Gel propellant, preparation method thereof and application of gel propellant in airspace engine power system
The gel propellant composed of carbon powder and aluminum powder in a specific proportion and particle size solves the problems of incomplete combustion and high viscosity of aluminum particles in the gel propellant, achieves efficient combustion and easy atomization, and reduces preparation costs.
Patent Information
- Application Number
- CN202511009847.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-07-22
- Publication Date
- 2025-10-10
AI Technical Summary
The incomplete combustion and high concentration viscosity of aluminum particles in existing gel propellants lead to decreased energy performance and difficulty in atomization. Existing improvement methods are costly and complex to operate.
Carbon powder and aluminum powder with specific proportions and particle sizes are used to form a non-Newtonian fluid fuel, which is gelled through a gelling agent to form a stable solid but easily liquefied gel propellant, including 5%-15% carbon powder, 35%-45% aluminum powder, 4%-6% gelling agent, and 44%-46% liquid fuel.
The combustion efficiency is increased to over 96%, the volumetric combustion heat can reach over 58.8 MJ/L, the viscosity is lower than 0.7 Pa·s at a shear rate of 1000s-1, it is easy to atomize, and the preparation cost is reduced.
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Figure CN120757428A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to a gel propellant and a preparation method thereof, and application thereof in a space engine power system. Background Art
[0002] Propellants are a crucial area of research in the aerospace field. With the continuous advancement of rockets and other spacecraft, the requirements for fuel performance are increasing. Gel propellants have emerged to develop new rocket propellants that offer high specific impulse, adjustable thrust, multiple ignition capabilities, and excellent safety and storage properties. Metallization by adding metal fuels to gel propellant systems can further enhance the energy performance of the gel system. Aluminum particles are widely used in gel propellants due to their high calorific value and thermal conductivity, abundant raw material resources, and non-polluting combustion products.
[0003] However, aluminum combustion products are Al2O3, and during combustion, a dense aluminum oxide film forms on the surface. This film hinders further contact between oxygen and the aluminum within, resulting in incomplete combustion. Numerous combustion experiments have shown that the agglomeration of aluminum particles can lead to a series of effects, including two-phase flow losses, decreased propellant energy characteristics, altered acoustic particle damping, and reduced engine specific impulse. Furthermore, adding too many aluminum particles to the gel system not only causes incomplete combustion but also results in excessive viscosity, complicating the subsequent atomization process.
[0004] Common methods for reducing the agglomeration of aluminum particles in propellants include coating the aluminum particles with fluorides, carbon-containing materials such as graphene oxide, and alloying with small amounts of other metals. These methods can improve aluminum's incomplete combustion characteristics to some extent, but some are costly and complex to prepare, making them difficult to implement in practice. Summary of the Invention
[0005] In order to solve the problems existing in the prior art, such as incomplete combustion of aluminum during the combustion process of high-concentration aluminum-containing gel propellants and the high viscosity of the high-concentration aluminum-containing gel, which makes atomization difficult, the present invention provides a gel propellant and a preparation method thereof, and its application in aerospace engine power systems. The gel propellant can improve the incomplete combustion of aluminum during the combustion process, has a high volumetric combustion heat, and can reduce the viscosity of the high-concentration aluminum-containing gel, thereby facilitating atomization. Therefore, the energy performance and practicality of the gel propellant can be simply and cost-effectively improved.
[0006] To achieve the above objectives, the present invention provides the following technical solutions.
[0007] The present invention provides a gel propellant, which comprises the following components, based on the total mass of the gel propellant being 100%:
[0008] Toner: 5%-15%;
[0009] Aluminum powder: 35%-45%;
[0010] Gelling agent: 4%-6%;
[0011] Liquid fuel: 44%-46%;
[0012] The particle size D32 of the carbon powder is 30 nm-20 μm; the particle size D32 of the aluminum powder is 1 μm-100 μm.
[0013] In the present invention, the gel propellant is a non-Newtonian fluid fuel formed by adding a small amount of gelling agent to a liquid fuel, thereby causing it to gel. In the absence of external forces, the gel propellant exhibits a stable solid form, does not flow, does not leak during storage, and rarely evaporates. However, under certain external forces, such as pressure or shear, it exhibits liquid properties, achieving flow and atomization.
