CN111925263B

CN111925263B - High-combustion-speed azide micro-smoke propellant and preparation process thereof

Info

Publication number: CN111925263B
Application number: CN202010524290.5A
Authority: CN
Inventors: 宋琴; 项丽; 徐海元; 尹必文; 李洋; 王艳萍; 吴京汉
Original assignee: Hubei Institute of Aerospace Chemical Technology
Current assignee: Hubei Institute of Aerospace Chemical Technology
Priority date: 2020-06-10
Filing date: 2020-06-10
Publication date: 2022-01-04
Anticipated expiration: 2040-06-10
Also published as: CN111925263A

Abstract

The invention provides a high-combustion-speed azide micro-smoke propellant and a preparation process thereof, wherein the propellant is prepared from the following raw material components in percentage by mass: adhesive: 5.2% -13%; an energy-containing plasticizer: 10% -20%; oxidizing agent: 35% -55%; energetic explosive: 15% -30%; nano burning rate catalyst: 2% -5.6%; a flame stabilizer: 0.5 to 1 percent; curing agent: 1% -2%; functional auxiliary agents: and (4) the balance. The invention carries out pre-dispersion treatment on a part of inert adhesive and the nano burning rate catalyst to form suspension, adds the pre-dispersed nano burning rate catalyst into the propellant, obviously improves the burning rate of the propellant, has the burning rate of 6.86MPa of more than or equal to 50mm/s, and greatly reduces the content of superfine or fine-grained oxidant in the formula under the condition of reaching the same burning rate, thereby greatly improving the process performance of the propellant and simultaneously reducing the safety risk in the production process of the propellant.

Description

High-combustion-speed azide micro-smoke propellant and preparation process thereof

Technical Field

The invention belongs to the technical field of solid propellants, and particularly relates to a high-combustion-speed azide micro-smoke propellant and a preparation process thereof.

Background

The new generation of antitank missiles, air defense missiles, interception missiles, high-speed kinetic energy missiles and the like have requirements on high energy, high burning speed, low characteristic signals and the like for a propellant system. The high-combustion-speed propellant can enable the solid rocket engine to generate larger thrust in a short time, meanwhile, the end face combustion charging of the rocket engine can be realized, the loading coefficient is increased, the loading amount is increased, the negative mass of the engine is reduced, and the range is increased. The azide propellant has the advantages of high energy, high burning speed of the body, clean fuel gas, low characteristic signals and the like, so that the azide propellant becomes the first choice of the current high-burning-speed high-energy low-smoke or micro-smoke propellant.

Generally, the method for improving the burning rate of the high-energy micro-smoke propellant mostly adopts the technical means of improving the content of fine-grained or ultrafine Ammonium Perchlorate (AP), adding a nanometer burning rate catalyst, improving the content of the nanometer burning rate catalyst, improving the solid content and the like. However, the contents of fine-grained solid filler and solid (mainly oxidant) in the components are high, so that the viscosity of the propellant in the mixing process and the discharged slurry is high, the phenomena of rapid increase of the temperature and the torque of the propellant are easy to occur when the propellant is mixed in a vertical mixer, and the safety risks of production and tests are greatly increased. Meanwhile, as the viscosity of propellant slurry is high, the nano burning rate catalyst is not uniformly dispersed in the propellant and is easy to agglomerate into small particles with the particle size of phi 1 mm-phi 3mm, and the flower plates are easy to block in the vacuum spraying and casting process, so that the casting requirement of a new generation of high-performance missile engine cannot be met. In addition, due to the agglomeration characteristic of the nano burning rate catalyst, after the addition amount of the nano burning rate catalyst in the propellant reaches a saturation amount, the burning rate of the propellant is basically unchanged along with the increase of the content of the nano burning rate catalyst, so that the addition amount of the nano burning rate catalyst is small or the burning rate catalysis efficiency of the nano burning rate catalyst is low, and the improvement range of the burning rate of the propellant is greatly limited.

In view of this, research is needed to solve the problems of low combustion rate catalytic efficiency, high production and test safety risks and poor process performance of the nano combustion rate catalyst in the high combustion rate and high energy micro-smoke propellant, so as to provide a high combustion rate azide micro-smoke propellant with controllable safety risks and excellent process performance and a preparation process thereof.

