Solid rocket engine pintle and cooling structure

Abstract

The invention relates to a solid rocket engine pintle and a cooling structure. A cavity is formed in one end of the pintle; a high-pressure liquid conveying pipe is further arranged in the throat bolt, and one end of the high-pressure liquid conveying pipe extends into the cavity inner shell of the cavity; a plurality of liquid film holes are formed in a cavity shell of the cavity and are respectively communicated with the outer wall surfaces of the cavity and the throat bolt; a plurality of jet flow holes are formed in the cavity inner shell and communicated with the cavity and the high-pressure liquid conveying pipe respectively. According to the scheme, low-temperature liquid flows out of the liquid film hole to reach the outer wall of the cavity shell to form a liquid film when passing through the liquid film hole, the temperature of the head area of the pintle is reduced, and therefore the pintle is effectively protected.

Description

Technical Field

[0001] This application relates to a throat plug and cooling structure for a solid rocket motor, and is applicable to the technical field of solid rocket motors. Background Technology

[0002] The key to throat-plug variable thrust solid rocket motors lies in their ability to change the cross-sectional area before and after the throat plug through mechanical or electronic means, effectively regulating the gas velocity and flow rate through the nozzle, thereby altering the engine's exhaust velocity and thrust. This technology not only enables extreme acceleration and deceleration in short periods but also allows for continuous adjustments during flight, making the rocket more adaptable to various complex mission requirements. However, this places the throat plug in a constantly high-temperature exhaust environment, making ablation a critical design consideration.

[0003] Although much research has been conducted both domestically and internationally on throat-plug-type variable thrust solid rocket motors, there is a lack of research specifically addressing the throat plug ablation mechanism under real-world conditions, and reports on throat plug ablation are scarce; currently, there is a lack of necessary understanding of the throat plug ablation problem. Furthermore, existing research indicates that the use of high-temperature propellants directly causes severe ablation of the throat plug head, reducing the accuracy of engine thrust adjustment and engine performance.

[0004] There are currently no publicly available documents concerning the throat plug impact gas-cooled structure technology for thrust-guided solid rocket motors.

[0005] Therefore, existing technologies require a throat plug and cooling structure for solid rocket motors. Summary of the Invention

[0006] The purpose of this application is to design a throat plug and cooling structure for a solid rocket motor, aiming to solve the problem of ablation at the head of the throat plug in existing solid rocket motors.

[0007] This application relates to a throat plug for a solid rocket motor, one end of which forms a cavity; a high-pressure infusion tube is also provided inside the throat plug, one end of which extends into the inner shell of the cavity; the outer shell of the cavity is provided with multiple liquid film holes, which are respectively connected to the outer wall of the cavity and the throat plug; the inner shell of the cavity is provided with multiple jet holes, which are respectively connected to the cavity and the high-pressure infusion tube.

[0008] In some embodiments, the ends of the outer shell and the inner shell of the cavity are conical structures; the end of the outer shell forms the head of the laryngeal plug, the length of which is G; the minimum distance M between the tip of the laryngeal plug and the liquid film orifice along the axial direction of the laryngeal plug satisfies: 0.5G≤M≤0.8G.

[0009] In some embodiments, the plurality of liquid film holes include a first row of liquid film holes and a second row of liquid film holes, which are distributed along the circumference of the cavity shell on the inner wall of the cavity shell, respectively; the end of the cavity shell forms the head of the laryngeal plug, the length of the head is G, and the distance C between the first row of liquid film holes and the second row of liquid film holes along the axial direction of the laryngeal plug satisfies: 0.7G≤C≤1.8G.

[0010] In some embodiments, the first and second liquid membrane holes are distributed intersectingly along the axial direction of the throat plug on the inner wall of the cavity shell, the period of two adjacent liquid membrane holes is γ, and the phase difference τ between the first and second liquid membrane holes satisfies: τ = 0.5γ.

[0011] In some embodiments, the phase difference τ between the first and second drain membrane orifices ranges from 5° to 15°.

