Solid-liquid rocket engine grain embedded with metal wires and application of solid-liquid rocket engine grain

Abstract

The invention provides a solid-liquid rocket engine grain embedded with metal wires and application of the solid-liquid rocket engine grain. The solid-liquid rocket engine grain embedded with the metal wires comprises a grain body of a hollow cylindrical structure. Wherein metal wires are embedded between the grain bodies. According to the solid-liquid rocket engine grain, a large amount of heat can be released based on combustion of the metal wires, the combustion temperature can be increased, the combustion efficiency can be improved, the good heat conductivity of the metal wires is utilized, the heat conduction effect can be achieved in the solid-liquid rocket engine grain, and therefore the combustion speed is increased. Meanwhile, the embedded metal wires can further improve the tensile strength and rigidity of the grain, and the shape of the grain can be kept.

Description

Technical Field

[0001] The invention relates to the technical field of solid-liquid rocket engines, in particular to a solid-liquid rocket engine powder column embedded with metal wires and application thereof. Background Art

[0002] Typical solid-liquid rocket engines usually use a combination of liquid oxidizer + solid fuel grains. Different combinations of oxidizers and fuels give solid-liquid engines different working characteristics and applicable fields. The combustion surface recession rate (hereinafter referred to as the burning rate) is an important working and design parameter of solid-liquid rocket engines. However, since the oxidizer and solid fuel of the engine are stored separately, the oxidizer is sprayed into the engine from the front injector when the engine is working, and reacts and burns with the pyrolysis gas of the solid fuel above the surface of the grain. This typical diffusion combustion characteristic makes the solid-liquid rocket engine have less heat feedback from the flame layer to the wall of the grain compared to the solid rocket engine, resulting in a combustion rate that is about an order of magnitude lower than that of the solid rocket engine. The low burning rate greatly limits the solid-liquid rocket engine in high burning rate application scenarios (such as boosters, small launch vehicles, and tactical missiles).

[0003] The grain is a solid propellant with a specific geometry and size. It is the energy and working fluid source of the engine. The geometry and size of the grain, and the choice of fuel formula affect the burning rate characteristics of the grain, thus determining the engine's gas generation rate and its changing law, and therefore determining the relationship between the combustion chamber pressure and the engine thrust over time.

[0004] As mentioned above, typical solid-liquid rocket engines usually use a combination of liquid (or gas) oxidizer + solid fuel pellets. However, the currently commonly used polymer solid fuel pellets have a low burning rate because the pyrolysis rate of the fuel is mainly limited by the heat transfer from the diffusion flame layer to the wall. Therefore, high-energy particles such as aluminum, platinum, magnesium, beryllium, boron, lithium and its lithium compounds are usually added to the above-mentioned solid pellet matrix to improve engine performance and quality characteristics; or adding a small amount of ammonium perchlorate (AP), glycidyl azide (GAP), and catalyst Fe2O3 can also increase the rate of combustion surface regression. Although the burning rate can be enhanced by adding high-energy particles (Al, Mg), ammonium perchlorate (AP), glycidyl azide (GAP), etc., it is still limited by the low pyrolysis, evaporation and molecular diffusion rates during the combustion of traditional polymer fuels, resulting in a low regression rate and difficulty in realizing engineering applications of the engine.

[0005] Traditional polymer paraffin-based fuels have the phenomenon of liquid film entrainment caused by the retreat of the low-temperature solid fuel combustion surface, which improves the transport of fuel mass. The liquid film becomes unstable under the shearing action of the incoming hot gas, and the liquid film breaks into droplets and is sucked into the engine flow field to accelerate combustion, improve combustion efficiency and significantly increase the rate of retreat of the combustion surface, increasing thrust. However, the main disadvantage of paraffin-based fuels is that their mechanical properties are insufficient, and they are easily softened and detached by the effect of radiant heat. Although the mechanical properties can be improved by adding polymer solid fuel to paraffin, and the tensile and compressive strength of the grain can be increased, this method will reduce the burning rate.

[0006] In addition, charge design is also an important part of solid-liquid rocket engine grain design. The burning rate can be increased by designing the charge structure of solid-liquid rocket engine grain. However, the current charge design has different defects. For example, the disadvantages of one-dimensional (end-burning grain) are: (1) the combustion area is very small, so the thrust is very small; (2) the engine center of gravity moves a lot during the combustion process; (3) the high-temperature combustion gas contacts the combustion chamber wall, and a thick insulation layer is required. The insulation layer may occupy 5-10% of the combustion chamber volume, thereby reducing the filling coefficient; (4) the engine thrust and pressure curves rise slowly; (5) ignition is difficult. The disadvantages of three-dimensional are: complex drug properties and difficult processes, but the emergence of detachable drug molds, meltable drug molds or combustible drug molds reduces the complexity; there is stress concentration at the top of the cone groove.

[0007] Therefore, it is urgent to develop a solid-liquid rocket engine propellant that can simultaneously improve the combustion performance and mechanical properties of the propellant, which provides a new way to achieve precise control of the burning rate of the rocket engine.

[0008] In view of this, the present invention is proposed. Summary of the invention

[0009] One of the purposes of the present invention is to provide a solid-liquid rocket engine grain embedded with a metal wire. The solid-liquid rocket engine grain not only improves the combustion performance and mechanical properties of the grain through the introduction of the metal wire, but also provides a new way to achieve accurate control of the burning rate of the rocket engine.

[0010] The second object of the present invention is to provide an application of the solid-liquid rocket engine grain embedded with metal wire in improving the burning rate of the solid-liquid rocket engine.

[0011] The third object of the present invention is to provide a solid-liquid rocket engine, which includes a liquid oxidizer delivery system and an engine main body system; wherein the engine main body system includes a combustion chamber, and the combustion chamber includes the self-igniting solid-liquid rocket engine propellant.

[0012] In order to achieve the above-mentioned purpose of the present invention, the following technical solutions are particularly adopted:

[0013] In a first aspect, the present invention provides a solid-liquid rocket engine grain embedded with metal wires, wherein the solid-liquid rocket engine grain embedded with metal wires comprises a grain body having a hollow cylindrical structure; wherein metal wires are embedded between the grain bodies.