Disclosure of Invention

The invention aims to overcome the defects and safety risks in the prior art and provide a high-combustion-rate azide micro-smoke propellant with controllable safety risks and excellent process performance. The invention is completed by adding the predispersed nano burning rate catalyst into the propellant, reasonably selecting and optimally designing each component, content and parameter in the propellant, obviously improving the burning rate of the propellant, reducing the addition of superfine or fine-grained AP, further greatly improving the flow leveling property of the discharged propellant slurry and the safety performance in the production process, obtaining the raw material composition of the high-burning-rate high-energy micro-smoke propellant with good process performance, and meeting the technical requirements of a new generation of high-performance missile weapon system on high-energy micro-smoke propellant with high burning rate, safety, controllability and excellent process performance.

The technical scheme provided by the invention is as follows:

in a first aspect, the high-combustion-speed azide micro-smoke propellant is prepared from the following raw material components in percentage by mass:

adhesive: 5.2% -13%;

an energy-containing plasticizer: 10% -20%;

oxidizing agent: 35% -55%;

energetic explosive: 15% -30%;

nano burning rate catalyst: 2% -5.6%;

a flame stabilizer: 0.5 to 1 percent;

curing agent: 1% -2%;

functional auxiliary agents: and (4) the balance.

In a second aspect, a process for preparing a high-combustion-rate azide micro-smoke propellant, is used for preparing the high-combustion-rate azide micro-smoke propellant of the first aspect, and includes:

step 1, performing pre-dispersion treatment on part of inert adhesive and a nano burning rate catalyst according to a set proportion to obtain a pre-dispersed nano burning rate catalyst;

step 2, premixing the energy-containing adhesive and the energy-containing plasticizer before use to form uniform glue solution;

step 3, pre-dispersing the pre-dispersed nano burning rate catalyst, the functional assistant, the flame stabilizer, the inert adhesive and the glue solution before mixing, adding the pre-mixed material into a mixing pot, sequentially adding the energetic explosive, the oxidant and the curing agent, uniformly mixing at 50-60 ℃, and then pouring the slurry into an engine shell or a mold by using a vacuum pouring system;

and 4, curing the engine shell or the die after the slurry is poured at 45-55 ℃ for at least 5 days.

According to the high-combustion-speed azide micro-smoke propellant and the preparation process thereof provided by the invention, the high-combustion-speed azide micro-smoke propellant has the following beneficial effects:

(1) the invention pre-disperses a part of inert adhesive in the propellant and the nano burning rate catalyst according to a certain proportion to form a fine suspension with good flow leveling property and uniform dispersion, solves the problems of easy agglomeration and non-uniform dispersion of the nano burning rate catalyst in the propellant, and greatly improves the addition amount and the burning rate catalysis efficiency. Under the condition that the formula composition is unchanged and the nano burning rate catalyst with the same content is added into the propellant in a pre-dispersion mode, the burning rate of the propellant is obviously improved;

(2) in the invention, no new inert additive is introduced into the pre-dispersed nano burning rate catalyst, so that the energy performance and the mechanical property of the propellant are basically not influenced, and the rest components, contents and parameters in the propellant are optimally designed, so that the propellant not only has high burning rate, but also has excellent performances such as high energy, excellent mechanical property and the like;

(3) according to the technical scheme, the oxidizer AP with different grain size grading is adopted, so that the addition amount of the superfine or fine grain size AP can be obviously reduced, the technological performance of the propellant and the safety performance in the production process are greatly improved, and the high-energy micro-smoke propellant composition with high burning speed, controllable production safety risk and excellent technological performance is obtained.

Detailed Description

The features and advantages of the present invention will become more apparent and appreciated from the following detailed description of the invention.

The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration. Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments.

According to the first aspect of the invention, the high-burning-rate azide micro-smoke propellant is prepared from the following raw material components in percentage by mass:

adhesive: 5.2% -13%;

an energy-containing plasticizer: 10% -20%;

oxidizing agent: 35% -55%;

energetic explosive: 15% -30%;

nano burning rate catalyst: 2% -5.6%;

a flame stabilizer: 0.5 to 1 percent;

curing agent: 1% -2%;

functional auxiliary agents: and (4) the balance.

