A detachable support plate rocket for RBCC engine

Abstract

The present invention discloses a detachable support plate rocket for an RBCC engine, comprising: a rocket body, a support plate body, and a cover plate; the support plate body comprises a fuel support plate located on the front side, the fuel support plate being vertically penetrated from top to bottom with an accommodating hole, the accommodating hole being used for a fuel pipe and an oxygen pipe to pass through from top to bottom; a first cavity is provided in the inner cavity of the rocket body, the first cavity being used for receiving fuel transported from top to bottom by the fuel pipe, a second cavity is provided in the inner cavity of the rocket body, the second cavity being used for receiving oxygen transported from top to bottom by the oxygen pipe, a third cavity is provided in the inner cavity of the rocket body, the third cavity being used for mixing oxygen and fuel, burning under the action of an igniter, and ejecting from the rear side of the rocket body into the inner cavity of an engine combustion chamber; the present invention reduces the engine flow channel space occupied by the support plate rocket, reduces the duty cycle of the support plate rocket, reduces the obstruction effect on the airflow, increases the amount of air ejected, and achieves thrust gain.

Description

Technical Field

[0001] The present invention belongs to the technical field of rocket-based combined cycle engines, and in particular relates to a detachable support plate rocket for an RBCC engine. Background Art

[0002] Rocket-Based Combined Cycle (RBCC) engines boast a wide operating range, high specific impulse, high thrust, and reusability. They hold broad application prospects in space shuttles, missile weapons, and hypersonic vehicles, and represent a key development direction for future aerospace propulsion systems. In RBCC engines, the struts play a crucial role. In ejection mode, they primarily serve to eject incoming atmospheric air, inject fuel into the struts, generate thrust, and ignite and stabilize the flame. In subsonic and scramjet modes, they primarily provide ignition and flame stabilization. In pure rocket mode, they primarily provide the required thrust.

[0003] Currently, commonly used launch rockets include gas generator-based launch rockets and bipropellant-based embedded strut rockets. Gas generator-based launch rockets channel gas from a gas generator outside the engine into the launch rocket. The gas then expands and accelerates within the rocket, drawing in the incoming air from the front of the engine. This then triggers secondary combustion within the engine flow path. However, this increases the wetted area and complicates the engine's thermal protection. Embedded strut rockets, on the other hand, can generate gas directly within the strut, but this requires the installation of a complete rocket structure within the engine flow path. Oxidant and fuel supply lines, as well as spark plugs, take up significant space within the engine flow path, impacting overall engine performance. Furthermore, the structure of embedded strut rockets is complex, making manufacturing, processing, and installation more challenging. Summary of the Invention

[0004] The purpose of the present invention is to provide a detachable support plate rocket for an RBCC engine, so as to solve the problem that the support plate rocket occupies a large space in the engine flow channel and is difficult to manufacture and install.

[0005] The present invention adopts the following technical solution: a detachable support plate rocket for an RBCC engine, comprising: a rocket body located in the inner cavity of the engine combustion chamber, a support plate body located in the inner cavity of the engine combustion chamber and extending perpendicularly to the rocket body, and a cover plate for sealing the outer wall of the inner cavity of the combustion chamber;

[0006] The support plate body includes a fuel support plate located at the front side, the fuel support plate is arranged vertically, and its lower end is fixedly connected to the horizontally arranged rocket body. The fuel support plate is vertically penetrated from top to bottom with a receiving hole, and the receiving hole is used for the fuel pipe and the oxygen pipe to pass through from top to bottom;

[0007] A first through hole is opened on the upper outer wall of the rocket body from top to bottom, and a first cavity is opened in the inner cavity of the rocket body. The first through hole is used for the lower end of the fuel pipe to pass through and extend into the first cavity. The first cavity is used to receive the fuel transported from top to bottom by the fuel pipe.

[0008] A second through hole is opened on the upper outer wall of the rocket body from top to bottom, and a second cavity is opened in the inner cavity of the rocket body. The second through hole is used for the lower end of the oxygen pipe to pass through and extend into the second cavity. The second cavity is used to receive the oxygen transported from top to bottom by the oxygen pipe.

