A fast response hydrocarbon propellant and a method of making the same

Abstract

The present application relates to propellant technical field, specifically disclose a kind of quick response hydrocarbon propellant and its preparation method, by mass percentage includes composite hydrocarbon fuel: 26~40%;Oxidant: 30~35%;Metal fuel: 8~15%;Binder: 18~23%;Process aid: 0.1~1.6%;Binder is the combination of butadiene rubber and polybutadiene.This hydrocarbon propellant uses butadiene rubber with melting temperature of 80 DEG C as binder matrix and uses liquid PB with molecular weight of 2000~2500 as auxiliary binder, ensure propellant mixing process performance, improve the bonding performance between hydrocarbon fuel system and binder, improve the mechanical properties of propellant;And the present application uses non-polyurethane binder system, solves the problem that polyurethane curing system is cured by environmental humidity, and propellant strength is less affected by environment.

Description

Technical Field

[0001] This invention relates to the field of propellant technology, specifically to a fast-responding hydrocarbon propellant and its preparation method. Background Technology

[0002] Hydrocarbon propellants are propellants that use solid hydrocarbon fuels as their primary fuel. They have low combustion and decomposition temperatures, and the resulting small-molecule hydrocarbon fragments are easily combustible. Furthermore, they produce clean combustion gases with minimal residue and low engine plume smoke, meeting the requirements for low-smoke or smokeless missiles. However, because hydrocarbon propellants use an isocyanate curing system, the curing process is highly sensitive to water. The propellant is susceptible to structural defects or performance deviations due to humidity levels caused by climatic conditions. Additionally, the long manufacturing cycle of isocyanate curing limits its mass production scale and restricts the deployment of isocyanate-based hydrocarbon propellants.

[0003] Thermoplastic adhesives eliminate the curing and cross-linking reaction in propellant manufacturing, avoiding a series of problems associated with traditional propellant manufacturing, particularly the chemical compatibility of key components and the pot life of the propellant. Thermoplastic adhesives possess a reversible curing system. The propellant development model and production process determined based on the characteristics of thermoplastic adhesives are fundamentally different from those of traditional propellants. The process is simpler, the production cycle is shorter, and it is easier to achieve large-scale continuous production of propellants.

[0004] ZL 201510940390.5 discloses a thermoplastic hydrocarbon propellant composition, using a hard segment monomer of styrene-containing polyester and 3,3-bis(azidomethyloxetane), a soft segment monomer of polyethylene glycol with a molecular weight of 800-4000, and a thermoplastic binder of isocyanate as the linker, achieving rapid propellant response. However, due to the weak interfacial interaction between the binder and the solid filler, the propellant strength is low, and since most hydrocarbon fuels used in the propellant have sublimation properties, the propellant cannot be stored for a long time. In addition, the binder used in ZL 201510940390.5 is self-prepared, and the raw materials for preparing the binder are all special raw materials with complex synthesis processes, requiring a lot of preparatory work. The total preparation cycle of the propellant is still long, and the production cost of the propellant is high, making it difficult to meet the needs of large-scale batch production. At the same time, the current polyurethane curing system is easily affected by the ambient temperature and humidity when preparing hydrocarbon propellants, resulting in poor environmental adaptability. Summary of the Invention

[0005] To address the aforementioned problems, the first objective of this invention is to provide a fast-responding hydrocarbon propellant. This hydrocarbon propellant uses styrene-butadiene rubber with a melting temperature of 80°C as the binder matrix and liquid PB with a molecular weight of 2000-2500 as an auxiliary binder. This ensures the performance of the propellant mixing process while improving the adhesion between the hydrocarbon fuel system and the binder, thereby enhancing the mechanical properties of the propellant. Furthermore, this invention uses a non-polyurethane binder system, solving the problem of polyurethane curing systems being affected by environmental temperature and humidity, thus minimizing the impact of environmental factors on propellant strength.

[0006] The second objective of this invention is to provide a method for preparing a fast-response hydrocarbon propellant. This method eliminates the curing and cross-linking reaction, so the propellant preparation does not require a long-term heat preservation and curing process, resulting in a short production cycle, low energy consumption, and low cost.