In the invention, the adhesive comprises an energy-containing adhesive and an inert adhesive, wherein the energy-containing adhesive is selected from any one or combination of polyazide glycidyl ether (GAP) or epoxy butane tetrahydrofuran azide Polyether (PBT); the inert adhesive is selected from any one or the combination of hydroxyl-terminated ethylene oxide-tetrahydrofuran copolyether (PET) or polyethylene glycol (PEG).

Furthermore, the mass ratio of the energy-containing adhesive to the inert adhesive is between 1.0 and 3.0. If the amount of energetic binder is low and below the minimum of the above range, low energy of the propellant results; if the amount of the energy-containing binder is higher than the maximum value of the above range, the amount of the inert binder is small, and a propellant having excellent mechanical properties cannot be obtained.

In the present invention, the energetic plasticizer is selected from any one of Nitroglycerin (NG), trimethylolethane trinitrate (TMETN), triethylene glycol dinitrate (TEGDN), butanetriol trinitrate (BTTN), or nitroxyethylnitramines (NENAs), or a combination thereof.

Furthermore, the plasticizing ratio (i.e. the mass ratio of the energetic plasticizer/the total amount of the binder) is between 1.0 and 3.0. If the energetic plasticizer is relatively low and is lower than the minimum value of the range, on one hand, the adhesiveness formed by premixing the adhesive and the energetic plasticizer is high, and on the other hand, the process performance of the prepared propellant is poor; if the energy-containing plasticization ratio is relatively high and is higher than the maximum value of the above range, the content of the adhesive is relatively low, that is, the concentration of the reactant of the crosslinking reaction in the propellant system is reduced, thereby affecting the network crosslinking reaction of the propellant system and causing poor mechanical properties of the propellant.

In the present invention, the oxidant is Ammonium Perchlorate (AP).

Further, the median diameter d of the oxidizing agent₅₀Is 1-300 μm. If the particle size is lower than the minimum value of the above range, on one hand, the process performance of the propellant is deteriorated, and on the other hand, as AP has moisture absorption property, the smaller the particle size is, the more moisture absorption is, and the network crosslinking reaction of the propellant is easily influenced due to the moisture absorption in the production and test processes; if the particle size is higher than the maximum value of the above range, the extent of increase in the burning rate of the propellant is limited.

Further, the oxidizer is divided into a fine-particle oxidizer and a coarse-particle oxidizer, the fine-particle oxidizer and the coarse-particle oxidizer are used as raw materials of the propellant, and the median particle diameter d of the fine-particle oxidizer₅₀1 to 10 mu m, the median diameter d of the coarse-grained oxidant₅₀Is 100-300 μm.

Furthermore, the mass ratio of the fine-grained oxidant to the coarse-grained oxidant is (1-2.3): 1.

In the present invention, the energetic explosive is selected from any one of or a combination of HMX, RDX, or CL-20.

In the invention, the nanometer burning rate catalyst is any one or the combination of lead salt, copper salt and oxides of lead, zinc, zirconium, iron and aluminum, wherein the median particle diameter d₅₀All are between 50nm and 100 nm. The particle size is important for the catalytic effect of the nano burning rate catalyst, and the inventor researches and discovers that the small particle size of the nano burning rate catalyst in the raw material components, which is lower than the minimum value of the range, can influence the dispersion uniformity of the nano burning rate catalyst; if the particle size of the nano burning rate catalyst in the raw material components is large and higher than the maximum value of the above range, the catalyst efficiency is lowered.

Further, the nano burning rate catalyst is used for preparing the propellant in a raw material state in a pre-dispersion treatment mode, and the pre-dispersion treatment comprises the following steps: mixing a part of inert adhesive in the adhesive with the nano burning rate catalyst according to a set proportion to form a fine suspension with good fluidity and uniform dispersion. Particularly, through research, the mass ratio of the inert adhesive to the nano burning rate catalyst in the pre-dispersed burning rate catalyst is 3/7-5/5. If the amount of the inert binder is small, a fine suspension cannot be formed; if the consumption of the inert adhesive is larger, the total content of the inert adhesive is unchanged after the formulation composition is fixed, and if the mass ratio of the inert adhesive to the nano burning rate catalyst is increased, the addition amount of the burning rate catalyst is reduced, so that the amplitude of increasing the burning rate of the propellant is reduced.