[0014] In the present invention, by using metal wires or metal fibers of different thicknesses, aspect ratios and materials, the heat conduction process inside the grain can be effectively controlled. The solid-liquid rocket engine grain embedded with metal wires can also participate in combustion during engine operation, thereby improving the specific impulse. And by adjusting the type, quantity, thickness and distribution parameters of the metal wires or metal fibers, the burning rate of the grain can be enhanced and precisely controlled. At the same time, the introduction of metal wire fibers significantly improves the mechanical properties of rocket engine fuel, increases the tensile strength and stiffness of the grain, and helps to maintain the shape of the grain. Mixing short metal wires in the propellant or embedding long metal wires can significantly increase the burning rate of the propellant to 2 to 5 times the original. This innovative application can optimize and improve the performance of solid-liquid rocket engines. The introduction of metal wires not only improves the combustion performance and mechanical properties of the grain, but also provides a new way to achieve precise control of the burning rate of rocket engines.

[0015] In the present invention, the use of metal wire has the following three effects: First, the energy density of the metal wire is very high, and the combustion of the metal wire itself can release a large amount of heat, which can increase the combustion temperature and combustion efficiency, improve the amount of energy released, and provide the high burning rate and large thrust required for the take-off stage of the aircraft. Second, the good thermal conductivity of the metal wire can be used to conduct heat in the grain of the solid-liquid rocket engine. During the combustion of the grain, the heat released by the combustion of the metal wire itself is transferred to the solid phase by relying on the good thermal conductivity of the metal wire, so that the grain adjacent to the metal wire in the solid phase will absorb more heat, forming a metal wire heating zone. The heat transfer of the gas phase combustion zone to the solid phase is enhanced, thereby increasing the burning rate. Third, the mechanical properties of the metal wire are very good, which can effectively support the fuel, increase the tensile strength and stiffness of the grain, and maintain the integrity of the grain during the combustion process, preventing it from falling off and affecting the internal ballistic performance.

[0016] Preferably, the ratio of the inner diameter to the outer diameter of the drug column body is 0.2-0.4, for example, it can be 0.2, 0.22, 0.24, 0.26, 0.28, 0.3, 0.32, 0.34, 0.36, 0.38, 0.4, etc.

[0017] Preferably, the ratio of the length to the outer diameter of the drug column body is 3 to 10, for example, it can be 3, 3.5, 4, 4.5, 5, 5.5, 6, 6.5, 7, 7.5, 8, 8.5, 9, 9.5, 10, etc.

[0018] Preferably, the material of the metal wire is selected from any one of silver, copper, tungsten, aluminum, platinum, magnesium, constantan or steel, or a combination of at least two thereof.

[0019] In the present invention, the metal wire is preferably made of a combustible metal such as aluminum, platinum, magnesium, steel, magnesium alloy and alloy steel. The thermal conductivity, melting point, diameter and length, arrangement or density of the metal wire all have different effects on the enhancement of the burning rate. By using metal wires of different sizes (length, diameter) and using metal wires of different arrangement modes, arrangement angles and arrangement densities, the burning rate of the charge column can be intelligently controlled.

[0020] Among them, the performance parameters and burning rate increase multiples of the metal wire are shown in Table 1 below:

[0021] Table 1

[0022]

[0023] The choice of wire material plays a key role. A variety of metals can be used, such as silver, copper, tungsten, platinum, aluminum, magnesium, steel, etc. The thermal conductivity of these metals, that is, the thermal diffusivity (a), has a significant effect on the increase in the burning rate. Among them, silver has the largest thermal diffusivity, resulting in the largest increase in the burning rate. In addition, the melting point of the metal also has a significant effect on the burning rate. A higher melting point allows the wire to remain longer in the high-temperature gas, absorbing more heat, which is conducive to the increase in the burning rate. In contrast, copper has a higher melting point, which makes its burning rate increase a greater multiple, although the thermal conductivity of copper and aluminum is not much different.

[0024] In addition, in order to take into account both thermal conductivity and heat resistance, a combination of two metal wires can be used. One of the metal wires has good thermal conductivity, and the other has a high melting point. Combining them together and embedding them in the propellant helps to achieve a greater increase in burning rate. Experimental results show that there are differences in the burning rate enhancement capabilities of different metal wires, and the order of increasing burning rate is: silver> copper> tungsten> aluminum> magnesium> constantan> steel. On the premise of meeting the requirements of mechanical properties and economy, steel wire can be selected. If the maximum burning rate increase is sought, silver wire or copper wire can be considered. In order to comprehensively consider performance and quality characteristics, aluminum wire and magnesium wire are usually selected to improve the overall performance of the engine.

[0025] The effect of the wire diameter on the burning rate (the oxidant is 98% hydrogen peroxide) is shown in Table 2 below:

[0026] Table 2

[0027]

[0028]

[0029] Among them, the physical properties of different types of metal wires are shown in Table 3 below:

[0030] Table 3

[0031]

[0032] Preferably, the diameter of the metal wire is 0.1-0.2 mm, for example, it can be 0.1 mm, 0.12 mm, 0.14 mm, 0.16 mm, 0.18 mm, 0.2 mm, etc.

[0033] In the present invention, the diameter of the metal wire is preferably 0.1-0.2 mm, because in addition to the properties of the metal, the diameter of the metal wire also affects the multiple of the increase in the burning rate. There is a most favorable diameter for the burning rate, and its multiple of the increase in the burning rate is the highest. In addition, as the pressure increases, the multiple of the increase in the burning rate also increases slightly. When the diameter of the metal wire is selected to be 0.1-0.2 mm, the burning rate enhancement effect of the metal wire in this range is better, and there is almost no effect on the energy characteristics.

[0034] Preferably, the steel is selected from any one of 304, 316, 45 steel, 4146 alloy steel or GH3030.

[0035] Preferably, the arrangement of the metal wires includes any one of radial arrangement, random embedding, annular arrangement or mesh cross arrangement, or a combination of at least two of them.

[0036] Preferably, when the arrangement of the metal wires is radial arrangement, the specific structure of the solid-liquid rocket engine grain embedded with metal wires is: long strips of metal wires are uniformly inserted in the grain body along the circumferential direction perpendicular to the combustion end face.

