Solid propellant rocket engine thrust vectoring nozzle

Abstract

The application provides a solid-liquid rocket engine thrust vector nozzle, which comprises a nozzle shell, a nozzle body and a catalytic assembly; the nozzle shell is sleeved on the nozzle body; the nozzle body has a converging section and a diverging section; a first liquid collecting cavity is surrounded between the converging section and the nozzle shell, and a second liquid collecting cavity is surrounded between the diverging section and the nozzle shell; the nozzle shell is provided with an inlet channel, and the nozzle body is provided with a cooling channel; the oxidizer is introduced into the first liquid collecting cavity through the inlet channel, and is introduced into the second liquid collecting cavity from the first liquid collecting cavity through the cooling channel; the oxidizer in the cooling channel exchanges heat with the fuel of the nozzle body; the diverging section is provided with a jet hole, the catalytic bed is communicated with the jet hole, the oxidizer after heat exchange is introduced into the catalytic assembly through the second liquid collecting cavity, and is injected from the jet hole to the nozzle body. The application takes away the excess heat through the heat convection, reduces the ablation of the nozzle body on one hand, and heats the oxidizer, produces a good secondary injection effect, and further produces the thrust vector.

Description

Technical Field

[0001] This application relates to the field of aerospace technology, and in particular to a thrust vectoring nozzle for a solid-liquid rocket engine. Background Technology

[0002] Fluid secondary injection thrust vector control technology is currently widely used in various aero-engines and rocket engines, enabling engines to obtain thrust vector adjustment capabilities. In the field of solid-liquid rocket engines, the secondary injection working fluid of this technology is often selected as high-temperature gas, while the nozzle itself relies on passive methods such as heat sinks for thermal protection. However, this technology still has the following shortcomings: (1) The secondary injection working fluid of traditional solid-liquid rocket engine vector control nozzles is often selected as high-temperature gas, which is difficult to obtain and has high risks. Moreover, it is difficult to change the pressure and flow rate of the gas drawn from the foreburner, resulting in poor thrust vectoring effect. (2) When using thermal protection methods such as heat sink nozzles, the nozzle is severely eroded. In the final stage of engine operation, the nozzle throat diameter often increases, the combustion chamber pressure drops, and specific impulse is lost.

[0003] Therefore, there is an urgent need for a solid-liquid rocket engine thrust vectoring nozzle to solve the technical problems existing in the current technology to some extent. Summary of the Invention

[0004] The purpose of this application is to provide a thrust vectoring nozzle for a solid-liquid rocket engine, which to some extent solves the technical problem of poor thrust vectoring effect in the prior art.

[0005] This application provides a solid-liquid rocket engine thrust vectoring nozzle, including a nozzle shell, a nozzle body, and a catalyst assembly;

[0006] The nozzle housing is fitted over the nozzle body; the nozzle body has a converging section and a diverging section communicating with the converging section; a first liquid collecting cavity is provided between the converging section and the nozzle housing, and a second liquid collecting cavity is provided between the diverging section and the nozzle housing.

[0007] The nozzle housing has an inlet channel that connects to the first liquid collection chamber, and the nozzle body has a cooling channel that connects the first liquid collection chamber and the second liquid collection chamber. The oxidant can be introduced into the first liquid collection chamber through the inlet channel, and then introduced from the first liquid collection chamber into the second liquid collection chamber through the cooling channel. The oxidant in the cooling channel can exchange heat with the fuel in the nozzle body.

[0008] The diffuser section has a jet hole. One end of the catalyst bed is connected to the second liquid collection chamber and the other end is connected to the jet hole. The oxidant after heat exchange is introduced into the catalyst assembly through the second liquid collection chamber and injected into the nozzle body through the jet hole.

[0009] In the above technical solution, the catalytic component further includes a catalytic bed, a first pipe, a second pipe, and a third pipe;

[0010] The jet orifice extends along the thickness direction of the nozzle body, and the first pipe is disposed in the nozzle shell and communicates with the jet orifice;

[0011] One end of the catalyst bed is connected to the second liquid collection chamber through the second pipe and the other end is connected to the first pipe through the third pipe. The heat-exchanged oxidant passes through the second pipe, the catalyst bed, the third pipe and the first channel in sequence, and is injected into the nozzle body from the jet hole.

[0012] In the above technical solution, the catalyst bed is further provided with multiple layers of nickel-based silver mesh, which are stacked sequentially along the radial direction of the nozzle body. The multiple layers of nickel-based silver mesh can decompose the oxidant into high-temperature decomposition gas.