[0007] The first technical solution adopted in this invention is: a fast-response hydrocarbon propellant, comprising the following components by mass percentage:

[0008] Composite hydrocarbon fuels: 26-40%;

[0009] Oxidizing agent: 30-35%;

[0010] Metal fuels: 8-15%;

[0011] Adhesive: 18-23%;

[0012] Processing aids: 0.1–1.6%;

[0013] The adhesive is a combination of styrene-butadiene rubber and polybutadiene.

[0014] Preferably, the composite hydrocarbon fuel uses porous polystyrene as a matrix, and under the action of the composite additive polyethylene glycol monobutyl ether acrylate / acrylonitrile / allylamine / propylene alcohol / hydroxyethyl acrylate copolymer, the cage-like hydrocarbon pentacyclic [5.4.0.0] are formed. 2,6 .0 3,10 .0 5,9 It was prepared by combining undecane with porous polystyrene.

[0015] Preferably, the particle size of the composite hydrocarbon fuel is 20–50 μm.

[0016] Preferably, the oxidant is one or more of ammonium perchlorate and potassium perchlorate.

[0017] Preferably, the metal fuel is one or more of aluminum powder, magnesium powder, and boron powder.

[0018] Preferably, the mass ratio of styrene-butadiene rubber to polybutadiene is 8:1 to 10:1.

[0019] Preferably, the molecular weight of the polybutadiene is 2000 to 2500.

[0020] Preferably, the process aid is one or more of the following: ferric polyacrylate, tris[1-(2-methyl)aziridinyl]phosphine oxide, N,N-diphenyl-p-phenylenediamine, N-phenyl-2-naphthylamine, and N-phenyl-N-cyclohexyl-p-phenylenediamine.

[0021] The second technical solution adopted in this invention is: a method for preparing a hydrocarbon propellant as described in the first technical solution, comprising the following steps:

[0022] S1. Weigh each component in a dry environment and set aside for later use;

[0023] S2. Add process aids to polybutadiene and mix well to obtain a premixed slurry; add the premixed slurry, styrene-butadiene rubber, metal fuel, composite hydrocarbon fuel, and oxidant to a mixer in sequence for mixing to obtain a hydrocarbon propellant slurry, and discharge it;

[0024] S3. The hydrocarbon propellant slurry is added to a twin-screw extruder for granulation to obtain hydrocarbon propellant pellets.

[0025] Preferably, the method for preparing the hydrocarbon propellant further includes the following steps:

[0026] Weigh the hydrocarbon propellant particles and add them to a mold, heat until melted, and then apply a vacuum. Cool the mixture to room temperature in a dry environment to obtain the hydrocarbon propellant product.

[0027] The beneficial effects of the above technical solution are as follows:

[0028] (1) The fast-response hydrocarbon propellant disclosed in this invention uses PCU series compounds with high density and high energy performance but sublimation characteristics to be adsorbed by porous polypropylene, which inhibits the sublimation of PCU and greatly enhances stability; at the same time, a thermoplastic adhesive is used to mix the propellant components by hot melting and to prepare the propellant by natural cooling molding, which solves the problem of the curing of polyurethane curing system being affected by environmental temperature and humidity, and the propellant strength is less affected by the environment; moreover, since there is no polyurethane reaction in the production process, the preparation of the propellant does not require a long heat preservation curing process, and the propellant production cycle is greatly shortened.

[0029] (2) The fast-response hydrocarbon propellant disclosed in this invention adopts a thermoplastic curing system, which solves the problem of the application of easily hygroscopic components in the propellant formulation. Moreover, since there is no polyurethane reaction in the production process, the problem of the curing of the polyurethane curing system being affected by the ambient temperature and humidity is solved. The propellant strength is less affected by the environment, and the propellant preparation does not require a long-term heat preservation curing process, which greatly shortens the propellant production cycle.

[0030] (3) The method for preparing a fast-response hydrocarbon propellant disclosed in this invention adopts a prefabrication method. The hydrocarbon propellant is first prefabricated into hydrocarbon propellant pellets. During loading, the hydrocarbon propellant pellets are directly placed in a mold for hot melting, cooling and solidification, which omits the casting process and simplifies the process. The hydrocarbon propellant manufacturing is less affected by the mold, and a fast response is achieved in loading hydrocarbon propellant.