[0037] Preferably, the ratio of the length of the long metal wire to the thickness of the drug column body is 1:(1-5), for example, it can be 1:1, 1:1.5, 1:2, 1:2.5, 1:3, 1:3.5, 1:4, 1:4.5, 1:5, etc.

[0038] Preferably, the length of the long metal wire is 10 to 100 mm, for example, it can be 10 mm, 15 mm, 20 mm, 25 mm, 30 mm, 35 mm, 40 mm, 45 mm, 50 mm, 55 mm, 60 mm, 65 mm, 70 mm, 75 mm, 80 mm, 85 mm, 90 mm, 95 mm, 100 mm, etc.

[0039] Preferably, the diameter of the long metal wire is 0.1-0.2 mm, for example, it can be 0.1 mm, 0.12 mm, 0.14 mm, 0.16 mm, 0.18 mm, 0.2 mm, etc.

[0040] Preferably, the angle formed between two adjacent long metal wires inserted into the drug column body is 10-120°, for example, it can be 10°, 20°, 30°, 40°, 50°, 60°, 70°, 80°, 90°, 100°, 110°, 120°, etc.

[0041] Preferably, the number of the long metal wires is 3 to 36, for example, it can be 3, 4, 6, 8, 10, 12, 14, 16, 18, 20, 22, 24, 26, 28, 30, 32, 34, 36, etc.

[0042] Preferably, when the arrangement of the metal wires is randomly embedded, the specific structure of the solid-liquid rocket engine grain embedded with metal wires is that short strips of metal wires are randomly distributed in the grain body.

[0043] Preferably, the distribution density of the short strip metal wires is 1×10 5 ~3×10 6 Root / m 3 , for example, it can be 1×10 5 Root / m 3 , 2×10 5 Root / m 3 , 3×10 5 Root / m 3 , 4×10 5 Root / m 3 , 5×10 5 Root / m 3 , 6×10 5 Root / m 3 ,7×10 5 Root / m 3 , 8×10 5 Root / m 3 ,9×10 5 Root / m 3 , 1×10 6 Root / m 3 , 2×10 6 Root / m 3 , 3×10 6 Root / m 3 wait.

[0044] Preferably, the short strip of metal wire is 1-30% of the mass of the drug column body, for example, it can be 1%, 2%, 3%, 4%, 5%, 6%, 7%, 8%, 9%, 10%, 15%, 20%, 25%, 30% and the like.

[0045] Preferably, the length of the short strip metal wire is 1 to 3 mm, for example, it can be 1 mm, 1.2 mm, 1.4 mm, 1.6 mm, 1.8 mm, 2 mm, 2.2 mm, 2.4 mm, 2.6 mm, 2.8 mm, 3 mm, etc.

[0046] Preferably, the diameter of the short strip metal wire is 0.1-0.2 mm, for example, it can be 0.1 mm, 0.12 mm, 0.14 mm, 0.16 mm, 0.18 mm, 0.2 mm, etc.

[0047] Preferably, when the arrangement of the metal wires is annular, the specific structure of the solid-liquid rocket engine grain embedded with the metal wires is: a metal ring is inserted into the grain body along the circumferential direction.

[0048] Preferably, the number of the metal rings is 1 to 5, for example, 1, 2, 3, 4, 5, etc.

[0049] Preferably, the ratio of the distance between adjacent metal rings to the thickness of the drug column body is 1:(1-5), for example, it can be 1:1, 1:1.5, 1:2, 1:2.5, 1:3, 1:3.5, 1:4, 1:4.5, 1:5, etc.

[0050] Preferably, the metal ring is a ring-shaped metal wire surrounded by long metal wires, and the diameter of the long metal wires is 0.1-0.2 mm, for example, 0.1 mm, 0.12 mm, 0.14 mm, 0.16 mm, 0.18 mm, 0.2 mm, etc.

[0051] Preferably, the arrangement of the metal wires is a combination of radial arrangement and annular arrangement.

[0052] Preferably, when the arrangement of the metal wires is a mesh-like cross, the specific structure of the solid-liquid rocket engine grain embedded with metal wires is: a metal mesh formed by the cross-shaped metal wires is embedded in the grain body.

[0053] Preferably, the diameter of the metal wire is 0.1-0.2 mm, for example, it can be 0.1 mm, 0.12 mm, 0.14 mm, 0.16 mm, 0.18 mm, 0.2 mm, etc.

[0054] Preferably, the crossing angle of adjacent metal wires is 30 to 90°, for example, it can be 30°, 32°, 34°, 36°, 38°, 40°, 42°, 44°, 46°, 48°, 50°, 52°, 54°, 56°, 58°, 60°, 62°, 64°, 66°, 68°, 70°, 72°, 74°, 76°, 78°, 80°, 82°, 84°, 86°, 88°, 90°, etc.

[0055] Preferably, the smallest unit mesh area in the metal mesh structure is 25 to 100 mm 2 , for example, it can be 25mm 2 , 30mm 2 , 35mm 2 , 40mm 2 , 45mm 2 , 50mm 2 , 55mm 2 、60mm 2 、65mm 2 , 70mm 2 , 75mm 2 , 80mm 2 、85mm 2 、90mm 2 、95mm 2 , 100mm 2 wait.

[0056] Preferably, the distribution density of the grids in the metal mesh structure is 1×10 4 ~4×10 4 pcs / m 2 , for example, it can be 1×10 4 pcs / m 2 , 1.5×10 4 pcs / m 2 , 2×10 4 pcs / m 2 , 2.5×10 4 pcs / m 2 , 3×10 4 pcs / m 2 , 3.5×10 4 pcs / m 2 , 4×10 4 pcs / m 2 wait.

[0057] Preferably, the vertical spacing between adjacent metal wires is 5-10 mm, for example, 5 mm, 5.5 mm, 6 mm, 6.5 mm, 7 mm, 7.5 mm, 8 mm, 8.5 mm, 9 mm, 9.5 mm, 10 mm, etc.

[0058] Preferably, the surface of the metal wire is coated with a coating that increases the burning rate.

