Solid rocket nozzle capable of repeatedly igniting and engine

Abstract

The invention discloses a solid rocket nozzle capable of repeatedly igniting and an engine. The solid rocket nozzle comprises an anti-ablation lining, a heat insulation sleeve and a shell, the anti-ablation lining is arranged on the innermost side of the spray pipe and is made of a tungsten / carbon + carbon / carbon + resin composite material or a tungsten / carbon + resin composite material, the heat insulation sleeve is arranged on the outer side of the anti-ablation lining in a sleeving mode, and the shell is arranged on the outer side of the heat insulation sleeve. The invention is suitable for solid rocket engines working for a long time, in particular to solid rocket engines of tactical missile rockets with tiny throat diameters and multi-pulse engines which are ignited for multiple times.

Description

Technical Field

[0001] The invention belongs to the technical field of solid rocket engines, and in particular relates to a solid rocket nozzle and an engine capable of repeated ignition. Background Art

[0002] Most solid rocket engines only undergo a short period of high temperature and high pressure working process during their life cycle. As long as the nozzle does not fail during this only working period, it is considered successful. In order to improve the range and penetration capability of missiles, the solid rocket engines of modern tactical missiles have begun to develop towards long burning time and multiple pulses. For multi-pulse solid engines, they have to undergo multiple intermittent high temperature and high pressure working during their life cycle. The engine will be in a flameout state during two working periods. Due to the high temperature and high pressure gas during the operation of the engine, the convergent section lining, throat lining, and expansion section lining of the nozzle will heat and expand, and the resin in the convergent section lining and insulation sleeve, expansion section lining and insulation sleeve made of fiber reinforced resin-based composite materials will be pyrolyzed, so that the parts of the nozzle lining will not be restored to their original state after the engine is turned off and cooled down. Since the parts of the nozzle lining are assembled by bonding with adhesives, gaps will appear between the parts after cooling down, and even parts will be damaged, which will bring hidden dangers to the next work. In order to ensure the subsequent work, the lining parts of the engine nozzle have to be strengthened and thickened, which significantly increases the negative mass. Application No. 202410369256.3 "A coarse and fine yarn mixed structure of an ablation-resistant lining preform" demonstrates a method for making an ablation-resistant lining preform for a solid rocket engine nozzle using coarse and fine yarn mixed technology, and proposes "a coarse and fine yarn mixed structure of an ablation-resistant lining preform, the consumable layer is finely knitted with fine yarn, and the thermal insulation layer is coarsely knitted with coarse yarn. The fine weft density of the consumable layer is 3 times the coarse weft density of the thermal insulation layer. The consumable layer is woven with 3 sections of fine yarn and the thermal insulation layer is woven with 1 section of coarse yarn, and the coarse warp yarn and the fine warp yarn are cross-linked with each other." This method only involves the lining parts of the convergence section and the expansion section but not the throat lining, and ultimately is made into a resin-based composite material. If used in the throat, it cannot work for a long time and cannot completely solve the stringent requirements of multi-pulse engines that require repeated work. Application number: 202411058525.0 "A low-cost ablation-resistant and erosion-resistant carbon / carbon lining and manufacturing method", by carbonizing the three-dimensional woven preform, the ablation-resistant lining becomes a solid material with a certain strength at high temperature. The so-called low-cost carbon / carbon lining only reduces the number of densification times compared with the traditional high-density carbon / carbon composite manufacturing, and the obtained carbon / carbon lining is of low density and high porosity. The cost is still very high due to high-temperature graphitization. In addition, the low-density carbon / carbon material has a high ablation rate and poor erosion resistance, and cannot meet the stringent requirements of the throat. Application number: 202411101406.9 "A nozzle and engine capable of reducing the back pressure of the throat lining" clearly reveals the problems existing in the working principle and structural design method of rocket nozzle parts in the prior art, and proposes a solution to the harm of pyrolysis gas back pressure to the throat lining during operation, but it still requires the use of special high-density carbon / carbon back lining materials or high-temperature resistant metal throat lining materials, and the entire manufacturing method is relatively complicated. Summary of the invention

[0003] The object of the present invention is to provide a solid rocket nozzle and engine capable of repeated ignition to solve the above-mentioned problems.

