Solid propellant multi-thermocouple dynamic combustion performance testing system and method

A solid propellant and combustion performance technology, applied in the direction of material thermal development, etc., can solve the problems of high cost, complicated testing process, and many testing personnel

Active Publication Date: 2013-12-11
JIANGSU ZHONGKE GUOTENG SCI & TECH +1
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, this method uses a large amount of propellant, the cost is too high, there are many te

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  • Solid propellant multi-thermocouple dynamic combustion performance testing system and method
  • Solid propellant multi-thermocouple dynamic combustion performance testing system and method
  • Solid propellant multi-thermocouple dynamic combustion performance testing system and method

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Embodiment Construction

[0063] Reference figure 1 , Solid propellant multi-thermocouple dynamic combustion performance test system, including at least:

[0064] Combustion chamber unit D provides the combustion chamber for solid propellant sample combustion and the initial environment required for testing.

[0065] The combustion chamber wall has a surrounding pipeline connected to the constant temperature bath 6; the combustion chamber 7 has air holes and mounting holes for the temperature and pressure sensor 8. The air circuit unit and the temperature and pressure sensor 8 are respectively connected through the air holes and the mounting holes, and the air holes are provided with a filter.

[0066] The combustion support is provided with a positioning grid 13 for positioning the thermal conductive metal wire 12 and the ignition wire 15 connecting the thermocouple 11. The metal rod plays the role of support and ground. The output end of the ignition wire 15 and the thermocouple 11 are connected to the mea...

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Abstract

The invention relates to a solid propellant multi-thermocouple dynamic combustion performance testing system and a method. The method adopts a multi-thermocouple combustion rate testing system; dynamic combustion performance testing can be conducted; static testing can be conducted; and two measurement modes are convenient to switch. A change relation of combustion rate-pressure and combustion rate-temperature is obtained, and a combustion rate pressure index and a combustion rate temperature sensitivity coefficient are calculated. Small-dose testing can evaluate the combustion performance of a tested propellant within a corresponding pressure temperature change range, and is very suitable for conducting rapid performance detection, quality control and the like on each batch of products in a production process of the propellant. Compared with the common combustion rate testing system, the system shortens a development production cycle of the propellant, reduces raw material consumption, reduces manual operation, and saves the cost.

Description

Technical field [0001] The invention relates to a solid propellant dynamic combustion performance test system, in particular to a solid propellant multi-thermocouple dynamic combustion performance test system and method. Background technique [0002] In the development and production of solid propellants, as well as the initial stage of solid engine development, the propellant burning rate and its burning rate pressure index, burning rate temperature sensitivity coefficient and other technical parameters directly affect the rocket engine’s internal ballistic performance, flight speed and stability jobs. The existing measurement of static burning rate characteristic detection mainly adopts nitrogen target line method or underwater acoustic emission method. Both methods are used to test the burning rate of solid propellant sample strips under constant pressure and temperature conditions. It is necessary to perform static burning rate tests on several pressure points to obtain the ...

Claims

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Application Information

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IPC IPC(8): G01N25/26
Inventor 毛光普刘科祥赵露刘倩
Owner JIANGSU ZHONGKE GUOTENG SCI & TECH
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