阅读说明：本技术 低易损推进剂及其制备方法 (Low-vulnerability propellant and preparation method thereof ) 是由 王晓倩 邓安华 牛草坪 甘露 李洋 张习龙 孙丽娜 刘佳 胡晓亮 于 2020-05-20 设计创作，主要内容包括：本发明公开了一种低易损推进剂及其制备方法,该推进剂的固含量在75.0~77.0%,具体包括按重量计的以下组分：粘合剂7.92~8.95份；增塑剂13.0~15.50份；氧化剂47~57份；燃料18~20份；炸药5~8份；键合剂0.2~0.35份；固化剂0.80~1.10份,此外,还加上述组分总质量0.05~0.2%的固化催化剂。本发明的推进剂以钝感粘合剂和低感增塑剂为基体,在配方中使用了氧化剂、金属燃料、炸药,降低固含量、氧化剂和炸药,配方具备较高的能量,适中的燃速,良好的力学性能,通过快烤、慢烤、殉爆、子弹撞击、破片、射流冲击六项低易损性试验考核,满足武器弹药的低易损要求。(The invention discloses a low-vulnerability propellant and a preparation method thereof, wherein the solid content of the propellant is 75.0-77.0%, and the propellant specifically comprises the following components in parts by weight: 7.92-8.95 parts of an adhesive; 13.0-15.50 parts of a plasticizer; 47-57 parts of an oxidant; 18-20 parts of fuel; 5-8 parts of explosive; 0.2-0.35 parts of bonding agent; 0.80-1.10 parts of curing agent, and in addition, 0.05-0.2% of curing catalyst by mass of the components is added. The propellant disclosed by the invention takes a insensitive adhesive and a low-sensitivity plasticizer as substrates, an oxidant, a metal fuel and an explosive are used in a formula, so that the solid content, the oxidant and the explosive are reduced, the formula has higher energy, moderate burning rate and good mechanical property, and the low-vulnerability test tests of six items of fast baking, slow baking, sympathetic explosion, bullet impact, fragment and jet impact meet the low-vulnerability requirement of weapon ammunition.)

1. The low-vulnerability propellant is characterized in that the solid content of the propellant is 75.0-77.0%, and the propellant comprises the following components in parts by weight: 7.92-8.95 parts of an adhesive; 13.0-15.50 parts of a plasticizer; 47-57 parts of an oxidant; 18-20 parts of fuel; 5-8 parts of explosive; 0.2-0.35 parts of bonding agent; 0.80-1.10 parts of curing agent, and in addition, 0.05-0.2% of curing catalyst by mass of the components is added.

2. The low vulnerability propellant of claim 1, characterized in that: the adhesive is one of hydroxyl-terminated ethylene oxide-tetrahydrofuran copolyether, hydroxyl-terminated ethylene oxide-tetrahydrofuran block copolyether and hydroxyl-terminated polytetrahydrofuran-caprolactone block copolyether.

3. The low vulnerability propellant of claim 1, characterized in that: the plasticizer is a mixture of bis-2, 2-dinitropropanol acetal and bis-2, 2-dinitropropanol formal in a mass ratio, and one or a combination of N-butyl nitrooxyethyl ammonium nitrate and 2, 2-dinitropropanol hexanoate.

4. The low vulnerability propellant of claim 1, characterized in that: the oxidant is ammonium perchlorate, one or a combination of more of type I, type II, type III or other types of AP is adopted, and the granularity of the other types of AP is less than 20 mu m.

5. The low vulnerability propellant of claim 1, characterized in that: the fuel is aluminum powder, and the aluminum powder is one or a combination of more of FLQT1 or FLQT2 or FLQT3 or FLQT6 aluminum powder.

6. The low vulnerability propellant of claim 1, characterized in that: the explosive is octogen or hexogen.

7. The low vulnerability propellant of claim 1, characterized in that: the bonding agent is one or a combination of more of triethanolamine and boron trifluoride complex, neutral bonding agent, tris [1- (2-methyl) aziridinyl ] phosphine oxide and triethanolamine.

8. The low vulnerability propellant of claim 1, characterized in that: the curing agent is one or more of toluene diisocyanate, isophorone diisocyanate and modified hexamethylene polyisocyanate; the curing catalyst is triphenyl bismuth or dibutyltin dilaurate.

9. The low vulnerability propellant according to any of claims 1-8, characterized in that: the propellant comprises the following components in parts by weight: 8.45-8.8 parts of an adhesive; 13.10-15.20 parts of a plasticizer; 47-52 parts of an oxidant; 18-20 parts of fuel; 5-8 parts of explosive; 0.25-0.3 part of bonding agent; 0.9-1.0 part of curing agent and curing catalyst accounting for 0.1 percent of the total mass of the components.