[0009] A third through hole is provided on the upper outer wall of the rocket body from top to bottom, and a third cavity is provided in the inner cavity of the rocket body. The third through hole is used for the lower end of the igniter to pass through and extend into the third cavity. The third cavity and the second cavity are connected through a fourth through hole, and the third cavity and the first cavity are connected through a fifth through hole. The third cavity is used for mixing gas oxygen and fuel, which are then burned under the action of the igniter and ejected from the rear side of the rocket body into the inner cavity of the engine combustion chamber.

[0010] Furthermore, the support plate body also includes a fixed support plate located on the rear side, which is vertically arranged and has a lower end fixedly connected to the horizontally arranged rocket body. The fixed support plate is used to cooperate with the fuel support plate to fix the rocket body.

[0011] Furthermore, a sixth through hole is opened in the center of the cover plate;

[0012] It also includes: a accommodating shell, which is located between the fuel support plate and the fixed support plate and extends downward through the fifth through hole. The accommodating shell is vertically arranged and is a cylindrical structure that is open at the top and bottom. The accommodating shell is coaxially arranged with the third through hole of the rocket body. The upper end of the accommodating shell is fixedly connected to the cover plate, and the lower end thereof extends downward and is fixedly connected to the upper outer wall of the rocket body. The inner cavity of the accommodating shell is used to accommodate the igniter. The accommodating shell is used to protect the igniter from damage caused by airflow erosion. The igniter is used to wind the ignition wire in sequence from bottom to top along its direction, and extend the ignition wire upward to the outside of the accommodating shell.

[0013] Furthermore, the third cavity is opened along the front-to-back direction, and the cross-sectional area of ​​the rear half of the third cavity gradually decreases and then gradually increases from front to back to form a nozzle, which is used to spray high-temperature gas into the inner cavity of the combustion chamber.

[0014] Furthermore, the first cavity is horizontal and cylindrical, the second cavity is annular, and the first cavity, the second cavity, and the third cavity are arranged in sequence from front to back, and their axes coincide.

[0015] Furthermore, the fifth through hole passes through the rocket body in the center of the second cavity, thereby connecting the first cavity and the third cavity.

[0016] Furthermore, a plurality of fifth through holes and a plurality of fourth through holes are provided, the plurality of fifth through holes are clustered together, and the plurality of fourth through holes are discrete and arranged to surround the plurality of fifth through holes.

[0017] Furthermore, the cross-sectional area of ​​the front half of the third cavity gradually decreases from the back to the front to form a cone-shaped area, and the cone-shaped area is used to accommodate the oxygen and fuel and allow the two to be fully mixed.

[0018] Furthermore, the upper end of the fuel support plate is also connected to the external fuel system through a connecting hole, and injection holes are provided on both side walls of the fuel support plate extending into the inner cavity of the combustion chamber, and the injection holes are used to inject fuel into the inner cavity of the combustion chamber.

[0019] Furthermore, the processing method thereof consists of the following steps:

[0020] Place the rocket body horizontally, and weld the lower ends of the fuel support plate and the fixed support plate to the upper outer wall of the rocket body, so that the direction of the fuel support plate and the fixed support plate is perpendicular to the direction of the rocket body.

[0021] Place the cover plate horizontally and weld the upper ends of the fuel support plate and the fixed support plate to the lower side of the cover plate.

[0022] Insert the welded fuel support plate and fixed support plate into the combustion chamber through the mounting holes on the outer wall of the engine combustion chamber, and fix the cover plate to the outer wall of the engine combustion chamber with screws around the edge of the cover plate.

[0023] Pass the ignition wire from top to bottom through the vertical housing and wrap it around the upper half of the igniter on the lower side of the housing.

[0024] The igniter with the ignition wire wrapped around it is passed vertically through the sixth through hole of the cover plate so that the lower end of the igniter extends into the third through hole of the rocket body and is threadedly connected to the rocket body.

[0025] Screw the compression bolt into the upper half of the igniter and tighten the ignition wire.

[0026] The housing is vertically extended into the sixth through hole of the cover plate so that the lower end of the housing abuts against the upper outer wall of the rocket body and is located outside the igniter.