[0012] In some implementations, the length of the high-pressure infusion tube is Q, and the distance P from the lowest end of the cavity 5 to the bottom of the laryngeal plug satisfies: 0.37Q≤P≤0.5Q.

[0013] In some embodiments, the multiple jet holes include multiple rows of jet holes, each row of jet holes is distributed circumferentially on the inner wall of the inner shell of the cavity, and the multiple rows of jet holes are distributed axially on the inner wall of the inner shell of the cavity, with the distance F between two adjacent rows of jet holes ranging from 0.5 mm to 3 mm.

[0014] In some embodiments, two adjacent rows of jet holes are distributed intersectingly along the axial direction of the inner shell of the cavity on the inner wall of the cavity, the period of two adjacent jet holes is δ, and the phase difference Ω between two adjacent rows of jet holes satisfies: Ω≤0.5δ.

[0015] In some embodiments, the diameter of the liquid film pore, J, ranges from 0.25 mm to 14 mm.

[0016] In some embodiments, the orifice inclination angle α of the liquid film orifice and the orifice inclination angle β of the jet orifice are in the range of 25°-65°.

[0017] In some embodiments, the period γ of the liquid film orifice and the period δ of the jet orifice are respectively in the range of 7.5°-30°.

[0018] In some implementations, the diameter K of the jet orifice ranges from 0.1 to 7 mm.

[0019] In some implementations, the diameter D of the laryngeal plug ranges from 10mm to 60mm.

[0020] In some implementations, the head length G of the laryngeal plug ranges from 8mm to 60mm.

[0021] In some implementations, the wall thickness X of the cavity shell ranges from 1.5mm to 5mm.

[0022] In some implementations, the wall thickness Y of the inner shell of the cavity ranges from 2mm to 5mm;

[0023] In some implementations, the diameter N of the high-pressure infusion tube ranges from 5mm to 55mm.

[0024] In some embodiments, the high-pressure infusion tube and the throat plug are coaxially arranged and have the same axis; the throat plug is also provided with a propellant chamber, which is connected to the other end of the high-pressure infusion tube, and the propellant chamber contains a cryogenic liquid.

[0025] This application also provides a solid rocket motor cooling structure, including a throat plug and an engine; the throat plug is the solid rocket motor throat plug described above; the throat plug is also provided with a driving device; the engine is provided with a gas generator; the throat plug is telescopically mounted on the engine; the gas generated by the gas generator can be mixed with the gas ejected from the liquid film orifice to form a protective gas film.

[0026] The solid rocket motor throat plug and cooling structure proposed in this application have the following technical advantages:

[0027] (1) This application proposes a solid rocket motor throat plug and cooling structure. High-pressure cryogenic liquid, delivered by a high-pressure delivery pipe, enters the inner shell of the cavity and then directly impacts the outer shell through a jet hole. When this cryogenic liquid passes through the liquid film hole, it flows out and forms a liquid film on the outer wall of the cavity shell, reducing the temperature of the throat plug head area and effectively protecting the throat plug. The high-pressure impact of the cryogenic liquid from the high-pressure delivery pipe onto the inner wall of the cavity shell through the jet hole effectively increases the local heat transfer coefficient, thereby reducing the throat plug head temperature and the surrounding temperature. Furthermore, after passing through the liquid film hole, the cryogenic liquid, under the pressure of the high-temperature propellant inside the engine and the Coanda effect, will adhere to the outer surface of the throat plug, thus isolating it from external heat. When the cryogenic liquid is exposed to a high-temperature environment for an extended period, it absorbs heat and evaporates to form gas, further effectively reducing the wall temperature of the throat plug head area and preventing it from being ablated by the high-temperature combustion gases. After being ejected through the liquid film hole, the cryogenic liquid forms an effective liquid film protection locally, thereby effectively reducing the occurrence of throat plug ablation.