[0014] In the present invention, the carbon powder refers to conventional amorphous carbon particles in the art.
[0015] In the present invention, the carbon powder is preferably one or more of charcoal, coke, bone char, sugar charcoal, activated carbon and carbon black.
[0016] In the present invention, the aluminum powder refers to conventional aluminum elemental particles in this field.
[0017] In the present invention, the particle size D32 refers to the Sauter Mean Diameter (SMD), which is six times the ratio of the sum of the particle volume to the sum of the surface area, and is an important parameter for characterizing the average particle size.
[0018] In some preferred embodiments, the particle size D32 of the carbon powder is 60 nm-20 μm, more preferably 500 nm-15 μm, for example 2 μm.
[0019] In some preferred embodiments, the content of the carbon powder is 5%-10%.
[0020] In some preferred embodiments, the particle size D32 of the aluminum powder is 1 μm-75 μm, more preferably 2 μm-50 μm, and further preferably 2 μm-5 μm.
[0021] In some preferred embodiments, the content of the aluminum powder is 40%-45%.
[0022] In some specific embodiments, the gel propellant includes the following components: carbon powder: 10%; aluminum powder: 40%; gelling agent: 6%; liquid fuel: 44%; wherein the particle size D32 of the carbon powder is 30 nm; and the particle size D32 of the aluminum powder is 1 μm.
[0023] In some specific embodiments, the gel propellant includes the following components: carbon powder: 5%; aluminum powder: 45%; gelling agent: 6%; liquid fuel: 44%; wherein the particle size D32 of the carbon powder is 30 nm; and the particle size D32 of the aluminum powder is 1 μm.
[0024] In some specific embodiments, the gel propellant includes the following components: carbon powder: 15%; aluminum powder: 35%; gelling agent: 6%; liquid fuel: 44%; wherein the particle size D32 of the carbon powder is 30 nm; and the particle size D32 of the aluminum powder is 1 μm.
[0025] In some specific embodiments, the gel propellant includes the following components: carbon powder: 10%; aluminum powder: 40%; gelling agent: 6%; liquid fuel: 44%; wherein the particle size D32 of the carbon powder is 500 nm; and the particle size D32 of the aluminum powder is 2 μm.
[0026] In some specific embodiments, the gel propellant includes the following components: carbon powder: 10%; aluminum powder: 40%; gelling agent: 6%; liquid fuel: 44%; wherein the particle size D32 of the carbon powder is 15 μm; and the particle size D32 of the aluminum powder is 1 μm.
[0027] In some specific embodiments, the gel propellant includes the following components: carbon powder: 10%; aluminum powder: 40%; gelling agent: 6%; liquid fuel: 44%; wherein the particle size D32 of the carbon powder is 20 μm; and the particle size D32 of the aluminum powder is 1 μm.
[0028] In some specific embodiments, the gel propellant comprises the following components: carbon powder: 10%; aluminum powder: 40%; gelling agent: 6%; liquid fuel: 44%; wherein the particle size D32 of the carbon powder is 60 nm; and the particle size D32 of the aluminum powder is 1 μm.
[0029] In some specific embodiments, the gel propellant comprises the following components: carbon powder: 10%; aluminum powder: 40%; gelling agent: 6%; liquid fuel: 44%; wherein the particle size D32 of the carbon powder is 30 nm; and the particle size D32 of the aluminum powder is 100 μm.
[0030] In some specific embodiments, the gel propellant comprises the following components: carbon powder: 10%; aluminum powder: 40%; gelling agent: 6%; liquid fuel: 44%; wherein the particle size D32 of the carbon powder is 30 nm; and the particle size D32 of the aluminum powder is 75 μm.
[0031] In some specific embodiments, the gel propellant comprises the following components: carbon powder: 10%; aluminum powder: 40%; gelling agent: 6%; liquid fuel: 44%; wherein the particle size D32 of the carbon powder is 30 nm; and the particle size D32 of the aluminum powder is 50 μm.
[0032] In some specific embodiments, the gel propellant includes the following components: carbon powder: 10%; aluminum powder: 40%; gelling agent: 6%; liquid fuel: 44%; wherein the particle size D32 of the carbon powder is 30 nm; and the particle size D32 of the aluminum powder is 5 μm.
