JPH08240309A - Treatment of pocket propellant and bursting charge - Google Patents

Abstract

PURPOSE: To provide this treatment wherein a rocket propellant and bursting charge are extremely safe so as to be burnt in the same manner as normal domestic waste, by changing the sensitivity and property of them, and the workability and efficiency of their treatment are remarkably heightened so that a large amount of them can be treated in a short time. CONSTITUTION: This treatment comprises a mixing or impregnating process and a combustion process. In the former process, a combustion retardant comprising any one or more mixtures of mineral oil, animal oil, vegetable oil, or these waste oil or polyhydric alcohol such as glycerin and ethylene glycol is mixed with a rocket propellant and a bursting charge which are cut or crushed in powder and grain shape, in shred shape, in tape shape, in belt shape, or in cord shape, or is permeated therein. In the latter process, the rocket propellant and the bursting charge with or in which the combustion retardant is mixed or permeated, in the former process, is burnt.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a method for treating rocket propellants and explosives, which disposes of rocket propellants and explosives that have been desensitized from missiles, shells and the like that have arisen from manufacturing processes or are no longer needed. , Rocket propellants, explosives, etc. are burned slowly in the incinerator, which is extremely safe and does not cause physical or human damage to the inside or outside of the furnace due to explosion or sudden combustion, and it can be processed efficiently in a short time. It relates to a method of processing rocket propellants and explosives that can be done.

[0002]

2. Description of the Related Art In recent years, various methods for treating dangerous substances such as rocket propellants and explosives have been researched and developed with a focus on safety and environment. The conventional methods for treating rocket propellants and explosives will be described below. (1) A method in which rocket propellant, explosive charge, etc. are packed in concrete in a container and dumped into the ocean. (2) A method of burning rocket propellants or explosives in the atmosphere by using a place with a large space such as a vacant lot. (3) In order to prevent the rocket propellant and explosive charge from exploding and damaging and destroying the combustion furnace, the amount of rocket propellant and explosive charge to the combustion furnace is controlled by a computer while measuring the temperature inside the combustion furnace. Meanwhile, a method of charging rocket propellant or explosive charge into a combustion furnace and burning it. (4) A method of chemically degrading rocket propellants, explosives, etc. by supercritical fluid oxidation, biodegradation, etc. to eliminate explosive properties. (5) In addition, Japanese Patent Application Laid-Open No. 5-279160 (hereinafter referred to as “A”) describes “A method for desensitizing a solid propellant composition, in order to form a desensitized composition, The solid propellant composition and the following components: (a) at least about 600
Comprising combining an oil having a viscosity of centipoise and (b) a solid particulate material selected from the group consisting of wood flour, nut shell particles, grain flour, starch and corn cob particles, wherein The impact sensitivity and at least about 25% of the components (a) and (b) in the desensitized composition are less than about 25% of the impact sensitivity of the solid propellant composition in the desensitized composition. A method characterized by being sufficient to impart a flame temperature of 1000 ° F. Is disclosed.

[0003]

However, the conventional rocket propellant and explosive charge treating methods described above have the following problems. (1) It has been pointed out that incineration / explosion processing and ocean dumping at open treatment plants using open land on land are not preferable from the viewpoint of atmospheric and ocean environmental pollution. (2) The method of directly burning the rocket propellant and explosive charge in the combustion furnace requires measures against high temperature and explosive combustion. That is, there is a risk that a high-temperature flame will be generated during combustion, which may cause wear of the combustion furnace.Therefore, various characteristics of the explosive to be incinerated to prevent this (ease of explosion, explosive power, combustion temperature, calorific value, decomposition rate) Computer control must be performed according to the requirements, and therefore complicated mechanisms and devices were required. Also, in order to eliminate the risk of explosion, negative pressure is applied to the inside of the combustion furnace and the furnace path, the amount of incineration is managed so that a large amount of lumps are not formed at one time, and a great deal of effort is required to control the temperature inside the furnace outside the danger zone. And required equipment. Furthermore, in the unlikely event of an electrical or mechanical failure, there is a danger of equipment or human damage due to explosion or combustion that deviates from the limit of control, which is a work hazard. Had. (3) The method of chemically modifying rocket propellants and explosives to eliminate their explosive properties is still at the stage of technological development, and at present, a large amount of rocket propellants and explosives cannot be treated in a short time. It had a problem of low processing efficiency. (4) In the treatment method described in JP-A-B, since the propellant, the oil, and the solid particulate matter are uniformly mixed, the mixture is molded into a predetermined shape and the molded article is burned. Therefore, the mixing step, the molding step, and the burning step are performed. There is a problem that a process is required, a large amount of equipment, labor and time are required, workability is poor, and processing efficiency is poor.