[0028] (2) The throat plug and cooling structure of the solid rocket engine proposed in this application have high cooling efficiency and wide cooling area. The jet holes are arranged in a periodic cross pattern to increase the impact area of ​​the cryogenic liquid on the inner wall of the cavity shell. The two rows of liquid film holes are arranged in a cross pattern to increase the liquid film coverage area and improve the cooling efficiency. This can effectively solve the cooling protection of the throat plug head, thereby better improving the thrust control accuracy of the solid rocket engine. Attached Figure Description

[0029] Figure 1 This is an overall schematic diagram of a solid rocket motor throat plug according to this application.

[0030] Figure 2 This is a cross-sectional view of a solid rocket motor throat plug according to this application.

[0031] Figure 3 This is a side view of a solid rocket motor throat plug according to this application.

[0032] Figure 4 This is a schematic diagram of a solid rocket motor cooling structure according to this application.

[0033] In the diagram: 1. Laryngeal plug; 2. Outer shell of the cavity; 3. Inner shell of the cavity; 4. Jet orifice; 5. Cavity; 6. Liquid film orifice; 7. High-pressure infusion tube; 8. Engine; 9. Gas generator; 10. Drive unit; C. Distance between the two rows of liquid film orifices along the axial direction of the laryngeal plug; D. Diameter of the laryngeal plug; F. Distance between two adjacent rows of jet orifices along the axial direction of the laryngeal plug; G. Length of the laryngeal plug head; J. Diameter of the liquid film orifice; K. Diameter of the jet orifice; L. Distance between the tip of the laryngeal plug and the inside of the cavity. Distance at the top of the shell; M, minimum distance between the top of the laryngeal plug and the liquid film orifice along the laryngeal plug axis; N, diameter of the high-pressure infusion tube; P, distance from the lowest point of cavity 5 to the bottom of the laryngeal plug; Q, length of the high-pressure infusion tube; X, wall thickness of the outer shell of the cavity; Y, wall thickness of the inner shell of the cavity; α, orifice inclination angle of the liquid film orifice; β, orifice inclination angle of the jet orifice; γ, period of the liquid film orifice; τ, phase difference between two rows of liquid film orifices; Ω, phase difference between two adjacent rows of jet orifices; δ, period of the jet orifice. Detailed Implementation

[0034] To make the objectives, technical solutions, and advantages of this application clearer, the embodiments of this application will be described in detail below with reference to the accompanying drawings. It should be noted that, unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other. Those skilled in the art will understand that this application provides a throat plug for a solid rocket motor, applicable to thrust-following solid rocket motors, to solve the problem of throat plug head erosion due to high-temperature combustion gases.

[0035] like Figure 1-3As shown, this application proposes a solid rocket motor throat plug. One end of the throat plug 1 forms a cavity 5, and a high-pressure liquid delivery pipe 7 is also provided inside the throat plug 1. One end of the high-pressure liquid delivery pipe 7 extends into the inner shell 3 of the cavity 5. Further, the outer shell 2 of the cavity 5 has multiple liquid film holes 6, each liquid film hole 6 communicating with the outer wall of the cavity 5 and the throat plug, respectively. Further, the inner shell 3 of the cavity has multiple jet holes 4, each jet hole 4 communicating with the cavity 5 and the high-pressure liquid delivery pipe 7, respectively. In the above design, the high-pressure cryogenic liquid delivered by the high-pressure liquid delivery pipe 7, after entering the inner shell 3 of the cavity, directly impacts the outer shell 2 of the cavity through the jet holes 4. When this cryogenic liquid passes through the liquid film holes 6, it flows out and reaches the outer wall of the outer shell 2 of the cavity, forming a liquid film, reducing the temperature of the throat plug head area, thereby effectively protecting the throat plug. Under normal circumstances, the high-temperature combustion gases in the engine are located in the high-temperature region at the head of the throat plug 1. The cryogenic liquid in the high-pressure inlet pipe 7, through the jet hole 4, impacts the inner wall of the outer shell 2 of the cavity, effectively increasing the local heat transfer coefficient and thus reducing the temperature of the throat plug head and the surrounding temperature. Furthermore, after passing through the liquid film hole 6, the cryogenic liquid, under the pressure of the high-temperature propellant inside the engine and the Coanda effect, flows and adheres to the outer surface of the throat plug, thus insulating it against external heat. When the cryogenic liquid is exposed to a high-temperature environment for an extended period, it absorbs heat and evaporates to form gas, further effectively reducing the wall temperature of the throat plug head area and preventing it from being ablated by the high-temperature combustion gases. After being ejected through the liquid film hole 6, the cryogenic liquid forms an effective liquid film on the outer wall of the throat plug, further reducing throat plug ablation. This structure has the advantages of high cooling efficiency and a large cooling area.