[0013] In the above technical solution, the first pipe, the second pipe, the third pipe, the catalyst bed, and the nozzle shell are integrally formed.

[0014] In the above technical solution, the nozzle housing further includes a first connecting portion and a second connecting portion having one end connected to the first connecting portion and the other end connected to the combustion chamber.

[0015] The first connecting part is provided with a flow channel communicating with the inner sidewall. The inlet channel is opened in the first connecting part, one end of which is connected to the outer sidewall of the expansion part and the other end is connected to the flow channel.

[0016] The first connecting part has a second annular groove on its end face facing the combustion chamber, so that the inner sidewall of the first connecting part has a first annular protruding edge facing the combustion chamber;

[0017] A third annular groove is provided on the tapered section, and the third annular groove is opposite to the flow channel, so that the third annular groove and the flow channel constitute the first liquid collection cavity;

[0018] The tapering section extends toward the first connecting portion and has a first limiting edge capable of abutting against the sidewall on which the second annular groove is formed.

[0019] In the above technical solution, a fourth annular groove is further provided at the end of the second connecting part away from the first connecting part, and a fifth annular groove is provided on the gradually expanding section at a position opposite to the fourth annular groove. The fourth annular groove and the fifth annular groove constitute the second liquid collection cavity.

[0020] In the above technical solution, the solid-liquid rocket engine thrust vector nozzle further includes a nozzle liner;

[0021] The nozzle housing has a straight cylindrical mounting cavity, and the nozzle body is disposed in the straight cylindrical mounting cavity;

[0022] The nozzle liner is disposed between the nozzle outer shell and the nozzle body.

[0023] In the above technical solution, the solid-liquid rocket engine thrust vector nozzle further includes a first sealing ring;

[0024] The first connecting part also has a sixth annular groove on the side facing the combustion chamber;

[0025] The first sealing ring is respectively disposed in the second annular groove and the sixth annular groove.

[0026] In the above technical solution, the solid-liquid rocket engine thrust vector nozzle further includes a second sealing ring and a third sealing ring;

[0027] The second sealing ring is disposed between the second connecting portion and the gradually expanding section, and the second sealing ring is located between the nozzle liner and the fifth annular groove;

[0028] The third sealing ring is disposed between the first connecting portion and the tapered section, and the third sealing ring is located between the nozzle liner and the third annular groove.

[0029] In the above technical solution, the cooling is further provided by providing multiple cooling channels, which are arranged at intervals along the circumferential direction of the nozzle body.

[0030] Compared with the prior art, the beneficial effects of this application are as follows:

[0031] This application provides a solid-liquid rocket engine thrust vectoring nozzle, including a nozzle shell, a nozzle body, and a catalyst assembly;

[0032] The nozzle housing is fitted over the nozzle body; the nozzle body has a converging section and a diverging section communicating with the converging section; a first liquid collecting cavity is provided between the converging section and the nozzle housing, and a second liquid collecting cavity is provided between the diverging section and the nozzle housing.

[0033] The nozzle housing has an inlet channel that connects to the first liquid collection chamber, and the nozzle body has a cooling channel that connects the first liquid collection chamber and the second liquid collection chamber. The oxidant can be introduced into the first liquid collection chamber through the inlet channel, and then introduced from the first liquid collection chamber into the second liquid collection chamber through the cooling channel. The oxidant in the cooling channel can exchange heat with the fuel in the nozzle body.

[0034] The diffuser section has a jet hole. One end of the catalyst bed is connected to the second liquid collection chamber and the other end is connected to the jet hole. The oxidant after heat exchange is introduced into the catalyst assembly through the second liquid collection chamber and injected into the nozzle body through the jet hole.

[0035] In summary, this application proposes a solid-liquid rocket engine nozzle that uses a common oxidizer for cooling in solid-liquid rocket engines, and then passes the cooling oxidizer through a catalytic converter to generate high-temperature gas for secondary injection vector control. Utilizing the oxidizer carried in the engine tank, it dissipates excess heat during engine operation through convection heat exchange across the outer wall of the nozzle body. This reduces nozzle body ablation and heats the oxidizer, ensuring it reaches a high temperature after passing through the catalytic converter, resulting in a good secondary injection effect and thus generating thrust vector. Attached Figure Description

[0036] To more clearly illustrate the technical solutions in the specific embodiments of this application or the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0037] Figure 1 A schematic diagram of the structure of a solid-liquid rocket engine thrust vectoring nozzle provided in an embodiment of this application, viewed from a first perspective.