[0033] In some preferred embodiments, the gelling agent comprises agarose and / or modified hydrogenated castor oil. The type of the modified hydrogenated castor oil is, for example, Thixatrol ST.
[0034] In some preferred embodiments, the content of the gelling agent is 5%-6%, for example, 5.5%.
[0035] In some preferred embodiments, the content of the liquid fuel is 45%-46%, for example 45.5%.
[0036] In some preferred embodiments, the liquid fuel includes kerosene and / or an alcohol fuel. The kerosene is, for example, RP-3 aviation kerosene. The alcohol fuel is, for example, ethanolamine. Alcohol fuel refers to a fuel containing at least one alcohol group. Kerosene, also known as kerosene or kerosene water, is a mixture of hydrocarbons obtained by fractional distillation of petroleum.
[0037] In some embodiments, the gel propellant is aviation kerosene gel propellant, the liquid fuel is RP-3 aviation kerosene and ethanol, the gelling agent is modified hydrogenated castor oil, and the type of the modified hydrogenated castor oil is Thixatrol ST.
[0038] In some embodiments, the volumetric heat of combustion of the gel propellant under 0.6 MPa of pure oxygen is greater than 58.8 MJ / L, preferably 58.81-60.34 MJ / L.
[0039] In some embodiments, the volumetric heat of combustion of the gel propellant under 3.5 MPa of pure oxygen is greater than 58.8 MJ / L, preferably 58.81-60.34 MJ / L.
[0040] In some embodiments, the gel propellant is subjected to a shear rate of 1000 s -1 The viscosity is lower than 0.7 Pa·s, preferably lower than 0.5 Pa·s.
[0041] The present invention provides a method for preparing the gel propellant as described above, comprising the following steps:
[0042] S1, mixing a gelling agent and a liquid fuel to obtain a first mixture;
[0043] The amount of the gelling agent is 4%-6%, and the amount of the liquid fuel is 44%-46%, where the percentages are the mass percentages of each component in the total mass of the gel propellant;
[0044] S2. Mixing carbon powder, aluminum powder, and the first mixed material to obtain a second mixed material, and letting the mixed material stand to obtain the gel propellant; wherein, the amount of the carbon powder is 5%-15%, and the amount of the aluminum powder is 35%-45%, and the percentage is the mass percentage of each component in the total mass of the gel propellant; the particle size D32 of the carbon powder is 30nm-20μm; and the particle size D32 of the aluminum powder is 1μm-100μm.
[0045] In step S1, the mixing temperature is preferably 50-70°C, for example 60°C.
[0046] In step S1, the mixing method may be stirring; the stirring speed is preferably 800-1200 rpm, for example, 1000 rpm, and the stirring time is preferably 5-10 minutes.
[0047] In step S2, the mixing temperature is preferably 50-70°C, for example 60°C.
[0048] In step S2, the mixing method may be stirring; the stirring speed is preferably 800-1200 rpm, for example, 1000 rpm, and the stirring time is preferably 5-15 minutes.
[0049] In step S2, the standing time is preferably 6-10 hours.
[0050] In step S2, the standing temperature is preferably room temperature.
[0051] In some preferred embodiments, in step S2, the method for preparing the second mixture includes the following steps: firstly mixing the carbon powder and the first mixture to obtain a third mixture; and then mixing the third mixture with the aluminum powder.
[0052] In some preferred embodiments, the method for preparing the second mixture in step S2 comprises the following steps: mixing the aluminum powder and the carbon powder to obtain a third mixture; and mixing the third mixture and the first mixture.
[0053] The solvent is added to the aluminum powder and the carbon powder, and the mixture is mixed to obtain a suspension; the suspension is filtered, and the solid is collected and dried to obtain the third mixture.
[0054] The application provides application of the gel propellant to a power system of a space engine.
[0055] On the basis of common knowledge in the art, the above-mentioned preferred conditions can be combined arbitrarily to obtain preferred examples of the application.
[0056] The reagents and raw materials used in the application are commercially available.
