KR102335951B1 - High specific impuls, high burning rate, high performance nepe propellant composition - Google Patents

Abstract

The present invention relates to a nitrate ester plasticized polyester (NEPE)-based solid propellant composition having high specific impulse, high burning rate, and high performance. An aspect of the present invention provides a solid propellant composition including: metal fuel; an oxidizing agent; a pre-polymer; and an additive, wherein the oxidizing agent includes at least one selected from the group consisting of ammonium perchlorate (AP), ammonium dinitramide (ADN), 1,3,5,7-tetranitro-1,3,5,7-tetrazocane (HMX), and hexanitrohexaazaisowurtzitane (HNIW).

Description

High specific thrust, high combustion rate, high performance NEPE propellant composition {HIGH SPECIFIC IMPULS, HIGH BURNING RATE, HIGH PERFORMANCE NEPE PROPELLANT COMPOSITION}

The present invention relates to a NEPE-based solid propellant composition having high specific thrust, high combustion rate and excellent mechanical properties.

Recently, the technology of guided missiles flying at high speed is developing rapidly, and this is drawing a trajectory similar to the development of propulsion engines. In other words, due to technological advances in propulsion engines, guided missiles have greater kinetic energy and can reach targets more quickly and accurately. The thrust of such a high-speed flying vehicle originates from the propulsion engine, and the propellant is burned in the combustion tube inside the propulsion engine and the combustion product is discharged through the nozzle at the same time to enable flying at high speed through the thrust generated. The type of propellant used at this time can be divided into solid or liquid depending on the state of the fuel, and solid propellants are generally used in weapon systems that require speed and maneuverability.

The solid propellant undergoes a curing process after mixing fuel, oxidizing agent, and other additives with a polymer binder or prepolymer.

Hydroxyl terminated polybutadiene (HTPB) is the most widely used polymer binder. However, the maximum performance of the HTPB binder-based solid propellant has a specific impulse (Isp) of about 260 s and a burning rate of 30 ~ 40 mm/s. There are limits. In addition, although the HTPB binder-based solid propellant has some differences depending on the formulation, it also generates a large amount of smoke during combustion, so that the location is easily exposed to the enemy.

Therefore, it is necessary to develop a NEPE-based high-performance propellant composition that can overcome the limitations of specific thrust and combustion rate of HTPB-based solid propellants.

The above-mentioned background art is possessed or acquired by the inventor in the process of deriving the disclosure of the present application, and it cannot necessarily be said to be a known technology disclosed to the general public prior to the present application.

The present invention is to solve the above-mentioned problems, and an object of the present invention is to overcome the limitations of HTPB-based solid propellants, while having high specific thrust and high combustion rate, and having mechanical properties equal to or greater than that of HTPB-based NEPE-based propellants. To provide a solid propellant composition.

However, the problems to be solved by the present invention are not limited to those mentioned above, and other problems not mentioned will be clearly understood by those skilled in the art from the following description.

One aspect of the present invention is a metal fuel; oxidizing agent; prepolymer; and an additive; the oxidizing agent is, ammonium peroxide chloride (Ammonium Perchlorate, AP), ammonium dinitramide (ADN), 1,3,5,7-tetranitro-1,3,5 , At least one selected from the group consisting of 7-tetrazocane (1,3,5,7-tetranitro-1,3,5,7-tetrazocane, HMX) and hexanitrohexaazaisowurtzitane (HNIW) It provides a solid propellant composition comprising a.

According to one embodiment, the content of the oxidizing agent may be 40 wt% to 70 wt%.

According to one embodiment, the oxidizing agent, including ammonium peroxide chloride (Ammonium Perchlorate, AP), a first oxidizing agent; and ammonium dinitramide (ADN), 1,3,5,7-tetranitro-1,3,5,7-tetrazocan (1,3,5,7-tetranitro-1,3, 5,7-tetrazocane, HMX) and a second oxidizing agent comprising at least one selected from the group consisting of hexanitrohexaazaisowurtzitane (HNIW);

According to one embodiment, the content of the first oxidizing agent, in the solid propellant composition, is 20% to 40% by weight, and the content of the second oxidizing agent is, in the solid propellant composition, 20% to 40% by weight may be

According to an embodiment, the particle size of the oxidizing agent may be 1 μm to 400 μm.

According to an embodiment, the metal fuel may include at least one selected from the group consisting of aluminum (Al), titanium (Ti), and magnesium (Mg).