[0027] The accommodating shell can be fixed to the cover plate by screws around the upper opening of the accommodating shell.

[0028] The beneficial effects of the present invention are:

[0029] 1. The fuel support plate and fixed support plate of the present invention are both arranged vertically, that is, perpendicular to the direction of the rocket body. The direction of the fuel support plate and the fixed support plate are both perpendicular to the axis of the combustion chamber. Moreover, the length of the fuel support plate and the fixed support plate extending into the inner cavity of the combustion chamber is also very short. Therefore, the space occupied by the support plate of the support plate rocket in the engine flow path is greatly reduced, thereby reducing the occupied engine flow path space and the duty cycle of the support plate rocket. When the RBCC operates in the ejection mode, it can reduce the obstruction of the airflow to a certain extent, increase the amount of ejected air, provide more oxidant to support better secondary combustion, and achieve thrust gain.

[0030] 2. The present invention arranges the first cavity, the second cavity, and the third cavity coaxially so that the fuel ejected from the first cavity is surrounded by the oxygen from the second cavity when entering the third cavity, thereby increasing the mixing effect and improving the combustion efficiency;

[0031] 3. The short length of the rocket body of the present invention also reduces the occupancy rate of the rocket body on the engine flow path volume. When the RBCC operates in the ejection mode, it can also reduce the obstruction effect on the airflow to a certain extent, increase the amount of ejected air, and achieve thrust gain;

[0032] 4. The igniter of the present invention is located in the housing and fixed to the rocket body. The igniter and the rocket body are highly integrated. Therefore, the housing can increase the stability of the fuel support plate and the fixed support plate and the rocket body while protecting the igniter, allowing the igniter to ignite the fuel in the rocket body.

[0033] 5. In the present invention, the cover plate, fuel support plate and fixed support plate are all welded, which has good stability, reduces the difficulty of processing and installation, reduces the complexity of the overall system, and increases the reliability of the support plate rocket. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 It is a structural schematic diagram of the present invention;

[0035] Figure 2 is a cross-sectional view of the present invention;

[0036] Figure 3 It is an overall schematic diagram of the present invention;

[0037] Figure 4 Detailed schematic diagram of the present invention.

[0038] in:

[0039] 1. Rocket body;

[0040] 2. Support plate; 20. Fuel injection hole; 21. Fuel support plate; 22. Fuel pipe; 23. Oxygen pipe; 24. Fifth through hole; 25. First cavity; 26. Fourth through hole; 27. Second cavity; 28. Connecting hole; 29. ​​Third cavity;

[0041] 3. Cover plate; 31. Sixth through hole;

[0042] 4. Containing shell; 5. Ignition; 6. Fixed support plate; 7. Engine combustion chamber. DETAILED DESCRIPTION

[0043] The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.

[0044] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more. The "direction" in the present invention is based on the direction of the present invention. Figure 1 Description of the direction of the state.

[0045] The present invention discloses a detachable support plate rocket for an RBCC engine, such as Figure 1-4 As shown, it includes: a rocket body 1 located in the inner cavity of the engine combustion chamber, a support plate body 2 located in the inner cavity of the engine combustion chamber and perpendicular to the rocket body 1, and a cover plate 3 for closing the outer wall of the inner cavity of the combustion chamber.

[0046] The support plate body 2 includes a fuel support plate 21 located on the front side. The fuel support plate 21 is vertically arranged, and the lower end of the fuel support plate 21 is fixedly connected to the horizontally arranged rocket body 1. The fuel support plate 21 is vertically penetrated from top to bottom with a receiving hole, which is used for the fuel pipe 22 and the oxygen pipe 23 to pass through from top to bottom.

[0047] A first through hole is opened on the upper outer wall of the rocket body 1 from top to bottom, and a first cavity 25 is opened in the inner cavity of the rocket body 1. The first through hole is used for the lower end of the fuel pipe 22 to pass through and extend into the first cavity 25. The first cavity 25 is used to receive the fuel transported from top to bottom by the fuel pipe 22.

