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A composite solid propellant with low burning rate, high energy and high mechanical properties

A solid propellant, burning rate technology, used in offensive equipment, compressed gas generation, explosives, etc., can solve problems such as difficult to dissolve, melting point exceeding 55 °C, etc., to meet the requirements of structural integrity, excellent and stable mechanical properties , the effect of large molecular weight

Active Publication Date: 2019-08-23
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The disadvantage is that when the molecular weight of PCL bulk polymerization exceeds 8000, the melting point exceeds 55°C
Therefore, polyPCL with a molecular weight of more than 10000 and f=2 is difficult to dissolve in nitrate esters during the preparation process with NG and BTTN at 50 °C, and cannot be used in high-energy propellants.

Method used

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  • A composite solid propellant with low burning rate, high energy and high mechanical properties
  • A composite solid propellant with low burning rate, high energy and high mechanical properties
  • A composite solid propellant with low burning rate, high energy and high mechanical properties

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0041] (1) Propellant composition

[0042] components PAO-PCL NG / BTTN AP HMX Al Content (%wt) 7 18.3 15 42 18 components TPB MNA NPBA TDI Content (%wt) 0.05 0.3 0.2 0.15

[0043] Among them: PAO-PCL is the PAO with f=3, Mn=10000 as the initiator, and the PAO-PCL adhesive with f=3, Mn=20000 is prepared according to the molar ratio PAO:PCL=1:1, and the melting point is 50.1°C .

[0044] (2) Propellant performance

[0045] Energy performance (6.86MPa measured specific impulse): 255.2s

[0046] Burning rate: r6.86MPa=7mm / s

[0047] Mechanical properties: 25℃ σ m =0.91MPa, ε m =115%

[0048] +70°C ε m =87%

[0049] -30℃ε m =92%

Embodiment 2

[0051] (1) Propellant composition

[0052] components PAO-PCL NG / BTTN AP HMX Al Content (%wt) 6 19 12.25 47 15 components TPB MNA NPBA HDI Content (%wt) 0.05 0.3 0.2 0.2

[0053] Wherein: PAO-PCL is to use the PAO of f=3, Mn=15000 as initiator, according to the molar ratio PAO:PCL=2:1 feeding intake, prepare f=3, the PAO-PCL adhesive of Mn=22500, melting point 50.2°C.

[0054] (2) Propellant performance

[0055] Energy performance (measured specific impulse of 6.86MPa): 255.3s

[0056] Burning rate: r6.86MPa=7.3mm / s

[0057] Mechanical properties: 25℃ σ m =0.91MPa, ε m =125%

[0058] +70°C ε m =97%

[0059] -30℃ε m =98%

Embodiment 3

[0061] (1) Propellant composition

[0062] components PAO-PCL NG / BTTN AP HMX Al Content (%wt) 6.3 19 12 46 16 components TPB MNA NPBA TDI Content (%wt) 0.05 0.3 0.2 0.15

[0063] Wherein: PAO-PCL is to use the PAO of f=3, Mn=20000 as initiator, according to molar ratio PAO:PCL=2:1 feeds intake, prepares f=3, the PAO-PCL adhesive of Mn=30000, melting point 51.2°C.

[0064] (2) Propellant performance

[0065] Energy performance (measured specific impulse of 6.86MPa): 255.3s

[0066] Burning rate: r6.86MPa=7.4mm / s

[0067] Mechanical properties: 25℃ σ m =0.91MPa, ε m =129%

[0068] +70°C ε m =102%

[0069] -30℃ε m =90%

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Abstract

The invention relates to a compound solid propellant with a low burning rate, high energy and high mechanical property. The compound solid propellant is prepared from components in parts by weight asfollows: 6-7 parts of an adhesive, 17-19 parts of a plasticizer, 10-15 parts of an oxidizing agent, 42-47 parts of energy-containing explosive, 15-18 parts of metal fuel, 0.15-0.25 parts of a curing agent, 0.05 parts of a curing catalyst, 0.3 parts of a stabilizing agent and 0.2 parts of a bonding agent. The minimum burning rate under the pressure of 6.686 MPa can reach 7 mm / s, the standard specific impulse is stably larger than 255 s according to actual testing, the technical problems that the burning rate of a high-energy propellant is further reduced and the energy of the propellant is substantially reduced are solved, and the technical requirements of existing propellants for weapon models for high energy, lower burning rate and high mechanical property are met.

Description

technical field [0001] The invention relates to a nitrate plasticized polyether polyester composite solid propellant (abbreviated as NEPE). Background technique [0002] The development trend of long-range, large load, strong penetration, small and high mobility of missile weapon systems constantly requires the solid propellant used in the engine combustion chamber to have high energy, the lowest possible burning rate, and higher mechanical properties. Among them, high energy and low burning rate are a pair of sharp conflicts, because the stable performance of energy performance can only be realized when the propellant reaches a certain burning rate. When the propellant burning rate is lower than a certain lower limit value, the lower limit value is usually 8mm / s~9mm / s for high-energy NEPE propellants, and the current decelerating agent method is used to further reduce the burning rate, and the energy performance of the propellant A sharp decline. As an important component...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C06B45/10C06B33/06C06D5/00
Inventor 吴芳庞爱民徐海元李洪旭周水平唐根徐星星宋会彬王艳萍
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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