10. A method of making the low vulnerability propellant of any of claims 1-9, characterized by comprising the steps of:

1) premixing the adhesive and the bonding agent at 60 +/-2 ℃ for 30-60 min, adding the plasticizer, the curing catalyst and the fuel after uniformly mixing, and uniformly mixing at room temperature;

2) adding the explosive in the step 1), mixing for 10-20 min at 55 +/-2 ℃, adding the oxidant, mixing for 30-60 min at 50 +/-2 ℃, and finally adding the curing agent, mixing for 20-30 min at 55 +/-2 ℃;

3) and (3) pouring the uniformly mixed mixture slurry into an engine at 55 +/-2 ℃ in vacuum, and curing and forming at the curing temperature of 60 +/-2 ℃ for 6-8 days to obtain the low-vulnerability propellant.

Technical Field

The invention relates to the technical field of propellants, in particular to a low-vulnerability propellant and a preparation method thereof.

Background

The danger of solid propellants as important component parts of ammunition and as energetic materials of the ammunition, the vulnerability of which has a crucial influence on the vulnerability of the entire weapon system, is increasingly appreciated. Low vulnerability engines require weapons munitions to not cause reactions more severe than combustion when subjected to unexpected stimuli such as heat, shock, charge, shock waves, and the like; tactical weapon systems are required to meet low vulnerability military standards and six low vulnerability test evaluations of fast fire, slow fire, bullet impact (gunshot), fragment impact, sympathetic explosion and jet are developed.

At present, the vulnerability of the propellant is mainly reduced by several technical approaches:

1) a low-feel adhesive and a low-feel energetic plasticizer are adopted;

2) using a low sensitivity nitramine compound;

3) adopting a novel high-energy oxidant;

4) reducing the particle size and defects of the solid components in the propellant, changing the shape of the solid particle size;

5) low sensitivity explosives are substituted for the oxidizer.

However, in many cases, the low vulnerability of the propellant cannot be compatible with the energy, and it is difficult to ensure that the propellant has excellent energy performance while reducing the vulnerability of the propellant.

Disclosure of Invention

The invention provides a low-vulnerability propellant and a preparation method thereof, the propellant takes a insensitive adhesive and a low-sensitivity plasticizer as a matrix, an oxidizer, a metal fuel and an explosive are used in a formula, the solid content and the using amount of the oxidizer are reduced, and the formula has higher energy, moderate burning speed and good mechanical property and meets the low-vulnerability requirement of weapon ammunition.

The technical scheme of the invention is that the low-vulnerability propellant has a solid content of 75.0-77.0%, and comprises the following components in parts by weight: 7.92-8.95 parts of an adhesive; 13.0-15.50 parts of a plasticizer; 47-57 parts of an oxidant; 18-20 parts of fuel; 5-8 parts of explosive; 0.2-0.35 parts of bonding agent; 0.80-1.10 parts of curing agent, and in addition, 0.05-0.2% of curing catalyst by mass of the components is added.

Further, the adhesive is one of hydroxyl-terminated ethylene oxide-tetrahydrofuran copolyether (PET), hydroxyl-terminated ethylene oxide-tetrahydrofuran block copolyether (HTPE) and hydroxyl-terminated polytetrahydrofuran-caprolactone block copolyether (HTCE).

Further, the plasticizer is one or a combination of several of a mixture (BDNPF/A) of bis-2, 2-dinitropropanol acetal and bis-2, 2-dinitropropanol formal in equal mass ratio, N-butyl nitrooxyethyl ammonium nitrate (BunNA) and 2, 2-dinitropropanol N-hexanoate (DNPH).

Further, the oxidant is Ammonium Perchlorate (AP), one or a combination of more of type I, type II, type III or other types of AP is adopted, and the particle size of other types of AP is less than 20 mu m.

Further, the fuel is aluminum powder (Al), and the aluminum powder is one or a combination of more of FLQT1, FLQT2, FLQT3 and FLQT6 aluminum powder.

Further, the explosive is octogen (HMX) or hexogen (RDX).

Further, the bonding agent is one or a combination of triethanolamine and boron trifluoride complex (LBA303), neutral bonding agent (NPBA), tris [1- (2-methyl) aziridinyl ] phosphine oxide (MAPO), and Triethanolamine (TEA).

Further, the curing agent is one or more of Toluene Diisocyanate (TDI), isophorone diisocyanate (IPDI) and modified hexamethylene polyisocyanate (N-100).