[0059] Preferably, the thickness of the coating that increases the burning rate is 0.01-0.02 mm, for example, it can be 0.01 mm, 0.012 mm, 0.014 mm, 0.016 mm, 0.018 mm, 0.02 mm, etc.

[0060] Preferably, the raw materials for preparing the coating for increasing the burning rate include the following components by mass percentage:

[0061] 4-5 parts of adhesive, 45-59 parts of oxidant, 11-12 parts of plasticizer, 0-15 parts of burning rate regulator, 18-35 parts of explosive, and 1-2 parts of curing agent.

[0062] In the present invention, in order to further increase the multiple of the burning rate increase, a feasible solution is to coat the outer surface of the long metal wire with a coating that increases the burning rate. The coating formed on the surface of the metal wire increases the burning rate along the direction of the metal wire, thereby increasing the multiple of the burning rate increase.

[0063] The coating on the metal wire is composed of a specific formula ratio of adhesive, oxidant, plasticizer, burning rate regulator, explosive and curing agent. Among them, the adhesive makes the coating form a continuous and uniform film, tightly attached to the metal wire, and acts as a fuel; the oxidant provides oxygen required for combustion in the coating; the plasticizer is used to improve the process performance and physical properties; the burning rate regulator is used to adjust the burning rate, expand the adjustment range, and adjust the temperature sensitivity coefficient and pressure index. The chemical coating is essentially a specially formulated high-burning rate propellant that can effectively increase the burning rate in the direction of the metal wire, providing a powerful means for optimizing the performance of solid-liquid rocket engines.

[0064] In the coating for increasing the burning rate, the content of the binder is 4 to 5 parts, for example, 4 parts, 4.2 parts, 4.4 parts, 4.6 parts, 4.8 parts, 5 parts, etc.

[0065] In the coating for increasing the burning rate, the content of the oxidant is 45 to 59 parts, for example, it can be 45 parts, 46 parts, 48 ​​parts, 50 parts, 52 parts, 54 parts, 56 parts, 58 parts, 59 parts, etc.

[0066] In the coating for increasing the burning rate, the content of the plasticizer is 11 to 12 parts, for example, it can be 11 parts, 11.2 parts, 11.4 parts, 11.6 parts, 11.8 parts, 12 parts, etc.

[0067] In the coating for increasing the burning rate, the content of the burning rate regulator is 0 to 15 parts, for example, it can be 0 parts, 2 parts, 4 parts, 6 parts, 8 parts, 10 parts, 12 parts, 14 parts, 15 parts, etc.

[0068] In the coating for increasing the burning rate, the content of explosive is 18 to 35 parts, for example, it can be 18 parts, 20 parts, 22 parts, 24 parts, 26 parts, 28 parts, 30 parts, 32 parts, 34 parts, 35 parts, etc.

[0069] In the coating for increasing the burning rate, the content of the curing agent is 1 to 2 parts, for example, it can be 1 part, 1.2 parts, 1.4 parts, 1.6 parts, 1.8 parts, 2 parts, etc.

[0070] Preferably, the binder is selected from glycidyl azide-tetrahydrofuran copolyether and / or 3,3-bis(azidomethyl)butylene oxide-tetrahydrofuran copolyether.

[0071] Preferably, the oxidant is selected from any one or a combination of at least two of ammonium perchlorate, potassium perchlorate, sodium perchlorate, ammonium nitrate, potassium nitrate or sodium nitrate.

[0072] Preferably, the plasticizer is selected from any one of nitroglycerin, butanetriol trinitrate, trimethylolethane trinitrate or triethylene glycol dinitrate, or a combination of at least two thereof.

[0073] Preferably, the burning rate regulator is selected from any one of ferric oxide, chromite or carbon black, or a combination of at least two thereof.

[0074] Preferably, the explosive is selected from any one of octogenin, hexanitrohexaazaisowurtzitane or a combination of at least two thereof.

[0075] Preferably, the curing agent is a diisocyanate curing agent.

[0076] Preferably, the diisocyanate curing agent is selected from hexamethylene diisocyanate and / or dimer fatty acid diisocyanate.

[0077] In a second aspect, the present invention provides an application of the solid-liquid rocket engine grain embedded with metal wires in improving the burning rate of the solid-liquid rocket engine.

[0078] In a third aspect, the present invention provides a solid-liquid rocket engine, which includes a liquid oxidizer delivery system and an engine main body system.

[0079] Wherein, the main engine system includes a combustion chamber, and the combustion chamber includes the above-mentioned self-igniting solid-liquid rocket engine propellant.

[0080] Preferably, the combustion chamber also includes a charge skeleton.

[0081] In the present invention, a charge column skeleton can be used to carry the easily softened charge column, because carbon fiber is a non-metallic wire material with excellent mechanical properties, can maintain the shape of the charge column and provide stress, and can also participate in combustion; that is, in order to maintain the mechanical properties of the charge column and the integrity of the charge column, a charge column skeleton can also be used to carry the easily softened charge column, such as paraffin. The charge column skeleton can be made by casting, extrusion molding, 3D printing and other methods.

[0082] Preferably, the material of the drug column skeleton is selected from any one or a combination of at least two of acrylonitrile-butadiene-styrene, polyethylene, nylon, polycarbonate, polylactic acid, polyphenylene sulfide or polycaprolactone.

[0083] Compared with the prior art, the present invention has the following beneficial effects:

[0084] (1) The present invention achieves enhancement and precise control of the burning rate of the propellant by adjusting parameters such as the type, quantity, thickness and distribution of the metal wire or metal fiber.

[0085] (2) The present invention can significantly improve the mechanical properties of solid-liquid rocket engine fuel through metal fibers, increase the tensile strength and rigidity of the grain, and maintain the shape of the grain. It can enhance the heat transfer process of the solid-liquid rocket engine, thereby increasing the fuel pyrolysis rate, and can achieve a high-performance and high-burning-rate solid-liquid rocket engine grain.

[0086] (3) The burning rate of the solid-liquid rocket engine grain embedded with metal wires of the present invention can reach 2 to 8 times that of the grain without embedded metal wires, and the burning rate can be adjusted within the range of 0.1 to 10 mm / s.