[0031] (4) The present invention adopts an adsorption-type hydrocarbon fuel system, which adsorbs small molecule PCU compounds with excellent combustion performance onto a porous hydrocarbon matrix, thereby greatly enhancing the stability of hydrocarbon fuel and the propellant storage performance.

[0032] (5) The present invention uses styrene-butadiene rubber with a melting temperature of 80°C as the adhesive matrix and liquid PB with a molecular weight of 2000-2500 as the auxiliary adhesive. While ensuring the performance of the propellant mixing process, it improves the adhesion between the hydrocarbon fuel system and the adhesive and enhances the mechanical properties of the propellant.

[0033] (6) The present invention adopts a composite hydrocarbon fuel system. During the combustion process of the propellant, at a higher temperature, PCU escapes from the porous structure, making combustion easier and the propellant has a higher burning rate and pressure index.

[0034] (7) The hydrocarbon propellant disclosed in this invention can be used for the rapid manufacturing of ramjet engines. This hydrocarbon propellant has a short production cycle, low energy consumption, and low cost. Furthermore, according to the room temperature sensitivity test data of the hydrocarbon propellant (friction sensitivity / % (25℃, 90°, 4.0MPa) is 0, electrostatic sensitivity E...),... 50 The values ​​of 143.1 to 150.4 mJ (25℃, 10000 PF) and 0% impact sensitivity (25℃, 50cm, 10kg) indicate that it has excellent safety performance and is a safe and insensitive propellant, suitable for the production of gas generators and battlefield rapid response small tactical weapons. Attached Figure Description

[0035] Figure 1 This is a schematic flowchart of a fast-response hydrocarbon propellant preparation method provided in one embodiment of the present invention. Detailed Implementation

[0036] The present invention will be further illustrated below with specific embodiments. It should be noted that those skilled in the art can make several modifications and improvements without departing from the principle of the present invention, and these should also be considered to fall within the protection scope of the present invention.

[0037] The terms “first,” “second,” etc. (if applicable) in the specification and claims are used to distinguish similar objects and are not necessarily used to describe a particular order or sequence. It should be understood that such data used in this way can be interchanged where appropriate so that the embodiments described herein can be implemented in orders other than those illustrated or described herein. Furthermore, the terms “comprising” and “having,” and any variations thereof, are intended to cover a non-exclusive inclusion, such as a process, method, system, product, or apparatus that comprises a series of steps or units, not necessarily limited to those explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0038] The contents not described in detail in this specification are common knowledge to those skilled in the art.

[0039] This invention discloses a fast-response hydrocarbon propellant, comprising the following components by mass percentage:

[0040] Composite hydrocarbon fuels: 26-40%;

[0041] Oxidizing agent: 30-35%;

[0042] Metal fuels: 8-15%;

[0043] Adhesive: 18-23%;

[0044] Processing aids: 0.1–1.6%.

[0045] The composite hydrocarbon fuel uses porous polystyrene (HPS) as a matrix, and under the combined action of the composite additive polyethylene glycol monobutyl ether acrylate / acrylonitrile / allylamine / propylene alcohol / hydroxyethyl acrylate copolymer (PANE), it can easily sublimate high-density cage-like hydrocarbon pentacyclic [5.4.0.0]. 2,6 .0 3,10 .0 5,9 Undecane (PCU) was combined with porous polystyrene to prepare a stable, non-sublimation composite hydrocarbon fuel (HPSPCU). The particle size of the composite hydrocarbon fuel was 20–50 μm.

[0046] Studies have found that porous activated carbon, silica, and hyperbranched resins can all adsorb PCU, and the adsorbed PCU does not sublimate at relatively low temperatures, significantly improving its storage stability. Polystyrene (PS) has a density of 1.04 g / cm³. 3 Its calorific value is 46 MJ / kg, and its volumetric calorific value is 47.8 MJ / dm³. 3Because polystyrene has a low density, using it alone as a propellant fuel would reduce the propellant density and consequently its volumetric calorific value. This invention employs porous HPS combined with PANE to adsorb PCU. HPS has irregular internal pores, and this irregular structure results in a high binding energy between it and PCU, allowing PCU to be adsorbed. PANE possesses active functional groups such as amino and hydroxyl groups, which further enhance the adsorption between PCU and HPS. Under the action of PANE, the binding energy between PCU and porous HPS is stronger, and it will not sublimate below 106℃, meeting the requirements for propellant storage stability. The prepared composite hydrocarbon fuel has a density of 1.20 g / cm³. 3 Its calorific value is 44.8 MJ / kg, and its volumetric calorific value is 53.6 MJ / dm³. 3 It can meet the requirements of high density and high calorific value of propellants.