[0038] Figure 2 A schematic diagram of the solid-liquid rocket engine thrust vectoring nozzle provided in an embodiment of this application from a second perspective;

[0039] Figure 3 A schematic diagram of the nozzle shell in the thrust vectoring nozzle of a solid-liquid rocket engine provided in an embodiment of this application, viewed from a first perspective.

[0040] Figure 4 A schematic diagram of the nozzle shell in the solid-liquid rocket engine thrust vectoring nozzle provided in the embodiments of this application, viewed from a second perspective.

[0041] Figure 5A schematic diagram of the structure of the nozzle body and nozzle liner in the solid-liquid rocket engine thrust vectoring nozzle provided in the embodiments of this application;

[0042] Figure 6 A schematic diagram of the main body of the nozzle in the solid-liquid rocket engine thrust vectoring nozzle provided in the embodiments of this application, viewed from a first perspective.

[0043] Figure 7 A schematic diagram of the main body of the nozzle in the solid-liquid rocket engine thrust vectoring nozzle provided in the embodiments of this application, viewed from a second perspective.

[0044] Figure 8 A cross-sectional view of the nozzle body in the thrust vectoring nozzle of the solid-liquid rocket engine provided in the embodiments of this application;

[0045] Figure 9 A cross-sectional view of a solid-liquid rocket engine thrust vectoring nozzle provided in an embodiment of this application.

[0046] Reference numerals: 1- Nozzle housing; 2- Nozzle body; 3- Catalytic assembly; 4- Converging section; 5- Diverging section; 6- First liquid collection chamber; 7- Second liquid collection chamber; 8- Inlet channel; 9- Cooling channel; 10- Jet nozzle; 11- Catalytic bed; 12- First pipe; 13- Second pipe; 14- Third pipe; 15- First connecting part; 16- Second connecting part; 17- Flow guide channel; 18- Second annular groove; 19- First annular protruding edge; 20- Third annular groove; 21- First limiting edge; 22- Fourth annular groove; 23- Fifth annular groove; 24- Nozzle liner; 26- Sixth annular groove; 27- Second sealing ring; 28- Third sealing ring; 29- Connecting hole; 30- Mounting groove. Detailed Implementation

[0047] The technical solutions of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are some embodiments of this application, but not all embodiments.

[0048] The components of the embodiments of this application described and shown in the accompanying drawings can be arranged and designed in a variety of different configurations. Therefore, the following detailed description of the embodiments of this application provided in the drawings is not intended to limit the scope of the claimed application, but merely to illustrate selected embodiments of the application.

[0049] Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0050] In the description of this application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0051] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection between two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0052] The following is combined with Figures 1-9 This application provides a detailed description of a solid-liquid rocket engine thrust vectoring nozzle.

[0053] Combination Figure 1 and Figure 2 As shown, this embodiment provides a solid-liquid rocket engine thrust vectoring nozzle, which includes a nozzle shell 1, a nozzle body 2, and a catalyst assembly 3.

[0054] Specifically, the nozzle housing 1 is fitted with the nozzle body 2; the nozzle body 2 has a converging section 4 and a diverging section 5 connected to the converging section 4; a first liquid collecting chamber 6 is provided between the converging section 4 and the nozzle housing 1, and a second liquid collecting chamber 7 is provided between the diverging section 5 and the nozzle housing 1.

[0055] Specifically, the nozzle shell 1 has an inlet channel 8 that connects to the first liquid collection chamber 6, and the nozzle body 2 has a cooling channel 9 that connects the first liquid collection chamber 6 and the second liquid collection chamber 7, that is, a cooling channel 9 is provided on the side wall of the nozzle body 2. In actual use, the oxidant (the oxidant is usually stored in the tank) can be introduced into the first liquid collection chamber 6 through the inlet channel 8, and then introduced into the second liquid collection chamber 7 through the cooling channel 9. The oxidant is preferably a hydrogen peroxide, and it is a low-temperature hydrogen peroxide. During the process of the hydrogen peroxide flowing from the first liquid collection chamber 6 to the second liquid collection chamber 7, it will exchange heat with the high-temperature fuel burning in the nozzle body 2. At this time, the heat exchange is convective heat transfer, that is, the low-temperature hydrogen peroxide absorbs the heat of the high-temperature gas inside the nozzle body 2 and is heated to near the decomposition temperature.