[0036] like Figure 1-3 As shown, in some embodiments, the ends of the outer shell 2 and the inner shell 3 are conical structures, and the conical structures of the outer shell 2 and the inner shell 3 are symmetrical along their axes. Further, the end of the outer shell 2 forms the head of the throat plug 1, and the length of the head is G; specifically, the minimum distance M between the top of the throat plug 1 and the liquid film hole 6 along the axial direction of the throat plug 1 satisfies: 0.5G≤M≤0.8G. The above structural dimensions are designed based on actual research, so that the high-pressure cryogenic liquid delivered by the high-pressure infusion pipe 7, after passing through the jet hole 4 and directly impacting the outer shell 2, achieves the best effect and improves cooling efficiency.

[0037] like Figure 1-3As shown, in some embodiments, the plurality of liquid film holes 6 include a first row of liquid film holes and a second row of liquid film holes, which are distributed circumferentially on the inner wall of the cavity shell 2. Specifically, the first row of liquid film holes 6 are distributed circumferentially on the inner wall of the cavity shell 2, and the second row of liquid film holes 6 are distributed circumferentially on the inner wall of the cavity shell 2. The first row of liquid film holes and the second row of liquid film holes have a fixed spacing along the axial direction of the cavity shell 2. The end of the cavity shell 2 forms the head of the laryngeal plug 1, the length of which is G, and the distance C between the first row of liquid film holes and the second row of liquid film holes along the axial direction of the laryngeal plug 1 satisfies: 0.7G≤C≤1.8G. With the above structural dimension design, the low-temperature liquid flowing out of the two rows of liquid film holes 6 reaches the outer wall of the cavity shell 2 to form a liquid film covering surface with good effect, which can reduce the temperature of the laryngeal plug head area and thus effectively protect the laryngeal plug.

[0038] like Figure 1-3 As shown, in some embodiments, the first and second rows of liquid film holes are intersected along the axial direction of the throat plug 1 on the inner wall of the cavity shell 2. The period of two adjacent liquid film holes 6 is γ, and the phase difference τ between the first and second rows of liquid film holes satisfies: τ = 0.5γ. This is done to obtain better liquid film coverage and liquid film cooling efficiency. The intersecting arrangement of the two rows of liquid film holes 5 increases the liquid film coverage area, improves cooling efficiency, and effectively solves the cooling protection of the throat plug head, thereby better improving the thrust control accuracy of the solid rocket motor. Specifically, the phase difference τ between the first and second rows of liquid film holes ranges from 5° to 15°.

[0039] like Figure 1-3 As shown, in some embodiments, the length of the high-pressure infusion tube 7 is Q, and the distance P from the lowest end of the cavity 5 to the bottom of the throat plug 1 satisfies: 0.37Q≤P≤0.5Q. This structural dimension design allows the cryogenic liquid to directly impact the cavity 5 of the outer shell 2 after passing through the jet hole 4 from the high-pressure infusion tube 7, achieving a better heat exchange effect and improving cooling efficiency.

[0040] like Figure 1-3 As shown, in some embodiments, the multiple jet holes 4 include multiple rows of jet holes. Each row of jet holes 4 is distributed circumferentially on the inner wall of the inner shell 3, and the multiple rows of jet holes are spaced apart axially on the inner wall of the inner shell 3. The distance F between two adjacent rows of jet holes ranges from 0.5 mm to 3 mm. This structural dimension design allows the cryogenic liquid inside the inner shell 3 to be ejected more efficiently from each row of jet holes 4, resulting in better impact efficiency.