[0087] (4) The radial arrangement scheme of the present invention will uniformly increase the burning rate at the front and rear ends of the grain, and form a conical burning rate enhancement zone around the metal wire; the random embedding scheme has a better effect on enhancing the mechanical properties, and random addition can also uniformly produce a burning rate enhancement effect in the radial and circumferential directions, and the burning rate enhancement is related to the proportion of metal wire added; the annular arrangement scheme will significantly increase the released heat when the metal ring burns, so that the grain will have an instantaneous burning rate enhancement; the mesh cross arrangement scheme: has the best effect on enhancing the mechanical properties, significantly improves the mechanical properties of the solid-liquid rocket engine grain, increases the tensile strength and stiffness of the grain, and can maintain the shape of the grain. The metal wire enhances the burning rate effect and is related to the arrangement density and angle of the mesh metal wire. BRIEF DESCRIPTION OF THE DRAWINGS

[0088] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0089] Figure 1 It is a cross-sectional view of the solid-liquid rocket engine grain embedded with radially arranged metal wires according to the present invention.

[0090] Among them, 1 is the main body of the medicine column, and 2 is a long strip of metal wire.

[0091] Figure 2 It is a cross-sectional view of the solid-liquid rocket engine grain with randomly embedded metal wires according to the present invention.

[0092] Among them, 1 is the main body of the medicine column, and 3 is a short strip of metal wire.

[0093] Figure 3 It is a cross-sectional view of the solid-liquid rocket engine grain embedded with an annular arrangement of metal wires according to the present invention.

[0094] Among them, 1 is the medicine column body, and 4 is the metal ring.

[0095] Figure 4 It is a cross-sectional view of a solid-liquid rocket engine grain embedded with radially arranged and annularly arranged metal wires according to the present invention.

[0096] Among them, 1 is the medicine column body, 2 is a long strip of metal wire, and 4 is a metal ring.

[0097] Figure 5 It is a cross-sectional view of a solid-liquid rocket engine grain embedded with a metal wire mesh cross according to the present invention.

[0098] Among them, 1 is the medicine column body, 2 is the long strip of metal wire, and 5 is the metal mesh.

[0099] Figure 6 It is a schematic structural diagram of the solid-liquid rocket engine of the present invention.

[0100] Among them, 10 is a liquid oxidant delivery system, 101 is a gas cylinder, 102 is a liquid oxidant tank, and 103 is a valve; 20 is the main engine system, 201 is a combustion chamber, and 202 is a nozzle. DETAILED DESCRIPTION

[0101] Unless otherwise defined herein, scientific and technical terms used in conjunction with the present invention shall have the meanings commonly understood by those of ordinary skill in the art. The meaning and scope of the terms should be clear, however, in the case of any potential ambiguity, the definitions provided herein take precedence over any dictionary or external definitions. In this application, unless otherwise stated, the use of "or" means "and / or". In addition, the use of the term "including" and other forms is non-limiting.

[0102] It should be noted that specific details are described in the following description to facilitate a full understanding of the present invention. However, the present invention can be implemented in a variety of other ways different from those described herein, and those skilled in the art can make similar generalizations without violating the connotation of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0103] The technical solution of the present invention will be clearly and completely described below in conjunction with the embodiments. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0104] In the present invention, the solid-liquid rocket engine grain embedded with metal wires comprises a grain body having a hollow cylindrical structure; wherein metal wires are embedded between the grain bodies.

[0105] like Figure 1 As shown, when the arrangement of the metal wires is radial arrangement, the specific structure of the solid-liquid rocket engine grain embedded with metal wires is: long metal wires 2 are uniformly inserted in the grain body 1 along the circumferential direction perpendicular to the combustion end face; that is, a group of long metal wires 2 are arranged at intervals along the length direction of the grain body 1.

[0106] like Figure 2 As shown, when the arrangement of the metal wires is randomly embedded, the specific structure of the solid-liquid rocket engine grain embedded with metal wires is: short strip metal wires 3 are randomly distributed in the grain body 1; that is, short strip metal wires 3 are randomly added, mixed with the grain body 1, and fully stirred and mixed, and the short strip metal wires 3 appear randomly in the grain body 1.

[0107] like Figure 3 As shown, when the arrangement of the metal wire is a ring arrangement, the specific structure of the solid-liquid rocket engine grain embedded with the metal wire is: a metal ring 4 is inserted into the grain body 1 along the circumferential direction; that is, along the length direction of the grain, a plurality of metal rings 4 are arranged at different diameters as a group, and are arranged at intervals.

[0108] like Figure 4 As shown, when the arrangement of the metal wires is a combination of radial arrangement and annular arrangement, the specific structure of the solid-liquid rocket engine grain embedded with metal wires is: a long metal wire 2 is evenly inserted into the grain body 1 along the circumferential direction perpendicular to the combustion end face; and a metal ring 4 is inserted into the grain body 1 along the circumferential direction.

[0109] like Figure 5 As shown, when the arrangement of the metal wires is a mesh cross, the specific structure of the solid-liquid rocket engine grain embedded with metal wires is: a metal mesh 5 formed by the cross-shaped metal wires is embedded in the grain body 1.

[0110] like Figure 6 As shown, the solid-liquid rocket engine includes a liquid oxidizer delivery system 10 and an engine main body system 20; the engine main body system includes a combustion chamber 201, and the combustion chamber includes the above Figure 1 to Figure 5 A solid-liquid rocket motor grain with wire embedded is shown.

[0111] The present invention is further described below by way of examples. Unless otherwise specified, the materials in the examples are prepared according to existing methods or directly purchased from the market.

[0112] Example 1

[0113] The present embodiment provides a solid-liquid rocket engine grain embedded with metal wires, wherein the solid-liquid rocket engine grain embedded with metal wires comprises a grain body having a hollow cylindrical structure; wherein metal wires are embedded between the grain bodies.

[0114] The material of the medicine column body is paraffin, the ratio of the inner diameter to the outer diameter of the medicine column body is 14:40; and the ratio of the length to the outer diameter of the medicine column body is 150:40.