[0047] The oxidant is one or more of ammonium perchlorate (AP) and potassium perchlorate (KP); the type of oxidant includes one or more of Class I, Class III, Class IV, and Class V; the particle size range of Class I is 280 μm to 360 μm, the particle size range of Class III is 90 μm to 140 μm, the particle size range of Class IV is 5 μm to 15 μm, and the particle size range of Class V is 0.5 μm to 2 μm.

[0048] The metal fuel is one or more of aluminum powder (Al), magnesium powder (Mg), and boron powder (B); the metal fuel is spherical and includes one or more of FLQT1, FLQT3, FLQT4, and FLQT5; the particle size range of FLQT1 is 29μm±3μm, the particle size range of FLQT3 is 13μm±3μm, the particle size range of FLQT4 is 6μm±1.5μm, and the particle size range of FLQT5 is 2μm±1μm.

[0049] The adhesive is a combination of styrene-butadiene rubber (PBS) and liquid polybutadiene (PB), wherein the mass ratio of PBS to liquid polybutadiene is 8:1 to 10:1, the melting temperature of PBS is 80°C, and the molecular weight of liquid polybutadiene is 2000 to 2500.

[0050] Experiments have confirmed that the composite hydrocarbon fuel (HPSPCU) does not soften or sublimate below 106℃. Using styrene-butadiene rubber (SBR) with a melting temperature of 80℃ as the binder matrix ensures that the composite hydrocarbon fuel does not undergo structural changes. Adding liquid polybutadiene with a molecular weight of 2000-2500 as an auxiliary binder to the binder system allows the SBR to swell sufficiently and lowers its melting temperature, ensuring that the viscosity of the binder system is below 5 Pa·s at 80℃, which is beneficial for the thorough mixing of hydrocarbon propellant components. Moreover, the composite hydrocarbon fuel has structural defects such as depressions and cracks on its surface. Liquid polybutadiene can penetrate into these defects and form a cross-linked network with the composite hydrocarbon fuel, making the bond between the composite hydrocarbon fuel and the binder matrix stronger.

[0051] The process aids are one or more of the following: polyferric acrylate (PAAF), tris[1-(2-methyl)aziridinyl]phosphine oxide, N,N-diphenyl-p-phenylenediamine (antioxidant DPPD), N-phenyl-2-naphthylamine (antioxidant D), and N-phenyl-N-cyclohexyl-p-phenylenediamine (antioxidant 4010). This invention uses polymeric iron salt PAAF as a burning rate catalyst, which ensures that the burning rate of hydrocarbon propellants is increased without reducing the safety performance of hydrocarbon propellants.

[0052] like Figure 1 As shown, this invention also discloses a method for preparing a fast-response hydrocarbon propellant, comprising the following steps:

[0053] S1. Weighing: Accurately weigh each component in a dry environment and set aside for later use;

[0054] S2. Mixing: Add process aids to liquid polybutadiene and mix manually to obtain a premixed slurry; add the premixed slurry, styrene-butadiene rubber, metal fuel, composite hydrocarbon fuel, and oxidant to a mixer in sequence, and mix at 80℃~85℃ for 1~1.5 hours to obtain a hydrocarbon propellant slurry, and discharge it.

[0055] S3. Granulation: The hydrocarbon propellant slurry is added to a twin-screw extruder for granulation to obtain hydrocarbon propellant pellets, which are then stored in a cool, dry, and dark place.

[0056] Furthermore, the preparation of hydrocarbon propellant products includes: weighing the hydrocarbon propellant particles and adding them into a mold, heating to 80°C to 85°C to melt, controlling the vacuum degree to be less than or equal to 300 Pa, and evacuating for 1 hour; cooling to room temperature in a dry environment to obtain the hydrocarbon propellant product.