[0057] The positive progress effect of the application is that:
[0058] The gel propellant in the application improves the incomplete combustion of aluminum in the combustion process by using carbon powder and aluminum powder with specific amounts and particle sizes, has a high volumetric combustion heat, and can solve the problem of high viscosity of high-concentration gel propellant and difficulty in atomization, specifically:
[0059] (1) The maximum volumetric combustion heat can reach 58.8 MJ / L or even 60.34 MJ / L;
[0060] (2) The combustion efficiency can reach 96% or even 98.7%;
[0061] (3) The viscosity of the gel propellant can be lower than 0.7 Pa·s or even lower than 0.5 Pa·s at a shear rate of 1000 s -1 , which is more easily atomized.
[0062] In addition, compared with other ways to alleviate the incomplete combustion of aluminum, the gel propellant in the application has obvious alleviating effect, is easy to prepare and has low cost. BRIEF DESCRIPTION OF DRAWINGS
[0063] Figure 1 The figure is a comparison of the volumetric combustion heat of the gel propellants in Examples 1-3 and Comparative Example 1 under pure oxygen at 3.5 MPa.
[0064] Figure 2 The figure is an XRD pattern of the combustion products of the gel propellants in Examples 1-3 and Comparative Example 1.
[0065] Figure 3This is a scanning electron microscope image of the combustion product of the gel propellant in Comparative Example 1.
[0066] Figure 4 This is a scanning electron microscope image of the combustion products of the gel propellant in Example 3. DETAILED DESCRIPTION
[0067] The present invention is further illustrated by way of examples below, but the present invention is not limited to the scope of the examples. Experimental methods in the following examples where specific conditions are not specified were performed according to conventional methods and conditions, or selected according to the product specifications.
[0068] In the following examples and comparative examples, the carbon powder used is carbon black.
[0069] Example 1
[0070] The composition and preparation method of the aluminum-containing aviation kerosene gel propellant mixed with nano-carbon powder, as well as the formula components and their mass fractions are shown in Table 1.
[0071] Table 1 Formula and components of aviation kerosene gel propellant
[0072]
[0073] The preparation method of the above-mentioned aviation kerosene gel propellant comprises the following steps:
[0074] S1: Pour weighed aluminum powder and carbon powder into anhydrous ethanol to prepare a suspension, stir evenly, and filter. Collect the solid on the filter paper and dry it in a vacuum drying oven to obtain a uniformly mixed aluminum powder-nanocarbon powder mixture.
[0075] S2: Preheat the water bath to 60°C. Add the weighed Thixatrol ST powder to the RP-3 aviation kerosene. Stir the mixture at 1000 rpm using a stirring paddle in a 60°C water bath. Once the Thixatrol ST is dispersed in the aviation kerosene, slowly add the weighed anhydrous ethanol and continue stirring for 5 minutes.
[0076] S3: The mixed particles obtained in S1 were added to the gel obtained in S2, and stirred at 1000 rpm for 15 min in a 60°C water bath with a stirring paddle to fully disperse the particles in the aviation kerosene gel system.
[0077] S4: The gel obtained in S3 was sealed and allowed to stand at room temperature for 6 h to obtain an aviation kerosene gel with an energetic particle (aluminum powder and carbon powder) concentration of 50 wt%.
[0078] RP-3 aviation kerosene is No. 3 jet fuel under GB 6537-2018 standard; it is composed of 10 kinds of main hydrocarbons, mainly alkanes and cycloalkanes, with low aromatic hydrocarbon content, and the specific ratio is as follows:
[0079] (1) Alkanes (about 62%): n-octane (4.56%), n-decane (9.49%), n-dodecane (22.69%), n-tridecane (9.82%), n-tetradecane (13.21%), n-hexadecane (15.08%);
[0080] (2) Cycloalkanes (about 33%): methylcyclohexane (13.08%), trans-1,3-dimethylcyclopentane (5.23%);
[0081] (3) Aromatic hydrocarbons (about 5%): n-propylbenzene (4.00%), 1-methylnaphthalene (2.84%);
[0082] (4) A small amount of additives: ① Antistatic agent: such as Stadis 450 (containing dinonylnaphthalene sulfonic acid), which can increase the conductivity to 50-600 pS / m and prevent static electricity accumulation; ② Antioxidant: such as AO-30 (alkaline phenol), which can inhibit the formation of gum and prolong the storage period; ③ Anti-icing agent: such as ethylene glycol monomethyl ether, which can lower the freezing point and prevent the fuel system from icing.