[0115] Wherein, the arrangement of the metal wire is as follows: Figure 1 The radial arrangement is shown; and the material of the metal wire is silver, the length is 18mm, the diameter is 0.1mm, the angle formed between two adjacent long metal wires is 60°, the number of wires is 6, and the amount of metal wire added is 10% of the mass of the drug column.

[0116] Example 2

[0117] The present embodiment provides a solid-liquid rocket engine grain embedded with metal wires, wherein the solid-liquid rocket engine grain embedded with metal wires comprises a grain body having a hollow cylindrical structure; wherein metal wires are embedded between the grain bodies.

[0118] The material of the medicine column body is HTPB, the ratio of the inner diameter to the outer diameter of the medicine column body is 2:5; and the ratio of the length to the outer diameter of the medicine column body is 3:1.

[0119] Wherein, the arrangement of the metal wire is as follows: Figure 2 The short strip metal wire is made of silver, has a length of 1 mm, a diameter of 0.1 mm, and a distribution density of 3,000,000 pieces / m 3 The added amount of the metal wire is 30% of the mass of the drug column.

[0120] Example 3

[0121] The present embodiment provides a solid-liquid rocket engine grain embedded with metal wires, wherein the solid-liquid rocket engine grain embedded with metal wires comprises a grain body having a hollow cylindrical structure; wherein metal wires are embedded between the grain bodies.

[0122] The material of the medicine column body is polyethylene PE, the ratio of the inner diameter to the outer diameter of the medicine column body is 1:3; and the ratio of the length to the outer diameter of the medicine column body is 4:1.

[0123] Wherein, the arrangement of the metal wire is as follows: Figure 3 The circular arrangement shown in the figure; and the number of the metal rings is 3, the metal ring is a circular metal wire surrounded by a long strip of metal wire, and the diameter of the long strip of metal wire is 0.1mm, and the added amount of the metal wire is 20% of the mass of the medicine column.

[0124] Example 4

[0125] The present embodiment provides a solid-liquid rocket engine grain embedded with metal wires, wherein the solid-liquid rocket engine grain embedded with metal wires comprises a grain body having a hollow cylindrical structure; wherein metal wires are embedded between the grain bodies.

[0126] The material of the medicine column body is ABS, the ratio of the inner diameter to the outer diameter of the medicine column body is 1:3; and the ratio of the length to the outer diameter of the medicine column body is 4:1.

[0127] Wherein, the arrangement of the metal wire is as follows: Figure 4 The invention discloses a combination of radial arrangement and annular arrangement; the material of the long metal wire is silver, the length is 10 mm, the diameter is 0.1 mm, the angle formed between two adjacent long metal wires is 30°, the number of wires is 12, and the amount of the metal wire added is 10% of the mass of the medicine column body; wherein the number of the metal rings is 5, the metal ring is annular metal wire surrounded by long metal wires, the diameter of the long metal wires is 0.1 mm, and the amount of the metal wire added is 30% of the mass of the medicine column body.

[0128] Example 5

[0129] The present embodiment provides a solid-liquid rocket engine grain embedded with metal wires, wherein the solid-liquid rocket engine grain embedded with metal wires comprises a grain body having a hollow cylindrical structure; wherein metal wires are embedded between the grain bodies.

[0130] The material of the medicine column body is PU, the ratio of the inner diameter to the outer diameter of the medicine column body is 1:3; and the ratio of the length to the outer diameter of the medicine column body is 4:1.

[0131] Wherein, the arrangement of the metal wire is as follows: Figure 5 The mesh cross shown in the figure; the material of the metal wire is silver, the diameter of the metal wire is 0.1mm; the intersection angle of adjacent metal wires is 90°; the minimum unit mesh area is 25mm 2 ; The distribution density of the grids in the metal mesh structure is 40,000 / m 2; The vertical spacing between the metal wires is 5 mm, and the amount of metal wire added is 20% of the mass of the drug column.

[0132] Example 6

[0133] This embodiment provides a solid-liquid rocket engine charge embedded with a metal wire, which is different from the first embodiment only in that the material of the metal wire is aluminum, and the other settings are exactly the same as those of the first embodiment.

[0134] Example 7

[0135] This embodiment provides a solid-liquid rocket engine grain embedded with a metal wire, which is different from the embodiment 2 only in that the material of the metal wire is aluminum, and the other settings are exactly the same as those of the embodiment 2.

[0136] Example 8

[0137] This embodiment provides a solid-liquid rocket engine charge embedded with a metal wire, which is different from the embodiment 3 only in that the material of the metal wire is aluminum, and the other settings are exactly the same as those of the embodiment 3.

[0138] Example 9

[0139] This embodiment provides a solid-liquid rocket engine charge embedded with a metal wire, which is different from the embodiment 4 only in that the material of the metal wire is aluminum, and the other settings are exactly the same as those of the embodiment 4.

[0140] Example 10

[0141] This embodiment provides a solid-liquid rocket engine charge embedded with a metal wire, which is different from Embodiment 5 only in that the material of the metal wire is aluminum, and the other settings are exactly the same as those of Embodiment 5.

[0142] Embodiment 11

[0143] This embodiment provides a solid-liquid rocket engine grain embedded with a metal wire. The only difference from Embodiment 1 is that the material of the metal wire is aluminum and the diameter of the metal wire is increased to 0.2 mm. The other settings are exactly the same as those in Embodiment 1.

[0144] Example 12

[0145] This embodiment provides a solid-liquid rocket engine charge embedded with a metal wire. The only difference from Embodiment 2 is that the material of the metal wire is aluminum and the diameter of the metal wire is increased to 0.2 mm. The other settings are exactly the same as those of Embodiment 2.

[0146] Example 13

[0147] This embodiment provides a solid-liquid rocket engine grain embedded with a metal wire. The only difference from Embodiment 3 is that the material of the metal wire is aluminum and the diameter of the metal wire is increased to 0.2 mm. The other settings are exactly the same as those of Embodiment 3.

[0148] Embodiment 14

[0149] This embodiment provides a solid-liquid rocket engine grain embedded with a metal wire. The only difference from Embodiment 4 is that the material of the metal wire is aluminum and the diameter of the metal wire is increased to 0.2 mm. The other settings are exactly the same as those of Embodiment 4.

