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

Abstract

The invention provides a solid rocket engine grain embedded with metal wires and application of the solid rocket engine grain. The solid rocket engine grain embedded with the metal wires is a grain body with a cylindrical structure; wherein the grain body contains a burning speed reducing agent, and a metal wire is further embedded between the grain bodies. The grain is divided into layers with different combustion speeds by adding different metal wires and the combustion speed reducing agent, the purposes of setting the combustion speed and thrust of each layer and adjusting the interval time are achieved, and the range, maneuverability, interception capability and combat capability of a missile can be improved by managing the energy of the propellant.

Description

Technical Field

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

[0002] As the power source of missile weapons and equipment, solid rocket engines directly determine the ability of missile weapons to be delivered long distances and to penetrate defenses in a mobile manner. They are the premise and foundation for the combat effectiveness of weapons and equipment, and are the core technology that promotes the upgrading of missile weapons. At the same time, with the rapid development of space exploration and commercial aerospace, solid rocket engines are gradually being used in the fields of aerospace transportation and solid boosters. Solid rocket engines have been widely used in various types of missile weapons due to their simple structure, fast response, easy use and maintenance, high reliability, and low cost. However, compared with other power systems, solid rocket engines have poor thrust controllability, which greatly restricts the performance of missile weapons. Thrust control technology can adjust the size or direction of thrust in real time according to the needs of the missile, and more reasonably distribute the propellant energy, thereby improving the range, speed, maneuverability and penetration capability of the missile. It is an important development trend of future missile power systems.

[0003] The current variable thrust technologies for solid rocket engines mainly include multi-pulse solid grains, nozzle throat area adjustment technology, thrust vector control technology, and direct lateral force control technology.

[0004] 1. There are three technical solutions for multi-pulse solid rocket engines: partition type, flame retardant type, and delayed combustion type. The partition type solution is to use a partition to separate two independent compartments in a shell, sharing a nozzle. This solution mainly has two structural forms: partition type and interlayer type. The flame retardant solution relies on certain technologies in the engine to achieve rapid flameout and rapid ignition, thereby controlling the engine to start twice. There are mainly pressure reduction flameout type, liquid flame retardant flameout type, and solid flame retardant flameout type. The delayed combustion chamber solution is in a combustion chamber, and a delay charge is sandwiched in the charge. The thickness of the delay charge is determined according to the delay time. The commonly used and simpler charge form is the end-burning column charge. The disadvantage of this technology is that the use of additional partitions or flame retardants increases the negative mass of the engine, reduces the total impulse of the engine, affects the engine performance parameters, and has low working reliability.

[0005] 2. Technology for adjusting the nozzle throat area. This solution is completed by a hydraulically driven throat plug installed in the combustion chamber support sleeve. The throat plug moves forward and backward along the center line of the engine according to the command to change the nozzle throat area, thereby changing the thrust. The advantage is that it has a large thrust adjustment range, and the thrust adjustment ratio is at least 10 or even up to 100. The disadvantage is that the system is relatively complex, and technologies such as lightweight and miniaturized thrust adjustment system, dynamic sealing structure and long-term thermal protection technology, fast and accurate closed-loop control technology have yet to be overcome, and it will also bring about the ablation problem of the throat plug. The technical difficulty is relatively high. Domestic research on throat plug engines is in its infancy. The principle research on aerodynamic control systems is mainly through experiments and flow field simulation to analyze the pressure response process.

[0006] 3. Thrust vector control technology Thrust vector control technology is a technology that generates the control torque required for missile maneuvering flight by controlling the displacement of engine thrust relative to the missile axis. Thrust vector control technology is divided into mechanical and fluid secondary injection according to the working principle. Mechanical thrust vector control technology mainly includes gas rudder, spoiler and swing nozzle. The advantages are good linkage, simple structure and can provide rolling torque; the disadvantages are large axial thrust loss, which will cause performance degradation, and the gas rudder is in high-temperature gas, with serious ablation.

[0007] 4. Direct lateral force control technology is a plurality of small pulse engines, which has the advantages of simple structure, high safety, good performance, small size, long storage cycle, easy maintenance and use, etc. The disadvantage is that it needs to set up additional small engines and the system structure is complex.

[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 rocket motor grain embedded with metal wires, wherein the solid rocket motor grain realizes variable thrust through layered charging based on the burning rate increasing technology of the metal wires and the burning rate reducing technology based on the burning rate reducing agent.

[0010] A second object of the present invention is to provide an application of the solid rocket motor charge embedded with metal wire in regulating the burning rate of the solid rocket motor.

[0011] The third object of the present invention is to provide a solid rocket engine, which includes a combustion chamber, and the combustion chamber includes a shell, an outer insulation layer, an inner insulation layer and a grain; wherein the outer insulation layer is arranged on the outer surface of the shell, the inner insulation layer is arranged on the inner surface of the shell, and the grain is filled in the inner insulation layer; and the grain is the above-mentioned solid rocket engine grain embedded with metal wire.

[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 rocket motor grain embedded with metal wires, wherein the solid rocket motor grain embedded with metal wires is a grain body having a cylindrical structure.

[0014] The main body of the grain contains a burning rate reducing agent, and metal wires are embedded between the main bodies of the grain.

[0015] In the present invention, a burning rate enhancement technology based on metal wires and a burning rate reduction technology based on a burning rate decelerator are used to achieve variable thrust through layered charge. That is, the burning rate can be enhanced by adding metal wires, and the burning rate decelerator is used to reduce the burning rate of the solid rocket engine. The variable thrust is achieved by adding the burning rate decelerator and metal wires in layers.