[0048] A second through hole is opened on the upper outer wall of the rocket body 1 from top to bottom, and a second cavity 27 is opened in the inner cavity of the rocket body 1. The second through hole is used for the lower end of the oxygen pipe 23 to pass through and extend into the second cavity 27. The second cavity 27 is used to receive the oxygen transported from top to bottom by the oxygen pipe 23.

[0049] A third through hole is provided on the upper outer wall of the rocket body 1 from top to bottom, and a third cavity 29 is provided in the inner cavity of the rocket body 1. The third through hole is used for the lower end of the igniter 5 to pass through and extend into the third cavity 29. The third cavity 29 and the second cavity 27 are connected through the fourth through hole 26, and the third cavity 29 and the first cavity 25 are connected through the fifth through hole 24. The third cavity 29 is used for mixing gas oxygen and fuel and then burning under the action of the igniter 5 and ejecting from the rear side of the rocket body 1 into the inner cavity of the engine combustion chamber.

[0050] The support plate body 2 also includes a fixed support plate 6 located on the rear side. The fixed support plate 6 is vertically arranged, and the lower end of the fixed support plate 6 is fixedly connected to the horizontally arranged rocket body 1. The fixed support plate 6 is used to cooperate with the fuel support plate 21 to fix the rocket body 1.

[0051] A sixth through hole 31 is provided in the center of the cover plate 3; the present invention also includes: a accommodating shell 4, which is located between the fuel support plate 21 and the fixed support plate 6, and extends downward through the fifth through hole 24. The accommodating shell 4 is vertically arranged and is a cylindrical structure with openings at the top and bottom. The accommodating shell 4 is coaxially arranged with the third through hole of the rocket body 1. The upper end of the accommodating shell 4 is fixedly connected to the cover plate 3, and the lower end of the accommodating shell 4 extends downward and is fixedly connected to the upper outer wall of the rocket body 1. The inner cavity of the accommodating shell 4 is used to accommodate the igniter 5. The accommodating shell 4 is used to protect the igniter 5 from damage by airflow erosion. The igniter 5 is used to wind the ignition wire in sequence from bottom to top along its direction, and extend the ignition wire upward to the outside of the accommodating shell 4.

[0052] Since the area of ​​the designed engine combustion chamber flow channel limits the volume of the support plate body 2 and the rocket body 1, and the first cavity 25, the second cavity 27 and the third cavity 29 of the rocket body 1 must all be installed inside the rocket body 1, this results in insufficient installation space for the igniter 5 in the rocket body 1, and the igniter 5 cannot be installed on the head of the rocket body 1, but can only be installed on the body of the rocket body 1; and since the volume of the rocket body 1 is limited by the inner cavity of the engine combustion chamber, the rocket body 1 is limited by the length of the combustion chamber after meeting the first cavity 25, the second cavity 27 and the third cavity 29. Therefore, the inner cavity of the combustion chamber can no longer provide space for the installation and arrangement of the igniter 5 and the corresponding ignition wire, that is, the ignition wire must be installed on the outer wall of the rocket body 1.

[0053] The third cavity 29 is opened along the front-to-back direction. The cross-sectional area of ​​the rear half of the third cavity 29 gradually decreases and then increases from the front to the back to form a nozzle, which is used to inject high-temperature gas into the inner cavity of the combustion chamber.

[0054] The first cavity 25 is horizontal and cylindrical, while the second cavity 27 is annular. The first cavity 25, the second cavity 27, and the third cavity 29 are arranged in sequence from front to back, with their axes coinciding. The fifth through hole 24 passes through the rocket body 1 in the center of the second cavity 27, connecting the first cavity 25 and the third cavity 29.

[0055] Multiple fifth through holes 24 and multiple fourth through holes 26 are provided. The multiple fifth through holes 24 are clustered together, and the multiple fourth through holes 26 are discrete and arranged to surround the multiple fifth through holes 24. The cross-sectional area of ​​the front half of the third cavity 29 gradually decreases from rear to front to form a tapered area. The tapered area is used to accommodate the oxygen and fuel and ensure thorough mixing of the two.

[0056] The upper end of the fuel support plate 21 is also connected to the external fuel system through the connecting hole 28. The fuel support plate 21 extends into the combustion chamber and is provided with injection holes 20 on both side walls. The injection holes 20 are used to inject fuel into the combustion chamber.