According to one embodiment, the metal fuel may be 5 wt% to 20 wt%.

According to one embodiment, the particle size of the metal fuel may be 0.5 μm to 50 μm.

According to one embodiment, the prepolymer, glycidyl azide polymer (GAP), polyethylene glycol (PEG), polycaprolactone (PCL), hydroxyl-terminated polyether (hydroxyl-terminated polyether, HTPE), It may include one or more selected from the group consisting of polypropylene glycol (PPG), polytetrahydrofuran (PTHF), polyethyl adipate (PEA), and polyglycol adipate (PGA).

According to one embodiment, the prepolymer may be 20 wt% to 40 wt%.

According to an embodiment, the additive may include at least one selected from the group consisting of a plasticizer, a curing agent, and a curing catalyst.

According to one embodiment, the plasticizer, diethylene glycol dinitrate (DEGDN), trimethyl ethylene trinitrate (TMETN), butanetriol trinitrate (BTTN) and triethylene glycol trinitrate (TEGDN) consisting of It may include one or more selected from the group, and in the solid propellant composition, 1 wt% to 20 wt%.

According to an embodiment, the curing agent is isophorone diisocyanate (IPDI), dimer diisocyanate (DDI), hexamethylene diisocyanate (HDI), toluene diisocyanate (TDI), N-100 (Biuret triisocyanate desmonour) and N -3200 (Polyfuctional aliphatic isocyanate) may be included in at least one selected from the group consisting of, and 0.1 wt% to 10 wt% of the solid propellant composition.

According to an embodiment, the curing catalyst may include triphenyl bismuth (TPB), and in the solid propellant composition, 0.005 wt% to 1.0 wt%.

According to an embodiment, the solid propellant composition may have a specific force of 265 s or more and a combustion rate of 30 mm/s to 60 mm/s under a pressure condition of 6.9 MPa.

According to an embodiment, the solid propellant composition may have a tensile strength of 9.0 bar or more and an elongation of 25% or more.

The NEPE-based solid propellant composition according to the present invention exhibits a high specific thrust of 265 s or more and a high combustion rate of 30 mm/s to 60 mm/s, which are difficult to implement in conventional HTPB-based solid propellants, It has the effect of having a similar level of mechanical properties.

In addition, the NEPE-based solid propellant composition according to the present invention can reduce the amount of smoke generated during combustion compared to the conventional solid propellant composition, and has the advantage of being applicable to hypersonic weapon systems and high-performance rocket systems.

Hereinafter, embodiments will be described in detail. However, since various changes may be made to the embodiments, the scope of the patent application is not limited or limited by these embodiments. It should be understood that all modifications, equivalents and substitutes for the embodiments are included in the scope of the rights.

The terms used in the examples are used for the purpose of description only, and should not be construed as limiting. The singular expression includes the plural expression unless the context clearly dictates otherwise. In this specification, terms such as "comprise" or "have" are intended to designate that a feature, number, step, operation, component, part, or a combination thereof described in the specification exists, but one or more other features It should be understood that this does not preclude the existence or addition of numbers, steps, operations, components, parts, or combinations thereof.

Unless otherwise defined, all terms used herein, including technical or scientific terms, have the same meaning as commonly understood by one of ordinary skill in the art to which the embodiment belongs. Terms such as those defined in commonly used dictionaries should be interpreted as having a meaning consistent with the meaning in the context of the related art, and should not be interpreted in an ideal or excessively formal meaning unless explicitly defined in the present application. does not

In addition, in describing the components of the embodiment, terms such as first, second, A, B, (a), (b), etc. may be used. These terms are only for distinguishing the elements from other elements, and the essence, order, or order of the elements are not limited by the terms.

Components included in one embodiment and components having a common function will be described using the same names in other embodiments. Unless otherwise stated, descriptions described in one embodiment may be applied to other embodiments as well, and detailed descriptions within the overlapping range will be omitted.

One aspect of the present invention is a metal fuel; oxidizing agent; prepolymer; and an additive; the oxidizing agent is, ammonium peroxide chloride (Ammonium Perchlorate, AP), ammonium dinitramide (ADN), 1,3,5,7-tetranitro-1,3,5 , At least one selected from the group consisting of 7-tetrazocane (1,3,5,7-tetranitro-1,3,5,7-tetrazocane, HMX) and hexanitrohexaazaisowurtzitane (HNIW) It provides a solid propellant composition comprising a.

The solid propellant composition is characterized in that it can implement high specific thrust by including an oxidizing agent, which is a material having high energy, alone or in combination.

According to one embodiment, the content of the oxidizing agent may be 40 wt% to 70 wt%.

The content of the oxidizing agent is an optimized content to improve mechanical properties as well as to improve specific force and combustion rate. In this case, the relative content of the prepolymer may decrease, and thus the mechanical properties of the solid propellant may be deteriorated.

In particular, the solid propellant composition according to the present invention is characterized in that it can have a specific force of 265 s or more even when the content of the oxidizing agent is 60% by weight or less.

According to one embodiment, the oxidizing agent, including ammonium peroxide chloride (Ammonium Perchlorate, AP), a first oxidizing agent; and ammonium dinitramide (ADN), 1,3,5,7-tetranitro-1,3,5,7-tetrazocan (1,3,5,7-tetranitro-1,3, 5,7-tetrazocane, HMX) and a second oxidizing agent comprising at least one selected from the group consisting of hexanitrohexaazaisowurtzitane (HNIW);

According to one embodiment, the oxidizing agent, by simultaneously including the first oxidizing agent and the second oxidizing agent, high specific thrust and high combustion rate characteristics can be implemented at the same time.

According to one embodiment, the second oxidizing agent may serve to partially replace the AP included in the first oxidizing agent because it contains a large amount of oxygen in the molecular structure.

In addition, by reducing the absolute content of AP contained in the first oxidizing agent through this, the amount of chlorine gas generated during combustion of the propellant can be reduced, so that it can be applied as a low smoke propellant (minimum smoke).

In particular, compared to the existing HTPB-based propellant, high performance can be realized while consuming a small amount of AP, an oxidizing agent, and the amount of chlorine gas generated during AP combustion can be reduced.

For example, ADN included in the second oxidizer is _{an eco-friendly high-energy material having a chemical formula of H 4} N ₄ O ₄ , and is composed of only nitrogen, oxygen, and hydrogen, and unlike the AP oxidizer, does not emit pollutants during combustion. In addition, HNIW contained in the second oxidizing agent is evaluated as the highest energy material among nitroamine-based materials, and has a large density and heat of formation.

Therefore, when they are mixed and used, high specific thrust and high combustion rate characteristics can be efficiently improved at the same time, and it can also have advantages in terms of environment.

According to one embodiment, the content of the first oxidizing agent, in the solid propellant composition, is 20% to 40% by weight, and the content of the second oxidizing agent is, in the solid propellant composition, 20% to 40% by weight may be

If the content of the first oxidizing agent and the second oxidizing agent is out of the above range, specific thrust and combustion rate may be reduced or the amount of gas generated during combustion may be increased.

In addition, the content of the first oxidizing agent and the second oxidizing agent may act as a key factor in simultaneously improving the specific thrust and the combustion rate.

According to an embodiment, the particle size of the oxidizing agent may be 1 μm to 400 μm. The particle size of the oxidizing agent may be a diameter, a radius, a maximum length, etc. depending on the shape of the particle.

According to an embodiment, the metal fuel may include at least one selected from the group consisting of aluminum (Al), titanium (Ti), and magnesium (Mg).

According to one embodiment, the metal fuel may be 5 wt% to 20 wt%.

According to one embodiment, the particle size of the metal fuel may be 0.5 μm to 50 μm. The particle size of the metal fuel may be a diameter, a radius, a maximum length, etc. according to the shape of the particle.

The particle size ranges of the oxidizing agent and the metal fuel are ranges for optimizing the combustion rate and the propellant mixing processability.

If the particle size range of the oxidizing agent and the metal fuel is less than the above range, it is difficult to expect an effect of increasing the combustion rate due to agglomeration and a problem in the propellant mixing process due to the increase in viscosity.

In addition, when the particle size range of the oxidizing agent and the metal fuel exceeds the above range, the performance of the propellant may be reduced, and problems similar to the above may occur in the propellant mixing process.

According to one embodiment, the prepolymer, glycidyl azide polymer (GAP), polyethylene glycol (PEG), polycaprolactone (PCL), hydroxyl-terminated polyether (hydroxyl-terminated polyether, HTPE), It may include one or more selected from the group consisting of polypropylene glycol (PPG), polytetrahydrofuran (PTHF), polyethyl adipate (PEA), and polyglycol adipate (PGA).

The prepolymer may include a material having a large heat of formation (ΔH _f ), thereby implementing high specific thrust and high combustion rate characteristics.

Specifically, the previously used prepolymer (polymer binder), HTPB, has a density of 0.92 g/cm ³ and a heat of formation of -29,700 cal/mol. In comparison, GAP, which is one of the prepolymer components of the present invention, has a density of 1.29 g/cm ³ and a heat of formation of 28,000 cal/mol.

Looking at each generation sequence, it can be seen that HTPB has a negative value and GAP has a positive value. That is, when HTPB is made from each single element, heat (energy) is released by a negative value to lower the energy level, and in the case of GAP, heat (energy) is absorbed by a positive value to increase the energy level. Therefore, as the heat of formation has a positive value and increases, the energy level of the product increases, so that a lot of heat (energy) can be generated during combustion.

According to one embodiment, the prepolymer may be 20 wt% to 40 wt%, preferably, 23 wt% to 30 wt%.

If the content of the prepolymer is out of the above range, mechanical properties, combustion rate, specific force, etc. of the propellant may be reduced, which may lead to deterioration of the performance of the propellant.

In particular, the solid propellant composition according to the present invention contains 20 wt% or more of a NEPE-based prepolymer having high energy, thereby improving excellent mechanical properties as well as high specific thrust characteristics.

In addition, high specific thrust and high combustion rate are realized simultaneously by mixing and including an oxidizing material having high energy in a specific content.

According to an embodiment, the additive may include at least one selected from the group consisting of a plasticizer, a curing agent, and a curing catalyst.

According to one embodiment, the plasticizer, diethylene glycol dinitrate (DEGDN), trimethyl ethylene trinitrate (TMETN), butanetriol trinitrate (BTTN) and triethylene glycol trinitrate (TEGDN) consisting of It may include one or more selected from the group, and in the solid propellant composition, 1 wt% to 20 wt%.

The plasticizer may be included in the content range to impart flow properties, flexibility, elasticity and processability of the solid propellant composition.

According to an embodiment, the curing agent is isophorone diisocyanate (IPDI), dimer diisocyanate (DDI), hexamethylene diisocyanate (HDI), toluene diisocyanate (TDI), N-100 (Biuret triisocyanate desmonour) and N -3200 (Polyfuctional aliphatic isocyanate) may be included in at least one selected from the group consisting of, and 0.1 wt% to 10 wt% of the solid propellant composition.

The curing agent is included in the above content range, so that the curing reaction of the solid propellant composition is sufficiently achieved.

According to an embodiment, the curing catalyst may include triphenyl bismuth (TPB), and in the solid propellant composition, 0.005 wt% to 1.0 wt%.

The curing catalyst is included in the content range to promote the curing reaction of the solid propellant composition.

According to an embodiment, the solid propellant composition may have a specific force of 265 s or more and a combustion rate of 30 mm/s to 60 mm/s under a pressure of 6.9 MPa.

According to an embodiment, the solid propellant composition may have a specific force of 265 s or more, a combustion rate of 40 mm/s to 60 mm/s under a pressure condition of 6.9 MPa, a specific force of 265 s or more, and a combustion rate may be 44 mm/s to 60 mm/s under a 6.9 MPa pressure condition.

The maximum performance of the existing HTPB-based propellants is about 260 s with specific thrust and about 30 mm/s to 40 mm/s of combustion speed. there was

In comparison, the NEPE-based solid propellant composition according to the present invention exhibits high specific thrust and combustion rate, which are not implemented with conventional HTPB-based propellants, and thus has the advantage of being applicable to inorganic systems requiring high performance.

The combustion rate may be measured after curing the solid propellant composition.

According to an embodiment, the solid propellant composition may have a tensile strength of 9.0 bar or more and an elongation of 25% or more.

According to one embodiment, the solid propellant composition, the tensile strength (Tensile stress) may be 9.5 bar or more, preferably, it may be 10 bar or more.

According to an embodiment, the solid propellant composition may have an elongation of 28% or more, preferably, 30% or more, and more preferably 40% or more.

In general, the NEPE-based propellant composition has lower mechanical properties than the HTPB-based propellant composition, because the mechanical properties of the propellant depend on the physical properties and curing properties of the prepolymer itself.

In comparison, the solid propellant composition according to the present invention has mechanical properties similar to or higher than that of the HTPB-based propellant composition, even though it is a NEPE-based propellant composition.