[0016] In the present invention, the charge column can also be divided into multiple layers with different burning speeds by adding different metal wires and burning speed reducing agents, and the burning speed and thrust of each layer are set and the interval time is adjusted. Through the energy management of the propellant, the range, maneuverability, interception capability and combat capability of the missile are improved. By adjusting the action time of the engine thrust, the acceleration and deceleration process during the flight of the missile can be optimized, thereby avoiding the energy loss caused by factors such as resistance and improving the utilization efficiency of energy. In addition, by controlling the action time of the subsequent engine thrust, the ballistic characteristics of the missile can be changed to meet special ballistic requirements, such as higher strike height, greater strike speed and variable speed flight before striking the target, etc., the terminal speed can be increased by 20%, and the range can be increased by 20% to 30%.

[0017] Preferably, the grain body comprises a grain body layer containing a burning rate reducing agent, and a grain body layer embedded with metal wires.

[0018] Preferably, in the grain body layer containing the burning rate reducing agent, the ratio of the inner diameter to the outer diameter of the grain body is 0.2 to 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.

[0019] Preferably, in the grain body layer containing the burning rate reducing agent, the ratio of the length to the outer diameter of the grain 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.

[0020] Preferably, in the grain body layer containing the burning rate reducing agent, the burning rate reducing agent accounts for 0.05-5% of the mass of the grain body of this layer, for example, it can be 0.05%, 0.1%, 0.2%, 0.3%, 0.4%, 0.5%, 0.6%, 0.8%, 1%, 1.5%, 2%, 2.5%, 3%, 3.5%, 4%, 4.5%, 5%, etc.

[0021] Preferably, the burning rate reducing agent is selected from any one or a combination of at least two of carbonates, fluorides, ammonium salts, amine compounds, ammonium salts, quaternary ammonium salts or sucrose octaacetate.

[0022] Preferably, the carbonate is selected from CaCO 3 and / or SrCO 3 .

[0023] Preferably, the fluoride is selected from LiF.

[0024] Preferably, the ammonium salt is selected from NH 4 F, (NH 4 ) 2 BF, NH 4 PF 6 NH 4 ) 2 SiF 6 or (NH 4 ) 2 HPO 4 Any one or a combination of at least two.

[0025] Preferably, the amine compound is selected from any one of urea, oxalamide, oxamide or dicyandiamide, or a combination of at least two thereof.

[0026] Preferably, the ammonium salt is selected from ammonium oxalate.

[0027] Preferably, the quaternary ammonium salt is selected from any one of tetraethylammonium chloride, tetraethylammonium tetrafluoroborate, benzalkonium chloride or a quaternary ammonium perchlorate salt, or a combination of at least two thereof.

[0028] Preferably, the burning rate reducing agent is SrCO 3 and ammonium salt combinations.

[0029] Preferably, the SrCO 3 The mass ratio of the ammonium salt to the sodium bicarbonate is 5:1 to 1:5, for example, it can be 5:1, 5:2, 5:3, 5:4, 1:1, 1:2, 1:3, 1:4, 1:5, etc.

[0030] Preferably, when the solid rocket engine fuel is selected from terminal hydroxyl polybutadiene, the burning rate decelerator is selected from any one of carbonate, fluoride, oxalamide or urea, or a combination of at least two thereof.

[0031] Preferably, when the solid rocket engine fuel is selected from ammonium perchlorate, the burning rate decelerator is selected from any one of ammonia salts, amine compounds, ammonium salts or quaternary ammonium salts, or a combination of at least two thereof.

[0032] Preferably, in the drug body layer embedded with metal wires, the ratio of the inner diameter to the outer diameter of the drug 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.

[0033] Preferably, in the drug body layer embedded with metal wires, the ratio of the length to the outer diameter of the drug 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.

[0034] In the present invention, the heat conduction process inside the grain is controlled by adding metal wires. The metal wires can also participate in combustion during the operation of the engine, which can improve the specific impulse. In addition, the present invention achieves enhancement and precise control of the burning rate of the grain by adjusting parameters such as the type, quantity, thickness and distribution of the metal wires or metal fibers. On the other hand, the metal wires can significantly improve the mechanical properties of the fuel of the solid rocket engine, increase the tensile strength and rigidity of the grain, and maintain the shape of the grain. Mixing metal wires into the propellant can significantly increase the burning rate of the propellant, which can reach 2 to 5 times the original, or even higher. The performance of the solid rocket engine can be optimized and improved. That is, the application of the grain body layer embedded with 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 the rocket engine.

[0035] Furthermore, the use of a grain body layer embedded with metal wire has the following effects. 1. The energy density of the metal wire is very high. The combustion of the metal wire itself can release a large amount of heat, which can increase the combustion temperature and combustion efficiency, increase the amount of energy released, and provide the high burning rate and high thrust required for the take-off phase of the aircraft. 2. The good thermal conductivity of the metal wire can be used to conduct heat in the grain of the solid 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. 3. The mechanical properties of the metal wire are very good. It can effectively support the fuel, increase the tensile strength and stiffness of the grain, maintain the integrity of the grain during the combustion process, and prevent it from falling off, thereby affecting the internal ballistic performance.

[0036] 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.

[0037] Preferably, the steel is selected from any one of 304, 316, 45 steel, 4146 alloy steel or GH3030.

[0038] In the present invention, the metal wire is usually made of the above-mentioned combustible metal. 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.