[0057] The processing method of the present invention consists of the following steps:

[0058] Place the rocket body 1 horizontally, and weld the lower ends of the fuel support plate 21 and the fixed support plate 6 to the upper outer wall of the rocket body 1, so that the direction of the fuel support plate 21 and the fixed support plate 6 is perpendicular to the direction of the rocket body 1.

[0059] Place the cover plate 3 horizontally, and weld the upper ends of the fuel support plate 21 and the fixed support plate 6 to the lower side of the cover plate 3.

[0060] Insert the welded fuel support plate 21 and fixed support plate 6 into the combustion chamber through the mounting holes on the outer wall of the engine combustion chamber, and fix the cover plate 3 to the outer wall of the engine combustion chamber with screws around the edge of the cover plate 3.

[0061] Pass the ignition wire from top to bottom through the vertical housing 4 and wind it around the upper half of the igniter 5 located on the lower side of the housing 4.

[0062] The igniter 5 wound with the ignition wire is passed vertically through the sixth through hole 31 of the cover plate 3 so that the lower end of the igniter 5 extends into the third through hole of the rocket body 1 and is threadedly connected to the rocket body 1.

[0063] By screwing the compression bolt into the upper half of the igniter 5 and tightening the ignition wire,

[0064] The housing 4 is vertically extended into the sixth through hole 31 of the cover plate 3 so that the lower end of the housing 4 abuts against the upper outer wall of the rocket body 1 and is located outside the igniter 5.

[0065] The accommodating shell 4 can be fixed to the cover plate 3 by screws around the upper opening of the accommodating shell 4 .

[0066] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A detachable support plate rocket for an RBCC engine, characterized in that: include: A rocket body (1) located in the inner cavity of the engine combustion chamber, a support plate body (2) located in the inner cavity of the engine combustion chamber and extending perpendicularly to the rocket body (1), and a cover plate (3) for sealing the outer wall of the inner cavity of the combustion chamber; The support plate body (2) includes a fuel support plate (21) located at the front side, the fuel support plate (21) is vertically arranged, and the lower end thereof is fixedly connected to the horizontally arranged rocket body (1), and the fuel support plate (21) is vertically penetrated from top to bottom to form a receiving hole, and the receiving hole is used for the fuel pipe (22) and the oxygen pipe (23) to pass through from top to bottom; A first through hole is provided on the upper outer wall of the rocket body (1) from top to bottom, and a first cavity (25) is provided in the inner cavity of the rocket body (1). The first through hole is used for the lower end of the fuel pipe (22) to pass through and extend into the first cavity (25). The first cavity (25) is used to receive fuel transported from the fuel pipe (22) from top to bottom. A second through hole is provided on the upper outer wall of the rocket body (1) from top to bottom, and a second cavity (27) is provided in the inner cavity of the rocket body (1). The second through hole is used for the lower end of the oxygen pipe (23) to pass through and extend into the second cavity (27). The second cavity (27) is used to receive the oxygen transported from the oxygen pipe (23) from top to bottom. A third through hole is provided on the upper outer wall of the rocket body (1) from top to bottom, and a third cavity (29) is provided in the inner cavity of the rocket body (1). The third through hole is used for the lower end of the igniter (5) to pass through and extend into the third cavity (29). The third cavity (29) and the second cavity (27) are communicated through the fourth through hole (26), and the third cavity (29) and the first cavity (25) are communicated through the fifth through hole (24). The third cavity (29) is used for mixing gas oxygen and fuel, burning under the action of the igniter (5), and ejecting from the rear side of the rocket body (1) into the inner cavity of the engine combustion chamber; The support plate body (2) further includes a fixed support plate (6) located at the rear side, the fixed support plate (6) being arranged vertically, and having a lower end fixedly connected to the horizontally arranged rocket body (1), the fixed support plate (6) being used to cooperate with the fuel support plate (21) to fix the rocket body (1); A sixth through hole (31) is provided in the center of the cover plate (3); It also includes: a accommodating shell (4), the accommodating shell (4) is located between the fuel support plate (21) and the fixed support plate (6), and extends downward through the fifth through hole (24), the accommodating shell (4) is vertically arranged, and is a cylindrical structure with openings at the top and bottom, the accommodating shell (4) is coaxially arranged with the third through hole of the rocket body (1), the upper end of the accommodating shell (4) is fixedly connected to the cover plate (3), and the lower end thereof extends downward and is fixedly connected to the upper outer wall of the rocket body (1), the inner cavity of the accommodating shell (4) is used to accommodate the igniter (5), the accommodating shell (4) is used to protect the igniter (5) from being damaged by airflow scouring, and the igniter (5) is used to wind the ignition wire in sequence from bottom to top along its direction, and extend the ignition wire upward to the outside of the accommodating shell (4).