The present invention solves the above-mentioned conventional problems by changing the sensitivity and combustion characteristics of rocket propellants and explosives by impregnating or mixing oils or polyhydric alcohols with rocket propellants and explosives. Rocket propellants and explosives are put into a combustion furnace and modified so that they can be burned. They are extremely safe and can process large amounts in a short time, which is almost the same as ordinary household waste. It is intended to provide a method for treating rocket propellants and explosives.

[0005]

To achieve this object, the present invention has the following constitution. A method for treating rocket propellant or explosive charge according to claim 1 is a mineral oil, an animal oil,
A vegetable oil, or a waste oil thereof, or a combustion retardant consisting of a mixture of one or more of polyhydric alcohols such as glycerin and ethylene glycol, in the form of powder, granules, shreds, tapes, strips or cords. A mixing / impregnation process of mixing or impregnating the rocket propellant or explosive that has been cut or crushed into a mixture, and a combustion process of burning the rocket propellant or explosive mixed or impregnated with the combustion retardant in the mixing / impregnation process. It has the composition which has. The method for treating a rocket propellant or explosive charge according to claim 2 is the method according to claim 1, wherein the combustion retardant is mixed or impregnated in the rocket propellant or explosive charge in an amount of 3 to 90 wt%, preferably 10 to 70 wt%. It has a configuration that is configured. According to a third aspect of the present invention, there is provided a method for treating a rocket propellant or explosive charge according to any one of the first or second aspects, wherein the combustion retardant contains water and / or a surfactant. A method for treating a rocket propellant or explosive charge according to claim 4 is the method according to any one of claims 1 to 3, wherein the combustion retardant has a viscosity of 0.3 to 50.
It has a configuration that is 0 centipoise. According to a fifth aspect of the present invention, there is provided a method for treating a rocket propellant or explosive charge according to any one of the first to fourth aspects, wherein the rocket propellant is a composite propellant. The rocket propellant and explosive charge treating method according to claim 6 is the method according to any one of claims 1 to 5.
In any one of the above, the composite propellant contains ammonium perchlorate as a main component and has an average thickness of 0.01
It has a configuration that is a cut product that is cut into a tape shape or a band shape of about 5 mm. A method for treating a rocket propellant or explosive charge according to claim 7 is the method according to any one of claims 1 to 4, wherein the explosive charge is cut and crushed to have an average particle size of 0.001 to 5 mm, preferably an average particle size. Diameter 0.00
1-3 mm, more preferably 0.001-average particle size
It has a structure which is a cut product in the form of a 1.5 mm powder or granule.

Examples of rocket propellants include double base propellants, composite propellants, composite double base propellants, and rocket ram propellants. Composite propellants include oxidizers such as perchlorates and nitrates, synthetic resins that are fuel and solid component binders, metal powders such as aluminum, and other minor components such as curing agents, curing catalysts, combustion catalysts, plasticizers. It is obtained by adding agents, surfactants, stabilizers, etc., and curing and molding. The objects to be processed by the rocket propellant include surplus and defective products generated in the manufacturing process, and those taken out from the rocket motor whose service life has expired. When used in the present invention, cutting is performed by a mechanical method using a lathe or the like, a method of shaving with a high water pressure jet, a method of freezing to extremely low temperature with liquid nitrogen or the like, and then crushing. In particular, the composite propellant has a thickness of 0.05 to 5 mm, preferably 0.
What is cut to 1 to 3 mm is used. If the thickness is less than 0.1 mm, cutting and cutting become difficult and workability tends to be poor, which is not preferable. Also, the thickness is 3m
When it exceeds m, the impregnation time of the combustion retardant exceeds several tens of hours, the impregnation workability is poor, and the combustion retardant is not sufficiently impregnated to the deep part of the propellant. Absent.