[0039] Among them, the performance parameters and burning rate increase multiples of the metal wire are shown in Table 1 below:

[0040] Table 1

[0041]

[0042] As shown in Table 1 above, the metal wire material can be silver, copper, tungsten, platinum, aluminum, magnesium, constantan, and steel. The main factor affecting the increase in the burning rate is the thermal conductivity of the metal wire, that is, the thermal diffusion coefficient a. Silver has the largest a, and its increase in burning rate is also the largest. Secondly, the melting point of the metal also has a significant impact. The higher the melting point, the longer the metal wire remains in the high-temperature gas, and the more heat can be absorbed into the metal wire, which is conducive to the increase in burning rate. Compared with copper and aluminum, their a values ​​are not much different, but copper has a higher melting point than aluminum, so the increase in burning rate is greater.

[0043] In addition, in order to improve the thermal conductivity and heat resistance of the metal wire at the same time, bimetallic wire can be used. One metal wire has good thermal conductivity, and the other has a high melting point. Combining the two and embedding them in the propellant can increase the burning rate even more. The burning rate enhancement ability of metal wires is obtained through experiments: silver> copper> tungsten> aluminum> magnesium> constantan> steel. Steel wire can be used when mechanical properties and economic requirements are required; silver wire or copper wire can be used to obtain the maximum burning rate increase multiple; and aluminum wire and magnesium wire are usually selected to consider comprehensive performance, and improve engine performance and quality characteristics at the same time.

[0044] Among them, the influence of metal wire diameter on burning rate is shown in Table 2 below:

[0045] Table 2

[0046]

[0047] As shown in Table 2 above, the diameter of the metal wire also affects the multiple of the increase in burning rate. There is a most favorable diameter for the burning rate, and its multiple of the increase in burning rate is the highest. In addition, as the pressure increases, the multiple of the increase in burning rate also increases slightly. The diameter of the metal wire is generally selected to be 0.1 to 0.2 mm. The metal wire in this range has a better burning rate enhancement effect, and has almost no effect on the energy characteristics.

[0048] 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.

[0049] 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.

[0050] Preferably, when the arrangement of the metal wires is radial arrangement, the specific structure of the solid rocket motor grain embedded with metal wires is: long strips of metal wires are evenly inserted in the grain body along the circumferential direction perpendicular to the combustion end face.

[0051] When the metal wires are arranged radially, the burning rates of the front and rear ends of the propellant column are uniformly increased, and a conical burning rate enhancement zone is formed around the metal wires.

[0052] 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.

[0053] 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.

[0054] 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.

[0055] 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.

[0056] 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.

[0057] Preferably, when the arrangement of the metal wires is randomly embedded, the specific structure of the solid rocket motor grain embedded with metal wires is that short strips of metal wires are randomly distributed in the grain body.

[0058] When the arrangement of the metal wires is randomly embedded, this scheme has a better effect on enhancing the mechanical properties. Random addition can also produce a burning rate enhancement effect uniformly in the radial direction and the circumferential direction. The burning rate enhancement is related to the proportion of metal wire addition.

[0059] 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.

[0060] 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.

[0061] 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.

[0062] 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.

[0063] Preferably, when the arrangement of the metal wires is annular, the specific structure of the solid rocket motor grain embedded with the metal wires is: a metal ring is inserted into the grain body along the circumferential direction.

[0064] When the metal wire is arranged in a ring-shaped manner, when the metal ring is burned, the ring-shaped metal ring will significantly increase the released heat, so that the burning rate of the powder column will be instantly enhanced.

[0065] Preferably, the number of the metal rings is 1 to 5, for example, 1, 2, 3, 4, or 5.

[0066] 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.

[0067] 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.

[0068] Preferably, the arrangement of the metal wires is a combination of radial arrangement and annular arrangement.

[0069] Preferably, when the arrangement of the metal wires is a mesh-like cross, the specific structure of the solid rocket motor grain embedded with metal wires is: a metal mesh formed by the cross-shaped metal wires is embedded in the grain body.

[0070] When the metal wires are arranged in a mesh cross pattern, this scheme has the best effect on enhancing the mechanical properties, significantly improving the mechanical properties of the solid rocket engine propellant, increasing the tensile strength and stiffness of the propellant, and being able to maintain the shape of the propellant. The effect of metal wires in enhancing the burning rate is related to the arrangement density and angle of the mesh metal wires.

[0071] 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.

[0072] 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.

[0073] 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.

[0074] 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.

[0075] 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.

[0076] Preferably, the surface of the metal wire is coated with a coating that increases the burning rate.

[0077] Preferably, the raw materials for preparing the coating for increasing the burning rate include the following components by mass percentage:

[0078] 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.

[0079] In the present invention, in order to further increase the multiple of the increase in burning rate, the burning rate along the direction of the metal wire can be improved. One solution is to coat the outer surface of the long metal wire with a chemical coating with a high burning rate, and rely on the high burning rate of the coating to increase the burning rate along the direction of the metal wire, thereby increasing the multiple of the increase in burning rate.

[0080] 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.

[0081] 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.

[0082] 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.

[0083] 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.

[0084] 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.

[0085] 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.

[0086] Preferably, the binder is selected from glycidyl azide-tetrahydrofuran copolyether and / or 3,3-bis(azidomethyl)butylene oxide-tetrahydrofuran copolyether.

[0087] 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.

[0088] 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.

[0089] 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.

[0090] Preferably, the explosive is selected from any one of octogenin, hexanitrohexaazaisowurtzitane or a combination of at least two thereof.

[0091] Preferably, the curing agent is a diisocyanate curing agent.

[0092] Preferably, the diisocyanate curing agent is selected from hexamethylene diisocyanate and / or dimer fatty acid diisocyanate.

[0093] In a second aspect, the present invention provides an application of the solid rocket motor charge embedded with metal wire in regulating the burning rate of the solid rocket motor.