[0004] To achieve the above object, the present invention adopts the following technical solutions: A solid rocket nozzle capable of repeated ignition comprises an anti-ablation lining, an insulating sleeve and an outer shell; the anti-ablation lining is located at the innermost side of the nozzle and is a composite material of "tungsten / carbon + carbon / carbon + resin" or "tungsten / carbon + resin", and its reinforcing material is a three-dimensionally woven preform; the insulating sleeve is arranged on the outer side of the anti-ablation lining, and the outer shell is arranged on the outer side of the insulating sleeve.

[0005] Furthermore, when the anti-ablation lining is "tungsten / carbon + carbon / carbon + resin", it includes an inner ablation layer and an outer high-temperature support layer. The ablation layer uses tungsten wire or metal-plated carbon fiber, and the high-temperature support layer uses carbon fiber. Low-temperature carbonization forms a basic composite material of "tungsten / carbon + carbon / carbon", and resin is vacuum impregnated to obtain a composite material of "tungsten / carbon + carbon / carbon + resin".

[0006] Furthermore, the thermal insulation sleeve is formed by 2D braided overlapping or pre-impregnated high-silicon cloth tape winding; the outer shell is a metal shell with a connecting flange or thread on the outer shell.

[0007] Furthermore, the resin used in the pre-impregnated high-silica cloth tape of the thermal insulation sleeve is the same as or compatible with the resin in the "tungsten / carbon+carbon / carbon+resin" composite material, and is cured by an autoclave to firmly bond the thermal insulation sleeve to the anti-ablation lining.

[0008] Furthermore, the weaving structure of the integrated three-dimensional weaving preform of the composite material of "tungsten / carbon + carbon / carbon" is a 2.5D circular weaving structure.

[0009] Furthermore, the weaving structure of the integrated three-dimensional braided preform of the composite material of "tungsten / carbon + carbon / carbon" is a 2.5D coarse and fine yarn mixed circular weaving structure. The inner part in contact with the flame is finely woven with tungsten wires with small tows or metal-plated carbon fiber, and the outer part that will not be ablated is coarsely woven with carbon fiber with large tows. The pitch of the coarse weaving is 3 times the pitch of the fine weaving and is shallowly crossed and bent.

[0010] Furthermore, the resin impregnated with the composite material of "tungsten / carbon + carbon / carbon" is mixed with metal nanopowders of chromium, zirconium or titanium metal elements.

[0011] Furthermore, the low-temperature carbonization temperature is 500°C to 800°C, and then the material is heated to 850°C to 3000°C in a vacuum or inert atmosphere and kept warm for more than 10 minutes to generate high-temperature resistant metal carbides.

[0012] Furthermore, when the anti-ablation lining is "tungsten / carbon + resin", its preform is made of 2.5D three-dimensional weaving of annealed tungsten wire. After vacuum impregnation with resin and curing, the preform is placed in a carbonization furnace for low-temperature carbonization to obtain a "tungsten / carbon" porous base composite material.

[0013] Compared with the prior art, the present invention has the following technical effects: The present invention provides a solid rocket nozzle and engine capable of repeated ignition. The convergent section lining, throat lining and expansion section lining are integrated into a three-dimensional woven preform, and are impregnated with a high carbon residue resin and then carbonized at low temperature to prepare a porous high-temperature resistant skeleton with a certain mechanical strength. After secondary impregnation with resin, a pre-impregnated high-silica cloth tape is used to wrap the outside, and then put into an autoclave for curing. Compared with the prior art, the present invention has the following technical effects: 1. The convergent section liner, throat liner and expansion section liner are integrated into a three-dimensional woven preform, and are impregnated with high-residual carbon resin and then carbonized at low temperature to produce a porous, high-temperature resistant "tungsten / carbon + carbon / carbon" skeleton with certain mechanical strength, ensuring that the inner diameter and position of the throat will not change during engine operation due to insufficient high-temperature strength of the material.

[0014] 2. The ablation-resistant layer made of finely woven tungsten wire or metal-plated carbon fiber has a low ablation rate and a uniform ablation surface, which is beneficial to maintaining the stability of the engine thrust and thrust direction.

[0015] 3. The integrated three-dimensional woven preform and the integral lining will not cause fire penetration like the traditional split-assembly nozzle.