Further, the curing catalyst is triphenyl bismuth (TPB) or dibutyltin dilaurate (DY-12).

The invention also relates to a method for preparing the low-vulnerability propellant, which comprises the following steps:

1) premixing the adhesive and the bonding agent at 60 +/-2 ℃ for 30-60 min, adding the plasticizer, the curing catalyst and the fuel after uniformly mixing, and uniformly mixing at room temperature;

2) adding the explosive in the step 1), mixing for 10-20 min at 55 +/-2 ℃, adding the oxidant, mixing for 30-60 min at 50 +/-2 ℃, and finally adding the curing agent, mixing for 20-30 min at 55 +/-2 ℃;

3) and (3) pouring the uniformly mixed mixture slurry into an engine at 55 +/-2 ℃ in vacuum, and curing and forming at the curing temperature of 60 +/-2 ℃ for 6-8 days to obtain the low-vulnerability propellant.

The invention has the following beneficial effects:

(1) in the low-vulnerability propellant, the type of the adhesive, the type of the plasticizer, the solid content and the dosage of the nitramine explosive of the components influence the vulnerability response degree of the propellant. Meanwhile, the excellent mechanical property also helps to reduce the vulnerability. The invention selects and optimally designs each component and content of the component propellant, and the adhesive is insensitive HTPE, PET and HTCE, which is helpful for inhibiting the combustion surface expansion caused by low-temperature decomposition of AP. The thermal decomposition temperature of the selected plasticizers BDNPF/A, BunENA and DNPH is before AP low-temperature decomposition, gas released by the plasticizer reaction is beneficial to breaking away the shell constraint, the improvement of vulnerability response degree caused by energy aggregation during AP low-temperature decomposition is reduced, meanwhile, the energy content of the plasticizer is reduced, the dosage of nitramine explosive and AP can be reduced under the condition of reducing solid content, and the formula is guaranteed to have higher energy performance. The solid content of the propellant is low, the dosage of AP is far lower than that of a general hydroxyl propellant formula, so that the vulnerability response degree increase caused by the energy released by the violent reaction of AP is reduced. The content of the nitramine explosive is low, the low-temperature decomposition peak of the nitramine explosive is close to that of AP, the addition of the nitramine explosive can promote the low-temperature decomposition of AP, so that the vulnerability response degree is improved, and the nitramine explosive is cancelledThe energy performance of the formula is reduced, so that the energy performance and the low vulnerability performance are combined, and the content of the nitramine explosive is reasonably controlled. The formula uses two bonding agents for compounding, and is helpful for improving the mechanical property of a low-vulnerability propellant high-swelling system. According to the dual-curing system and the single-curing system disclosed by the invention, the formulas of the two curing systems can achieve excellent mechanical properties, and the dual-curing system is less used in the conventional propellant. The plasticizer DNPH used in the formula has a low glass transition temperature, and when the plasticizer DNPH is compounded with BDNPF/A or BunNA, the temperature application range of the propellant can be expanded on the basis of ensuring energy and reducing vulnerability. In addition, by adopting a proper proportion, the invention can give consideration to both low vulnerability and excellent energy performance, and the energy performance of the invention is equivalent to that of HTPB propellant. In addition, the combustion performance of the formula can be adjusted within a certain range by adjusting the particle size distribution of the formula. The solid propellant obtained by the invention can give consideration to excellent energy performance and safety performance, and has higher energy through six low-vulnerability tests, the measured specific impulse Isp is more than or equal to 245s (6.86MPa, 20 ℃), and the density rho of the propellant is more than or equal to 1.750g/cm³。

(2) The solid propellant has good normal, high and low temperature mechanical properties, and can meet the use requirements of engines of most models. The normal temperature tensile strength is more than or equal to 0.75MPa, and the normal temperature, high temperature and low temperature elongation is more than or equal to 40 percent.

(3) The burning rate of the solid propellant is adjustable between 6 and 10mm/s (6.86MPa), and the burning performance of the propellant can meet the requirements of advanced missiles and tactical missiles on the burning performance.

(4) The low-vulnerability propellant prepared by the invention has moderate energy performance and passes six low-vulnerability tests. Meanwhile, the propellant has moderate burning speed and good high-low temperature mechanical property, and meets the requirements of low vulnerability and high energy.

Detailed Description

Embodiments of the present invention will be described in detail below with reference to examples, but those skilled in the art will appreciate that the following examples are only illustrative of the present invention and should not be construed as limiting the scope of the present invention.