[0094] In a third aspect, the present invention provides a solid rocket engine comprising a combustion chamber, wherein the combustion chamber comprises a shell, an outer insulation layer, an inner insulation layer and a grain. The outer insulation layer is arranged on the outer surface of the shell, the inner insulation layer is arranged on the inner surface of the shell, and the grain is filled in the inner insulation layer; and the grain is the solid rocket engine grain embedded with metal wire as described in the first aspect.

[0095] Based on this, the solid rocket engine using this type of charge can use flexible manufacturing and tailor-made charge with different burning rates and burning rate layers for different tasks, optimize the engine's thrust change range and size, define the charge according to mission requirements, more reasonably distribute the propellant's energy, and use it according to combat needs to achieve different ballistic characteristics. According to different tasks, the missile can quickly fly to close-range targets; it can also reduce the flight speed during flight to increase the range or sense the target, and then accelerate to attack the target in the terminal stage. The application of variable thrust charge enables the missile to cover any threat from within the defense zone and has nonlinear beyond-visual-range interception and attack capabilities. For example, when intercepting long-range and high-speed targets, two layers of charge are used to increase the range and impact speed.

[0096] As a technical solution for implementing the present invention: star-shaped charge inner hole combustion is adopted, and the metal wire adopts a three-layer arrangement scheme, and metal magnesium wire or aluminum wire is added to the inner layer of the grain column, and the arrangement method can use mesh metal wire; a burning rate reducing agent is added to the middle part of the grain column to reduce the burning rate; metal magnesium wire or aluminum wire is also added to the outer layer of the grain column, and the arrangement method uses short metal wires to be randomly arranged. In the take-off stage, the metal wire meets the needs of high burning rate and high thrust, takes off quickly and accelerates to reach the cruising speed. The burning rate in the middle part of the grain column is relatively low, which meets the ballistic cruise requirements. In the final approach to the target stage, the metal wire is also used to achieve a high burning rate to meet the requirements of maneuverability and high thrust.

[0097] As a technical solution of the present invention: booster solution: the engine as a whole needs high burning rate and high thrust in a short time, so metal wires are added to the whole engine without adding burning rate reducing agent, and the metal wire adding solution is such as radial long metal wire solution, short metal wire random arrangement solution, or metal mesh solution. The booster using this kind of grain can quickly reach the cruising speed.

[0098] As a technical solution for implementing the present invention: the arrangement of multiple layers of metal wires or burning rate reducing agents can be used as a technical route for multi-pulse solid rocket engines. According to the requirements of missile guidance, the thrust of each level is set and the duration of each level is adjusted, and then the thickness of each level of the grain, the content of metal wire added and the adding scheme are set. The metal wire is used to manage the energy of the propellant to improve the range maneuverability and interception capability of the missile.

[0099] As a technical solution for implementing the present invention: a multi-pulse technical solution, by adding different metal wires, burning rate reducing agents, etc. to the same propellant, high burning rate propellant, low burning rate propellant, and complex ballistic propellant can be manufactured for different tasks, different targets, different temperatures, different usage locations, etc.

[0100] Compared with the prior art, the present invention has the following beneficial effects:

[0101] (1) The solid rocket engine grain embedded with metal wires of the present invention is divided into multiple layers with different burning rates by adding different metal wires and burning rate reducing agents, setting the burning rate and thrust of each layer and adjusting the interval time, thereby improving the range, maneuverability, interception capability and combat capability of the missile through energy management of the propellant.

[0102] (2) The present invention can optimize the acceleration and deceleration process of the missile during flight by adjusting the action time of the engine thrust, thereby avoiding energy loss caused by factors such as resistance and improving energy utilization efficiency. In addition, by controlling the action time of the subsequent engine thrust, the ballistic characteristics of the missile can be changed to meet special ballistic requirements, such as higher strike altitude, greater strike speed, and variable speed flight before striking the target, etc. The terminal speed can be increased by 20% and the range can be increased by 20-30%. BRIEF DESCRIPTION OF THE DRAWINGS

[0103] 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.

[0104] Figure 1 It is a cross-sectional view of the main body layer of the drug column embedded with radially arranged metal wires according to the present invention.

[0105] Among them, 1 is the main body of the medicine column, and 2 is a long strip of metal wire.

[0106] Figure 2 It is a cross-sectional view of the main body layer of the medicine column with randomly embedded metal wires according to the present invention.

[0107] Among them, 1 is the main body of the medicine column, and 3 is a short strip of metal wire.

[0108] Figure 3 It is a cross-sectional view of the main body layer of the drug column of the present invention embedded with metal wires arranged in an annular manner.

[0109] Among them, 1 is the medicine column body, and 4 is the metal ring.

[0110] Figure 4 It is a cross-sectional view of the main body layer of the drug column embedded with radially arranged and annularly arranged metal wires according to the present invention.

[0111] Among them, 1 is the medicine column body, 2 is a long strip of metal wire, and 4 is a metal ring.

[0112] Figure 5 It is a cross-sectional view of the drug column body layer of the present invention embedded with a metal wire mesh cross.

[0113] Among them, 1 is the medicine column body, 2 is the long strip of metal wire, and 5 is the metal mesh.

[0114] Figure 6 The present invention provides a side view of the entire end-burning solid rocket engine grain.

[0115] Among them, 10 is a combustion chamber, 11 is a grain body layer embedded with metal wires, and 12 is a grain body layer containing a burning rate reducing agent.

[0116] Figure 7 The present invention is a side view of the entire inner hole combustion solid rocket engine grain provided by the present invention.