[0041] like Figure 1-3As shown, in some embodiments, adjacent rows of jet holes are intersected along the axial direction of the inner shell 3 on the inner wall of the inner shell 3. The period of two adjacent jet holes 4 is δ, and the phase difference Ω between two adjacent rows of jet holes satisfies: Ω≤0.5δ. The periodic intersecting arrangement of the jet holes 4 increases the impact area of ​​the cryogenic liquid on the inner wall of the outer shell 2 of the cavity. The inclination angle of each jet hole 4 is kept the same, which can avoid the high-pressure cryogenic liquid from not being able to maintain parallel ejection when passing through the jet holes 4, and the liquid flow colliding and splashing with each other before reaching the inner wall of the outer shell 2 of the cavity, which would lead to uneven cooling and indirectly reduce the cooling effect.

[0042] like Figure 1-3 As shown, in some embodiments, the diameter J of the liquid film orifice 6 ranges from 0.25 mm to 14 mm. Further, the orifice inclination angle α of the liquid film orifice 6 and the orifice inclination angle β of the jet orifice 4 range from 25° to 65°. Further, the period γ of the liquid film orifice 6 and the period δ of the jet orifice 4 range from 7.5° to 30°. Further, the diameter K of the jet orifice 4 ranges from 0.1 to 7 mm. The above structural dimensions are designed in actual research and design processes, achieving better technical effects and improving cooling efficiency.

[0043] like Figure 1-3 As shown, in some embodiments, the diameter D of the laryngeal plug 1 ranges from 10mm to 60mm. Further, the head length G of the laryngeal plug 1 ranges from 8mm to 60mm. Further, the wall thickness X of the outer shell 2 ranges from 1.5mm to 5mm. Further, the wall thickness Y of the inner shell 3 ranges from 2mm to 5mm. Further, the diameter N of the high-pressure infusion tube 7 ranges from 5mm to 55mm. The above structural dimensions are designed in actual research and design processes, achieving better technical results and improving cooling efficiency.

[0044] like Figure 1-3 As shown, in some embodiments, the high-pressure infusion tube 7 and the throat plug 1 are coaxially arranged and have the same axis. Furthermore, the throat plug 1 is also provided with a propellant chamber, which is connected to the other end of the high-pressure infusion tube 7, and the propellant chamber contains a cryogenic liquid.

[0045] like Figure 1-4 As shown, this application also provides a solid rocket motor cooling structure, including a throat plug 1 and an engine 8; wherein, the throat plug 1 is the solid rocket motor throat plug described above. Further, the throat plug 1 is also provided with a drive device 10; the engine 8 is provided with a gas generator 9; the throat plug 1 is retractably mounted on the engine 8; the gas generated by the gas generator 9 can mix with the gas ejected from the liquid film orifice 6, thereby forming a protective gas film, which protects the head of the throat plug.

[0046] like Figure 1-4As shown, the working time of conveying cryogenic liquid in the high-pressure infusion pipe 7 of the throat plug 1 is longer than the working time of the thrust follower solid rocket motor. Moreover, the high-pressure infusion pipe 7 must first introduce cryogenic liquid before the thrust follower solid rocket motor is ignited.