[0016] 4. The nozzle adopts an integrated three-dimensional woven convergent section lining, throat lining and expansion section lining. The ablation-resistant lining has a long working life and will not crack after the work is completed. It is particularly suitable for engine nozzles with long working time and multi-pulse solid rocket engine nozzles with multiple ignition segmented operations. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 The present invention is a schematic diagram of a reusable solid rocket engine nozzle.

[0018] Figure 2 The present invention is a schematic diagram of a reusable solid rocket engine nozzle.

[0019] Among them: 1 - anti-ablation lining, 2 - insulation sleeve, 3 - outer shell, 4 - ablation layer, 5 - high temperature support layer. DETAILED DESCRIPTION

[0020] The present invention is further described below in conjunction with the accompanying drawings: As we all know, the matrix of resin-based composite materials itself cannot withstand high temperatures. The convergent section and expansion section lining of the resin-based composite materials in the one-time solid-fired nozzle withstand high temperatures by gradually decomposing and consuming the resin. Under reasonable design, the decomposed and consumed resin can withstand the high temperature during operation so that the heat cannot be immediately transferred to the outside of the nozzle. However, because the nozzle throat also has to withstand large shear stress, only carbon / carbon materials or high-temperature resistant metal materials can be used. This is because carbon / carbon materials or high-temperature resistant metal materials do not undergo chemical reactions when subjected to high temperatures and remain solid with a certain strength. If a resin-based composite material is used in the nozzle throat, the resin in the resin-based composite material will decompose when exposed to high temperatures and spread rapidly from the ignition surface to the inside of the material, causing the strength of the part that loses the resin to drop significantly, and the throat diameter and the position of the throat diameter will change significantly, making the working state of the engine uncontrollable. Although the throat liner made of carbon / carbon material or high-temperature resistant metal material can withstand the erosion of high-temperature flames in the throat, the manufacturing cost of carbon / carbon material or high-temperature resistant metal material is very high, especially for small tactical missiles and rockets with a throat diameter of less than 3 cm. Due to the small throat diameter and the poor microscopic uniformity of carbon / carbon material, obvious grooves will appear during operation, especially under the erosion of aluminum powder propellant. The ablation rate is also relatively high, so it is not suitable for engines with tiny throat diameters, especially for small unguided rockets. The use of carbon / carbon throat liner will greatly reduce the hit accuracy.

[0021] High-temperature metal materials mainly refer to tungsten-infiltrated copper, molybdenum alloy, etc. This material is completely uniform in structure at the millimeter-level microscopic scale, so the ablation surface of the throat liner made of high-temperature metal materials is relatively smooth and uniform. In addition, due to the characteristics of high-temperature metal materials themselves, aluminum oxide droplets in the high-energy propellant flame are not easily adsorbed or condensed on the surface of high-temperature metal materials, and the ablation rate is significantly lower than that of carbon / carbon throat liners. This is why engines with smaller throat diameters prefer to use metal throat liners.