[0117] Among them, 10 is a combustion chamber, 11 is a grain body layer embedded with metal wires, and 12 is a grain body layer containing a burning rate reducing agent. DETAILED DESCRIPTION

[0118] 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.

[0119] 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.

[0120] In the present invention, the solid rocket engine grain embedded with metal wires is a grain body with a hollow cylindrical structure, wherein the grain body contains a burning rate reducing agent, and metal wires are also embedded between the grain bodies.

[0121] like Figure 1 As shown, in the grain body layer embedded with metal wires, when the arrangement of the metal wires is radial arrangement, the specific structure of the solid 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.

[0122] like Figure 2 As shown, in the grain body layer embedded with metal wires, when the arrangement of the metal wires is randomly embedded, the specific structure of the solid rocket engine grain embedded with metal wires is: short strips of metal wires 3 are randomly distributed in the grain body 1; that is, short strips of metal wires 3 are randomly added, mixed with the grain body 1, and fully stirred and mixed, and the short strips of metal wires 3 appear randomly in the grain body 1.

[0123] like Figure 3 As shown, in the grain body layer embedded with metal wires, when the arrangement of the metal wires is a ring arrangement, the specific structure of the solid rocket engine grain embedded with metal wires 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.

[0124] like Figure 4As shown, in the grain body layer embedded with metal wires, when the arrangement of the metal wires is a combination of radial arrangement and annular arrangement, the specific structure of the solid rocket engine grain embedded with metal wires is: long strips of metal wires 2 are uniformly inserted in the grain body 1 along the circumferential direction perpendicular to the combustion end face; and metal rings 4 are inserted in the grain body 1 along the circumferential direction.

[0125] like Figure 5 As shown, in the grain body layer embedded with metal wires, when the arrangement of the metal wires is a mesh cross, the specific structure of the solid rocket engine grain embedded with metal wires is: a metal mesh 5 formed by the crossing of metal wires is embedded in the grain body 1.

[0126] like Figure 6 As shown, the solid rocket motor grain embedded with metal wires is an end-face burning double-layer charge grain, and the combustion chamber 10 includes a grain body layer 11 embedded with metal wires and a grain body layer 12 containing a burning rate reducing agent.

[0127] like Figure 7 As shown, the solid rocket engine grain embedded with metal wires is an inner hole type combustion double-layer charge grain, and the combustion chamber 10 includes a grain body layer 11 embedded with metal wires and a grain body layer 12 containing a burning rate reducing agent; and the grain body layer 11 embedded with metal wires is located in the inner layer, and the grain body layer 12 containing a burning rate reducing agent is located in the outer layer.

[0128] 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.

[0129] 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.

[0130] Example 1

[0131] The present embodiment provides a solid rocket motor grain embedded with metal wires, wherein the solid rocket motor grain embedded with metal wires comprises a grain body layer containing a burning rate reducing agent, and a grain body layer embedded with metal wires.

[0132] In the drug column body layer embedded with metal wires, the material of the drug column body is paraffin, the ratio of the inner diameter to the outer diameter of the drug column body is 14:40; and the ratio of the length to the outer diameter of the drug column body is 150:40.

[0133] In the main body layer of the drug column embedded with metal wires, the arrangement of the metal wires 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.

[0134] In the grain body layer containing the burning rate reducing agent, the material of the grain body is HTPB, and the burning rate reducing agent is (NH 4 ) 2 C 2 O 4 The amount of the speed reducing agent added is 3% of the mass of the drug column.

[0135] Example 2

[0136] The present embodiment provides a solid rocket motor grain embedded with metal wires, wherein the solid rocket motor grain embedded with metal wires comprises a grain body layer containing a burning rate reducing agent, and a grain body layer embedded with metal wires.

[0137] 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.

[0138] 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.

[0139] In the grain body layer containing the burning rate reducing agent, the material of the grain body is HTPB, the burning rate reducing agent is LiF, and the added amount of the reducing agent is 3% of the mass of the grain body.

[0140] Example 3

[0141] The present embodiment provides a solid rocket motor grain embedded with metal wires, wherein the solid rocket motor grain embedded with metal wires comprises a grain body layer containing a burning rate reducing agent, and a grain body layer embedded with metal wires.

[0142] In the drug column body layer embedded with metal wires, the material of the drug column body is polyethylene PE, the ratio of the inner diameter to the outer diameter of the drug column body is 1:3; and the ratio of the length to the outer diameter of the drug column body is 4:1.

[0143] In the main body layer of the drug column embedded with metal wires, the arrangement of the metal wires is as follows: Figure 3The 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.

[0144] In the grain body layer containing the burning rate reducing agent, the material of the grain body is HTPB, and the burning rate reducing agent is CaCO 3 The amount of the speed reducing agent added is 3% of the mass of the drug column.

[0145] Example 4

[0146] The present embodiment provides a solid rocket motor grain embedded with metal wires, wherein the solid rocket motor grain embedded with metal wires comprises a grain body layer containing a burning rate reducing agent, and a grain body layer embedded with metal wires.

[0147] In the drug column body layer embedded with metal wires, the material of the drug column body is ABS, the ratio of the inner diameter to the outer diameter of the drug column body is 1:3; and the ratio of the length to the outer diameter of the drug column body is 4:1.

[0148] In the main body layer of the drug column embedded with metal wires, the arrangement of the metal wires 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.

[0149] In the grain body layer containing the burning rate reducing agent, the material of the grain body is HTPB, and the burning rate reducing agent is SrCO 3 The amount of the speed reducing agent added is 3% of the mass of the drug column.