[0047] like Figure 1-4 As shown, the drive unit 10 can control the movement of the throat plug 1 in the engine 8, effectively adjusting the equivalent cross-sectional area of ​​the throat in the engine 8, thereby achieving the purpose of adjusting the thrust. Cryogenic liquid enters from the drive unit 10, is transported to the inner shell 3 of the cavity through the high-pressure infusion pipe 7, and then directly impacts the outer shell 2 of the cavity through the jet hole 4. When this cryogenic liquid passes through the liquid film hole 6, it flows out and reaches the outer wall of the outer shell 2 of the cavity to form a liquid film, reducing the temperature of the throat plug head area, thereby effectively protecting the throat plug. Increasing the diameter of the liquid film orifice 6 increases the liquid film coverage area at the head of the throat plug 1; decreasing the diameter of the jet orifice 4 enhances the impact heat transfer effect on the inner wall of the cavity shell 2; decreasing the period γ of the liquid film orifice 6 increases the liquid film coverage area at the head of the throat plug 1; decreasing the period δ of the jet orifice 4 increases the impact area of ​​the cryogenic liquid on the cavity shell 2, thereby improving heat transfer efficiency; while ensuring strength, decreasing the wall thickness X of the cavity shell 2 can improve heat transfer efficiency; increasing the wall thickness Y of the cavity inner shell 3 increases the strength of the high-pressure infusion pipe 7, improves the stability of the throat plug, and at the same time, improves the pressure-bearing capacity of the high-pressure infusion pipe 7; decreasing the distance L between the top of the throat plug 1 and the cavity inner shell 3 allows the cryogenic liquid to fully contact the head area of ​​the cavity shell 2, improving the cooling effect.

[0048] The solid rocket motor throat plug and cooling structure proposed in this application have the following technical advantages:

[0049] (1) This application proposes a solid rocket motor throat plug and cooling structure. High-pressure cryogenic liquid, delivered by a high-pressure delivery pipe, enters the inner shell of the cavity and then directly impacts the outer shell through a jet hole. When this cryogenic liquid passes through the liquid film hole, it flows out and forms a liquid film on the outer wall of the cavity shell, reducing the temperature of the throat plug head area and effectively protecting the throat plug. The high-pressure impact of the cryogenic liquid from the high-pressure delivery pipe onto the inner wall of the cavity shell through the jet hole effectively increases the local heat transfer coefficient, thereby reducing the throat plug head temperature and the surrounding temperature. Furthermore, after passing through the liquid film hole, the cryogenic liquid, under the pressure of the high-temperature propellant inside the engine and the Coanda effect, will adhere to the outer surface of the throat plug, thus isolating it from external heat. When the cryogenic liquid is exposed to a high-temperature environment for an extended period, it absorbs heat and evaporates to form gas, further effectively reducing the wall temperature of the throat plug head area and preventing it from being ablated by the high-temperature combustion gases. After being ejected through the liquid film hole, the cryogenic liquid forms an effective liquid film protection locally, thereby effectively reducing the occurrence of throat plug ablation.

[0050] (2) The throat plug and cooling structure of the solid rocket engine proposed in this application have high cooling efficiency and wide cooling area. The jet holes are arranged in a periodic cross pattern to increase the impact area of ​​the cryogenic liquid on the inner wall of the cavity shell. The two rows of liquid film holes are arranged in a cross pattern to increase the liquid film coverage area and improve the cooling efficiency. This can effectively solve the cooling protection of the throat plug head, thereby better improving the thrust control accuracy of the solid rocket engine.

[0051] Although the embodiments disclosed in this application are as described above, the content is merely for the purpose of facilitating understanding of this application and is not intended to limit this application. Any person skilled in the art to which this application pertains may make any modifications and changes in the form and details of the implementation without departing from the spirit and scope disclosed in this application; however, the scope of patent protection of this application shall still be determined by the scope defined in the appended claims.

Claims

1. A throat plug for a solid rocket motor, characterized in that, One end of the laryngeal plug (1) forms a cavity (5); a high-pressure infusion tube (7) is also provided inside the laryngeal plug (1), and one end of the high-pressure infusion tube (7) extends into the inner shell (3) of the cavity (5); a plurality of liquid film holes (6) are provided on the outer shell (2) of the cavity (5), and the liquid film holes (6) are respectively connected to the outer wall surface of the cavity (5) and the laryngeal plug; a plurality of jet holes (4) are provided on the inner shell (3), and the jet holes (4) are respectively connected to the cavity (5) and the high-pressure infusion tube (7).

