, the combustion temperature of propellants has far exceeded the temperature measurement range of thermocouples, which cannot meet the measurement requirements. In addition, there are also laser spectrum active measurement methods (such as CARS technology) to explore the diagnosis of solid propellant combustion. Laser spectroscopy active methods are not widely used. [0004] Existing m...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01D21/02
CPCG01D21/02
Inventor 王伟杨斌
Owner ELECTROMECHANICAL ENG INST OF SICHUAN AEROSPACE
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