[0022] The present invention discloses a solid rocket engine nozzle capable of repeated ignition, comprising an anti-ablation liner 1, an insulation sleeve 2 and an outer shell 3. The anti-ablation liner is located at the innermost side of the nozzle and is a composite material of "tungsten / carbon + carbon / carbon + resin". The inner side of the integrated three-dimensional braided preform is made of tungsten wire or metal-plated carbon fiber, and the outer side is made of carbon fiber. The preform is vacuum impregnated with resin and cured, and then placed in a carbonization furnace for low-temperature carbonization to obtain a basic composite material of "tungsten / carbon + carbon / carbon", and then vacuum impregnated with resin again to obtain a composite material of "tungsten / carbon + carbon / carbon + resin"; the insulation sleeve 2 is located at the outer side of the anti-ablation liner and is wound with 2D braided sleeves or pre-impregnated high-silica cloth tape; the outermost side of the nozzle is an outer shell 3 made of high specific strength metal. In order to ensure a firm bond between the insulation sleeve and the anti-ablation liner, the resin used in the pre-impregnated high-silica cloth tape of the insulation sleeve is the same as or compatible with the resin in the composite material of "tungsten / carbon + carbon / carbon + resin". The composite material of "tungsten / carbon + carbon / carbon" adopts an integrated three-dimensional braided preform with a 2.5D circular weave structure. This braided structure has the characteristics of large normal thermal resistance, which is particularly conducive to the requirements of thermal insulation. In order to improve the weaving efficiency, the braiding structure of the integrated three-dimensional braided preform of the composite material of "tungsten / carbon + carbon / carbon" adopts a 2.5D coarse and fine mixed circular weave structure. The inner part that will be in contact with the flame adopts fine tungsten wire or metal-plated carbon fiber fine weaving, and the outer part that will not be ablated adopts coarse carbon fiber with larger wire tow. The pitch of the coarse weaving is 3 times that of the fine weaving pitch and is shallowly crossed and bent. In addition, the resin impregnated with the composite material of "tungsten / carbon+carbon / carbon" is mixed with metal nanopowders of metal elements such as chromium, zirconium, and titanium. After low-temperature carbonization at 500°C to 800°C, the metal nanopowders are heated to a temperature above the melting temperature of the metal nanopowders in a vacuum or inert atmosphere and maintained for a period of time so that the chromium, zirconium, and titanium metal elements in the nanopowders produce some bonding points with the surface of the tungsten wire and carbon fiber and part of the free carbon, generate high-temperature resistant metal carbides, and connect the tungsten wire and carbon fiber with pyrolytic carbon, so that the strength of the composite material of "tungsten / carbon+carbon / carbon" is further improved. The composite material of "tungsten / carbon+carbon / carbon" generated by one carbonization has low density and more voids. Before the high-silicon tape of the insulation sleeve 2 is wound, the composite material matrix of "tungsten / carbon+carbon / carbon" needs to be vacuum impregnated again to fill the pores in the "tungsten / carbon+carbon / carbon" material with phenolic resin. When the "tungsten / carbon + carbon / carbon + resin" composite material lining is subjected to high temperature and high pressure flame, the "tungsten / carbon + carbon / carbon" matrix always maintains a tough solid shape, and the "resin" will be pyrolyzed under the action of high temperature. Part of the carbon in the product will remain in the gaps, while the pyrolysis gas will flow into the flame through the micropores and take out part of the heat.

[0023] The invention discloses a reusable solid rocket engine nozzle, wherein the convergent section lining, the throat lining and the expansion section lining are an integrated three-dimensional woven preform, and are impregnated with a high carbon residue resin and then carbonized at low temperature to prepare a porous high-temperature resistant skeleton with a certain mechanical strength, and are impregnated with resin for the second time and then wrapped with a pre-impregnated high-silica cloth tape on the outside, and then put into an autoclave for curing.

[0024] Example 1 See also Figure 1 , a solid rocket engine nozzle capable of repeated ignition, comprising an anti-ablation liner 1, an insulation sleeve 2 and a metal shell 3. The anti-ablation liner 1 is located on the innermost side of the nozzle and is a composite material of "tungsten / carbon + resin". Its preform is made of 2.5D three-dimensional weaving of annealed tungsten wires, which are 160 tungsten wires with a diameter of 30μm combined into a bundle. After vacuum impregnation with resin and curing, the preform is placed in a carbonization furnace for low-temperature carbonization to obtain a "tungsten / carbon" porous basic composite material, and then vacuum impregnation with resin is performed again without curing to make a quasi-"tungsten / carbon + resin" composite material; the insulation sleeve 2 is on the outer side of the anti-ablation liner 1, and is wound with 2D woven sleeves or pre-impregnated high-silica cloth tape; the outermost side of the nozzle is a metal shell 3 made of titanium alloy. In order to ensure a firm bond between the thermal insulation sleeve 1 and the anti-ablation liner 1, the resin used for the pre-impregnated high-silica tape wrapped around the thermal insulation sleeve is the same as the resin in the "tungsten / carbon + resin" composite material, which is phenolic resin or compatible phenolic and epoxy resin, and can be combined into one during curing. The "tungsten / carbon" composite material adopts an integrated three-dimensional woven preform with a 2.5D circular weave structure. This woven structure has the characteristics of large normal thermal resistance, which is particularly beneficial to the requirements of thermal insulation. The "tungsten / carbon" composite material generated by one-time impregnation densification and carbonization has many voids. Before winding the high-silica tape around the thermal insulation sleeve, the "tungsten / carbon" composite material matrix needs to be vacuum impregnated again to fill the pores in the "tungsten / carbon" material with phenolic resin. When the composite material lining of "tungsten / carbon + resin" is subjected to high temperature and high pressure flame, the porous "tungsten / carbon" skeleton always maintains a solid shape, and the "resin" in the pores will be pyrolyzed under the action of high temperature. The carbon in the product will partially remain in the gap, and the pyrolyzed gas will flow into the flame along the micropores and take out part of the heat. The "tungsten / carbon" matrix has a low ablation rate and always maintains a solid shape. After each work, the throat diameter and throat position will not change significantly. The integrated three-dimensional woven lining preform has integrity, and will not have gaps and cracks between the convergence section and the throat lining, and between the throat lining and the expansion section after a work is completed like the traditional nozzle, which significantly improves the reliability of repeated ignition of the solid rocket engine. However, it is very uneconomical to use tungsten wire woven lining preforms, and it will also increase the negative mass.