2. The solid rocket engine closure as recited in claim 1, wherein, The ends of the outer shell (2) and the inner shell (3) of the cavity are conical structures; the end of the outer shell (2) forms the head of the laryngeal plug (1), and the length of the head is G; the minimum distance M between the top of the laryngeal plug (1) and the liquid membrane hole (6) along the axial direction of the laryngeal plug (1) satisfies: 0.5G≤M≤0.8G.

3. The solid rocket engine closure as recited in claim 1, wherein, The plurality of liquid film holes (6) include a first liquid film hole and a second liquid film hole, which are distributed circumferentially on the inner wall of the cavity shell (2); the end of the cavity shell (2) forms the head of the laryngeal plug (1), the length of the head is G, and the distance C between the first liquid film hole and the second liquid film hole along the axial direction of the laryngeal plug (1) satisfies: 0.7G≤C≤1.8G; and / or, The first and second drainage membrane holes are distributed axially along the throat plug (1) on the inner wall of the cavity shell (2). The period of two adjacent drainage membrane holes (6) is γ. The phase difference τ between the first and second drainage membrane holes satisfies: τ = 0.5γ.

4. The solid rocket motor throat plug according to claim 3, wherein the phase difference τ between the first drainage film hole and the second drainage film hole ranges from 5° to 15°.

5. The solid rocket engine closure as recited in claim 1, wherein, The length of the high-pressure infusion tube (7) is Q, and the distance P from the lowest end of the cavity (5) to the bottom of the laryngeal plug (1) satisfies: 0.37Q≤P≤0.5Q.

6. The solid rocket engine closure as recited in claim 1, wherein, The plurality of jet holes (4) includes multiple rows of jet holes, each row of jet holes (4) being distributed circumferentially on the inner wall of the inner shell (3) of the cavity, and the multiple rows of jet holes being spaced apart axially on the inner wall of the inner shell (3), with the distance F between two adjacent rows of jet holes ranging from 0.5 mm to 3 mm; and / or, Two adjacent rows of jet holes are intersected along the axial direction of the inner shell (3) of the cavity and are distributed on the inner wall of the inner shell (3). The period of two adjacent jet holes (4) is δ, and the phase difference Ω between two adjacent rows of jet holes satisfies: Ω≤0.5δ.

7. The solid rocket motor throat plug according to claim 1, characterized in that, The diameter J of the liquid film orifice (6) ranges from 0.25 mm to 14 mm; and / or, the orifice inclination angle α of the liquid film orifice (6) and the orifice inclination angle β of the jet orifice (4) range from 25° to 65°; and / or, the period γ of the liquid film orifice (6) and the period δ of the jet orifice (4) range from 7.5° to 30°; and / or, the diameter K of the jet orifice (4) ranges from 0.1 to 7 mm.

8. The solid rocket motor throat plug according to claim 1, characterized in that, The diameter D of the laryngeal plug (1) is in the range of 10mm-60mm; and / or, the head length G of the laryngeal plug (1) is in the range of 8mm-60mm; and / or, the wall thickness X of the outer shell (2) of the cavity is in the range of 1.5mm-5mm; and / or, the wall thickness Y of the inner shell (3) of the cavity is in the range of 2mm-5mm; and / or, the diameter N of the high-pressure infusion tube (7) is in the range of 5mm-55mm.

9. The solid rocket motor throat plug according to claim 1, characterized in that, The high-pressure infusion tube (7) is coaxially arranged with the throat plug (1) and the axes are the same; the throat plug (1) is also provided with a propellant chamber, which is connected to the other end of the high-pressure infusion tube (7), and the propellant chamber is provided with a cryogenic liquid.

10. A solid rocket motor cooling structure, comprising a throat plug (1) and an engine (8); characterized in that, The throat plug (1) is the throat plug of a solid rocket engine as described in any one of claims 1 to 9; the throat plug (1) is also provided with a driving device (10); the engine (8) is provided with a gas generator (9); the throat plug (1) is telescopically mounted on the engine (8); the gas generated by the gas generator (9) can be mixed with the gas ejected from the liquid film hole (6) to form a protective gas film.

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