Water-air cross-medium rocket engine and rocket

Abstract

The invention relates to the technical field of rockets, in particular to a water-air cross-medium rocket engine and a rocket. The propelling main body comprises first fixed connecting plates, a fixed mounting disc, a first protective sleeve, a second protective sleeve, a liquid rocket engine, an auxiliary propelling system, a conveying spraying pipe, a first stop valve, a flow guide disc and a first spraying adjusting main body, and the first fixed connecting plates are fixedly connected to the two sides of the fixed mounting disc; the first protective sleeve is fixedly connected to the bottom end of the fixed mounting disc, and the second protective sleeve is fixedly connected to the bottom end of the first protective sleeve through a bolt. The rocket can stably operate in water and air, the mode of operation in the water and the mode of operation in the air can be freely switched, water-air cross-medium stable operation is achieved, the engine can automatically switch the operation modes according to the difference of the two operation modes, and the water-air cross-medium water-air cross-medium water-air cross-medium water-air cross-medium water-air cross-medium water-air cross-medium water-air cross-medium stable operation is achieved. And the rocket can be conveniently used and operated.

Description

Technical Field

[0001] The present invention relates to the technical field of rockets, and specifically to an underwater-air cross-medium rocket engine and a rocket. Background Art

[0002] A rocket mainly consists of three major parts: a structure system (rocket body structure), a power device system (propulsion system), and a control system. The operating principle of a rocket is based on Newton's third law, that is, the action force and the reaction force are equal in magnitude and opposite in direction. When the rocket engine ignites, the propellant (liquid or solid fuel plus oxidizer) burns in the combustion chamber of the engine, generating a large amount of high-pressure gas. These high-pressure gases are ejected from the engine nozzle at high speed, generating a reaction force on the combustion chamber (i.e., the rocket), causing the rocket to move forward in the opposite direction of the gas ejection.

[0003] During the flight of a rocket, as the propellant is consumed, the mass of the rocket continuously decreases, while the speed continuously increases. To increase the final velocity of the rocket, methods such as using high-energy propellants, increasing the number of rocket stages, or optimizing the rocket structure can be adopted. Among them, a multi-stage rocket is a commonly used method to improve rocket performance. It uses a combination of multi-stage rockets and gradually discards the used stages, thereby reducing the mass of the rocket and increasing the final velocity of the rocket.

[0004] When an underwater-air cross-medium rocket operates, it needs to switch the working environment in different media. Traditional rockets usually adopt independent power systems, and a single operating engine cannot operate normally in different media, which limits the flexibility and application range of the rocket in complex environments. With the continuous development of military and civilian needs, the demand for a vehicle that can simultaneously adapt to underwater and air environments and achieve cross-medium navigation is becoming increasingly urgent. Moreover, the existing rockets not only cannot operate stably in different media, but also are inconvenient to stand during the recovery process, making it easy to damage components such as the engine when recovering and falling. Therefore, an engine and a rocket are needed to improve the above problems. Summary of the Invention

[0005] In view of the problems in the prior art, the present invention provides an underwater-air cross-medium rocket engine and a rocket.

[0006] The technical solution adopted by the present invention to solve its technical problems is as follows: A water-air cross-medium rocket engine and a rocket, including a propulsion main body, the propulsion main body includes a first fixed connection plate, a fixed mounting plate, a first protective sleeve, a second protective sleeve, a liquid rocket engine, an auxiliary propulsion system, a delivery nozzle, a first stop valve, a deflector plate and a first injection adjustment main body. The first fixed connection plate is fixedly connected to both sides of the fixed mounting plate. The first protective sleeve is fixedly connected to the bottom end of the fixed mounting plate. The second protective sleeve is fixedly connected to the bottom end of the first protective sleeve by bolts. The liquid rocket engine is fixedly installed inside the first protective sleeve by bolts. The auxiliary propulsion system is arranged inside the second protective sleeve, and the liquid rocket engine is arranged above the auxiliary propulsion system. The delivery nozzle is fixedly connected to the bottom end of the liquid rocket engine. The first stop valve is fixedly connected to the bottom end of the delivery nozzle. The deflector plate is fixedly connected to the bottom end of the first stop valve. The first injection adjustment main body is uniformly and fixedly arranged at the bottom end of the deflector plate.