The explosive charge refers to explosives that are usually filled in shells and destroy the shell, and usually include nitrates, nitro compounds, furoxane, nitramine, amine nitrates as a single substance or a mixture or eutectic. Explosive wastes include powder, solid blocks,
Examples include powders and solid blocks eluted from shells. As a method of taking out these explosives, a method of cutting and crushing after elution and solidification from the shell of a shell, a method of crushing with a high pressure jet, a method of crushing after freezing to extremely low temperature with liquid nitrogen etc. are used. , Average particle size is 7m
m or less, preferably 0.001 to 5 mm, more preferably 0.001 to 3 mm, and more preferably 0.001 to 1.
It is cut and crushed to 5 mm. As the particle size exceeds 1.5 mm, explosive properties remain, but the burning rate tends to be high and the burning temperature tends to be high, depending on the type of explosive, and as the particle size exceeds 3 mm, it takes time to impregnate the combustion retardant and uneven impregnation occurs. This is not preferred because it tends to occur and tends to lack safety.

As the combustion retardant, mineral oil, animal oil, vegetable oil or waste oil thereof, or a polyhydric alcohol such as glycerin or ethylene glycol, or a mixture of two or more thereof is used. This is because it is easily compatible with rocket propellants and explosives, has a high boiling point, and can delay combustion time and effectively lower the combustion temperature. Examples of the mineral oil include heavy oil, light oil, kerosene, etc., which are produced from crude oil. Further, machine oil, turbine oil, gear oil, lubricating oil, cutting oil, asphalt base oil, aromatic mineral oil and the like can be used. As the animal oil, those which are liquid at room temperature, such as fish oil and whale oil, are preferably used. Vegetable oils include linseed oil, eno oil, tung oil, sesame oil, rapeseed oil,
Cottonseed oil, soybean oil, camellia oil, olive oil, castor oil, coconut oil, palm oil, corn oil, peanut oil and the like are used. As the polyhydric alcohol, ethylene glycol,
Examples include trimethylene glycol, propylene glycol, glycerin and the like.

The flame retardant is used by adjusting its viscosity to 0.3 to 500 centipoise, preferably 1 to 400 centipoise. As the viscosity becomes less than 1 centipoise, the evaporation rate of the combustion retardant generally tends to increase during the combustion process, the impregnated amount of the flame retardant decreases, the desensitization decreases, and the explosive charge directly burns, leading to a lack of safety. It is not preferred.
When the viscosity exceeds 400 centipoise, the speed of mixing or impregnating with the rocket propellant or explosive becomes slow, and impregnation spots are likely to occur, which is unfavorable for safety. The boiling point of these combustion retardants is preferably 150 ° C. or higher, more preferably 200 ° C. or higher. Boiling point is 20
When the temperature is lower than 0 ° C, the evaporation rate of the combustion retardant is high at the time of combustion and the rocket propellant and explosive charge tend to be reactivated and explosive, which is not preferable.

The flame retardant may contain water, a surfactant or a mixture thereof. Examples of the surfactant include anionic surfactants such as higher fatty acid alkali salt, alkylsulfate and alkylaryl sulfonate, higher amine halogenate, quaternary ammonium salt and cationic surfactant such as alkylpyridinium halide. , Amphoteric surfactants such as amino acids, nonionic surfactants such as polyethylene glycol alkyl ethers, polyethylene glycol fatty acid esters, sorbitan fatty acid esters, fluoroalkylcarboxylic acids, disodium N-perfluorooctanesulfonylglutamate, fluoroalkylcarboxylic acids, etc. Fluorine-based surfactants, polyoxyethylene allyl glycidyl nonyl phenyl ether sulfate ester salts, polyoxyethylene allyl glycidyl nonyl phenyl ether reactive surfactants, and the like. Particularly hydrophilic ones are preferable. Surfactants can disperse water in oils and fats to form an emulsion. Also, the wettability of the combustion retardant can be improved to facilitate impregnation and mixing.

The combustion retardant is used in rocket propellants and explosives.
90 wt%, preferably 10-70 wt% are mixed or impregnated. When the mixed or impregnated amount is less than 10 wt%, impregnation unevenness is liable to occur depending on the kind of the explosive and the like, and the combustion retarding effect is diminished and rapid combustion may occur, which is not preferable. When the mixing or impregnation amount exceeds 70 wt%, the combustibility in the combustion process may be uneven or the combustion continuity may occur, resulting in a long working time and lack of workability, which is not preferable. In the mixing / impregnating step, the rocket propellant or explosive processed into the above shape is put into a container filled with a combustion retardant, soaked for 1 minute to several tens of minutes, and then taken out. Examples of the combustion furnace used in the combustion process include a fixed bed, a moving bed, and a rotary furnace. A combustion retardant is mixed in these combustion furnaces.
The impregnated rocket propellant or explosive charge can be added and burned in the same manner as ordinary combustion products.