[0150] Embodiment 15

[0151] This embodiment provides a solid-liquid rocket engine charge embedded with a metal wire. The only difference from Embodiment 5 is that the material of the metal wire is aluminum and the diameter of the metal wire is increased to 0.2 mm. The other settings are exactly the same as those of Embodiment 5.

[0152] Example 16

[0153] This embodiment provides a solid-liquid rocket engine grain embedded with a metal wire, which is different from the first embodiment only in that the material of the metal wire is magnesium, and the other settings are exactly the same as the first embodiment.

[0154] Embodiment 17

[0155] This embodiment provides a solid-liquid rocket engine charge embedded with a metal wire, which is different from the embodiment 2 only in that the material of the metal wire is magnesium, and the other settings are exactly the same as those of the embodiment 2.

[0156] Embodiment 18

[0157] This embodiment provides a solid-liquid rocket engine grain embedded with a metal wire, which is different from the embodiment 3 only in that the material of the metal wire is magnesium, and the other settings are exactly the same as those of the embodiment 3.

[0158] Embodiment 19

[0159] This embodiment provides a solid-liquid rocket engine charge embedded with a metal wire, which is different from the embodiment 4 only in that the material of the metal wire is magnesium, and the other settings are exactly the same as those of the embodiment 4.

[0160] Embodiment 20

[0161] This embodiment provides a solid-liquid rocket engine grain embedded with a metal wire, which is different from Embodiment 5 only in that the material of the metal wire is magnesium, and the other settings are exactly the same as those of Embodiment 5.

[0162] Embodiment 21

[0163] This embodiment provides a solid-liquid rocket engine grain embedded with a metal wire. The only difference from Embodiment 1 is that the material of the metal wire is magnesium and the diameter of the metal wire is increased to 0.2 mm. The other settings are exactly the same as those in Embodiment 1.

[0164] Embodiment 22

[0165] This embodiment provides a solid-liquid rocket engine grain embedded with a metal wire. The only difference from Embodiment 2 is that the material of the metal wire is magnesium and the diameter of the metal wire is increased to 0.2 mm. The other settings are exactly the same as those of Embodiment 2.

[0166] Embodiment 23

[0167] This embodiment provides a solid-liquid rocket engine grain embedded with a metal wire. The only difference from Embodiment 3 is that the material of the metal wire is magnesium and the diameter of the metal wire is increased to 0.2 mm. The other settings are exactly the same as those of Embodiment 3.

[0168] Embodiment 24

[0169] This embodiment provides a solid-liquid rocket engine grain embedded with a metal wire. The only difference from Embodiment 4 is that the material of the metal wire is magnesium and the diameter of the metal wire is increased to 0.2 mm. The other settings are exactly the same as those of Embodiment 4.

[0170] Embodiment 25

[0171] This embodiment provides a solid-liquid rocket engine grain embedded with a metal wire. The only difference from Embodiment 5 is that the material of the metal wire is magnesium and the diameter of the metal wire is increased to 0.2 mm. The other settings are exactly the same as those of Embodiment 5.

[0172] Embodiment 26

[0173] The present embodiment provides a solid-liquid rocket engine charge embedded with a metal wire, which is different from the embodiment 1 only in that the outer layer of the metal wire has a 0.015 mm thick coating for increasing the burning rate; the raw materials for preparing the coating for increasing the burning rate include the following components in terms of mass percentage: 4 parts of glycidyl azide-tetrahydrofuran copolyether, 54 parts of ammonium perchlorate, 11 parts of nitroglycerin, 30 parts of octogenin, and 1 part of hexamethylene diisocyanate, and the other settings are exactly the same as those in the embodiment 1.

[0174] Embodiment 27

[0175] The present embodiment provides a solid-liquid rocket engine charge embedded with a metal wire, which is different from the embodiment 6 only in that the outer layer of the metal wire has a 0.01 mm thick coating for increasing the burning rate; the raw materials for preparing the coating for increasing the burning rate include the following components in terms of mass percentage: 5 parts of 3,3-bis(azidomethyl)butylene oxide-tetrahydrofuran copolyether, 50 parts of potassium perchlorate, 12 parts of butanetriol trinitrate, 6 parts of ferric oxide, 25 parts of RDX, and 2 parts of dimer fatty acid diisocyanate, and the other settings are exactly the same as those in the embodiment 6.

[0176] Embodiment 28

[0177] The present embodiment provides a solid-liquid rocket engine propellant embedded with metal wires, which is different from the embodiment 16 only in that the outer layer of the metal wire has a 0.02 mm thick coating for increasing the burning rate; the raw materials for preparing the coating for increasing the burning rate include the following components in percentage by mass: 4.5 parts of azidoglyceryl ether-tetrahydrofuran copolyether, 50 parts of ammonium nitrate, 11.5 parts of trimethylolethane trinitrate, 12 parts of chromite, 20 parts of hexanitrohexaazaisowurtzitane, and 2 parts of dimer fatty acid diisocyanate, and the other settings are exactly the same as those in the embodiment 16.

[0178] Comparative Example 1

[0179] This comparative example provides a solid-liquid rocket engine charge, which is different from Example 1 only in that no metal wire is added, and the other settings are exactly the same as those of Example 1.

[0180] Performance Testing:

[0181] Test samples: solid-liquid rocket engine grains embedded with metal wires provided in Examples 1 to 28, and solid-liquid rocket engine grains not embedded with metal wires provided in Comparative Example 1;

[0182] The specific test results are shown in Table 4 below:

[0183] Table 4

[0184]

[0185]

[0186] As shown in Table 4, the present invention can achieve the enhancement of burning rate by adding metal wire to part of the solid-liquid rocket engine grain. When the adding ratio is within 40%, the burning rate can reach 2 to 10 times of the original, and the burning rate can be adjusted within the range of 0.1 to 10 mm / s.

[0187] In summary, the combustion of the metal wire of the present invention can release a large amount of heat, which can increase the combustion temperature and combustion efficiency. Moreover, the good thermal conductivity of the metal wire can be used to conduct heat in the grain of a solid-liquid rocket engine, thereby increasing the burning rate. At the same time, the tensile strength and rigidity of the grain are increased, and the shape of the grain can be maintained.

