A high-energy solid propellant

A solid propellant, high-energy technology, applied in the direction of offensive equipment, compressed gas generation, non-explosive/non-thermal agent components, etc., can solve the problems of limited application, low elongation, high glass transition temperature, etc., and achieve low-temperature mechanical properties Improvement, lower glass transition temperature, widen the effect of application range

Active Publication Date: 2021-07-13
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In azide polyether (GAP (polyazide glycidyl ether), BAMO (3,3-bis (azidomethyl) butylene oxide copolyether), AMMO (3-methyl-3-azidomethyl Butylene oxide copolyether) and other) high-energy and low-signature propellants use insensitive explosive FOX-7 to replace conventional explosives such as HMX or RDX in the formula. , AMMO and other azide binders have a high glass transition temperature, usually above -40°C, causing the propellant to basically be in a brittle glass state below -50°C, and the elongation is extremely low, which limits its wide adaptability. Applications in Tactical Missiles

Method used

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  • A high-energy solid propellant
  • A high-energy solid propellant
  • A high-energy solid propellant

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0032] (1) The propellant formula composition (mass percentage) is shown in Table 1-1:

[0033] Table 1-1 Propellant formulation

[0034]

[0035] According to the above formula, the raw materials are weighed and mixed by a vertical mixer. The mixture of binder and plasticizer is pre-mixed to form a homogeneous liquid, referred to as glue. In the mixer, first add Al powder, neutral polymer bonding agent, stabilizer, curing catalyst and 70% glue mixture and mix for 10 minutes, then add HMX or FOX-7 and mix for 15 minutes, then add AP and mix for 30 minutes, and finally add curing The mixture of propellant and 30% glue is mixed for 20 minutes at a mixing temperature of 55°C±2°C. After the propellant slurry is discharged, it is poured into the mold through a vacuum pouring tank, and finally placed in an oil bath oven at 50°C for 7 days to be propelled. The preparation method of each subsequent embodiment is the same as that of this embodiment.

[0036] (2) The comprehensive...

Embodiment 2

[0042] (1) The propellant formula composition (mass percentage) is shown in Table 1-2:

[0043] Table 1-2 Propellant formulation

[0044]

[0045] (2) The overall performance of the propellant is shown in Table 2-2:

[0046] Table 2-2 Propellant Performance Parameters

[0047]

[0048] Signal characteristics: visible light transmittance of propellant plume is 65.6%, laser transmittance is 73.9%, near-infrared transmittance is 82.4%, mid-infrared transmittance is 84.9%, far-infrared transmittance is 90.4%, microwave attenuation is 0.34dB, The middle and far infrared radiation intensity of plume flame is 70% and 90% lower than that of 18.5% Al butylated hydroxyl propellant.

Embodiment 3

[0050] (1) The propellant formula composition (mass percentage) is as shown in Table 1-3:

[0051] Table 1-3 Propellant formulation

[0052]

[0053] (2) The combustion performance of the propellant is shown in Table 2-3:

[0054] Table 2-3 Propellant Performance Parameters

[0055]

[0056] Signal characteristics: Propellant plume visible light transmittance 75.5%, laser transmittance 87.1%, near-infrared transmittance 87.6%, mid-infrared transmittance 94.2%, far-infrared transmittance 98.6%, microwave attenuation 0.27dB, The middle and far infrared radiation intensity of the plume flame is 73% and 95% lower than that of the 18.5% Al butylated hydroxyl propellant.

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Abstract

The invention provides a high-energy solid propellant and belongs to the technical field of propellants. The propellant raw material includes the following components in mass percentage: 45%-59% of ammonium perchlorate, 0-5% of aluminum powder, 18%-35% of explosive, 1.29%-1.64% of curing agent, and 0.91% of functional auxiliary agent ‑1.91%, energetic plasticizer 11.07%~12.60%, and binder 4.11%~5.93%, wherein, the binder is azide glycidyl ether and tetrahydrofuran copolyether or 3,3-bis(azide Methyl) butylene oxide and tetrahydrofuran copolyether, the energetic plasticizer is nitroglycerin, butanetriol trinitrate, trimethylolethane trinitrate, triethylene glycol dinitrate A mixture of N-butyl-2-ethyl ammonium nitrate. On the premise of maintaining the high specific impulse and low characteristic signal performance of the original propellant, the present invention reduces the vitrification temperature of the propellant and improves the high and low temperature mechanical properties of the propellant, thereby broadening its use temperature range, and at the same time further improving the propellant safety performance.

Description

technical field [0001] The invention relates to a high-energy solid propellant and belongs to the technical field of solid propellants. Background technique [0002] General-purpose missiles and multi-purpose tactical missiles for the land, sea and air forces are currently a type of tactical weapon that countries around the world focus on developing. These missiles have the characteristics of high survival, strong penetration, long-range precision strikes, and adaptability to a wide range of working environments. The propellant used as the power source of the missile needs to take into account a wide range of temperature application and good safety performance while satisfying high specific impulse and low characteristic signal. Affected by my country's terrain, which is high in the west and low in the east, and has a large span between the north and the south, missile engines are usually required to work reliably in an environment of -60°C to +70°C, so the propellant is req...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C06B33/08C06B23/00C06D5/06
CPCC06B23/001C06B23/009C06B33/08C06D5/06
Inventor 尹必文宋琴吴京汉项丽徐海元顾健代志高王艳萍
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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