With this configuration, the rocket propellant and explosive that have been cut and cut are mixed and impregnated with the combustion retardant,
The composition of the explosive or the like is altered to become an oil-rich composition.
Therefore, the condition of the combustion composition is relaxed, the combustion speed is reduced correspondingly, and the combustion temperature can be lowered, so that the rocket propellant and the explosive charge can be gently combusted. Also,
Since the reaction rate is reduced to the same level of combustion reaction as a normal combustion product, the combustion furnace is less damaged. When the combustion retardant contains water and a surfactant, the wettability of the rocket propellant and explosive is significantly improved, so that the impregnation rate is high and the mixing can be performed uniformly. Further, since water has a high latent heat of vaporization, it is possible to lower the combustion temperature and slow the combustion rate.

[0013]

Embodiments of the present invention will be described below. (Embodiment 1) 1 kg of a composite propellant consisting of 80 wt% of ammonium perchlorate and 20 wt% of a polybutadiene-based binder is formed into a strip shape on a lathe with a maximum thickness of about 2.5 mm.
I cut it out. This composite propellant was immersed in a combustion retardant composed of waste oil of gear oil having a viscosity of 50 centipoise for 15 minutes, and then an excessive combustion retardant was dropped. Next, the composite propellant impregnated with the combustion retardant was charged into the combustion furnace. The combustion furnace maintained a normal combustion state, and the composite propellant completely burned after 6 minutes. As described above, in this embodiment, the composite propellant was impregnated with the combustion retardant made of waste oil of gear oil having a viscosity of 50 centipoise and then burned in the combustion furnace.
The treatment process is extremely simple and excellent in workability, and since the combustion speed is slow and the combustion temperature is low, it is excellent in safety, and the combustion proceeds gently compared with the case where the treatment of the present invention is not performed and the combustion furnace is not damaged. I understand.

(Embodiment 2) Ammonium perchlorate 8
1 kg of a composite propellant consisting of 0 wt% and a polybutadiene-based binder of 20 wt% was cut into a maximum thickness of about 1 mm with a lathe. The viscosity of this composite propellant is 50 wt% of light oil and 50 wt% of turbine oil.
After soaking in a flame retardant which is 9 centipoise for 15 minutes, an excess flame retardant was dropped. Next, the composite propellant impregnated with the combustion retardant was put into a combustion furnace. The combustion furnace maintained a normal combustion state, and the composite propellant completely burned after 6 minutes. As described above, in this example, the composite propellant was impregnated with the combustion retardant consisting of 50 wt% of light oil having a viscosity of 19 centipoise and 50 wt% of turbine oil, and then burned in the combustion furnace.
In addition to the effects described in the first example, it was found that the composite propellant can be safely treated without damaging the furnace because the combustion time is long and the combustion proceeds gently.

(Embodiment 3) 1 kg of a TNT explosive pulverized to a particle size of 1 mm or less was dipped and mixed in a combustion retardant having a viscosity of 350 centipoise consisting of 90 wt% of light oil and 10 wt% of asphalt base oil for 15 minutes. The TNT explosive mixed with the combustion retardant was put into a combustion furnace. The combustion furnace maintained a normal combustion state, and the TNT explosive completely burned and disappeared after 7 minutes. As described above, according to this example, it was found that the TNT explosive can be safely processed without damaging the combustion furnace or the like and without fear of explosion.
It was also found that the treatment method is simple, the treatment is completed in a short time, and no special device is required.

(Embodiment 4) 1 kg of TNT explosive crushed to a particle size of 1 mm or less is 50 wt% of light oil and 50 gear oil.
The composition was immersed in a combustion retardant having a viscosity of 23% by weight of 23 centipoise for 30 minutes and mixed. T mixed with this combustion retardant
The NT explosive was put into a fixed-bed combustion furnace for incineration. The combustion furnace maintained a normal combustion state and the TNT explosive completely burned and disappeared after 6 minutes. As described above, according to this embodiment, in addition to the effect of the third embodiment, the combustion time can be long and the combustion temperature can be lowered, so that the combustion furnace is less damaged and the TNT explosive can be treated more safely. I found that I could do it.