[0150] Example 5

[0151] The present embodiment provides a solid rocket motor grain embedded with metal wires, wherein the solid rocket motor grain embedded with metal wires comprises a grain body layer containing a burning rate reducing agent, and a grain body layer embedded with metal wires.

[0152] In the drug column body layer embedded with metal wires, the material of the drug column body is PU, the ratio of the inner diameter to the outer diameter of the drug column body is 1:3; and the ratio of the length to the outer diameter of the drug column body is 4:1.

[0153] In the main body layer of the drug column embedded with metal wires, the arrangement of the metal wires is as follows: Figure 5 The mesh cross is shown; 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.

[0154] In the grain body layer containing a burning rate reducing agent, the material of the grain body is HTPB, the burning rate reducing agent is sucrose octaacetate, and the added amount of the reducing agent is 3% of the mass of the grain body.

[0155] Example 6

[0156] This embodiment provides a solid rocket engine grain embedded with metal wires, which differs from Embodiment 1 only in that, in the grain body layer embedded with metal wires, the metal wires are made of aluminum; and in the grain body layer containing a burning rate reducing agent, the burning rate reducing agent is a quaternary ammonium salt (tetraethylammonium chloride), and the added amount is reduced to 0.3%. Other settings are exactly the same as Embodiment 1.

[0157] Example 7

[0158] This embodiment provides a solid rocket engine grain embedded with metal wires, which is different from the second embodiment only in that the material of the metal wires in the grain body layer embedded with metal wires is aluminum; and the material of the burning rate reducing agent in the grain body layer containing the burning rate reducing agent is NH 4 PF 6 , the addition amount was reduced to 1.5%, and other settings were exactly the same as in Example 2.

[0159] Example 8

[0160] This embodiment provides a solid rocket engine grain embedded with metal wires, which is different from the embodiment 3 only in that the material of the metal wires in the grain body layer embedded with metal wires is aluminum; and the material of the grain body layer containing a burning rate decelerator is a quaternary ammonium salt (tetraethylammonium chloride) and SrCO in a mass ratio of 1:1. 3 The other settings are exactly the same as those in Example 3.

[0161] Example 9

[0162] This embodiment provides a solid rocket engine grain embedded with metal wires, which is different from the embodiment 4 in that the material of the metal wires in the grain body layer embedded with metal wires is aluminum; and the material of the grain body layer containing a burning rate decelerator is a quaternary ammonium salt (tetraethylammonium chloride) and SrCO in a mass ratio of 2:1. 3, other settings are exactly the same as those in Example 4.

[0163] Example 10

[0164] This embodiment provides a solid rocket engine grain embedded with metal wires, which is different from the embodiment 5 in that the material of the metal wires in the grain body layer embedded with metal wires is aluminum; and the material of the grain body layer containing a burning rate decelerator is a quaternary ammonium salt (tetraethylammonium chloride) and SrCO in a mass ratio of 1:2. 3 , other settings are exactly the same as those in Example 5.

[0165] Embodiment 11

[0166] The present embodiment provides a solid rocket engine grain embedded with metal wires, which differs from the first embodiment only in that, in the grain body layer embedded with metal wires, the material of the metal wires is aluminum, and the diameter of the metal wires is increased to 0.2 mm; and in the grain body layer containing a burning rate reducing agent, the burning rate reducing agent is a quaternary ammonium salt (tetraethyl tetrafluoroborate ammonium), and the addition amount is reduced to 0.3%. The other configurations are exactly the same as the first embodiment.

[0167] Example 12

[0168] This embodiment provides a solid rocket engine grain embedded with metal wires. The difference from the embodiment 2 is that in the grain body layer embedded with metal wires, the material of the metal wires is aluminum, and the diameter of the metal wires is increased to 0.2 mm; and in the grain body layer containing a burning rate reducing agent, the burning rate reducing agent is NH 4 PF 6 , the addition amount was reduced to 1.5%, and other settings were exactly the same as in Example 2.

[0169] Embodiment 13

[0170] This embodiment provides a solid rocket engine grain embedded with metal wires, which is different from the embodiment 3 only in that in the grain body layer embedded with metal wires, the material of the metal wires is aluminum, and the diameter of the metal wires is increased to 0.2 mm; and in the grain body layer containing a burning rate decelerator, the burning rate decelerator is a quaternary ammonium salt (tetraethyl tetrafluoroborate ammonium) and SrCO in a mass ratio of 1:1. 3 The other settings are exactly the same as those in Example 3.

[0171] Embodiment 14

[0172] This embodiment provides a solid rocket engine grain embedded with metal wires, which is different from the embodiment 4 only in that in the grain body layer embedded with metal wires, the material of the metal wires is aluminum, and the diameter of the metal wires is increased to 0.2 mm; and in the grain body layer containing a burning rate decelerator, the burning rate decelerator is a quaternary ammonium salt (tetraethyl tetrafluoroborate ammonium) and SrCO in a mass ratio of 2:1. 3, other settings are exactly the same as those in Example 4.

[0173] Embodiment 15

[0174] This embodiment provides a solid rocket engine grain embedded with metal wires, which is different from the embodiment 5 only in that in the grain body layer embedded with metal wires, the material of the metal wires is aluminum, and the diameter of the metal wires is increased to 0.2 mm; and in the grain body layer containing a burning rate decelerator, the burning rate decelerator is a quaternary ammonium salt (tetraethyl tetrafluoroborate ammonium) and SrCO in a mass ratio of 1:2. 3 , other settings are exactly the same as those in Example 5.