[0188] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A solid-liquid rocket engine grain embedded with metal wires, characterized in that: The solid-liquid rocket engine grain embedded with metal wires comprises a grain body with a hollow cylindrical structure; wherein metal wires are embedded between the grain bodies.

2. The solid-liquid rocket engine grain embedded with metal wire according to claim 1, characterized in that: The ratio of the inner diameter to the outer diameter of the medicine column body is 0.2-0.4; and the ratio of the length to the outer diameter of the medicine column body is 3-10.

3. The solid-liquid rocket engine grain embedded with metal wire according to claim 1, characterized in that: The material of the metal wire is selected from any one of silver, copper, tungsten, aluminum, platinum, magnesium, constantan or steel, or a combination of at least two thereof; Preferably, the arrangement of the metal wires includes any one of radial arrangement, random embedding, annular arrangement or mesh cross arrangement, or a combination of at least two of them.

4. The solid-liquid rocket engine grain embedded with metal wire according to claim 1 or 3, characterized in that: When the arrangement of the metal wires is radial arrangement, the specific structure of the solid-liquid rocket engine grain embedded with metal wires is as follows: long strips of metal wires are uniformly inserted into the grain body along the circumferential direction perpendicular to the combustion end surface; Preferably, the ratio of the length of the long metal wire to the thickness of the drug column body is 1:(1-5); Preferably, the length of the long metal wire is 10 to 100 mm; and the diameter of the long metal wire is 0.1 to 0.2 mm; Preferably, the angle formed between two adjacent long strips of metal wires inserted into the drug column body is 10 to 120°; Preferably, the number of the long strip metal wires is 3 to 36.

5. The solid-liquid rocket engine grain embedded with metal wire according to claim 1 or 3, characterized in that: When the arrangement of the metal wires is randomly embedded, the specific structure of the solid-liquid rocket engine grain embedded with metal wires is as follows: short strips of metal wires are randomly distributed in the grain body; Preferably, the distribution density of the short strip metal wires is 1×10 5 ~3×10 6 Root / m 3 ; Preferably, the short strip of metal wire is 1 to 30% of the mass of the drug column body; Preferably, the length of the short metal wire strip is 1-3 mm; and the diameter of the short metal wire strip is 0.1-0.2 mm.

6. The solid-liquid rocket engine grain embedded with metal wire according to claim 1 or 3, characterized in that: When the arrangement of the metal wires is annular, the specific structure of the solid-liquid rocket engine grain embedded with metal wires is as follows: a metal ring is inserted into the grain body along the circumferential direction; Preferably, the number of the metal rings is 1 to 5; Preferably, the ratio of the distance between adjacent metal rings to the thickness of the drug column body is 1:(1-5); Preferably, the metal ring is a ring-shaped metal wire surrounded by a long strip of metal wire, and the diameter of the long strip of metal wire is 0.1 to 0.2 mm; Preferably, the arrangement of the metal wires is a combination of radial arrangement and annular arrangement.

7. The solid-liquid rocket engine grain embedded with metal wire according to claim 1 or 3, characterized in that: When the arrangement of the metal wires is a mesh cross, the specific structure of the solid-liquid rocket engine grain embedded with metal wires is as follows: a metal mesh formed by the cross of metal wires is embedded in the grain body; Preferably, the diameter of the metal wire is 0.1 to 0.2 mm; Preferably, the crossing angle of adjacent metal wires is 30 to 90°; Preferably, the smallest unit mesh area in the metal mesh structure is 25 to 100 mm 2 ; Preferably, the distribution density of the grids in the metal mesh structure is 1×10 4 ~4×10 4 pcs / m 2 ; Preferably, the vertical spacing between adjacent metal wires is 5 to 10 mm.

8. The solid-liquid rocket engine grain embedded with metal wires according to claim 1, characterized in that: The surface of the metal wire is coated with a coating that increases the burning rate; Preferably, the thickness of the coating that increases the burning rate is 0.01 to 0.02 mm; Preferably, the raw materials for preparing the coating for increasing the burning rate include the following components by mass percentage: 4-5 parts of adhesive, 45-59 parts of oxidant, 11-12 parts of plasticizer, 0-15 parts of burning rate regulator, 18-35 parts of explosive, 1-2 parts of curing agent; Preferably, the adhesive is selected from azide glycidyl ether-tetrahydrofuran copolyether and / or 3,3-bis(azidomethyl)butylene oxide-tetrahydrofuran copolyether; Preferably, the oxidant is selected from any one or a combination of at least two of ammonium perchlorate, potassium perchlorate, sodium perchlorate, ammonium nitrate, potassium nitrate or sodium nitrate; Preferably, the plasticizer is selected from any one or a combination of at least two of nitroglycerin, butanetriol trinitrate, trimethylolethane trinitrate or triethylene glycol dinitrate; Preferably, the burning rate regulator is selected from any one of ferric oxide, chromite or carbon black, or a combination of at least two thereof; Preferably, the explosive is selected from any one or a combination of at least two of octogenin, hexanitrohexaazaisowurtzitane; Preferably, the curing agent is a diisocyanate curing agent; Preferably, the diisocyanate curing agent is selected from hexamethylene diisocyanate and / or dimer fatty acid diisocyanate.

9. Use of a solid-liquid rocket engine grain embedded with metal wire according to any one of claims 1 to 8 in improving the burning rate of a solid-liquid rocket engine.

10. A solid-liquid rocket engine, characterized in that: The solid-liquid rocket engine includes a liquid oxidizer delivery system and an engine main body system; Wherein, the main engine system includes a combustion chamber, and the combustion chamber includes a solid-liquid rocket engine grain embedded with a metal wire as described in any one of claims 1 to 8; Preferably, the combustion chamber further includes a charge frame; Preferably, the material of the drug column skeleton is selected from any one or a combination of at least two of acrylonitrile-butadiene-styrene, polyethylene, nylon, polycarbonate, polylactic acid, polyphenylene sulfide or polycaprolactone.

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