[0083] Example 2
[0084] On the basis of Example 1, the amount of carbon powder is 5wt%, and the amount of aluminum powder is 45wt%. The remaining conditions and Example 1 remain unchanged.
[0085] Example 3
[0086] On the basis of Example 1, the amount of carbon powder is 15wt%, and the amount of aluminum powder is 35wt%. The remaining conditions and Example 1 remain unchanged.
[0087] Example 4
[0088] S1: The water bath is heated to 60°C in advance, and the weighed Thixatrol ST powder is added to the RP-3 aviation kerosene, and stirred at a speed of 1000 rpm under the water bath at 60°C with a stirring paddle. After the Thixatrol ST is dispersed in the aviation kerosene, slowly pour the weighed anhydrous ethanol, and continue to stir for 5 min.
[0089] S2: First, add carbon powder particles to the gel obtained in S1, and stir at 1000 rpm with a stirring paddle in a water bath at 60°C for 15 minutes to fully disperse the particles in the aviation kerosene gel system; then, add aluminum powder particles to the gel, and stir at 1000 rpm with a stirring paddle in a water bath at 60°C for 15 minutes to fully disperse the particles in the aviation kerosene gel system.
[0090] S3: The gel obtained in S2 was sealed and allowed to stand at room temperature for 6 h to obtain an aviation kerosene gel with an energetic particle concentration of 50 wt%.
[0091] Example 5
[0092] Except that the particle size of the carbon powder and the particle size of the aluminum powder in Table 1 are different from those in Example 4, the other conditions are the same as those in Example 4.
[0093] Examples 6-12
[0094] Except that the particle size of the carbon powder or the particle size of the aluminum powder in Table 1 is different from that in Example 1, other conditions are the same as those in Example 1.
[0095] Comparative Example 1
[0096] Based on Example 1, no carbon powder was added, the amount of aluminum powder used was 50 wt %, and the other conditions remained the same as in Example 1.
[0097] Comparative Examples 2-5
[0098] Except that the particle size of the carbon powder or the particle size of the aluminum powder in Table 1 is different from that in Example 1 (too large or too small), the other conditions are the same as those in Example 1.
[0099] Effect Example 1
[0100] The following tests were performed on the gel propellants in Examples 1-12 and Comparative Examples 1-5:
[0101] (1) Combustion performance
[0102] Volumetric heat of combustion under pure oxygen: An oxygen bomb calorimeter (manufacturer: Changsha Kaiyuan Instrument Co., Ltd., model 5E-AC8018) was used to test the volumetric heat of combustion under pure oxygen (at 3.5 MPa or 0.6 MPa, respectively). The specific test method is as follows:
[0103] In an oxygen bomb, fuel is mixed with excess oxygen and ignited. The heat generated by the combustion is absorbed by the water or other medium and converted into a temperature rise. By measuring parameters such as the mass, initial temperature, final temperature, and heat capacity of the medium, the volumetric heat of combustion of the fuel can be calculated.
[0104] Based on this, the combustion efficiency is calculated using the test data of volumetric combustion heat under 0.6MPa pure oxygen. The specific calculation method is: the ratio of the heat actually utilized by the fuel during the combustion process to the maximum heat that can be released when the fuel is completely burned.
[0105] When the content of energetic particles (carbon powder and aluminum powder) in the gel propellant obtained by using aviation kerosene as liquid fuel is 50wt%, the comparison of the volumetric combustion heat of the gel propellant in Examples 1-3 and Comparative Example 1 under 3.5MPa pure oxygen is shown in the figure below: Figure 1 As shown in the figure, the results show that the addition of carbon powder effectively increases the volumetric combustion heat of gel propellant.
[0106] In Example 1, the volumetric heat of combustion of the gel propellant provided in this example under 0.6 MPa of pure oxygen is 59.71 MJ / L, which is 21.2% higher than that of the gel propellant without carbon powder added (Comparative Example 1).
[0107] The specific test results are shown in Table 1.
[0108] (2) Shear rate is 1000s -1 Viscosity
[0109] A rotational rheometer (manufacturer: Anton Paar, model: MCR302) was used to perform the shearing at a rate of 1000 s. -1 The specific test method for viscosity test is as follows:
[0110] Take 25 mL of gel propellant and place it in the sample holder of the rotational rheometer.