[0175] Example 16

[0176] This embodiment provides a solid rocket engine grain embedded with metal wires. The only difference from Embodiment 1 is that in the grain body layer embedded with metal wires, the metal wires are made of magnesium; and in the grain body layer containing a burning rate reducing agent, the burning rate reducing agent is a quaternary ammonium salt (benzalkonium chloride), and the added amount is reduced to 0.5%. Other settings are exactly the same as Embodiment 1.

[0177] Embodiment 17

[0178] This embodiment provides a solid rocket engine grain embedded with metal wires, which is different from the second embodiment only in that the material of the metal wires in the grain body layer embedded with metal wires is magnesium; and the material of the burning rate reducing agent in the grain body layer containing the burning rate reducing agent is NH 4 PF 6 , the addition amount was reduced to 2%, and the other settings were exactly the same as in Example 2.

[0179] Embodiment 18

[0180] This embodiment provides a solid rocket engine grain embedded with metal wires, which is different from the third embodiment only in that the material of the metal wires in the grain body layer embedded with metal wires is magnesium; and the material of the grain body layer containing a burning rate decelerator is a quaternary ammonium salt (benzalkonium chloride) and SrCO in a mass ratio of 1:1. 3 The mixture was added in an amount reduced to 2%, and the other settings were completely consistent with those in Example 3.

[0181] Embodiment 19

[0182] This embodiment provides a solid rocket engine grain embedded with metal wires, which is different from the embodiment 4 only in that the material of the metal wires in the grain body layer embedded with metal wires is magnesium; and the material of the grain body layer containing a burning rate decelerator is a quaternary ammonium salt (benzalkonium chloride) and SrCO in a mass ratio of 2:1. 3 , the addition amount was reduced to 2%, and the other settings were exactly the same as those in Example 4.

[0183] Embodiment 20

[0184] This embodiment provides a solid rocket engine grain embedded with metal wires, which is different from the embodiment 5 in that the material of the metal wires in the grain body layer embedded with metal wires is magnesium; and the material of the grain body layer containing a burning rate decelerator is a quaternary ammonium salt (benzalkonium chloride) and SrCO in a mass ratio of 1:2. 3 , the addition amount was reduced to 2%, and other settings were exactly the same as in Example 5.

[0185] Embodiment 21

[0186] This embodiment provides a solid rocket engine grain embedded with metal wires. The only difference from Embodiment 1 is that in the grain body layer embedded with metal wires, the material of the metal wires is magnesium, and the diameter of the metal wires is increased to 0.2 mm; and in the grain body layer containing a burning rate reducing agent, the burning rate reducing agent is a quaternary ammonium salt (quaternary ammonium perchlorate salt), and the added amount is reduced to 0.5%. Other settings are exactly the same as Embodiment 1.

[0187] Embodiment 22

[0188] This embodiment provides a solid rocket engine grain embedded with metal wires. The difference from the embodiment 2 is that in the grain body layer embedded with metal wires, the material of the metal wires is magnesium, and the diameter of the metal wires is increased to 0.2 mm; and in the grain body layer containing a burning rate reducing agent, the burning rate reducing agent is NH 4 PF 6 , the addition amount was reduced to 2%, and the other settings were exactly the same as in Example 2.

[0189] Embodiment 23

[0190] This embodiment provides a solid rocket engine grain embedded with metal wires, which is different from the embodiment 3 only in that in the grain body layer embedded with metal wires, the material of the metal wires is magnesium, and the diameter of the metal wires is increased to 0.2 mm; and in the grain body layer containing a burning rate decelerator, the burning rate decelerator is a quaternary ammonium salt (quaternary ammonium perchlorate salt) and SrCO in a mass ratio of 1:1. 3 The mixture was added in an amount reduced to 2%, and the other settings were completely consistent with those in Example 3.

[0191] Embodiment 24

[0192] This embodiment provides a solid rocket engine grain embedded with metal wires, which is different from the embodiment 4 only in that in the grain body layer embedded with metal wires, the material of the metal wires is magnesium, and the diameter of the metal wires is increased to 0.2 mm; and in the grain body layer containing a burning rate decelerator, the burning rate decelerator is a quaternary ammonium salt (quaternary ammonium perchlorate) and SrCO in a mass ratio of 2:1. 3 , the addition amount was reduced to 2%, and the other settings were exactly the same as those in Example 4.

[0193] Embodiment 25

[0194] This embodiment provides a solid rocket engine grain embedded with metal wires, which is different from the embodiment 5 only in that in the grain body layer embedded with metal wires, the material of the metal wires is magnesium, and the diameter of the metal wires is increased to 0.2 mm; and in the grain body layer containing a burning rate decelerator, the burning rate decelerator is a quaternary ammonium salt (quaternary ammonium perchlorate salt) and SrCO in a mass ratio of 1:2. 3 , the addition amount was reduced to 2%, and other settings were exactly the same as in Example 5.

[0195] Comparative Example 1

[0196] This comparative example provides a solid rocket engine grain, which differs from Example 1 only in that no metal wire is added to the grain body layer and no burning rate reducing agent is added. Other settings are exactly the same as Example 1.

[0197] Performance Test:

[0198] Test samples: solid rocket motor grains embedded with metal wires provided in Examples 1 to 25, and solid rocket motor grains not embedded with metal wires provided in Comparative Example 1;

[0199] The specific test results of the main body layer of the medicine column embedded with metal wire are shown in Table 3 below:

[0200] Table 3

[0201]

[0202]

[0203] As shown in Table 3, the present invention can achieve the enhancement of the burning rate by adding metal wire to part of the solid rocket motor grain, and the burning rate can reach 2 to 10 times the original, and the burning rate can be adjusted within the range of 1 to 100 mm / s.