It is worth noting that the nano burning rate catalyst in the propellant can be added in higher content without aggravating agglomeration phenomenon and slurry viscosity/fluidity due to the pre-dispersion treatment of the nano burning rate catalyst. In the prior art, the addition amount of the nano burning rate catalyst accounts for about 1-2.5% of the propellant, but in the invention, the addition amount of the nano burning rate catalyst can reach 2.5-5% of the propellant, and the added nano burning rate catalyst can obviously improve the burning rate of the propellant.

In the invention, the combustion stabilizer is selected from high-melting-point zirconium carbide ZrC or one or more of the following high-melting-point metal oxides: titanium oxide TiO₂Magnesium oxide MgO, nickel oxide NiO, aluminum oxide Al₂O₃。

In the present invention, the curing agent is preferably any one or a combination of Tolylene Diisocyanate (TDI), polyfunctional isocyanate (N-100), and the like;

in the invention, the functional auxiliary agent comprises a curing catalyst, a stabilizer and a bonding agent, wherein the curing catalyst is preferably triphenyl bismuth TPB, the stabilizer is preferably N-methyl paranitroaniline (MNA), and the bonding agent is preferably a Neutral Polymer Bonding Agent (NPBA).

The high-combustion-speed nitrogen-laminated micro-smoke propellant has the combustion speed of more than or equal to 50mm/s at 6.86MPa under the condition of keeping higher energy and better mechanical property level, the yield value of the propellant discharged slurry and the yield value of the slurry after 5 hours are not more than 50Pa, the viscosity is not more than 400 Pa.s, and the technical requirements of a new generation of tactical missile engine on high-combustion speed and excellent technological property of the high-energy micro-smoke propellant are met.

According to a second aspect of the present invention, there is provided a process for preparing a high-combustion-rate azide-based micro-smoke propellant, for preparing the high-combustion-rate azide-based micro-smoke propellant according to the first aspect, comprising the following steps:

and 4, curing the engine shell or the die after the slurry is poured at 45-55 ℃ for at least 5 days, such as 5-7 days.

Examples

Example 1

The propellant composition is shown in table 1:

TABLE 1

Composition of raw materials	Quality (g)
		Polyazidoglycidyl ether GAP/hydroxy-terminated ethylene oxide-tetrahydrofuran copolyether PET	70/35
Nitro glycerin NG/triethylene glycol dinitrate TEGDN	79/79
		HMX (HMX)	200
Ammonium perchlorate AP (2 mu m)	100
		Ammonium perchlorate AP (7 mu m)	220
Ammonium perchlorate AP (130 μm)	155
		Nanometer burning rate catalyst (100nm)	30
Flame-retardant agent (Al)₂O₃)	10
		Curing agent (TDI)	13.1
Triphenylbismuth (TPB)	0.1
		N-methyl-p-nitroaniline (MNA)	6
Neutral Polymer Bonding Agent (NPBA)	2.8

The preparation process of 1kg of propellant is as follows:

step 1, performing pre-dispersion treatment on 30g of inert adhesive and 30g of nano burning rate catalyst to obtain a pre-dispersed nano burning rate catalyst; the mass ratio of the inert adhesive to the nano burning rate catalyst is 5/5;

step 2, premixing the energy-containing adhesive and the plasticizer to form uniform glue solution before use;

step 3, pre-dispersing the pre-dispersed nano burning rate catalyst, the functional assistant, the flame stabilizer, the inert adhesive and the glue solution before mixing, adding the pre-mixed material into a mixing pot, sequentially adding the energetic explosive, the oxidant, the curing agent and the like, uniformly mixing at 55 ℃, and pouring the slurry into a mold by using a vacuum pouring system;

and 4, placing the mixture in an oil bath oven at 50 ℃ for curing for 5 days.