[0056] Specifically, the diffuser section 5 has a jet hole 10. One end of the catalyst bed 11 is connected to the second liquid collection chamber 7, and the other end is connected to the jet hole 10. In actual use, the oxidant after heat exchange is introduced into the catalyst assembly 3 through the second liquid collection chamber 7 and injected into the nozzle body 2 through the jet hole 10. When the heat-exchanged hydrogen peroxide passes through the catalyst assembly 3, the catalyst assembly 3 can decompose the hydrogen peroxide. The high-pressure gas after decomposition is injected into the nozzle body 2 through the injection hole, compressing the mainstream combustion gas and inducing its direction deflection, thereby generating a thrust vector.

[0057] In summary, this application proposes a solid-liquid rocket engine nozzle that uses hydrogen peroxide, a common oxidizer in solid-liquid rocket engines, for cooling. The hydrogen peroxide used for cooling is then passed through a catalytic converter 3 to generate high-temperature gas for secondary injection vector control. Utilizing hydrogen peroxide carried in the engine tank, it is convectively cooled through the outer wall of the nozzle body 2 to dissipate excess heat during engine operation. This reduces nozzle erosion and heats the hydrogen peroxide, ensuring it reaches a high temperature after passing through the catalytic converter 3, resulting in a good secondary injection effect and thus generating thrust vector. Furthermore, the hydrogen peroxide used for cooling is controlled by a separate flow path, allowing for a wide range of pressure and flow rate adjustments, thereby achieving a wider range and higher precision thrust vector control.

[0058] In this embodiment, the catalytic component 3 includes a catalytic bed 11, a first pipe 12, a second pipe 13, and a third pipe 14.

[0059] Specifically, the jet hole 10 extends along the thickness direction of the nozzle body 2, and preferably, the diameter of the jet hole is 3.3 mm or 2 mm.

[0060] Specifically, the first pipe 12 is disposed in the nozzle housing 1 and communicates with the jet hole 10; one end of the catalyst bed 11 is connected to the second liquid collection chamber 7 through the second pipe 13 and the other end is connected to the first pipe 12 through the third pipe 14.

[0061] Furthermore, the catalyst bed 11 is provided with multiple layers of nickel-based silver mesh, which are stacked sequentially along the radial direction of the nozzle body 2. The multiple layers of nickel-based silver mesh can decompose the oxidant into high-temperature decomposition gas. Since the oxidant is hydrogen peroxide, the nickel-based silver mesh catalyst bed 11 can catalytically decompose high-temperature hydrogen peroxide into high-temperature gas. The decomposition gas mainly contains oxygen and water vapor at a temperature of about 1000K.

[0062] Furthermore, the first pipe 12, the second pipe 13, the third pipe 14, the catalyst bed 11, and the nozzle shell 1 are integrally formed.

[0063] In actual use, the heat-exchanged hydrogen peroxide hydroxide flows sequentially through the second pipe 13, the catalyst bed 11, the third pipe 14, and the first channel, and is injected into the nozzle body 2 through the jet hole 10. High-temperature decomposition gas is injected into the nozzle body 2 through the secondary injection hole, compressing and inducing the mainstream to generate a thrust vector.

[0064] In this embodiment, the nozzle housing 1 includes a second connecting portion 16 and a first connecting portion 15, one end of which is connected to the first connecting portion 15 and the other end of which is connected to combustion.

[0065] Specifically, the first connecting part 15 is connected to the combustion chamber through a connecting member, and a connecting hole 29 is provided on the end face of the first connecting part 15 facing the combustion chamber, through which the connecting member passes and connects to the combustion chamber.

[0066] Specifically, the first connecting part 15 is provided with a guide channel 17 that communicates with the inner side wall, and the inlet channel 8 is provided in the first connecting part 15, with one end communicating with the outer side wall of the expansion part and the other end communicating with the guide channel 17.

[0067] Specifically, the first connecting part 15 has a second annular groove 18 on its end face facing the combustion chamber, so that the inner sidewall of the first connecting part 15 has a first annular protruding edge 19 facing the combustion chamber.

[0068] Furthermore, a first sealing ring is provided in the second annular groove 18 to prevent the high-temperature gas in the nozzle body 2 from entering the cooling channel.