[0057] Example 1

[0058] Table 1 Propellant Formulation Composition

[0059]

[0060] Weigh each component according to the formula in Table 1, add the process aids to the liquid polybutadiene and mix by hand to obtain a premixed slurry;

[0061] The propellant mixing process is shown in Table 2;

[0062] Table 2 Propellant Mixing

[0063]

[0064] Granulation: The propellant is added to a twin-screw extruder for granulation. The temperature is controlled at 90℃, and granulation is completed in 3 hours to obtain propellant pellets with a diameter of 0.7 mm and a length of 2 mm.

[0065] Product preparation: Weigh the propellant particles and add them to the mold. Heat to 80℃~85℃ to melt in an environment with a vacuum degree not exceeding 300Pa, and then evacuate for 1 hour. After that, cool to room temperature in a dry environment for 6 hours to obtain the propellant product.

[0066] The propellant performance test results are shown in Table 3.

[0067] Table 3 Performance of hydrocarbon propellants

[0068]

[0069] Example 2

[0070] Table 4 Propellant Formulation Composition

[0071]

[0072] Weigh each component according to the formula in Table 4, add the process aids to the liquid polybutadiene and mix by hand to obtain a premixed slurry;

[0073] The propellant mixing process is shown in Table 5;

[0074] Table 5 Propellant Mixing

[0075]

[0076]

[0077] Granulation: The propellant is added to a twin-screw extruder for granulation. The temperature is controlled at 90℃, and granulation is completed in 3 hours to obtain propellant pellets with a diameter of 0.7 mm and a length of 2 mm.

[0078] Product preparation: Weigh the propellant particles and add them to the mold. Heat to 80℃~85℃ to melt in an environment with a vacuum degree not exceeding 300Pa, and then evacuate for 1 hour. After that, cool to room temperature in a dry environment for 6 hours to obtain the propellant product.

[0079] The propellant performance test results are shown in Table 6.

[0080] Table 6 Performance of hydrocarbon propellants

[0081]

[0082] Example 3

[0083] Table 7 Propellant Formulation Composition

[0084]

[0085] Weigh each component according to the formula in Table 7, and prepare the hydrocarbon propellant product according to the preparation method in Example 1.

[0086] The propellant performance test results are shown in Table 8.

[0087] Table 8 Performance of hydrocarbon propellants

[0088]

[0089]

[0090] Example 4

[0091] Table 9 Propellant Formulation Composition

[0092]

[0093] Weigh each component according to the formula in Table 9, and prepare the hydrocarbon propellant product according to the preparation method in Example 1.

[0094] The propellant performance test results are shown in Table 10.

[0095] Table 10 Performance of hydrocarbon propellants

[0096]

[0097] Example 5

[0098] Table 11 Propellant Formulation Composition

[0099]

[0100]

[0101] Weigh each component according to the formula in Table 11, and prepare the hydrocarbon propellant product according to the preparation method in Example 1.

[0102] The propellant performance test results are shown in Table 12.

[0103] Table 12 Performance of hydrocarbon propellants

[0104]

[0105] Example 6

[0106] Table 13 Propellant Formulation Composition

[0107]

[0108] Weigh each component according to the formula in Table 13, and prepare the hydrocarbon propellant product according to the preparation method in Example 1.

[0109] The propellant performance test results are shown in Table 14.

[0110] Table 14 Performance of hydrocarbon propellants

[0111]

[0112] Example 7

[0113] Table 15 Propellant Formulation Composition

[0114]

[0115] Weigh each component according to the formula in Table 15, and prepare the hydrocarbon propellant product according to the preparation method in Example 1.

[0116] The propellant performance test results are shown in Table 16.

[0117] Table 16 Performance of Hydrocarbon Propellants

[0118]

[0119] Example 8

[0120] 300 kg of hydrocarbon propellant product was prepared according to the formulation of Example 3;

[0121] Weighing: Accurately weigh 61.5 kg of PBS, 7.2 kg of PB, 81 kg of HPSPCU, 105 kg of AP, 45 kg of boron powder and magnesium powder (36 kg of boron powder and 9 kg of magnesium powder) and 300 g of DPPD in a dry environment; and add DPPD to liquid PB and mix by hand to obtain a premixed slurry.