The performance tests of the propellant obtained in the embodiment specifically comprise the tests of combustion performance and process performance, wherein the test standard of the combustion performance is GJB770B-2005 (gunpowder test method); the rheological properties of the propellant discharged slurry are characterized by a rotational viscometer (HAAKE, Germany) and the shear rate is mainly 1s^-1Viscosity (i.e., apparent viscosity) and shear rate of 1s^-1The fluidity and the leveling property of the propellant discharged slurry are respectively judged according to the maximum shear stress (namely the yield value).

The combustion and processing properties of the propellant are shown in table 2 below:

TABLE 2

As can be seen from Table 2, the combustion rate of the propellant 6.86MPa is 58.86mm/s, the yield value and the viscosity of the discharged slurry are 17.3Pa and 266.8Pa · s respectively, the propellant has better flow leveling property, and the yield value and the viscosity increase amplitude are not large along with the increase of time. Therefore, the azide micro-smoke propellant has the characteristics of high burning speed and excellent process performance.

Example 2

The propellant composition is shown in table 3:

TABLE 3

The preparation process of 1kg of propellant is as follows:

step 1, carrying out pre-dispersion treatment on 18g of inert adhesive and 40g of nano burning rate catalyst to obtain a pre-dispersed nano burning rate catalyst; the mass ratio of the inert adhesive to the nano burning rate catalyst is 3/6.7 (between 3/7-5/5);

steps 2 to 4 were the same as those in example 1.

The combustion and processing properties of the propellant are shown in table 4 below:

TABLE 4

As can be seen from Table 4, the burning rate of the propellant 6.86MPa is 63.15mm/s, the yield value and the viscosity of the discharged slurry are 22.1Pa and 259.2 Pa.s respectively, the flow leveling property is better, and the yield value and the viscosity increase amplitude are not large along with the increase of time. The azide micro-smoke propellant has the characteristics of high burning speed and excellent process performance.

Example 3

The propellant composition is shown in table 5:

TABLE 5

The preparation process of 1kg of propellant is as follows:

step 1, pre-dispersing 30g of inert adhesive and 50g of nano burning rate catalyst to obtain a pre-dispersed nano burning rate catalyst; the mass ratio of the inert adhesive to the nano burning rate catalyst is 3/5;

steps 2 to 4 were the same as those in example 1.

The combustion and processing properties of the propellant are shown in table 6 below:

TABLE 6

As can be seen from Table 6, the burning rate of the propellant 6.86MPa is 53.22mm/s, the yield value and the viscosity of the discharged slurry are respectively 20.5Pa and 246.9Pa · s, the flow leveling property is better, and the yield value and the viscosity increase amplitude are not large along with the increase of time. The azide micro-smoke propellant has the characteristics of high burning speed and excellent process performance.

Example 4

The propellant composition is shown in table 7:

TABLE 7

The preparation process of the propellant comprises the following steps:

step 1, pre-dispersing 20g of inert adhesive and 30g of nano burning rate catalyst to obtain a pre-dispersed nano burning rate catalyst; the mass ratio of the inert adhesive to the nano burning rate catalyst is 4/6;

steps 2 to 4 were the same as those in example 1.

The combustion and processing properties of the propellant are shown in table 8 below:

TABLE 8

As can be seen from Table 8, the burning rate of the propellant 6.86MPa is 55.42mm/s, the yield value and the viscosity of the discharged slurry are 23.3Pa and 263.1Pa · s respectively, the flow leveling property is good, and the yield value and the viscosity increase amplitude are not large along with the increase of time. The azide micro-smoke propellant has the characteristics of high burning speed and excellent process performance.

