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A low burning rate high energy solid propellant

A technology of solid propellant and burning rate, which is applied in the direction of offensive equipment, compressed gas generation, explosives, etc., can solve the problems that cannot meet the technical requirements of the development of new strategic weapon models, and solve the contradiction between high energy and low burning rate, The effect of low burning rate

Active Publication Date: 2020-03-24
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The standard static burning rate of the GAP / CL-20 high-energy propellant reaches above 15mm / s, which cannot meet the technical requirements for the development of new strategic weapon models in the future

Method used

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  • A low burning rate high energy solid propellant
  • A low burning rate high energy solid propellant
  • A low burning rate high energy solid propellant

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0029] (1) Composition of high energy solid propellant

[0030] Components (Specifications) Content (%wt) AP (Military Standard III) 6.0 CL-20(20μm) 52.0 Al(Q 3 )

14.0 gaps 6.75 NG 7.5 BTTN 7.5 Bu-NENA 5.25 TDI 0.3 2-NDPA 0.4 TEA 0.2 NPBA 0.1

[0031] (2) Performance of high energy solid propellant

[0032] 6.86MPa measured specific impulse: 260.6s

[0033] 6.86MPa standard static burning rate: 8.3mm / s

[0034] Burning rate pressure index (3MPa~9MPa): 0.68

Embodiment 2

[0036] (1) Composition of high energy solid propellant

[0037] Components (Specifications) Content (%wt) AP(Ⅲ) 8.0 CL-20(20μm) 48.0 Al(Q 3 )

16.0 gaps 6.25 NG 7 BTTN 7 TMETN 4.75 TDI 0.4 2-NDPA 0.8 TEA 1.6 NPBA 0.2

[0038] (2) Performance of high energy solid propellant

[0039] 6.86MPa measured specific impulse: 261.0s

[0040] 6.86MPa Static standard burning rate: 8.9mm / s

[0041] Burning rate pressure index (3MPa~9MPa): 0.72

Embodiment 3

[0043] (1) Composition of high energy solid propellant

[0044]

[0045]

[0046] (2) Performance of high energy solid propellant

[0047] 6.86MPa measured specific impulse: 260.2s

[0048] 6.86MPa static standard burning rate: 8.7mm / s

[0049] Burning rate pressure index (3MPa~9MPa): 0.66

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Abstract

The invention provides a low burning rate and high energy solid propellant, and belongs to the technical field of solid propellants. The solid propellant comprises the following components in percentage by weight: 17.5 to 22.5% of plasticizer, 6 to 7.5% of adhesive, 6.0 to 8.0% of oxidant, 48.0 to 52.0% of energy containing explosive, 14.0 to 16.0% of metal fuel, and 1.0 to 4.0% of functional additive; wherein the plasticizer comprises a plasticizer A and a plasticizer B, the plasticizer A is composed of nitroglycerin (NG) and butanetrioltrinitrate (BTTN), and the plasticizer B is one or two of butyl nitroxyethyl nitramine (Bu-NENA) and trimethylolethanetrinitrate (TMETN). The provided propellant can solve the problem that low burning rate and high energy cannot be achieved at the same time. The propellant has a low burning rate and high energy, and the standard static burning rate can reach 9 mm / s or lower.

Description

technical field [0001] The invention relates to a high-energy solid propellant formula for requiring high propellant energy and low burning rate, and belongs to the field of solid propellant. Background technique [0002] High-energy solid propellant is the power source of advanced strategic and tactical missile engines, and its performance directly affects the combat effectiveness and survivability of missile weapons. Due to the high energy, the high-energy solid propellant generally has the characteristics of high basic burning rate, while the long working time of advanced solid rocket motor requires its propellant to have a lower burning rate. In recent years, advanced solid rocket motors require high energy, high loading, and high mass ratio to require high-energy propellants with high elongation and high modulus. 10mm / s technical requirements. [0003] GAP / CL-20 high-energy solid propellant uses GAP as a binder and contains CL-20 explosives. The standard measured spec...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C06B33/06C06B33/04C06D5/06
CPCC06B33/04C06B33/06C06D5/06
Inventor 唐根庞爱民周晓杨吴芳徐海元宋会彬徐星星周水平李洪旭胡翔
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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