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Low-vulnerability propellant and preparation method thereof

A technology of propellant and adhesive, which is applied in the field of low-fragile propellant and its preparation, can solve the problem that it is difficult to ensure the energy performance of the propellant, reduce the fragility of the propellant, the low fragility of the propellant and the inability to balance the energy, etc. The problem is to reduce the vulnerability response degree, improve the vulnerability response degree, and improve the mechanical properties.

Inactive Publication Date: 2020-08-28
HUBEI SANJIANG AEROSPACE JIANGHE CHEM TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0009] However, in many cases, the low vulnerability and energy of the propellant cannot be balanced. It is difficult to ensure that the propellant has excellent energy performance while reducing the vulnerability of the propellant.

Method used

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  • Low-vulnerability propellant and preparation method thereof
  • Low-vulnerability propellant and preparation method thereof
  • Low-vulnerability propellant and preparation method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0031] The specific formulation of the low-fragile propellant is shown in Table 1 below.

[0032] Table 1

[0033]

[0034]

[0035] The specific preparation method of the propellant is as follows:

[0036] First premix the adhesive and bonding agent at 60±2℃ for 30~60min, then add plasticizer, curing catalyst and fuel to mix evenly at room temperature; then add explosive and mix at 55±2℃ for 10~20min , then add oxidant and mix at 55±2℃ for 30~60min, finally add curing agent and mix at 55±2℃ for 20~30min.

[0037] After the uniformly mixed mixture slurry is vacuum poured into the engine at 55±2°C, the low-fragile propellant is cured and formed at a curing temperature of 60±2°C and a curing time of 6-8 days.

[0038] In the preparation process of low-fragile propellants, vertical mixers are generally used for mixing, and a vacuum casting system is used to realize the production of engine grains. The oxidant should be added in batches to avoid adding too much at one tim...

Embodiment 2

[0051] (1) The specific formula of the low-fragile propellant is shown in Table 4 below. The specific preparation method is the same as in Example 1.

[0052] Table 4

[0053]

[0054] (2) Properties of propellant:

[0055] 1) Measured specific impulse Isp of propellant: 245.8s (6.86MPa, 20℃);

[0056] 2) Propellant density ρ: 1.750g / cm 3 ;

[0057] 3) The propellant burning rate is 10.0mm / s (6.86MPa)

[0058] 4) The mechanical properties of the propellant are shown in Table 5.

[0059] table 5

[0060]

[0061] 5) See Table 6 for the fragility of the propellant.

[0062] Table 6

[0063] Pilot projects burn quickly slow burn bullet impact Fragment impact martyrdom jet impingement response level combustion combustion lower than burn lower than burn deflagration deflagration in conclusion pass pass pass pass pass pass

Embodiment 3

[0065] (1) The specific formulation of the low-fragile propellant is shown in Table 7 below. The specific preparation method is the same as in Example 1.

[0066] Table 7

[0067]

[0068]

[0069] (2) Properties of propellant:

[0070] 1. The measured specific impulse Isp of the propellant: 245.0s (6.86MPa, 20℃);

[0071] 2. Propellant density ρ: 1.766g / cm 3 ;

[0072] 3. The propellant burning speed is 6.0mm / s (6.86MPa)

[0073] 4. The mechanical properties of the propellant are shown in Table 8.

[0074] Table 8

[0075]

[0076] 5. See Table 9 for propellant fragility.

[0077] Table 9

[0078] Pilot projects burn quickly slow burn bullet impact Fragment impact martyrdom jet impingement response level combustion combustion lower than burn combustion deflagration deflagration in conclusion pass pass pass pass pass pass

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Abstract

The invention discloses a low-vulnerability propellant and a preparation method thereof. The solid content of the propellant is 75.0-77.0%, and the propellant specifically comprises, by weight, 7.92-8.95 parts of an adhesive, 13.0-15.50 parts of a plasticizer, 47-57 parts of an oxidizing agent, 18-20 parts of a fuel, 5-8 parts of an explosive, 0.2-0.35 part of a bonding agent and 0.80-1.10 parts of a curing agent, and a curing catalyst accounting for 0.05-0.2% of the total mass of the components is also added. The propellant disclosed by the invention takes the insensitive adhesive and the low-sensitivity plasticizer as matrixes, and the oxidizing agent, the metal fuel and the explosive are used in the formula, so the solid content, the oxidizing agent and the explosive are reduced, the formula has high energy, moderate combustion speed and good mechanical properties, and the low-vulnerability requirements of weapons and ammunition are met through six low-vulnerability test assessmentsof quick baking, slow baking, sympathetic detonation, bullet impact, fragment and jet impact.

Description

technical field [0001] The invention relates to the technical field of propellants, in particular to a low-fragile propellant and a preparation method thereof. Background technique [0002] As an important component of ammunition and the danger of its own energetic materials, the vulnerability of solid propellant has a crucial impact on the vulnerability of the entire weapon system, so the vulnerability of solid propellant is more and more vulnerable. of attention. Low vulnerability engines require weapons and ammunition to not cause more violent reactions than combustion when encountering unexpected heat, impact, charge, shock waves and other stimuli; require tactical weapon systems to comply with low vulnerability military standards and carry out rapid roasting , slow roasting, bullet impact (gunshot), fragment impact, detonation and jet six low vulnerability test evaluation. [0003] At present, the vulnerability of propellants is reduced mainly through the following te...

Claims

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Application Information

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IPC IPC(8): C06B33/06C06B23/00C06B45/10C06D5/06
CPCC06B23/00C06B33/06C06B45/10C06D5/06
Inventor 王晓倩邓安华牛草坪甘露李洋张习龙孙丽娜刘佳胡晓亮
Owner HUBEI SANJIANG AEROSPACE JIANGHE CHEM TECH
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