[0111] Test condition setting: Set the test conditions of the rotational rheometer according to the experimental requirements, including speed range, temperature, measurement mode, etc. Select the appropriate test mode according to the properties of the sample.
[0112] Insert the sample holder into the rotational rheometer and ensure that the holder is stable. Start the instrument, set the appropriate speed, and wait for the instrument to stabilize.
[0113] Start the test according to the set test conditions. The instrument automatically applies shear force while measuring the rotor's rotational resistance. Adjust the speed and test time as needed.
[0114] After the test, the data can be processed and analyzed using the software provided by the instrument.
[0115] In Example 1: The gel propellant provided in this example is subjected to a shear rate of 1000s -1 The viscosity of the gel system at high shear rate is 0.44 Pa. Compared with the gel without adding carbon powder, the viscosity of the gel system is reduced by 23% at high shear rate.
[0116] The specific test results are shown in Table 1.
[0117] (3) XRD pattern
[0118] The XRD patterns of the combustion products obtained by measuring the volumetric heat of combustion of the gel propellants prepared in the examples and comparative examples were obtained using an X-ray diffractometer (manufacturer: PANalytical Analytical Instruments, model: D / MAX2550-VB / PC). The specific testing method is as follows:
[0119] Turn on the X-ray diffractometer and adjust it to ensure stable operation. Start scanning, and the instrument will automatically record the position and intensity of the diffraction peaks. Use specialized software to process the diffraction data, including background subtraction, peak position correction, and peak shape fitting. Compare the processed diffraction data with a standard card to determine the phase composition of the sample.
[0120] When the content of energetic particles (carbon powder and aluminum powder) in the gel propellant obtained by using aviation kerosene as liquid fuel is 50 wt%, the XRD patterns of the combustion products of the gel propellants in Examples 1-3 and Comparative Example 1 are as follows: Figure 2 As shown, from Figure 2 It can be seen that in Comparative Example 1, when no carbon powder is added to the gelling agent, the combustion products of the aluminum-containing gel are mainly α-Al2O3 and some incompletely burned aluminum. After the carbon powder is added in Examples 1-3, the aluminum in the combustion products almost disappears, and the oxidation products include a large amount of γ-Al2O3 in addition to α-Al2O3.
[0121] (4) Scanning electron microscope image
[0122] Scanning electron microscope (Hitachi, SU1510) was used to take scanning electron microscope images of the combustion products obtained after measuring the volumetric combustion heat of the gel propellants prepared in the examples and comparative examples, as shown below:
[0123] Turn on the power, warm up the equipment, and evacuate the sample chamber to ensure a high vacuum. Check and adjust the electron gun beam current. Place the sample on the sample stage and adjust its position, moving the sample using the stage's X and Y axes to ensure it is centered. Adjust the electron beam focus and brightness to obtain a clear image. Observe the sample through the microscope lens, record the image, and perform image processing and analysis. The voltage is 15.0 kV.
[0124] The scanning electron microscope image of the combustion product when the gel propellant in Comparative Example 1 is not mixed with carbon powder is as follows: Figure 3 As shown, the SEM image of the combustion product of the gel propellant (blended with 15 wt% carbon powder) in Example 3 is as follows: Figure 4It can be seen that, after mixing the carbon powder, the combustion product of the gel changes from large-size alumina agglomerates to small-particle-size alumina powder, and the combustion is more complete.
[0125] Table 1
[0126]
[0127] Note: " / " in Table 1 means that the parameter is not involved in the specific experiment.
[0128] In the present application, the gel propellants in Examples 1-12 have high volume combustion heat under pure oxygen (0.6 MPa, 3.5 MPa) and low viscosity at a shear rate of 1000 s -1 -1, which is beneficial to improve the incomplete combustion problem of aluminum in the combustion process of the gel propellant, and can solve the problem of high concentration of gel propellant, high viscosity, and difficult atomization. Specifically, the volume combustion heat of the obtained gel propellant under pure oxygen at 0.6 MPa can be up to 58.8 MJ / L or even up to 60 MJ / L, and the volume combustion heat under pure oxygen at 3.5 MPa can be up to 58.8 MJ / L or even up to 60 MJ / L, and the viscosity at a shear rate of 1000 s -1 -1 can be less than 0.7 Pa·s or even less than 0.5 Pa·s. In addition, the combustion efficiency can be up to 96% or more.
