Synchronous measurement method for combustion rate and combustion wave of solid propellant

A solid propellant and synchronous testing technology, which is applied in fluid velocity measurement, fluid velocity measurement using thermal variables, velocity/acceleration/impact measurement, etc., can solve problems such as inaccurate timing, and achieve improved timing accuracy and burning rate test results Precise, short response time effects

Inactive Publication Date: 2019-11-15
XIAN MODERN CHEM RES INST
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Problems solved by technology

[0004] In order to solve the problem of inaccurate timing of the target line burning rate test under the condition of low combustion temperature, the present invention proposes the method of using miniature thermocouples to replace the traditional target line, which can effectively improve the timing accuracy of the target line, and can realize solid propellant Simultaneous testing of burning rate and burning wave

Method used

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  • Synchronous measurement method for combustion rate and combustion wave of solid propellant
  • Synchronous measurement method for combustion rate and combustion wave of solid propellant
  • Synchronous measurement method for combustion rate and combustion wave of solid propellant

Examples

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Effect test

Embodiment 1

[0033] The boron-containing fuel-rich propellant was cut into 4×4×150mm rectangular medicinal strips, and the surface of the medicinal strips was coated with 8% polyvinyl butyral alcohol solution. A micro-drilling machine was used to perforate the coated propellant strips, the size of the drill bit was 0.4mm, and the distance between the two target line holes was 100.10mm. Punch a hole on one side of the propellant strip and insert a nickel-chromium ignition wire with a diameter of 1mm. The distance between the ignition wire and the thermocouple hole at the same end is 25mm. Two S-type platinum-rhodium thermocouples with a wire diameter of 13 μm were inserted into two target wire holes, and the diameters of the temperature measurement points of the two hot spot couples were 48 μm and 45 μm, respectively. Ignite the propellant strips in a constant pressure bomb, which is filled with nitrogen and the pressure is 1 MPa. The voltage-time curve measured by the thermocouple is conve...

Embodiment 2

[0035] The boron-containing fuel-rich propellant was cut into 4×4×150mm rectangular medicinal strips, and the surface of the medicinal strips was coated with 8% polyvinyl butyral alcohol solution. A micro-drilling machine was used to perforate the coated propellant strips, the size of the drill bit was 0.4mm, and the distance between the two target line holes was 99.35mm. Punch a hole on one side of the propellant strip and insert a nickel-chromium ignition wire with a diameter of 1mm. The distance between the ignition wire and the thermocouple hole at the same end is 28mm. Two R-type platinum-rhodium thermocouples with a wire diameter of 13 μm were inserted into two target wire holes respectively, and the diameters of the temperature measurement points of the two hot spot couples were 45 μm and 43 μm, respectively. The propellant strips are ignited in a constant pressure bomb, which is filled with nitrogen and the pressure is 10MPa. The voltage-time curve measured by the ther...

Embodiment 3

[0037] Use 8% polyvinyl butyral alcohol solution to coat the surface of a cylindrical double-base propellant strip with a size of Φ5×150mm, and use a micro drilling machine to beat the coated propellant strip The size of the drill bit is 0.4mm, and the distance between the two target line holes is 80.22mm. Punch a hole on one side of the propellant strip and insert a nickel-chromium ignition wire with a diameter of 1 mm. The distance between the ignition wire and the thermocouple hole at the same end is 22 mm. Two R-type platinum-rhodium thermocouples with a wire diameter of 13 μm were inserted into two target wire holes, and the diameters of the temperature measurement points of the two hot spot couples were 42 μm and 39 μm, respectively. The propellant strips are ignited in the constant pressure bomb, which is filled with nitrogen and the pressure is 3MPa. The voltage-time curve measured by the thermocouple is converted into a temperature-time curve to obtain the combustion ...

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Abstract

The invention discloses a synchronous measurement method for a combustion rate and a combustion wave of a solid propellant. The method comprises the following steps: drilling holes in a radial direction at both axial ends of a cuboid-shaped or cylindrical propellant strip, and measuring a spacing between the two holes; drilling holes on one side of the propellant strip in an axial direction and inserting ignition wires into the holes; inserting two micro platinum-iridium thermocouples into the holes respectively; putting the propellant strip in a constant pressure bomb for ignition, recordinga time t1 at which the first thermocouple shows a maximum voltage when the burned solid propellant is close to a temperature measuring head of the first thermocouple and recording a time t2 at which the second thermocouple shows a maximum voltage when the burned solid propellant is close to a temperature measuring head of the second thermocouple, calculating a combustion rate of the propellant andthen obtaining two combustion wave curves of the propellant strip. The synchronous measurement method of the invention adopts micro thermocouples with a small wire diameter and has a short response time. The synchronous measurement method uses micro thermocouples instead of traditional target line methods to effectively improve a timing accuracy of the target line and realize synchronous test forthe combustion rate and the combustion wave of the solid propellant.

Description

Technical field [0001] The invention relates to a method for testing the combustion performance of solid propellants, which is suitable for low-combustion temperature solid propellants. Background technique [0002] Burning rate and combustion temperature are one of the core technical parameters of solid propellants, and they are also an important performance parameter in rocket engine interior ballistic design. It is often necessary to know the burning rate and combustion of the propellant when adjusting the propellant formulation and mass production. temperature. In addition, in order to deeply study the combustion mechanism of the propellant, it is often necessary to test the combustion wave of the propellant. In a test process, the propellant burning rate and combustion wave test results can be obtained simultaneously, which improves the test efficiency and has better economic benefits. [0003] The target line method has become the most widely used solid propellant burning r...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01N25/26G01P5/18G01P5/10G01K7/02
CPCG01N25/26G01P5/18G01P5/10G01K7/02
Inventor 孙志华刘林林仪建华许毅王长健赵凤起秦钊郝宁
Owner XIAN MODERN CHEM RES INST
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