Example 5

The propellant composition is shown in table 9:

TABLE 9

Composition of raw materials	Quality (g)
		Butylene oxide tetrahydrofuran azide polyether PBT/hydroxyl-terminated ethylene oxide-tetrahydrofuran copolyether PET	73.4/36.6
Triethylene glycol dinitrate TEGDN/butyl nitroxyethyl nitramine Bu-NENA	72/72
		HMX (HMX)	200
High chlorineAmmonium acid AP (2 μm)	50
		Ammonium perchlorate AP (7 mu m)	280
Ammonium perchlorate AP (130 μm)	145
		Nanometer burning rate catalyst (100nm)	40
Flame-retardant agent (Al)₂O₃)	5
		Curing agent (N-100)	12.8
Triphenylbismuth (TPB)	0.2
		N-methyl-p-nitroaniline (MNA)	8
Neutral Polymer Bonding Agent (NPBA)	5

The preparation process of the propellant comprises the following steps:

step 1, pre-dispersing 30g of inert adhesive and 40g of nano burning rate catalyst to obtain a pre-dispersed nano burning rate catalyst; the mass ratio of the inert adhesive to the nano burning rate catalyst is 3/4;

steps 2 to 4 were the same as those in example 1.

The combustion and processing properties of the propellant are shown in table 10 below:

watch 10

As can be seen from Table 10, the burning rate of the propellant 6.86MPa is 52.36mm/s, the yield value and the viscosity of the discharged slurry are respectively 21.3Pa and 244.3Pa · s, the flow leveling property is better, and the yield value and the viscosity increase amplitude are not large along with the increase of time. The azide micro-smoke propellant has the characteristics of high burning speed and excellent process performance.

Example 6

The propellant composition is shown in table 11:

TABLE 11

Composition of raw materials	Quality (g)
		Polybutylene oxide-tetrahydrofuran azide polyether PBT/polyethylene glycol PEG	83.4/41.6
Trimethylolethane trinitrate TMETN/butylnitroxyethylnitramine Bu-NENA	62.5/62.5
		RDX of hexogen	180
Ammonium perchlorate AP (2 mu m)	60
		Ammonium perchlorate AP (5 mu m)	200
Ammonium perchlorate AP (130 μm)	240
		Nanometer burning rate catalyst (80nm)	35
Flame-retardant agent (Al)₂O₃)	8
		Curing agent (TDI)	13.7
Triphenylbismuth (TPB)	0.3
		N-methyl-p-nitroaniline (MNA)	8
Neutral Polymer Bonding Agent (NPBA)	5

The preparation process of the propellant comprises the following steps:

step 1, pre-dispersing 35g of inert adhesive and 35g of nano burning rate catalyst to obtain a pre-dispersed nano burning rate catalyst; the mass ratio of the inert adhesive to the nano burning rate catalyst is 5/5;

steps 2 to 4 were the same as those in example 1.

The combustion and processing properties of the propellant are shown in table 12 below:

TABLE 12

As can be seen from Table 12, the burning rate of the propellant 6.86MPa is 51.11mm/s, the yield value and the viscosity of the discharged slurry are 19.8Pa and 251.1Pa · s respectively, the flow leveling property is better, and the yield value and the viscosity increase amplitude are not large along with the increase of time. The azide micro-smoke propellant has the characteristics of high burning speed and excellent process performance.

Example 7

The propellant composition is shown in table 13:

watch 13

Composition of raw materials	Quality (g)
		Butylene oxide tetrahydrofuran azide polyether PBT/hydroxyl-terminated ethylene oxide-tetrahydrofuran	67.5/22.5
Triethylene glycol dinitrate TEGDN	70.5/70.5
		Hexanitrohexaazaisowurtzitane CL-20	200
Ammonium perchlorate AP (5 mu m)	250
		Ammonium perchlorate AP (130 μm)	245
Nano burning rate catalyst(50nm)	40
		Flame-retardant agent (Al)₂O₃)	5
Curing agent (TDI/N-100)	14.4
		Triphenylbismuth (TPB)	0.6
N-methyl-p-nitroaniline (MNA)	8
		Neutral Polymer Bonding Agent (NPBA)	6

The preparation process of the propellant comprises the following steps:

step 1, pre-dispersing 20g of inert adhesive and 40g of nano burning rate catalyst to obtain a pre-dispersed nano burning rate catalyst; the mass ratio of the inert adhesive to the nano burning rate catalyst is 1/2;

steps 2 to 4 were the same as those in example 1.