[0007] Preferably, the auxiliary propulsion system includes a second fixed connection plate, a storage tank, a delivery pipe, a reaction chamber, a second injection adjustment main body and a one-way pneumatic combination valve. The second fixed connection plate is uniformly and fixedly installed on the upper edge of the storage tank. The reaction chamber is arranged directly below the storage tank. The delivery pipes are uniformly and fixedly connected between the storage tank and the reaction chamber. The one-way pneumatic combination valve is fixedly installed on the delivery pipe. The second injection adjustment main body is uniformly arranged on the bottom edge of the reaction chamber.

[0008] Preferably, a first air pump is uniformly and fixedly arranged on the upper end of the storage tank. The first air pump is communicated with the inside of the storage tank. The second injection adjustment main body has the same structure as the first injection adjustment main body.

[0009] Preferably, fixed brackets are uniformly distributed on the outside of the reaction chamber. A second air pump is fixedly installed on the upper end of the fixed bracket. A water storage tank is fixedly installed inside the fixed bracket. Liquid level sensors are uniformly and fixedly installed on the water storage tank. The bottom end of the second air pump is communicated with the upper inside of the water storage tank. A sealing cover is threadedly arranged on the outer side of the upper end of the water storage tank.

[0010] Preferably, both the first injection adjustment body and the second injection adjustment body include a fixed plate, an adjustment nozzle, a second motor, an adjustment shaft, and a conveying connection metal bellows. The fixed plates are symmetrically arranged. The adjustment shaft is rotationally clamped between the fixed plates. The adjustment nozzle is fixedly installed in the middle of the adjustment shaft. The conveying connection metal bellows is fixedly connected to the middle of the upper end of the adjustment nozzle. The second motor is fixedly installed at the outer end of the fixed plate. The driving end of the second motor is fixedly connected to the middle of the adjustment shaft.

[0011] Preferably, a control valve is fixedly installed in the middle of the outer end of the adjustment nozzle. An angle sensor is fixedly installed at the outer end of the fixed plate without the second motor. The angle sensor is connected to the end of the adjustment shaft.

[0012] Preferably, the conveying nozzle passes through the middle of the storage tank and the reaction chamber. The conveying connection metal bellows in the second injection adjustment body is fixedly connected to the reaction chamber and is internally connected to the reaction chamber. The conveying connection metal bellows in the first injection adjustment body is internally connected to the inside of the guide disk.

[0013] An air-water cross-medium rocket includes a conical top cover, an installation chamber, and a propulsion chamber. The installation chamber is fixedly connected to the bottom end of the conical top cover by bolts. The propulsion chamber is fixedly connected to the bottom end of the installation chamber by bolts.

[0014] Preferably, the first fixed connection plate is fixedly installed inside the propulsion chamber by bolts. The second fixed connection plate is fixedly installed inside the second protective sleeve by bolts. The first protective sleeve and the second protective sleeve are located inside the propulsion chamber.

[0015] Preferably, swing support arms are evenly and rotatably installed at the outer end of the propulsion chamber. An adjustment support leg is slidably clamped inside the swing support arm. A first electric push rod is fixedly installed at the upper end of the swing support arm. The driving end of the first electric push rod is fixedly connected to the upper front part of the adjustment support leg. First motors are evenly fixedly installed on the propulsion chamber. The driving end of the first motor is fixedly connected to the upper side end of the swing support arm.

[0016] Advantages of the present invention:

[0017] 1. The rocket in the present invention can operate stably in water and air, and the operation modes in water and air can be freely switched to achieve stable air-water cross-medium operation. Moreover, the engine can automatically switch the operation mode according to the differences between the two operation modes, making the rocket convenient to use and operate.

[0018] II. When the rocket in the present invention is used and recovered, it can be stably supported and used, enabling the rocket to be stably, conveniently recovered and reused. By starting the first electric motor, each swing support arm can be controlled to rotate outward and open. By starting the swing support arm, each adjusting support leg can be controlled to telescopically move along the swing support arm. As a result, the opened swing support arm and adjusting support leg can stably support the rocket, facilitating the recovery and reuse of the rocket. Moreover, according to different landing locations, the opening angles of the swing support arm and adjusting support leg can be adaptively adjusted and controlled, as well as the positions and heights supported by the swing support arm and adjusting support leg, enabling the rocket to be stably supported and recovered on different terrains, and protecting the rocket to a greater extent during the recovery process. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The present invention will be further described below in conjunction with the drawings and embodiments.

