Solid propellant multi-target wire dynamic combustion performance testing system and method thereof

A technology of solid propellant and combustion performance, which is applied in the direction of chemical analysis using combustion, can solve the problems of complex testing process, large amount of propellant, and many testers, so as to reduce manual operation, reduce raw material consumption, and facilitate switching. Effect

Inactive Publication Date: 2015-02-11
XIDIAN UNIV
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  • Abstract
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  • 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 testers, the test process is complicated, and there are also potential safety hazards in the test.

Method used

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  • Solid propellant multi-target wire dynamic combustion performance testing system and method thereof
  • Solid propellant multi-target wire dynamic combustion performance testing system and method thereof
  • Solid propellant multi-target wire dynamic combustion performance testing system and method thereof

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Embodiment Construction

[0050] refer to figure 1, a solid propellant multi-target line dynamic combustion performance test system, at least including:

[0051] Combustion chamber unit D, which provides the combustion chamber for solid propellant sample combustion and the initial environment required for testing.

[0052] The wall of the combustion chamber has a surrounding pipeline connected to the constant temperature bath 6; the combustion chamber 7 has an air hole and a mounting hole for the temperature and pressure sensor 8, through which the air circuit unit and the temperature and pressure sensor 8 are connected respectively, and a filter is provided at the air hole.

[0053] The combustion bracket is provided with a positioning grid 13 for positioning and connecting the multi-target wire 11 and the ignition wire 15 . The metal rod plays the role of support and ground wire. One end of the multi-target wire 11 passes through the solid propellant pill 10, and the other end is connected to a high...

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Abstract

The invention relates to a solid propellant multi-target wire dynamic combustion performance testing system and a method. The method adopts a multi-target wire 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 testing system, in particular to a solid propellant multi-target line dynamic combustion performance testing system and method. Background technique [0002] In the development and production of solid propellants, as well as the initial stage of solid engine development, technical parameters such as propellant burning rate, burning rate pressure index, and burning rate temperature sensitivity coefficient directly affect the internal ballistic performance, flight speed and stability of the rocket engine. Work. Existing methods for measuring static burning rate characteristics mainly use nitrogen target line method or underwater acoustic emission method. These two methods are to test the burning rate of the solid propellant sample rod under the condition of constant pressure and temperature. It is necessary to test the static burning rate at several pressure points to obtain the ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01N31/12
Inventor 刘科祥赵露刘倩
Owner XIDIAN UNIV
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