[0129] The gel propellants in Comparative Examples 1-5 either have low volume combustion heat or have high viscosity at a shear rate of 1000 s -1 -1, and cannot achieve low viscosity at a high shear rate while maintaining excellent volume combustion heat.
[0130] The above only describes the preferred embodiments of the present application, and does not limit the patent scope of the present application. Any equivalent structural transformation made according to the content of the present application, or direct / indirect application in other related technical fields is included in the patent protection scope of the present application.
Claims
1. A gel propellant, characterized in that: Taking the total mass of the gel propellant as 100%, it includes the following components: Toner: 5%-15%; Aluminum powder: 35%-45%; Gelling agent: 4%-6%; Liquid fuel: 44%-46%; The particle size D32 of the carbon powder is 30 nm-20 μm; the particle size D32 of the aluminum powder is 1 μm-100 μm.
2. The gel propellant according to claim 1, wherein The particle size D32 of the carbon powder is 60 nm-15 μm, preferably 500 nm-15 μm, for example 2 μm; And / or, the content of the carbon powder is 5%-10%.
3. The gel propellant according to claim 1, wherein The particle size of the aluminum powder is 1 μm-75 μm, preferably 2 μm-50 μm, and more preferably 2 μm-5 μm; And / or, the content of the aluminum powder is 40%-45%.
4. The gel propellant according to claim 1, wherein The gelling agent includes agarose and / or modified hydrogenated castor oil; the type of the modified hydrogenated castor oil is, for example, Thixatrol ST; And / or, the content of the gelling agent is 5%-6%.
5. The gel propellant according to claim 1, wherein The liquid fuel includes kerosene and / or alcohol fuel; the kerosene is, for example, RP-3 aviation kerosene; the alcohol fuel is, for example, ethanolamine; And / or, the content of the liquid fuel is 45%-46%.
6. A method for preparing the gel propellant according to any one of claims 1 to 5, characterized in that: It includes the following steps: S1, mixing a gelling agent and a liquid fuel to obtain a first mixture; The amount of the gelling agent is 4%-6%, and the amount of the liquid fuel is 44%-46%, where the percentages are the mass percentages of each component in the total mass of the gel propellant; S2. Mixing carbon powder, aluminum powder, and the first mixed material to obtain a second mixed material, and letting the mixed material stand to obtain the gel propellant; wherein, the amount of the carbon powder is 5%-15%, and the amount of the aluminum powder is 35%-45%, and the percentage is the mass percentage of each component in the total mass of the gel propellant; the particle size D32 of the carbon powder is 30nm-20μm; and the particle size D32 of the aluminum powder is 1μm-100μm.
7. The method for preparing the gel propellant according to claim 6, wherein: In step S1, the mixing temperature is preferably 50-70°C, for example 60°C; And / or, in step S1, the mixing method is stirring; the stirring speed is preferably 800-1200 rpm, for example, 1000 rpm; the stirring time is preferably 5-10 min; And / or, in step S2, the mixing temperature is preferably 50-70°C, for example 60°C; And / or, in step S2, the mixing method is stirring; the stirring speed is preferably 800-1200 rpm, for example, 1000 rpm; the stirring time is preferably 5-15 min; And / or, in step S2, the standing time is 6-10 hours; And / or, in step S2, the standing temperature is room temperature.
8. The method for preparing the gel propellant according to claim 6, wherein: In step S2, the preparation method of the second mixed material includes the following steps: firstly mixing the carbon powder and the first mixed material to obtain a third mixed material; and then mixing the third mixed material and the aluminum powder.
9. The method for preparing the gel propellant according to claim 6, wherein: In step S2, the method for preparing the second mixture includes the following steps: firstly mixing the aluminum powder and the carbon powder to obtain a third mixture; and then mixing the third mixture with the first mixture; wherein the method for preparing the third mixture preferably includes the following steps: A solvent is added to the aluminum powder and the carbon powder, and the mixture is mixed to obtain a suspension; the suspension is filtered, and the solid is collected and dried to obtain the product.
10. Use of the gel propellant according to any one of claims 1 to 5 in an aerospace engine power system.