(Embodiment 5) Ammonium perchlorate 8
1 kg of a composite propellant consisting of 0 wt% and a polybutadiene-based binder of 20 wt% was cut into a maximum thickness of about 3 mm with a lathe. This composite propellant was immersed in a combustion retardant having a viscosity of 3 centipoise containing 95 wt% of light oil and 4.5 wt% of water and 0.5 wt% of polyethylene glycol alkyl ether for 10 minutes. The composite propellant impregnated with the combustion retardant was placed in a combustion furnace. The combustion furnace maintained a normal combustion state, and the composite propellant completely burned after 5 minutes. As described above, according to the present embodiment, by impregnating the composite propellant with the combustion retardant containing polyethylene glycol alkyl ether and water, in addition to the effects described in the first embodiment, It was found that the impregnation speed of the combustion retardant can be increased and the impregnation time can be shortened, thus improving workability.
In addition, it was found that since the composite propellant was impregnated with water, the combustion temperature could be further lowered due to the influence of water having a large latent heat of vaporization, and the combustion speed could be delayed and combustion could be moderated.

Experimental Example Ammonium perchlorate 80 wt
% And 200 g of polybutadiene-based binder, 200 g of composite propellant in a lathe on a lathe with a maximum thickness of 2.
It was cut into 5 mm. This composite propellant was impregnated and mixed with the following flame retardant. Experimental Example 1 Light oil 50 wt% Gear oil 50 wt% Viscosity 23 cp Experimental example 2 Light oil viscosity 3 cp Experimental example 3 Light oil 25 wt% Rapeseed oil 75 wt% Viscosity 8 cp Experimental example 4 Light oil 50 wt% Turbine oil 50 wt% Viscosity 19 cp Experimental example 5 Light oil 50 wt% Soybean oil 50 wt % Viscosity 6 cp Experimental example 6 Light oil 25 wt% Turbine oil 75 wt% Viscosity 35 cp Experimental example 7 Soybean oil viscosity 10 cp Experimental example 8 Rapeseed oil viscosity 15 cp Experimental example 9 Ethylene glycol viscosity 45 cp Experimental example 10 Gear oil viscosity 40 cp Experimental example 11 Light oil 50 wt% Rapeseed oil 50 wt % Viscosity 9 cp Next, 200 g of TNT explosive having an average particle diameter of 1 mm or less was prepared. This TNT explosive was impregnated and mixed with the following flame retardant. Experimental Example 12 Light Oil Viscosity 3 cp Experimental Example 13 Light Oil 25 wt% Rapeseed Oil 75 wt% Viscosity 8 cp Experimental Example 14 Light Oil 50 wt% Gear Oil 50 wt% Viscosity 23 cp Experimental Example 15 Light Oil 50 wt% Turbine Oil 50 wt% Viscosity 19 cp Experimental Example 16 Turbine Oil Viscosity 48 cp Experimental Example 17 Soybean oil Viscosity 10 cp TNT explosive not soaked in combustion retardant (Experimental Example 18)
Also, 200 g of a composite propellant (Experimental Example 19) was prepared. Next, in Experimental Examples 1 to 19, the diameter of the bottom surface is 10 cm.
It was piled up in a conical shape with a height of 15 cm and ignited from one end of the bottom. The time until about 90% of the entire explosive was burned was defined as the burning time, and the maximum temperature during burning was measured by the radiation thermometer, and the respective results are shown in (Table 1) and (Table 2).

[Table 1]

[Table 2] Next, the sensitivity of the hammer was measured according to JIS K for Experimental Examples 1 to 19.
The measurement was performed according to 4810, and the results are shown in (Table 1) and (Table 2). Further, No. 6 detonator detonation sensitivity test was conducted on Experimental Examples 1 to 19. In the No. 6 detonator detonation sensitivity test, 50 g of the reagent was packed in a bottomed carton box having a capacity of 50 ml and an inner diameter of 30 mm, the No. 6 electric detonator was inserted, and the lid was placed upright on soft sand. Explode an electric detonator on the sand 3
The one that did not cause the funnel hole at all times was non-explosive, the one that occurred even once was half-explosive, and the thing that caused the funnel hole at all three times was detonated.
The results are shown in (Table 1) and (Table 2).