[0069] Furthermore, a sixth annular groove 26 is provided on the side of the first connecting part 15 facing the combustion chamber; a first sealing ring is provided in the sixth annular groove 26, and the first sealing ring here is used to seal the combustion chamber and the first connecting part 15.

[0070] Specifically, a third annular groove 20 is provided on the tapered section 4, and the third annular groove 20 is opposite to the guide channel 17, so that the third annular groove 20 and the guide channel 17 constitute the first liquid collection chamber 6.

[0071] Specifically, the tapered section 4 extends toward the first connecting portion 15 with a first limiting edge 21 capable of abutting against the sidewall on which the second annular groove 18 is formed.

[0072] In this embodiment, a fourth annular groove 22 is provided at the end of the second connecting portion 16 away from the first connecting portion 15, and a fifth annular groove 23 is provided on the gradually expanding section 5 at a position opposite to the fourth annular groove 22. The fourth annular groove 22 and the fifth annular groove 23 constitute the second liquid collecting cavity 7.

[0073] Specifically, the starting end of the cooling channel is opened in the third annular groove 20, and the ending end is opened in the fifth annular groove 23, so that the cooling channel can connect the first liquid collection chamber 6 and the second liquid collection chamber 7.

[0074] In this embodiment, the solid-liquid rocket engine thrust vectoring nozzle also includes a nozzle liner 24.

[0075] Specifically, the nozzle housing 1 has a straight cylindrical mounting cavity, and the nozzle body 2 is disposed in the straight cylindrical mounting cavity; the nozzle liner 24 is disposed between the nozzle housing 1 and the nozzle body 2.

[0076] Furthermore, the nozzle liner 24 is actually two halves of a rotating body, made of F4. The main function of the nozzle liner 24 is to fill the gap between the converging section 4 and the diverging section 5 of the nozzle body 2 and the nozzle shell 1, thus preventing the concentration of easily decomposable working fluid.

[0077] In this embodiment, the solid-liquid rocket engine thrust vectoring nozzle also includes a second sealing ring 27 and a third sealing ring 28.

[0078] Specifically, the second sealing ring 27 is disposed between the second connecting part 16 and the expanding section 5 (the expanding section 5 is provided with an installation groove 30, and the installation groove 30 is used to install the second sealing ring 27), and the second sealing ring 27 is located between the nozzle liner 24 and the fifth annular groove 23. The second sealing ring 27 here is used to seal the second connecting part 16 and the expanding section 5.

[0079] Specifically, the third sealing ring 28 is disposed between the first connecting part 15 and the tapered section 4 (the tapered section 4 is provided with an installation groove 30, and the installation groove 30 is used to install the third sealing ring 28), and the third sealing ring 28 is located between the nozzle liner 24 and the third annular groove 20. The second sealing ring 27 here is used to seal the first connecting part 15 and the tapered section 4.

[0080] In this embodiment, cooling is achieved by providing multiple cooling channels 9 arranged at intervals along the circumferential direction of the nozzle body 2.

[0081] Specifically, multiple cooling channels 9 can increase the rate at which hydrogen peroxide flows from the first liquid collection chamber 6 to the second liquid collection chamber 7.

[0082] In summary, this application utilizes hydrogen peroxide flowing through the cooling channel 9 of the nozzle body 2 to remove excess heat during engine operation, exhibiting superior cooling performance compared to passive cooling. This is beneficial for reducing nozzle erosion and improving the performance of solid-liquid rocket engines.

[0083] Secondly, by using hydrogen peroxide for cooling in a secondary injection, the initial temperature of hydrogen peroxide entering the catalytic bed 11 can be increased, thereby improving the catalytic effect and the enthalpy of the high-temperature gas after catalysis, and enhancing the effect of secondary injection.

[0084] Finally, by using a separate flow path control scheme with secondary hydrogen peroxide injection, the pressure and flow rate can be varied over a wide range, thereby achieving thrust vector control with a wider range and higher precision.

[0085] Obviously, those skilled in the art can make various modifications and variations to the embodiments of this application without departing from the spirit and scope of the embodiments of this application. Therefore, if these modifications and variations to the embodiments of this application fall within the scope of the claims in this application and their equivalents, then this application also intends to include these modifications and variations.

