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Constant-pressure apparatus used in testing of burning rate of solid propellant

A technology of solid propellant and constant pressure device, which is applied in the direction of using combustion for chemical analysis, etc. It can solve the problem of difficult constant pressure, and achieve the effect of easy cleaning, convenient maintenance, and getting rid of the use of nitrogen

Inactive Publication Date: 2016-08-31
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] In order to avoid the problem that the pressure is difficult to keep constant in the burning rate test process of solid propellant under low pressure in the prior art, the present invention proposes a constant pressure device for testing the burning rate of solid propellant

Method used

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  • Constant-pressure apparatus used in testing of burning rate of solid propellant
  • Constant-pressure apparatus used in testing of burning rate of solid propellant
  • Constant-pressure apparatus used in testing of burning rate of solid propellant

Examples

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example 1

[0028] In this embodiment, a boron-containing fuel-rich propellant with a boron content of 35% is used as the test piece for the burning rate test. The size of the propellant rod is a cuboid of 4×4×150 mm, and the burning rate of the propellant under the test pressure is 0.2 MPa. . The diameter of the combustion chamber is 50mm, the height is 200mm, the number of cylinders is N=2, and the inner diameter of the cylinder is d 0 =65mm, cylinder length L 0 =1.5m, piston outer diameter D 1 =65mm, inner diameter of piston d 1 =30mm, piston length L 1 =40mm, the mass of the weight in the weight pan is 115kg.

[0029] The constant pressure device is installed on a special bench to ensure the stable operation of the device during the experimental test. After assembling the components of the combustion chamber, close the high-pressure nitrogen gas charging valve and exhaust valve of the combustion chamber, and at the same time, turn on the vacuum pump, and evacuate the combustion c...

example 2

[0031] In this embodiment, a boron-containing fuel-rich propellant with a boron content of 35% is used as the test piece. The propellant rod is a cuboid with a size of 4×4×150 mm, and the burning rate of the propellant is tested at a pressure of 5 MPa. The diameter of the combustion chamber is 50mm, the height is 200mm, the number of cylinders is N=2, and the inner diameter of the cylinder is d 0 =24mm, cylinder length L 0 =1.0m, piston outer diameter D 1 =24mm, inner diameter of piston d 1 =12mm, piston length L 1=40mm, the mass of the weight in the weight pan is 397kg.

[0032] After assembling the components of the combustion chamber, close the exhaust valve of the combustion chamber, and at the same time, turn on the vacuum pump to evacuate the combustion chamber to discharge the air in the combustion chamber. Then open the high-pressure nitrogen charging valve and charge nitrogen into the combustion chamber, and when the pressure in the combustion chamber reaches 5MPa...

example 3

[0034] In this embodiment, a composite propellant with an aluminum content of 17% is used as the test object. The size of the propellant rod is a cuboid of 4×4×150 mm. The mass is 52kg, and the burning rate is tested at 5MPa. The diameter of the combustion chamber is 50mm, the height is 200mm, the number of cylinders is N=4, and the inner diameter of the cylinder is d 0 =15mm, cylinder length L 0 =1.5m, piston outer diameter D 1 =15mm, inner diameter of piston d 1 =8mm, piston length L 1 =40mm, the mass of the weight in the weight pan is 342kg.

[0035] After assembling the components of the combustion chamber, close the exhaust valve of the combustion chamber, and at the same time, turn on the vacuum pump to evacuate the combustion chamber to discharge the air in the combustion chamber. Then open the high-pressure nitrogen charging valve and charge nitrogen into the combustion chamber, and when the pressure in the combustion chamber was 5MPa, close the high-pressure nitr...

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Abstract

The invention discloses a constant-pressure apparatus used in testing of the burning rate of a solid propellant. The constant-pressure apparatus is composed of a combustion chamber, a pedestal, a plurality of cylinders and a weight disk, wherein the combustion chamber is fixedly connected with the pedestal; a sealing ring is installed at the joint of the pedestal and a flange of the sidewall of the combustion chamber; two cylindrical cylinders are symmetrically installed at two sides of the combustion chamber, and two same rubber pistons are arranged in the cylinders; one end of a support bar is connected with a groove located on the outer bottom of the weight disk, and the other end of the support bar is connected with the two rubber pistons in the cylinders; the distance between the two rubber pistons is adjustable; the combustion chamber is connected with the cylinders through arc circular pipes; the side wall of the combustion chamber is provided with a nitrogen filling hole, a gas vent, a sensor connection hole and a vacuum pump connection hole which are respectively connected with a high-pressure nitrogen cylinder, an exhaust valve, a pressure sensor and a vacuum pump; and a propellant strip is fixed in a groove located on the pedestal in the combustion chamber. The constant-pressure apparatus is simple in structure and convenient to dismount; combustion products in a cleaning device are easy to clean, which is beneficial for maintenance of the apparatus; and testing precision is improved.

Description

technical field [0001] The invention relates to the technical field of low-pressure testing of solid rocket motors, in particular to a constant pressure device for testing the burning rate of solid propellants. Background technique [0002] Burning rate is a core technical indicator of solid propellants and an important performance parameter in rocket engine internal ballistic design. Therefore, it is often necessary to test the burning rate of propellants during propellant formulation adjustment and mass production to confirm The burning rate of the propellant. The burning rate of solid propellants generally increases with the increase of pressure, and the burning rate and pressure satisfy the law of Vieri exponent [0003] r=ap n [0004] In the formula, r is the burning rate of the propellant; a is the burning rate coefficient; n is the burning rate pressure index. Therefore, in order to know the burning rate characteristics of the propellant, it is necessary to test ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01N31/12
CPCG01N31/12
Inventor 刘林林胡松启刘元敏
Owner NORTHWESTERN POLYTECHNICAL UNIV
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