As is clear from (Table 1) and (Table 2), the combustion time of the composite propellant subjected to the mixing / impregnation step of the present invention was 30 seconds to 3 minutes and 20 seconds. Experimental example 19 (comparative example) in which direct combustion was performed took 3 seconds. From this, according to the present embodiment, it is 10 times to 65 times that of the comparative example.
It was found that the burning time was twice as long and the burning speed was slow. Further, the burning time of the TNT explosive subjected to the mixing / impregnation process of the present invention is 1 minute 38 seconds to 3 minutes 17 seconds, and the direct burning experimental example 18 (comparative example) of the comparative example is 49 seconds, According to this example, it was found that the burning time was 2 to 4 times longer than that of the comparative example. The combustion temperature of the composite propellant that has been subjected to the mixing / impregnation step of the present invention is 840 to 980 ° C., and the combustion temperature of Example 19 (comparative example) in which it is directly burned is 156.
It was 0 ° C, and it was found that the combustion temperature was lowered by 580 ° C. Similarly, the combustion temperature of TNT explosive is 790 to 9
80 ° C., the combustion temperature of Example 18 in which direct combustion of the comparative example is 1100 ° C., and the combustion temperature is 120 to 310 ° C.
It turned out that it can be lowered. It was found that the drop sensitivity was grade 8 in Examples 1 to 17 in which the mixing / impregnation step of the present invention was performed, which markedly reduces the sensitivity. It was also found that the detonator detonation sensitivity of No. 6 was non-explosive and extremely low in Examples 1 to 17 to which the mixing / impregnation process of the present invention was applied. In the comparative example, the sensitivity of the mallet is 7 (Experimental Example 18), 5
It was Class (Experimental Example 19), and the detonation sensitivity of No. 6 tube was detonation.

[0020]

INDUSTRIAL APPLICABILITY As described above, the present invention is applied to mineral oil, animal oil,
By providing a step of impregnating or mixing rocket propellant or explosive with a combustion retardant consisting of vegetable oil, waste oil thereof, or a mixture of one or more of polyhydric alcohols, the following remarkable effects are obtained. It is possible to realize a method for processing rocket propellants and explosives. (1) The handling sensitivity of rocket propellants and explosives is reduced, and work can be performed safely. Further, the combustion state is as flammable as ordinary paper, wood, waste oil, etc., and extremely safe treatment can be performed without fear of physical or human accident due to rapid and high temperature combustion or explosion during incineration. (2) The treatment is completed simply by immersing the rocket propellant or explosive treatment material in the combustion retardant, so no special equipment is required.
The processing is extremely simple, the processing time is short, and the processing can be performed effectively. (3) A large amount of rocket propellant or explosive powder is simply burned after soaking the rocket propellant or explosive powder that has been cut into powder, shredded, string-shaped, tape-shaped, or strip-shaped in a combustion retardant. At the same time, it can be processed in a short time and has good work efficiency, which is suitable for a large amount of processing. (4) Since the combustion retardant contains a surfactant, the impregnation speed of the treatment agent is high, the work efficiency of the mixing / impregnation step is high, and the treatment efficiency is improved. Further, since water is impregnated, the latent heat of vaporization is high, the combustion temperature is low, the combustion speed is delayed, and safer and more reliable treatment is possible.

Claims (7)

[Claims] 1. A combustion retardant comprising a mineral oil, an animal oil, a vegetable oil, a waste oil thereof, or a mixture of one or more of polyhydric alcohols such as glycerin and ethylene glycol, in the form of powder or fine particles. Mixing / impregnating step of mixing or impregnating rocket propellant or explosive which has been cut or crushed into a cut shape, tape shape, band shape or string shape;
And a burning step of burning the rocket propellant or explosive mixed and impregnated with a combustion retardant in the impregnating step. 2. The mixing and impregnating step according to claim 1, wherein the combustion retardant is mixed or impregnated with rocket propellant or explosive in an amount of 3 to 90 wt%, preferably 10 to 70 wt%. How to process rocket propellants and explosives. 3. The method for treating a rocket propellant or explosive charge according to claim 1 or 2, wherein the combustion retardant contains water and / or a surfactant. 4. The viscosity of the combustion retardant is 0.3 to 500.
The method for treating a rocket propellant or explosive charge according to any one of claims 1 to 3, wherein the method is centipoise. 5. The method for treating a rocket propellant or an explosive charge according to claim 1, wherein the rocket propellant is a composite propellant. 6. The composite propellant contains ammonium perchlorate as a main component and has an average thickness of 0.01 to 5 m.
The method for treating a rocket propellant or explosive charge according to any one of claims 1 to 5, wherein the cut object is a tape-shaped or band-shaped cut product of m. 7. The explosive powder is cut and crushed to have an average particle size of 0.001 to 5 mm, preferably an average particle size of 0.
001 to 3 mm, more preferably an average particle size of 0.001
The method for treating rocket propellant or explosive charge according to any one of claims 1 to 4, which is a cut product in the form of powder or granules having a size of up to 1.5 mm.