The combustion and processing properties of the propellant are shown in table 14 below:

TABLE 14

As can be seen from Table 14, the burning rate of the propellant 6.86MPa is 54.68mm/s, the yield value and the viscosity of the discharged slurry are 25.1Pa and 287.1Pa · s respectively, the propellant has better flow leveling property, and the yield value and the viscosity increase amplitude are not large along with the increase of time. The azide micro-smoke propellant has the characteristics of high burning speed and excellent process performance.

The invention has been described in detail with reference to specific embodiments and illustrative examples, but the description is not intended to be construed in a limiting sense. Those skilled in the art will appreciate that various equivalent substitutions, modifications or improvements may be made to the technical solution of the present invention and its embodiments without departing from the spirit and scope of the present invention, which fall within the scope of the present invention. The scope of the invention is defined by the appended claims.

Claims

1. The high-combustion-speed azide micro-smoke propellant is characterized by being prepared from the following raw materials in percentage by mass:

adhesive: 5.2% -13%;

an energy-containing plasticizer: 10% -20%;

oxidizing agent: 35% -55%;

energetic explosive: 15% -30%;

nano burning rate catalyst: 2% -5.6%;

a flame stabilizer: 0.5 to 1 percent;

curing agent: 1% -2%;

functional auxiliary agents: the balance;

the adhesive comprises an energy-containing adhesive and an inert adhesive;

the nano burning rate catalyst is used for preparing the propellant in a raw material state in a pre-dispersion treatment mode, and the pre-dispersion treatment comprises the following steps: mixing a part of inert adhesive in the adhesive with the nano burning rate catalyst according to a set proportion to form a suspension.

2. The propellant of claim 1, wherein the energetic binder is any one or a combination of polyazidyl glycidyl ether or butylene oxide tetrahydrofuran azide polyether.

3. The propellant of claim 1, wherein the inert binder is any one or a combination of a hydroxyl terminated ethylene oxide-tetrahydrofuran copolyether or polyethylene glycol.

4. The propellant of claim 1, wherein the mass ratio of energetic binder to inert binder is between 1.0 and 3.0.

5. The propellant of claim 1, wherein the energetic plasticizer is any one or a combination of nitroglycerin, trimethylolethane trinitrate, triethylene glycol dinitrate, or butanetriol trinitrate or nitrooxyethyl nitramine compounds.

6. The propellant of claim 1, wherein the mass ratio of the energetic plasticizer to the binder is between 1.0 and 3.0.

7. The propellant of claim 1 wherein the oxidizer is ammonium perchlorate and the median particle size of the oxidizer, d, is₅₀Is 1-300 μm.

8. The propellant of claim 7 wherein the oxidizer is divided into a fine particle oxidizer and a coarse particle oxidizer, the fine particle oxidizer and the coarse particle oxidizer together being the oxidizer of the propellant, the fine particle oxidizer having a median particle size, d₅₀1 to 10 mu m, the median diameter d of the coarse-grained oxidant₅₀Is 100-300 μm.

9. The propellant according to claim 8, wherein the mass ratio of the fine-particle-size oxidizer to the coarse-particle-size oxidizer is (1-2.3): 1.

10. The propellant of claim 1 wherein the energetic explosive is selected from any one or a combination of octogen, hexogen, or hexanitrohexaazaisowurtzitane.

11. The propellant of claim 1, wherein the nano burning rate catalyst is any one or combination of lead salt, copper salt and oxides of lead, zinc, zirconium, iron and aluminum;

median particle diameter d of nano burning rate catalyst₅₀Is 50nm to 100 nm.

12. The propellant according to claim 1, wherein the mass ratio of the inert binder to the nano burning rate catalyst in the pre-dispersion treated burning rate catalyst is between 3/7 and 5/5.

13. The propellant of claim 1, wherein the combustion stabilizer is zirconium carbide (ZrC), or one or more of the following metal oxides: titanium oxide TiO₂Magnesium oxide MgO, nickel oxide NiO, aluminum oxide Al₂O₃。

14. A process for preparing a high-burning-rate azide-based micro-smoke propellant, which is used for preparing the high-burning-rate azide-based micro-smoke propellant as claimed in any one of claims 1 to 13, and comprises the following steps: