A high-stability solid propellant and a method for preparing the same

Abstract

The application relates to the field of propellants, and particularly discloses a high-stability solid propellant and a preparation method thereof. The preparation method of the solid propellant comprises the following steps: taking 70-85 wt% of oxidants, 5-10 wt% of nano-iron powder, 6-14 wt% of binders and 4-6 wt% of stabilizers, mixing, compacting and forming, drying at 5-15 DEG C until the weight is constant, and sealing and packaging, so as to obtain a new solid propellant with high combustion heat. In the process, the generation of harmful gases is reduced by optimizing the oxidant formula, the safety is improved by moisture-proof treatment and the addition of stabilizers, the propellant raw materials have low danger, and the production and processing are easy.

Description

Technical Field

[0001] This invention belongs to the field of propellants, and particularly relates to a highly stable solid propellant and its preparation method. Background Technology

[0002] Solid propellants are typically composed of a binder (which also functions as fuel), an oxidizer, metallic additives, and small amounts of other substances. Through chemical reactions between these components, chemical energy is converted into thermal energy, releasing a large amount of energy. They play an irreplaceable role in missile weaponry and aerospace, serving as the fundamental guarantee for maximizing the power of missiles. To adapt to the rapid development of missile weaponry and aerospace, researchers have conducted extensive research on how to improve propellant energy.

[0003] For example, patent CN112028724B discloses a method for preparing a solid propellant containing a bimetallic oxide accelerator to improve the heat release and combustion rate of the propellant. By introducing a bimetallic oxide accelerator with synergistic effects, it brings higher heat of explosion, heat of combustion, and combustion rate, effectively promoting the redox reaction of the propellant. Another example is patent CN115925500B, which obtained a core-shell structured solid propellant of Al@PF coated with perchlorate and organic nitramine compounds through a spray method. This reduces the reaction temperature of existing Al-based composite solid propellants and increases the combustion rate of the composite solid propellant.

[0004] It is worth noting that solid propellants currently typically contain a large number of hazardous chemicals, especially high-energy oxidizers and reducing agents, which pose significant safety risks during production, storage, and use. Furthermore, the production process of solid propellants is complex and costly, and combustion produces gases harmful to the environment and human health. Therefore, developing a solid propellant with relatively safe components, a simple process, high heat of combustion, high storage stability, and environmental friendliness has broad application prospects. Summary of the Invention

[0005] To address the shortcomings of existing technologies, this invention optimizes the oxidant formulation, applies moisture-proof treatment to the oxidant, and adds a stabilizer, resulting in a novel solid propellant that is safe in composition, simple in process, has high heat of combustion, high storage stability, and is environmentally friendly.

[0006] To achieve the above objectives, the technical solution adopted by the present invention is as follows:

[0007] The present invention provides a method for preparing a highly stable solid propellant, comprising the following steps: weighing 70-85 wt% oxidant, 5-10 wt% nano iron powder, 6-14 wt% binder, and 4-6 wt% stabilizer, based on 100 wt%, mixing and compacting the mixture, drying it at 5-15°C to constant weight, and sealing and packaging it to obtain the novel solid propellant;

[0008] The oxidant comprises moisture-resistant dinitramide ammonium, pentamidotetraazole nitrate, and RDX.

[0009] Preferably, the mass ratio of the moisture-proof dinitramide ammonium, pentaaminotetrazole nitrate and RDX is 1:(0.16-0.25):(0.12-0.18).

[0010] To improve safety, environmental friendliness, and storage stability, the novel solid propellant of this invention incorporates stabilizers and binders. Furthermore, through optimization of the oxidant formulation, a highly safe oxidant with non-toxic and harmless combustion products was selected, reducing production hazards and environmental pollution. This results in a solid propellant with advantages such as high heat of combustion, easy storage, resistance to deterioration, and environmental friendliness.

[0011] This invention uses nano-iron powder as a combustion catalyst, which reacts with the oxidant during combustion. It can change the reaction process and combustion process of the propellant by means of thermal decomposition, regulating the burning rate and reducing the pressure index, thereby improving the combustion performance of the propellant.

[0012] In some embodiments, the preparation steps of the moisture-proof dinitramide ammonium are as follows:

[0013] Prepare an acetone-dichloromethane mixed solution. Add dinitramide ammonium to the mixed solution at 15-25°C until a saturated dinitramide ammonium solution is formed. While stirring at 800-1200 rpm, add the saturated dinitramide ammonium solution dropwise to a CuO-dichloromethane suspension at a rate of 0.5-1.5 mL / min. Add Tween-80, stir for 30-60 min, and then recrystallize at -3-5°C to obtain the moisture-proof dinitramide ammonium.

[0014] Preferably, the volume ratio of acetone to dichloromethane in the acetone-dichloromethane mixed solution is 1:(8-12).

[0015] In some embodiments, the concentration of the CuO-dichloromethane suspension is 0.005 to 0.012 g / mL.

[0016] In some embodiments, the volume ratio of the saturated dinitramide ammonium solution to the CuO-dichloromethane suspension is 1:(8-12).

[0017] This invention provides sufficient oxidizing power by combining three oxidants: ammonium dinitramide, pentaaminotetrazole nitrate, and RDX, ensuring efficient combustion of the propellant. Among the three oxidants, ammonium dinitramide has poor hygroscopic stability, making the mixed oxidant unsuitable for direct mixing with binders. The hygroscopicity of ammonium dinitramide is usually due to its plate-like crystal morphology. This invention changes the crystal morphology of ammonium dinitramide through recrystallization, reducing the specific surface area of ​​the crystals and thus lowering its hygroscopicity. Simultaneously, during recrystallization, some ammonium dinitramide grows on the CuO surface, which not only reduces CuO agglomeration but also increases the contact area between CuO and ammonium dinitramide, providing more catalytic centers and allowing CuO to fully catalyze combustion.

[0018] In some embodiments, the adhesive is any one of polyurethane, glycidyl ether, polycaprolactone, and polybutadiene.

[0019] Preferably, the adhesive is polybutadiene with a hydroxyl value of 0.47 mmol / g to 0.70 mmol / g.

[0020] This invention selects polybutadiene as the binder for the propellant, which not only provides combustible elements during combustion, but also improves the mechanical strength and processing performance of the propellant, enabling the propellant to be made into propellant grains of specific shapes.

[0021] In some embodiments, the preparation steps of the stabilizer are as follows:

[0022] S1. Methyl cyanoacetate, sodium nitrite and distilled water were stirred to obtain a mixture. The mixture was cooled to -3 to 5°C and glacial acetic acid was added. The mixture was stirred at room temperature for 3 to 4 hours. After stirring, the pH was adjusted to 1 to 2. The mixture was extracted, washed, dried and distilled under reduced pressure to obtain reactant 1.

[0023] S2. Prepare a potassium hydroxide solution with a concentration of 0.18–0.24 g / mL. Add a hydroxylamine solution with a concentration of 45–55 wt% and a reactant 1 solution with a concentration of 0.42–0.56 g / mL at -3–5℃. Stir for 1–2 hours, raise the temperature to 90–100℃, and continue stirring for 1–2 hours. After stirring, cool to 5–15℃, adjust the pH to <1, lower the temperature to -10–-5℃, let stand for 1–2 hours, filter, and dry to obtain an amino heterocyclic compound.

[0024] S3. Mix fullerene and bromine and let stand for 12-20 minutes. Filter and air dry to obtain brominated fullerene.

[0025] S4. Under nitrogen protection, brominated fullerene and o-dichlorobenzene are stirred at room temperature for 20-40 minutes, and the amino heterocyclic compound obtained in step S2 is added. The mixture is stirred at 10-20°C until the solid disappears, filtered, distilled under reduced pressure, and recrystallized to obtain the stabilizer.

[0026] In some embodiments, in step S1, the mass ratio of methyl cyanoacetate to sodium nitrite is 1:(0.79-0.92).

[0027] In some embodiments, in step S2, the mass ratio of potassium hydroxide, hydroxylamine, and reactant 1 is 1:(1.14-1.25):(2.2-3.0).

[0028] In some embodiments, in step S3, the ratio of fullerene to bromine is (10-16) mg: 1 mL.

[0029] In some embodiments, in step S4, the mass ratio of the brominated fullerene to the amino heterocyclic compound is 1:(3.2 to 5.8).

[0030] In practical use, due to the influence of high temperature, moisture, oxygen and other conditions, some oxidants will decompose to produce nitrogen and oxygen free radicals and nitrogen and oxygen acid gases. These substances will accelerate the decomposition and failure of solid propellants. This invention ensures safety and reliability throughout the entire production, transportation, use and storage process by adding stabilizers.

[0031] This invention provides a stabilizer obtained through the reaction of brominated fullerene and amino heterocyclic compounds. This stabilizer can rapidly absorb nitrogen-oxygen acid gases and nitroxide free radicals, generating stable and non-toxic compounds. Furthermore, this stabilizer exhibits low chemical activity and does not react with effective energetic components. The amino heterocyclic compound contains a large number of electron-rich groups in its molecular structure, enabling it to undergo nucleophilic reactions with nitrogen oxides generated during propellant decomposition, thereby inhibiting the autocatalytic decomposition process. Additionally, after the brominated fullerene is linked to the amino heterocyclic compound, its original conjugated large π delocalized system is disrupted, enhancing the activity of the fullerene carbon cage in absorbing nitroxide free radicals.

[0032] In another aspect, the present invention provides a highly stable solid propellant obtained by the above preparation method, wherein the heat of combustion of the solid propellant is ≥9900 J / g.

[0033] Compared with the prior art, the present invention has the following beneficial effects:

[0034] 1. The novel solid propellant of the present invention has the advantages of high heat of combustion, easy storage, environmental friendliness and harmlessness, and simple and easy production process.

[0035] 2. This invention provides sufficient oxidizing power by compounding three oxidants and by moisture-proofing dinitramide ammonium, thus ensuring efficient combustion of the propellant.

[0036] 3. This invention uses nano-iron powder and CuO in moisture-proof dinitramide ammonium as combustion catalysts to improve the combustion performance of the propellant.

[0037] 4. This invention utilizes a stabilizer obtained by reacting brominated fullerene with an amino heterocyclic compound to absorb the nitrogen-oxygen acid gas and nitrogen-oxygen free radicals generated by the decomposition of the oxidant itself, thereby ensuring safety and reliability throughout the entire production, transportation, use, and storage process. Detailed Implementation

[0038] The present invention will be described below with reference to specific embodiments. It should be noted that the following embodiments are examples of the present invention and are used only to illustrate the invention, not to limit it. Other combinations and various modifications within the scope of the present invention can be made without departing from its spirit or scope.

[0039] It should be noted that the post-processing steps such as "extraction", "recrystallization", and "reduced pressure distillation" appearing in the following preparation examples and embodiments are routine operations for those skilled in the art, and should be selected according to actual operations.

[0040] To facilitate implementation of this invention by those skilled in the art, some of the raw materials and manufacturers of the embodiments are described below:

[0041] Hydroxyl-terminated polybutadiene has a hydroxyl value of 0.47 mmol / g to 0.70 mmol / g and can be purchased from any manufacturer.

[0042] Preparation Example 1

[0043] The preparation steps for stabilizer-A are as follows:

[0044] S1. 100g of methyl cyanoacetate, 86g of sodium nitrite and 450mL of distilled water were stirred to obtain a mixture. The mixture was cooled to 0℃ and 92mL of glacial acetic acid was added. The mixture was stirred at room temperature for 4h. After stirring, the pH was adjusted to 1 with 20wt% hydrochloric acid. The mixture was extracted, washed with saturated brine, dried with anhydrous magnesium sulfate and distilled under reduced pressure to obtain reactant 1.

[0045] S2. Prepare 30 mL of potassium hydroxide solution with a concentration of 0.21 g / mL, add 15 mL of 50 wt% hydroxylamine solution and 35 mL of reactant 1 solution with a concentration of 0.48 g / mL at 0℃, stir for 1 h, heat to 95℃, continue stirring for 2 h, cool to 10℃ after stirring, adjust pH to <1 with 20 wt% hydrochloric acid, cool to -8℃, let stand for 2 h, filter, and dry with anhydrous magnesium sulfate to obtain an amino heterocyclic compound;

[0046] S3. Mix 2g of fullerene and 150mL of bromine, let stand for 18min, filter, and air dry to obtain brominated fullerene.

[0047] S4. Under nitrogen protection, 4g of fullerene bromide and 400mL of o-dichlorobenzene were stirred at room temperature for 30min. 18.7g of the amino heterocyclic compound obtained in step S2 was added, and the mixture was stirred at 15℃ until the solid disappeared. The mixture was then filtered, distilled under reduced pressure, and recrystallized to obtain stabilizer-A.

[0048] Preparation Example 2

[0049] The preparation steps for stabilizer-B are as follows:

[0050] S1. 100g of methyl cyanoacetate, 86g of sodium nitrite and 450mL of distilled water were stirred to obtain a mixture. The mixture was cooled to 0℃ and 92mL of glacial acetic acid was added. The mixture was stirred at room temperature for 4h. After stirring, the pH was adjusted to 1 with 20wt% hydrochloric acid. The mixture was extracted, washed with saturated brine, dried with anhydrous magnesium sulfate and distilled under reduced pressure to obtain reactant 1.

[0051] S2. Prepare 30 mL of potassium hydroxide solution with a concentration of 0.21 g / mL. Add 15 mL of 50 wt% hydroxylamine solution and 35 mL of reactant 1 solution with a concentration of 0.48 g / mL at 0℃. Stir for 1 h, raise the temperature to 95℃, and continue stirring for 2 h. After stirring, cool to 10℃, adjust the pH to <1 with 20 wt% hydrochloric acid, cool to -8℃, let stand for 2 h, filter, and dry with anhydrous magnesium sulfate to obtain stabilizer-B.

[0052] Preparation Example 3

[0053] The preparation steps of stabilizer-C are as follows:

[0054] The difference between this preparation example and preparation example 1 is that the amount of sodium nitrite used in step S1 is 78g.

[0055] Preparation Example 4

[0056] The preparation steps of stabilizer-D are as follows:

[0057] The difference between this preparation example and preparation example 1 is that the amount of sodium nitrite used in step S1 is 95g.

[0058] Preparation Example 5

[0059] The preparation steps for stabilizer-E are as follows:

[0060] The difference between this preparation example and preparation example 1 is that the amount of the amino heterocyclic compound used in step S4 is 12g.

[0061] Preparation Example 6

[0062] The preparation steps of stabilizer-F are as follows:

[0063] The difference between this preparation example and preparation example 1 is that the amount of the amino heterocyclic compound used in step S4 is 24g.

[0064] Preparation Example 7

[0065] The preparation steps for moisture-proof dinitramide ammonium-A are as follows:

[0066] Prepare a 1:10 volume ratio acetone-dichloromethane mixed solution. At 20°C, add dinitramide ammonium to the mixed solution until a saturated dinitramide ammonium solution is formed. While stirring at 1000 rpm, add 10 mL of the saturated dinitramide ammonium solution dropwise at a rate of 1 mL / min to 100 mL of CuO-dichloromethane suspension with a concentration of 0.008 g / mL. Add 0.3 g of Tween-80, stir for 40 min, and then recrystallize at 0°C to obtain moisture-proof dinitramide ammonium-A.

[0067] Preparation Example 8

[0068] The preparation steps for moisture-proof dinitramide-B are as follows:

[0069] Prepare a 1:10 volume ratio acetone-dichloromethane mixed solution. At 20°C, add ammonium dinitramide to the mixed solution until a saturated ammonium dinitramide solution is formed. While stirring at 1000 rpm, add 10 mL of the saturated ammonium dinitramide solution dropwise to 100 mL of a 0.008 g / mL CuO-dichloromethane suspension at a rate of 1 mL / min. After stirring for 40 min, recrystallize at 0°C to obtain moisture-proof ammonium dinitramide-B.

[0070] Preparation Example 9

[0071] The preparation steps of moisture-proof dinitramide-C are as follows:

[0072] Prepare a 1:10 volume ratio acetone-dichloromethane mixture. Add ammonium dinitramide to the mixture at 20°C until a saturated ammonium dinitramide solution is formed. While stirring at 1000 rpm, add 10 mL of the saturated ammonium dinitramide solution dropwise to 100 mL of dichloromethane at a rate of 1 mL / min. Add 0.3 g of Tween-80, stir for 40 min, and then recrystallize at 0°C to obtain moisture-proof ammonium dinitramide-C.

[0073] Example 1

[0074] A method for preparing a highly stable solid propellant includes the following steps:

[0075] Weigh out 77 wt% oxidant, 8 wt% nano iron powder, 10 wt% hydroxyl-terminated polybutadiene, and 5 wt% stabilizer-A based on 100 wt%. Mix them, compact them into a mold, dry them at 10°C to constant weight, and seal them in a package to obtain a new type of solid propellant. The oxidant contains moisture-proof dinitramide ammonium-A, pentaaminotetrazole nitrate, and RDX in a mass ratio of 1:0.2:0.15.

[0076] Example 2

[0077] A method for preparing a highly stable solid propellant includes the following steps:

[0078] Weigh out 85 wt% oxidant, 5 wt% nano iron powder, 6 wt% hydroxyl-terminated polybutadiene, and 4 wt% stabilizer-A based on 100 wt%. Mix them, compact them into a mold, dry them at 15°C to constant weight, and seal them in a package to obtain a new type of solid propellant. The oxidant contains moisture-proof dinitramide ammonium-A, pentaaminotetrazole nitrate, and RDX in a mass ratio of 1:0.16:0.12.

[0079] Example 3

[0080] A method for preparing a highly stable solid propellant includes the following steps:

[0081] Weigh out 70 wt% oxidant, 10 wt% nano iron powder, 14 wt% hydroxyl-terminated polybutadiene, and 6 wt% stabilizer-A based on 100 wt%. Mix them, compact them into a mold, dry them at 5°C to constant weight, and seal them in a package to obtain a new type of solid propellant. The oxidant contains moisture-proof dinitramide ammonium-A, pentaaminotetrazole nitrate, and RDX in a mass ratio of 1:0.25:0.18.

[0082] Example 4

[0083] This embodiment provides a method for preparing a highly stable solid propellant. The specific implementation method is the same as in Embodiment 1, except that stabilizer-A is replaced by an equal amount of stabilizer-B.

[0084] Example 5

[0085] This embodiment provides a method for preparing a highly stable solid propellant. The specific implementation method is the same as in Embodiment 1, except that stabilizer-A is replaced by an equal amount of stabilizer-C.

[0086] Example 6

[0087] This embodiment provides a method for preparing a highly stable solid propellant. The specific implementation method is the same as in Embodiment 1, except that stabilizer-A is replaced by an equal amount of stabilizer-D.

[0088] Example 7

[0089] This embodiment provides a method for preparing a highly stable solid propellant. The specific implementation method is the same as in Embodiment 1, except that stabilizer-A is replaced by an equal amount of stabilizer-E.

[0090] Example 8

[0091] This embodiment provides a method for preparing a highly stable solid propellant. The specific implementation method is the same as in Embodiment 1, except that stabilizer-A is replaced by an equal amount of stabilizer-F.

[0092] Example 9

[0093] This embodiment provides a method for preparing a highly stable solid propellant. The specific implementation method is the same as in Embodiment 1, except that moisture-proof dinitramide ammonium-A is replaced by an equal amount of moisture-proof dinitramide ammonium-B.

[0094] Example 10

[0095] This embodiment provides a method for preparing a highly stable solid propellant. The specific implementation method is the same as in Embodiment 1, except that moisture-proof dinitramide ammonium-A is replaced by an equal amount of moisture-proof dinitramide ammonium-C.

[0096] Comparative Example 1

[0097] This comparative example provides a method for preparing a highly stable solid propellant. The specific implementation method is the same as in Example 1, except that the moisture-proof dinitramide ammonium-A is replaced by an equal amount of dinitramide ammonium.

[0098] Performance testing:

[0099] 1. Combustion heat test:

[0100] The specific testing methods are described in section 2.2.9, "Energy Performance Testing Methods," of the paper "Preparation and Combustion Performance Study of Novel TAGN Fuel-Rich Solid Propellant."

[0101] 2. Combustion rate test

[0102] The solid propellants provided in each embodiment were cut into strips of 5mm × 5mm × 150mm. The burning rate was measured according to QJ 915-85, "Determination Method of Burning Rate, Burning Rate Pressure Index and Burning Rate Temperature Sensitivity Coefficient of Composite Solid Propellant Strips (Target Line Method)". An ignition wire was passed through the beginning of the strip for ignition. The strip was then coated with a coating liquid (for flame retardation). Timing began when the first target line melted and stopped when the second target line melted. The burning rate was calculated based on the distance between the two target lines and the time difference between melting points. The test pressure was 7MPa.

[0103] The test results are shown in Table 1.

[0104] Table 1 Performance Test Results

[0105] Example 1 11178.3 9.79 Example 2 11095.5 9.24 Example 3 11122.9 9.47 Example 4 10141.3 8.80 Example 5 10547.4 8.92 Example 6 10883.3 8.97 Example 7 10428.1 8.86 Example 8 10705.7 8.95 Example 9 10123.8 8.71 Example 10 10004.2 8.45 Comparative Example 1 9962.5 8.34

[0106] As shown in Table 1, compared with other examples and comparative examples, the solid propellants of Examples 1-3 have higher heat of combustion and faster combustion rate. As shown in Example 1 and Comparative Example 1, ammonium dinitramide that has not undergone moisture-proofing treatment reduces the heat of combustion and combustion rate of the solid propellant.

[0107] Compared to Example 1, the stabilizer in Example 4 did not contain fullerene, but only amino heterocyclic compounds. The changes in combustion heat and combustion rate indicate that although the amino heterocyclic compounds still inhibit the autocatalytic decomposition of solid propellants, the presence of fullerene can further enhance this performance. As shown in Examples 1 and 5-6, the amount of sodium nitrite used in the preparation of the stabilizer affects the formation of amino heterocyclic compounds, which is detrimental to the stabilizer's inhibition of autocatalytic decomposition of solid propellants, leading to partial decomposition of the oxidizer and a decrease in combustion heat and combustion rate. In Examples 7-8, compared to Example 1, the amount of amino heterocyclic compounds used in the stabilizer preparation was changed, resulting in a change in its ratio with brominated fullerene. This affected the connection between brominated fullerene and the amino heterocyclic compounds, which is detrimental to inhibiting the self-decomposition of the oxidizer, leading to oxidizer failure and ultimately a decrease in combustion heat and combustion rate.

[0108] Compared to Example 1, Example 9 did not use a surfactant when preparing moisture-proof dinitramide ammonium; while the moisture-proof dinitramide ammonium in Example 10 did not use CuO as a template during preparation. Both of these will lead to insufficient moisture-proof treatment, which in turn will result in a decrease in combustion heat and combustion rate.

[0109] The embodiments and comparative examples described above do not limit the present invention in any way. Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make some modifications or alterations to the above-disclosed technical content to create equivalent embodiments without departing from the scope of the present invention. Any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the scope of the present invention shall still fall within the scope of the present invention.

Claims

1. A method for preparing a highly stable solid propellant, characterized in that, The process includes the following steps: Weigh 70-85 wt% oxidant, 5-10 wt% nano iron powder, 6-14 wt% binder, and 4-6 wt% stabilizer per 100 wt%, mix them, compact them into a mold, dry them at 5-15°C to constant weight, and seal them in packaging to obtain the novel solid propellant. The oxidant comprises moisture-resistant dinitramide ammonium, pentamidotetraazole nitrate, and RDX.

2. The method for preparing a highly stable solid propellant according to claim 1, characterized in that, The preparation steps of the moisture-proof dinitramide ammonium are as follows: Prepare an acetone-dichloromethane mixed solution. Add dinitramide ammonium to the mixed solution at 15-25°C until a saturated dinitramide ammonium solution is formed. While stirring at 800-1200 rpm, add the saturated dinitramide ammonium solution dropwise to a CuO-dichloromethane suspension at a rate of 0.5-1.5 mL / min. Add Tween-80, stir for 30-60 min, and then recrystallize at -3-5°C to obtain the moisture-proof dinitramide ammonium.

3. The method for preparing a highly stable solid propellant according to claim 2, characterized in that, The concentration of the CuO-dichloromethane suspension is 0.005–0.012 g / mL.

4. The method for preparing a highly stable solid propellant according to claim 3, characterized in that, The volume ratio of the saturated dinitramide ammonium solution to the CuO-dichloromethane suspension is 1:(8-12).

5. The method for preparing a highly stable solid propellant according to claim 1, characterized in that, The adhesive is any one of polyurethane, glycidyl ether, polycaprolactone, and polybutadiene.

6. The method for preparing a highly stable solid propellant according to claim 1, characterized in that, The preparation steps of the stabilizer are as follows: S1. Methyl cyanoacetate, sodium nitrite and distilled water were stirred to obtain a mixture. The mixture was cooled to -3 to 5°C and glacial acetic acid was added. The mixture was stirred at room temperature for 3 to 4 hours. After stirring, the pH was adjusted to 1 to 2. The mixture was extracted, washed, dried and distilled under reduced pressure to obtain reactant 1. S2. Prepare a potassium hydroxide solution with a concentration of 0.18–0.24 g / mL. Add a hydroxylamine solution with a concentration of 45–55 wt% and a reactant 1 solution with a concentration of 0.42–0.56 g / mL at -3–5℃. Stir for 1–2 hours, raise the temperature to 90–100℃, and continue stirring for 1–2 hours. After stirring, cool to 5–15℃, adjust the pH to <1, lower the temperature to -10–-5℃, let stand for 1–2 hours, filter, and dry to obtain an amino heterocyclic compound. S3. Mix fullerene and bromine and let stand for 12-20 minutes. Filter and air dry to obtain brominated fullerene. S4. Under nitrogen protection, brominated fullerene and o-dichlorobenzene are stirred at room temperature for 20-40 minutes, and the amino heterocyclic compound obtained in step S2 is added. The mixture is stirred at 10-20°C until the solid disappears, filtered, distilled under reduced pressure, and recrystallized to obtain the stabilizer.

7. The method for preparing a highly stable solid propellant according to claim 6, characterized in that, In step S1, the mass ratio of methyl cyanoacetate to sodium nitrite is 1:(0.79-0.92).

8. The method for preparing a highly stable solid propellant according to claim 6, characterized in that, In step S3, the ratio of fullerene to bromine is (10-16) mg: 1 mL.

9. The method for preparing a highly stable solid propellant according to claim 6, characterized in that, In step S4, the mass ratio of the brominated fullerene to the amino heterocyclic compound is 1:(3.2-5.8).

10. A highly stable solid propellant obtained by the preparation method according to any one of claims 1-9, characterized in that, The heat of combustion of the solid propellant is ≥9900 J / g.