[0122] The propellant mixing process is shown in Table 17;

[0123] Table 17 Propellant Mixing

[0124]

[0125]

[0126] Granulation: The propellant is added to a twin-screw extruder for granulation. The temperature is controlled at 90℃, and granulation is completed in 3 hours to obtain propellant pellets with a diameter of 0.7 mm and a length of 2 mm.

[0127] Product preparation: Weigh the propellant particles and add them to the mold. Heat to 80℃~85℃ to melt in an environment with a vacuum degree not exceeding 300Pa, and then evacuate for 1 hour. After that, cool to room temperature in a dry environment for 6 hours to obtain the product.

[0128] The total manufacturing time for the propellant product is 12 hours.

[0129] The propellant performance test results are shown in Table 18;

[0130] Table 18 Performance of Hydrocarbon Propellants

[0131]

[0132] The performance data of hydrocarbon propellants in Examples 1 to 8 show that the combustion efficiency of the propellants is above 95%, the strength at room temperature is around 1.0 MPa, and the strength of the propellants did not change after 3 years of storage. Meanwhile, Examples 8 and 3 show that the prepared propellants have stable performance and high reproducibility.

[0133] Example 9

[0134] Taking the formulation of Example 3 as an example, the effect of preparing fast-response hydrocarbon propellants in different humidity environments on the mechanical properties of hydrocarbon propellants was further tested; the test results are shown in Table 19.

[0135] Table 19 Mechanical properties of the formulation in Example 3 under different humidity conditions

[0136]

[0137] As can be seen from the data in Example 9, the mechanical properties of the fast-response hydrocarbon propellant do not change much under different humidity conditions, and the hydrocarbon propellant has low sensitivity to humidity.

[0138] Comparative Example 1

[0139] Based on Example 8, 300 kg of hydrocarbon propellant product was prepared using a polyurethane curing system; the effects of different curing systems on propellant performance were investigated; Table 20 lists the formulation composition and performance for comparison.

[0140] Table 20 Propellant Formulation Composition

[0141]

[0142] Weighing: Accurately weigh 54.50 kg of HTPB, 4.60 kg of IPDI, 9.0 kg of HCEM, 81 kg of HPSPCU, 105 kg of AP, 45 kg of boron powder and magnesium powder (36 kg of boron powder and 9 kg of magnesium powder), 60 g of TPB, 540 g of MAPO, and 300 g of DPPD in a dry environment; add TPB, MAPO, DPPD, and HCEM to HTPB and mix by hand to obtain a premixed slurry.

[0143] The propellant mixing process is shown in Table 21;

[0144] Table 21 Propellant Mixing

[0145]

[0146] Casting: Add the propellant slurry to the vacuum casting tank, control the casting temperature at 50°C, control the vacuum degree to not exceed 300Pa, and complete the casting in 2 to 3 hours. Then continue to evacuate and maintain pressure for 30 minutes, and release the vacuum within 30 to 40 minutes to obtain the propellant prepolymer.

[0147] Curing: The propellant prepolymer is placed in a 60℃ dry environment for 7 days to cure and then discharged. It is then allowed to cool naturally in a room temperature dry environment for 5 hours to obtain the propellant product.

[0148] The total propellant manufacturing time is 178 hours.

[0149] The propellant performance test results are shown in Table 22.

[0150] Table 22 Performance of Hydrocarbon Propellants

[0151]

[0152] As can be seen from the data in Examples 3, 8 and Comparative Example 1, the mechanical properties of the propellant prepared by the thermoplastic curing system of the present invention are slightly lower than those of the propellant prepared by the polyurethane curing system, but the difference is not significant and can meet the application requirements; that is, the burning rate, pressure index, injection efficiency and combustion efficiency of the propellant prepared by the thermoplastic curing system are comparable to those of the propellant prepared by the polyurethane curing system.

[0153] The total preparation time for hydrocarbon propellant prepared by the thermoplastic curing system of this invention is 12 hours, while the total preparation time for hydrocarbon propellant prepared by the polyurethane curing system is 178 hours. Compared with the hydrocarbon propellant prepared by the polyurethane curing system, the preparation time of the thermoplastic curing hydrocarbon propellant is significantly reduced, making it suitable for rapid response in propellant preparation.