[0025] Example 2 See also Figure 1 and Figure 2A solid rocket engine nozzle capable of repeated ignition includes an ablation-resistant liner 1, an insulation sleeve 2, and a metal shell 3. The ablation-resistant liner 1 is located on the innermost side of the nozzle and is a composite material of "tungsten / carbon + carbon / carbon + resin". The inner ablation layer 4 of the integrated three-dimensional braided preform is made of tungsten wire or metal-plated carbon fiber, and the outer high-temperature support layer 5 is made of carbon fiber. The preform is vacuum impregnated with resin and cured, and then placed in a carbonization furnace for low-temperature carbonization to obtain a basic composite material matrix of "tungsten / carbon + carbon / carbon", and then vacuum impregnated with resin again, and the resin is not cured temporarily to make a composite material liner of "tungsten / carbon + carbon / carbon + resin"; the insulation sleeve 2 is on the outer side of the ablation-resistant liner 1, and is wound with 2D braided sleeves or pre-impregnated high-silicon cloth tape; the outermost side of the nozzle is a metal shell 3 made of high specific strength metal. In order to ensure a firm bond between the insulation sleeve 2 and the outer high-temperature support layer 5 of the anti-ablation liner, the resin used in the pre-impregnated high-silica tape wrapped around the insulation sleeve is the same as the resin in the "tungsten / carbon + carbon / carbon + resin" composite material, both of which are the same brand of solvent-free barium phenolic resin, which can be combined into one during curing. The "tungsten / carbon + carbon / carbon" basic composite material uses an integrated three-dimensional woven preform with a 2.5D circular weave structure. This woven structure has the characteristics of large normal thermal resistance, which is particularly conducive to the requirements of thermal insulation. In order to improve the weaving efficiency, the weaving structure of the integrated three-dimensional weaving preform of the "tungsten / carbon + carbon / carbon" basic composite material adopts a 2.5D coarse and fine yarn mixed circular weaving structure. The inner part that will be in contact with the flame adopts a fine tungsten wire bundle composed of 80 tungsten wires with a diameter of 30μm, and the outer part that will not be ablated adopts a T700-12K carbon fiber coarse weaving with a larger wire bundle. The pitch of the coarse weaving is 3 times the pitch of the fine weaving and is shallowly crossed and bent. This not only has high production efficiency, but also makes the surface of the anti-ablation lining smoother after work. Since there are more voids in the coarse weaving part after carbonization, it can accommodate more resin and significantly slow down the speed of the high-temperature interface moving outward, which is very beneficial to the insulation of the outside of the nozzle. In order to further improve the strength of the "tungsten / carbon + carbon / carbon" basic composite material, 1% to 5% (mass ratio) of molybdenum-titanium-zirconium alloy nanopowder is mixed in the phenolic resin impregnated with the lining preform 1. After low-temperature carbonization at 500°C to 800°C, it is heated to 2650°C to 2700°C in vacuum or inert atmosphere and kept warm for 30 minutes to allow the chromium, zirconium and titanium metal elements in the nanopowder to produce some bonding points with the surface of the tungsten wire and carbon fiber and part of the free carbon, thereby generating high-temperature resistant metal carbides and connecting the tungsten wire and carbon fiber with the pyrolytic carbon, thereby further improving the high-temperature strength of the porous composite.The "tungsten / carbon + carbon / carbon" composite material obtained by only one carbonization has low density and more voids. Before wrapping the insulation sleeve 2 with high-silica tape, the "tungsten / carbon + carbon / carbon" basic composite material needs to be vacuum impregnated again to fill the pores in the "tungsten / carbon + carbon / carbon" material with phenolic resin. When the "tungsten / carbon + carbon / carbon + resin" composite material lining is subjected to high-temperature and high-pressure flame, the "tungsten / carbon + carbon / carbon" matrix always maintains a tough solid shape, and the "resin" will be pyrolyzed from the inside to the outside under the action of high temperature. Part of the carbon in the product will remain in the voids, and the pyrolyzed gas substance will flow out through the micropores into the flame, taking out part of the heat.