The tensile strength and elongation may be measured after curing the solid propellant composition.

The solid propellant composition according to the present invention can be applied to hypersonic weapon systems and high-performance guided missiles, and the propulsion engine can improve overall weapon system performance with water. In addition, it can be applied as a propellant for large rockets of satellite launch vehicles that require large thrust.

Hereinafter, the present invention will be described in more detail by way of Examples and Experimental Examples.

However, the following examples are only for illustrating the present invention, and the content of the present invention is not limited to the following examples.

<Example> Preparation of solid propellant composition

A solid propellant composition was prepared by mixing the metal fuel, prepolymer, and oxidizing agent.

Specific components and contents of each Example composition are shown in Table 1.

metal fuel prepolymer oxidizer Example 1 Al 15 wt% GAP 23.5 wt% AP 20 wt%
ADN 20% by weight
HMX 20% by weight Example 2 Al 16 wt% GAP 28 wt% AP 26 wt%
ADN 30% by weight Example 3 Al 16 wt% GAP 28 wt% AP 26 wt%
ADN 30% by weight Example 4 Al 16 wt% GAP 28 wt% AP 21 wt%
ADN 35 wt% Example 5 Al 16 wt% GAP 28 wt% AP 21 wt%
ADN 35 wt% Example 6 Al 16 wt% GAP 23.5 wt% AP 40 wt%
HMX 20% by weight Example 7 Al 16 wt% GAP 23.5 wt% AP 30 wt%
30% by weight of HMX Example 8 Al 16 wt% GAP 23.5 wt% AP 20 wt%
HMX 40 wt% Example 9 Al 16 wt% GAP 28 wt% AP 30 wt%
HNIW 26 wt% Example 10 Al 16 wt% GAP 23.5 wt% AP 20 wt%
HNIW 40 wt%

<Experimental Example 1> Measurement of specific force and combustion rate of solid propellant composition

Specific thrust and combustion rate of the solid propellant composition prepared in the Examples were measured.

The specific force value was calculated using the CEA (Chemical equilibrium with applications) code developed by NASA, and the density specific force is the product of the density of the propellant and the specific force. In addition, the combustion rate of the propellant was measured using a strand burner equipment after processing the cured propellant into a specimen of an appropriate size. The measurement results are shown in Table 2.

non-power
(S) density specific force
(g/cm ³ s) Burning speed @ 6.9MPa
(mm/s) Example 1 270.7 494.6 44.3 Example 2 269.6 473.6 32.7 Example 3 269.6 474.3 31.4 Example 4 267.0 468.7 30.4 Example 5 270.4 474.6 29.4 Example 6 267.0 494.5 53.15 Example 7 268.8 497.6 50.28 Example 8 271.3 499.2 45.44 Example 9 268.0 491.2 53.03 Example 10 271.4 513.5 47.10

Referring to Table 2, it can be seen that the specific force of 265s or more was exhibited in all of the Examples. In addition, it can be seen that all of the Examples exhibit a combustion rate of about 30 mm/s or more, and in particular, Examples 1, 6 to 10 can confirm that a combustion rate of 40 mm/s or more is exhibited.

Referring to the results of Examples 1 to 5, it can be seen that the specific force value increases as the content of the oxidizing agent ADN increases. However, the combustion rate did not increase at the same time. In addition, it can be seen that in Example 1, in which AP, ADN, and HMX were all used as oxidizing agents, the specific thrust and the combustion rate showed the highest values.

Through this, it can be understood that when another nitroamine-based material such as HMX is added as an oxidizing agent in addition to AP and ADN, specific force and combustion rate can be effectively improved at the same time.

Referring to the results of Examples 6 to 8, it can be seen that the specific force increases as the amount of HMX, which is a nitroamine-based material, increases. This is because the heat of generation of HMX is large, so a lot of energy is released during combustion to increase the temperature inside the combustion chamber, which increases specific force. On the other hand, as the amount of HMX increased, the combustion rate decreased because the amount of AP decreased relatively.

Referring to the results of Examples 9 and 10, it can be seen that as the amount of HNIW increases, the value of specific force increases and the combustion rate decreases slightly.