[0204] The specific test results of the main layer of the grain containing the burning rate reducing agent are shown in Table 4 below:

[0205] Table 4

[0206]

[0207]

[0208] As shown in Table 4, adding 0.5-5% of the burning rate decelerator can reduce the burning rate by 0.2-3 mm / s. When a single burning rate decelerator is added to the propellant formula, (NH 4 ) 2 C 2 O 4 Speed ​​reduction effect and SrCO3 Same, but (NH 4 ) 2 C 2 O 4 Good gas formation; in carbonates, SrCO 3 The speed reduction effect is better than CaCO 3 Sucrose octaacetate is a type of speed reducer with good gasification performance and has a certain speed reduction effect, while LiF has a poor speed reduction effect. More specifically, the speed reduction effect is ranked as follows: (NH 4 ) 2 C 2 O 4 ≈SrCO 3 >CaCO 3 > sucrose octaacetate > LiF. From the comparison between Examples 4 / 6 and Examples 8 to 10, it can be seen that the combination of quaternary ammonium salt and carbonate has significant synergy and can significantly reduce the propellant burning rate. In summary, a burning rate reducer (quaternary ammonium salt + SrCO 3 ) to significantly reduce the burning rate; in the propellant layer where the burning rate needs to be slightly reduced, a burning rate reducer such as carbonate, LiF, etc. with a lower content and a smaller burning rate reduction multiple can be added.

[0209] It can be seen from the test data of Table 3 and Table 4 that the present invention can achieve variable thrust by adding metal wires of different types, contents, and arrangements or burning rate reducing agents of different types and contents to divide the grain into multiple layers with different burning rates; and further by setting the burning rate and thrust of each layer and adjusting the interval time, through the energy management of the propellant, the range, maneuverability, interception capability and combat capability of the missile are improved, so that the terminal velocity can be increased by 20%, and the range can be increased by 20% to 30%.

[0210] 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 by 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 rocket motor grain embedded with a metal wire, characterized in that: The solid rocket motor grain embedded with metal wire is a grain body with a cylindrical structure; The main body of the grain contains a burning rate reducing agent, and metal wires are embedded between the main bodies of the grain.

2. The solid rocket motor grain embedded with metal wire according to claim 1, characterized in that: The solid rocket motor grain embedded with metal wires comprises a grain body layer containing a burning rate reducing agent and a grain body layer embedded with metal wires; Preferably, 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 rocket motor grain embedded with metal wire according to claim 1 or 2, characterized in that: In the grain body layer containing the burning rate reducing agent, the burning rate reducing agent accounts for 0.05 to 5% of the mass of the grain body in the layer; Preferably, the burning rate reducing agent is selected from any one or a combination of at least two of carbonates, fluorides, ammonium salts, amine compounds, ammonium salts, quaternary ammonium salts or sucrose octaacetate; Preferably, the carbonate is selected from CaCO3 and / or SrCO3; Preferably, the fluoride is selected from LiF; Preferably, the ammonium salt is selected from any one or a combination of at least two of NH4F, (NH4)2BF, NH4PF6, (NH4)2SiF6 or (NH4)2HPO4; Preferably, the amine compound is selected from any one or a combination of at least two of urea, oxalamide, oxalamide or dicyandiamide; Preferably, the ammonium salt is selected from ammonium oxalate; Preferably, the quaternary ammonium salt is selected from any one or a combination of at least two of tetraethylammonium chloride, tetraethylammonium tetrafluoroborate, benzalkonium chloride or perchlorate quaternary ammonium salt; Preferably, the burning rate reducing agent is a combination of SrCO3 and ammonium salt; Preferably, the mass ratio of SrCO3 to ammonium salt is 5:1 to 1:5; Preferably, the raw materials for preparing the grain body include solid rocket engine fuel, and the solid rocket engine fuel is selected from terminal hydroxyl polybutadiene and / or ammonium perchlorate; Preferably, when the solid rocket engine fuel is selected from hydroxy-terminated polybutadiene, the burning rate decelerator is selected from any one or a combination of at least two of carbonate, fluoride, oxalamide or urea; Preferably, when the solid rocket engine fuel is selected from ammonium perchlorate, the burning rate decelerator is selected from any one of ammonia salts, amine compounds, ammonium salts or quaternary ammonium salts, or a combination of at least two thereof.

4. The solid rocket motor 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.

5. The solid rocket motor grain embedded with metal wire according to claim 4, characterized in that: When the arrangement of the metal wires is radial arrangement, the specific structure of the solid 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.

6. The solid rocket motor grain embedded with metal wire according to claim 4, characterized in that: When the arrangement of the metal wires is randomly embedded, the specific structure of the solid rocket motor 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.

7. The solid rocket motor grain embedded with metal wire according to claim 4, characterized in that: When the arrangement of the metal wires is annular, the specific structure of the solid rocket motor 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.

8. The solid rocket motor grain embedded with metal wire according to claim 4, characterized in that: When the arrangement of the metal wires is a mesh cross, the specific structure of the solid 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.

9. Use of a solid rocket motor grain embedded with a metal wire according to any one of claims 1 to 8 in regulating the burning rate of a solid rocket motor.

10. A solid rocket engine, characterized in that: The solid rocket engine comprises a combustion chamber, wherein the combustion chamber comprises a casing, an outer insulation layer, an inner insulation layer and a grain; Wherein, the outer insulation layer is arranged on the outer surface of the shell, the inner insulation layer is arranged on the inner surface of the shell, and the grain is filled in the inner insulation layer; and the grain is a solid rocket engine grain embedded with metal wire as described in any one of claims 1 to 8.

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