[0026] 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 rocket nozzle capable of repeated ignition, characterized in that: The invention comprises an anti-ablation liner (1), an insulating sleeve (2) and an outer shell (3); the anti-ablation liner (1) is located at the innermost side of the nozzle and is a composite material of "tungsten / carbon + carbon / carbon + resin" or "tungsten / carbon + resin", and its reinforcing material is a preform woven in three dimensions; the insulating sleeve (2) is sleeved on the outer side of the anti-ablation liner (1), and the outer shell (3) is arranged on the outer side of the insulating sleeve (2).

2. A solid rocket nozzle capable of repeated ignition according to claim 1, characterized in that: When the anti-ablation lining (1) is "tungsten / carbon + carbon / carbon + resin", it includes an inner ablation layer (4) and an outer high-temperature support layer (5), the ablation layer (4) is made of tungsten wire or metal-plated carbon fiber, and the high-temperature support layer (5) is made of carbon fiber. Low-temperature carbonization forms a basic composite material of "tungsten / carbon + carbon / carbon", and vacuum impregnation of resin is performed to obtain a composite material of "tungsten / carbon + carbon / carbon + resin".

3. A solid rocket nozzle capable of repeated ignition according to claim 1, characterized in that: The thermal insulation sleeve (2) is made of 2D braided sleeve or pre-impregnated high-silicon cloth tape; the outer shell (3) is a metal outer shell, and a connecting flange or thread is provided on the outer shell (3).

4. A solid rocket nozzle and engine capable of repeated ignition according to claim 1, characterized in that: The resin used in the pre-impregnated high-silica cloth tape of the thermal insulation sleeve (2) is the same as or compatible with the resin in the "tungsten / carbon+carbon / carbon+resin" composite material, and is cured by an autoclave to firmly bond the thermal insulation sleeve (2) to the anti-ablation liner (1).

5. A solid rocket nozzle capable of repeated ignition according to claim 2, characterized in that: The weaving structure of the integrated three-dimensional weaving preform of the composite material of "tungsten / carbon + carbon / carbon" is a 2.5D circular weaving structure.

6. A solid rocket nozzle capable of repeated ignition according to claim 5, characterized in that: The weaving structure of the integrated three-dimensional braided preform of the composite material of "tungsten / carbon + carbon / carbon" is a 2.5D coarse and fine mixed circular weave structure. The inner part in contact with the flame is finely woven with tungsten wire with small tow or metal-plated carbon fiber, and the outer part that will not be ablated is coarsely woven with carbon fiber with large tow. The pitch of the coarse weaving is 3 times the pitch of the fine weaving and is shallowly crossed and bent.

7. A solid rocket nozzle capable of repeated ignition according to claim 2, characterized in that: The resin impregnated with the composite material of "tungsten / carbon + carbon / carbon" is mixed with metal nanopowders of chromium, zirconium or titanium metal elements.

8. A solid rocket nozzle capable of repeated ignition according to claim 7, characterized in that: The low-temperature carbonization temperature is 500℃~800℃, and then it is heated to 850℃~3000℃ in vacuum or inert atmosphere and kept warm for more than 10 minutes to generate high-temperature resistant metal carbides.

9. A solid rocket nozzle capable of repeated ignition according to claim 1, characterized in that: When the anti-ablation lining (1) is "tungsten / carbon + resin", its preform is made of annealed tungsten wire integrated 2.5D three-dimensional weaving. After the preform is vacuum impregnated with resin and cured, it is placed in a carbonization furnace for low-temperature carbonization to obtain a "tungsten / carbon" porous base composite material.

10. A solid rocket engine capable of repeated ignition, characterized in that: A solid rocket nozzle capable of repeated ignition as claimed in any one of claims 1 to 9.

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