<Experimental Example 2> Measurement of mechanical properties of solid propellant composition

In order to confirm the mechanical properties of the solid propellant composition, the tensile strength and elongation of Examples 8 to 10 were measured. The measurement results are shown in Table 3.

specific force(s) Tensile strength (bar) Elongation (%) Example 8 271.3 9.9 28 Example 9 268.0 9.5 44 Example 10 271.4 10.6 33

Referring to Table 3, it can be seen that the solid propellant compositions of Examples 8 to 10 exhibited a tensile strength of 9.5 bar or more and an elongation of 28% or more.

In particular, it can be seen that Examples 9 and 10 exhibited an elongation of 30% or more, and Example 9 exhibited an elongation of 44% or more.

Through this, it can be seen that the solid propellant composition according to the present invention secures excellent mechanical properties as well as high specific thrust and high combustion rate.

Although the embodiments have been described as described above, those skilled in the art may apply various technical modifications and variations based on the above. For example, the described techniques are performed in an order different from the described method, and/or the described components of the system, structure, apparatus, circuit, etc. are combined or combined in a different form than the described method, or other components Or substituted or substituted by equivalents may achieve an appropriate result.

Therefore, other implementations, other embodiments, and equivalents to the claims are also within the scope of the following claims.

Claims (16)

metal fuel;
oxidizing agent;
prepolymers, including glycidylazide polymer (GAP); and
A solid propellant composition comprising; an additive comprising at least one selected from the group consisting of a plasticizer, a curing agent, and a curing catalyst,
The oxidizing agent, including ammonium peroxide chloride (Ammonium Perchlorate, AP), a first oxidizing agent; and ammonium dinitramide (ADN), 1,3,5,7-tetranitro-1,3,5,7-tetrazocan (1,3,5,7-tetranitro-1,3, 5,7-tetrazocane, HMX) and a second oxidizing agent comprising at least one selected from the group consisting of hexanitrohexaazaisowurtzitane (HNIW);
The content of the first oxidizing agent is, in the solid propellant composition, 20% by weight to 40% by weight,
The content of the second oxidizing agent is, in the solid propellant composition, 20% by weight to 40% by weight,
The prepolymer is 20% to 40% by weight,
The plasticizer is at least one selected from the group consisting of diethylene glycol dinitrate (DEGDN), trimethyl ethylene trinitrate (TMETN), butanetriol trinitrate (BTTN) and triethylene glycol trinitrate (TEGDN) including,
The curing agent is isophorone diisocyanate (IPDI), dimer diisocyanate (DDI), hexamethylene diisocyanate (HDI), toluene diisocyanate (TDI), N-100 (Biuret triisocyanate desmonour) and N-3200 (Polyfuctional aliphatic isocyanate) ) comprising at least one selected from the group consisting of,
The curing catalyst, including triphenyl bismuth (TPB),
A solid propellant composition.
According to claim 1,
The content of the oxidizing agent is
40% to 70% by weight,
A solid propellant composition.
delete delete According to claim 1,
The particle size of the oxidizing agent is,
1 μm to 400 μm,
A solid propellant composition.
According to claim 1,
The metal fuel is
Which comprises at least one selected from the group consisting of aluminum (Al), titanium (Ti) and magnesium (Mg),
A solid propellant composition.
According to claim 1,
The metal fuel is
5% to 20% by weight,
A solid propellant composition.
According to claim 1,
The particle size of the metal fuel is,
0.5 μm to 50 μm,
A solid propellant composition.
According to claim 1,
The prepolymer is
Polyethylene glycol (PEG), polycaprolactone (PCL), hydroxyl-terminated polyether (HTPE), polypropylene glycol (PPG), polytetrahydrofuran (PTHF), polyethyl adipide ( PEA) and polyglycol adipate (PGA) that further comprises one or more selected from the group consisting of,
A solid propellant composition.
delete delete According to claim 1,
The plasticizer is, in the solid propellant composition, 1 wt% to 20 wt%,
solid propellant composition
According to claim 1,
The curing agent is, in the solid propellant composition, 0.1 wt% to 10 wt%,
A solid propellant composition.
According to claim 1,
The curing catalyst is, in the solid propellant composition, 0.005 wt% to 1.0 wt%,
A solid propellant composition.
According to claim 1,
specific force of 265 s or more,
The combustion rate is 30 mm / s to 60 mm / s under 6.9 MPa pressure conditions,
A solid propellant composition.
According to claim 1,
Tensile stress is 9.0 bar or more,
Elongation (Elongation) is 25% or more,
A solid propellant composition.