Claims

1. A solid-liquid rocket engine thrust vectoring nozzle, characterized in that, This includes the nozzle housing, the nozzle body, and the catalytic converter assembly; The nozzle housing is fitted over the nozzle body; the nozzle body has a converging section and a diverging section communicating with the converging section; a first liquid collecting cavity is provided between the converging section and the nozzle housing, and a second liquid collecting cavity is provided between the diverging section and the nozzle housing. The nozzle housing has an inlet channel that connects to the first liquid collection chamber, and the nozzle body has a cooling channel that connects the first liquid collection chamber and the second liquid collection chamber. The oxidant can be introduced into the first liquid collection chamber through the inlet channel, and then introduced from the first liquid collection chamber into the second liquid collection chamber through the cooling channel. The oxidant in the cooling channel can exchange heat with the fuel in the nozzle body. The diffuser section has a jet hole. One end of the catalytic component is connected to the second liquid collection chamber and the other end is connected to the jet hole. The oxidant after heat exchange is introduced into the catalytic component through the second liquid collection chamber and injected into the main channel of the nozzle body through the jet hole. The catalytic assembly includes a catalytic bed, a first pipe, a second pipe, and a third pipe; The jet orifice extends along the thickness direction of the nozzle body, and the first pipe is disposed in the nozzle shell and communicates with the jet orifice; One end of the catalyst bed is connected to the second liquid collection chamber through the second pipe and the other end is connected to the first pipe through the third pipe. The heat-exchanged oxidant passes through the second pipe, the catalyst bed, the third pipe and the first pipe in sequence, and is injected into the nozzle body from the jet hole. The nozzle housing includes a second connecting portion and a first connecting portion, one end of which is connected to the second connecting portion and the other end of which is connected to combustion. The first connecting part is provided with a flow channel communicating with the inner sidewall. The inlet channel is opened in the first connecting part, one end of which is connected with the outer sidewall of the gradually expanding section and the other end is connected with the flow channel. The first connecting part has a second annular groove on its end face facing the combustion chamber, so that the inner sidewall of the first connecting part has a first annular protruding edge facing the combustion chamber; A third annular groove is provided on the tapered section, and the third annular groove is opposite to the flow channel, so that the third annular groove and the flow channel constitute the first liquid collection cavity; The tapering section extends toward the first connecting portion and has a first limiting edge capable of abutting against the sidewall on which the second annular groove is formed.

2. The solid-liquid rocket engine thrust vectoring nozzle according to claim 1, characterized in that, The catalyst bed is provided with multiple layers of nickel-based silver mesh, which are stacked sequentially along the radial direction of the nozzle body. The multiple layers of nickel-based silver mesh can decompose the oxidant into high-temperature decomposition gas.

3. The solid-liquid rocket engine thrust vectoring nozzle according to claim 2, characterized in that, The first pipe, the second pipe, the third pipe, the catalyst bed, and the nozzle shell are integrally formed.

4. The solid-liquid rocket engine thrust vectoring nozzle according to claim 3, characterized in that, A fourth annular groove is provided at the end of the second connecting portion away from the first connecting portion, and a fifth annular groove is provided on the gradually expanding section at a position opposite to the fourth annular groove. The fourth annular groove and the fifth annular groove constitute the second liquid collection cavity.

5. The solid-liquid rocket engine thrust vectoring nozzle according to claim 4, characterized in that, The solid-liquid rocket engine thrust vectoring nozzle also includes a nozzle liner; The nozzle housing has a straight cylindrical mounting cavity, and the nozzle body is disposed in the straight cylindrical mounting cavity; The nozzle liner is disposed between the nozzle outer shell and the nozzle body.

6. The solid-liquid rocket engine thrust vectoring nozzle according to claim 3, characterized in that, The solid-liquid rocket engine thrust vectoring nozzle also includes a first sealing ring; The first connecting part also has a sixth annular groove on the side facing the combustion chamber; The first sealing ring is respectively disposed in the second annular groove and the sixth annular groove.

7. The solid-liquid rocket engine thrust vectoring nozzle according to claim 5, characterized in that, The solid-liquid rocket engine thrust vectoring nozzle also includes a second sealing ring and a third sealing ring; The second sealing ring is disposed between the second connecting portion and the gradually expanding section, and the second sealing ring is located between the nozzle liner and the fifth annular groove; The third sealing ring is disposed between the first connecting portion and the tapered section, and the third sealing ring is located between the nozzle liner and the third annular groove.

8. The solid-liquid rocket engine thrust vectoring nozzle according to claim 1, characterized in that, The cooling is achieved by providing multiple cooling channels, which are arranged at intervals along the circumferential direction of the nozzle body.

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