[0154] Comparative Example 2

[0155] Taking the formulation of Comparative Example 1 as an example, the influence of different humidity environments on the mechanical properties of hydrocarbon propellants when using a polyurethane curing system to prepare hydrocarbon propellants was further tested; the test results are shown in Table 23.

[0156] Table 23 Effects of different humidity environments on the mechanical properties of hydrocarbon propellants

[0157]

[0158] Data from Comparative Example 2 and Example 9 show that the hydrocarbon propellant prepared using the polyurethane curing system can withstand temperatures of 5.5 g H₂O·kg dry air. -1 With 6.8 g H2O·kg dry air -1 Under certain conditions, the mechanical properties do not change significantly, especially when the water content reaches 9.5 g H₂O·kg dry air. -1 When the humidity is above the specified level, the mechanical properties of the propellant decrease significantly; however, the thermoplastic fast-response hydrocarbon propellant of this invention does not change much in mechanical properties under different humidity conditions, and the hydrocarbon propellant has low humidity sensitivity and stronger environmental adaptability.

[0159] The present invention has been described in detail above with reference to specific embodiments and exemplary examples. These descriptions are exemplary and not exhaustive, and are not limited to the disclosed embodiments; the above descriptions should not be construed as limiting the present invention. Those skilled in the art will understand that various equivalent substitutions, modifications, or improvements can be made to the technical solutions and implementation methods of the present invention without departing from the spirit and scope of the present invention, and all such modifications and improvements fall within the scope of the present invention; the scope of protection of the present invention is determined by the appended claims.

Claims

1. A fast-response hydrocarbon propellant, characterized in that, The following components are included by mass percentage: Composite hydrocarbon fuels: 26-40%; Oxidizing agent: 30-35%; Metal fuels: 8-15%; Adhesive: 18-23%; Processing aids: 0.1–1.6%; The composite hydrocarbon fuel uses porous polystyrene as a matrix. Under the action of the composite additive polyethylene glycol monobutyl ether acrylate / acrylonitrile / allylamine / propylene alcohol / hydroxyethyl acrylate copolymer, the cage-like hydrocarbon pentacyclic [5.4.0.0] are... 2, 6 .0 3,10 .0 5,9 The composite hydrocarbon fuel is prepared by combining undecane with porous polystyrene; the particle size of the composite hydrocarbon fuel is 20~50μm; the binder is a combination of styrene-butadiene rubber and polybutadiene, the mass ratio of styrene-butadiene rubber to polybutadiene is 8:1~10:1, and the molecular weight of polybutadiene is 2000~2500.

2. The hydrocarbon propellant according to claim 1, characterized in that, The oxidant is one or more of ammonium perchlorate and potassium perchlorate.

3. The hydrocarbon propellant according to claim 1, characterized in that, The metal fuel is one or more of aluminum powder, magnesium powder, and boron powder.

4. The hydrocarbon propellant according to claim 1, characterized in that, The process aid is one or more of the following: iron polyacrylate, tris[1-(2-methyl)aziridinyl]phosphine oxide, N,N-diphenyl-p-phenylenediamine, N-phenyl-2-naphthylamine, and N-phenyl-N-cyclohexyl-p-phenylenediamine.

5. A method for preparing a hydrocarbon propellant as described in any one of claims 1-4, characterized in that, Includes the following steps: S1. Weigh each component in a dry environment and set aside for later use; S2. Add process aids to polybutadiene and mix well to obtain a premixed slurry; add the premixed slurry, styrene-butadiene rubber, metal fuel, composite hydrocarbon fuel, and oxidant to a mixer in sequence for mixing to obtain a hydrocarbon propellant slurry, and discharge it; S3. The hydrocarbon propellant slurry is added to a twin-screw extruder for granulation to obtain hydrocarbon propellant pellets.

6. The preparation method according to claim 5, characterized in that, It also includes the following steps: Weigh the hydrocarbon propellant particles and add them to a mold, heat until melted, and then apply a vacuum. Cool the mixture to room temperature in a dry environment to obtain the hydrocarbon propellant product.

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