2. A detachable support plate rocket for an RBCC engine according to claim 1, characterized in that: The third cavity (29) is opened in the front-to-back direction, and the cross-sectional area of ​​the rear half of the third cavity (29) gradually decreases from the front to the back and then gradually increases to form a nozzle, which is used to spray high-temperature gas into the inner cavity of the combustion chamber.

3. A detachable support plate rocket for an RBCC engine according to claim 2, characterized in that: The first cavity (25) is horizontal and columnar, the second cavity (27) is annular, and the first cavity (25), the second cavity (27), and the third cavity (29) are arranged in sequence from front to back, and their axes coincide.

4. A detachable support plate rocket for an RBCC engine according to claim 3, characterized in that: After the fifth through hole (24) passes through the rocket body (1) at the center of the second cavity (27), the first cavity (25) and the third cavity (29) are connected.

5. A detachable support plate rocket for an RBCC engine according to claim 4, characterized in that: The fifth through hole (24) and the fourth through hole (26) are both provided in plurality, the plurality of the fifth through holes (24) are clustered together, and the plurality of the fourth through holes (26) are discrete from each other and are provided to surround the plurality of the fifth through holes (24).

6. A detachable support plate rocket for an RBCC engine according to claim 5, characterized in that: The cross-sectional area of ​​the front half of the third cavity (29) gradually decreases from the back to the front to form a conical area, and the conical area is used to accommodate gas oxygen and fuel and allow the two to be fully mixed.

7. A detachable support plate rocket for an RBCC engine according to claim 1, characterized in that: The upper end of the fuel support plate (21) is also connected to the external fuel system through the connecting hole (28). The fuel support plate (21) is provided with fuel injection holes (20) on both side walls extending into the inner cavity of the combustion chamber. The fuel injection holes (20) are used to inject fuel into the inner cavity of the combustion chamber.

8. A detachable support plate rocket for an RBCC engine according to any one of claims 2 to 7, characterized in that: The processing method consists of the following steps: The rocket body (1) is placed horizontally, and the lower ends of the fuel support plate (21) and the fixed support plate (6) are welded to the upper outer wall of the rocket body (1), so that the direction of the fuel support plate (21) and the fixed support plate (6) is perpendicular to the direction of the rocket body (1). Place the cover plate (3) horizontally, and weld the upper ends of the fuel support plate (21) and the fixed support plate (6) to the lower side of the cover plate (3). The welded fuel support plate (21) and the fixed support plate (6) are extended into the inner cavity of the combustion chamber through the mounting hole of the outer wall of the engine combustion chamber, and the cover plate (3) is fixed to the outer wall of the engine combustion chamber by screws around the edge of the cover plate (3). The ignition wire is passed through the vertically arranged housing (4) from top to bottom and is wound around the upper half of the igniter (5) located on the lower side of the housing (4). The igniter (5) wound with the ignition wire is passed vertically through the sixth through hole (31) of the cover plate (3) so that the lower end of the igniter (5) extends into the third through hole of the rocket body (1) and is threadedly connected to the rocket body (1). Screw the compression bolt into the upper half of the igniter (5) and tighten the ignition wire. The accommodating shell (4) is vertically extended into the sixth through hole (31) of the cover plate (3), so that the lower end of the accommodating shell (4) abuts against the upper outer wall of the rocket body (1) and is located outside the igniter (5). The accommodating shell (4) is fixed to the cover plate (3) by screws around the upper opening of the accommodating shell (4).

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