[0020] Figure 1 Schematic diagram of the three-dimensional structure of the front view of the main body in the present invention;

[0021] Figure 2 Schematic diagram of the second state structure of the main body in the present invention;

[0022] Figure 3 Schematic diagram of the internal structure of the propulsion chamber in the present invention;

[0023] Figure 4 Schematic diagram of the propulsion main body structure in the present invention;

[0024] Figure 5 Schematic diagram of the internal structure of the propulsion main body in the present invention;

[0025] Figure 6 Schematic diagram of the bottom structure of the propulsion main body in the present invention;

[0026] Figure 7 Schematic diagram of the auxiliary propulsion system structure in the present invention;

[0027] Figure 8 Schematic diagram of the side view three-dimensional structure of the auxiliary propulsion system in the present invention;

[0028] Figure 9 Schematic diagram of the second jet adjustment main body structure in the present invention.

[0029] In the figure: 1 - conical top cover, 2 - installation bin, 3 - propulsion bin, 4 - first electric motor, 5 - first electric push rod, 6 - swing support arm, 7 - adjusting support leg, 8 - propulsion main body, 9 - first fixed connecting plate, 10 - fixed mounting plate, 11 - first protective sleeve, 12 - second protective sleeve, 13 - liquid rocket engine, 14 - auxiliary propulsion system, 15 - delivery nozzle, 16 - first stop valve, 17 - deflector, 18 - first injection adjustment main body, 20 - second fixed connecting plate, 21 - first air pump, 22 - storage tank, 23 - second air pump, 24 - water storage tank, 25 - liquid level sensor, 26 - fixed bracket, 27 - delivery pipe, 28 - reaction chamber, 29 - second injection adjustment main body, 30 - one-way pneumatic combination valve, 31 - sealing cover, 33 - fixing plate, 34 - angle sensor, 35 - control valve, 36 - adjustment nozzle, 37 - second electric motor, 38 - adjustment shaft, 39 - delivery connection metal bellows. Detailed implementation mode

[0030] In order to enable those skilled in the art of this technology to better understand the solution of this application, the technical solutions in the embodiments of this application will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of this application. Obviously, the described embodiments are only a part of the embodiments of this application, rather than all the embodiments. Based on the embodiments in this application, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of this application.

[0031] The present invention will be further described below in conjunction with the accompanying drawings.

[0032] Embodiment 1

[0033] As Figure 4 、 Figure 5 and Figure 6As shown in the figure, a water-air cross-medium rocket engine and a rocket of the present invention include a propulsion main body 8. The propulsion main body 8 includes a first fixed connection plate 9, a fixed mounting plate 10, a first protective sleeve 11, a second protective sleeve 12, a liquid rocket engine 13, an auxiliary propulsion system 14, a delivery nozzle 15, a first stop valve 16, a deflector 17 and a first injection adjustment main body 18. The first fixed connection plate 9 is fixedly connected to both sides of the fixed mounting plate 10. The first protective sleeve 11 is fixedly connected to the bottom end of the fixed mounting plate 10. The second protective sleeve 12 is fixedly connected to the bottom end of the first protective sleeve 11 by bolts. The liquid rocket engine 13 is fixedly installed inside the first protective sleeve 11 by bolts. The auxiliary propulsion system 14 is arranged inside the second protective sleeve 12, and the liquid rocket engine 13 is arranged above the auxiliary propulsion system 14. The delivery nozzle 15 is fixedly connected to the bottom end of the liquid rocket engine 13. The first stop valve 16 is fixedly connected to the bottom end of the delivery nozzle 15. The deflector 17 is fixedly connected to the bottom end of the first stop valve 16. The first injection adjustment main bodies 18 are uniformly and fixedly arranged at the bottom end of the deflector 17. The heat energy generated in the liquid rocket engine 13 is delivered to the delivery nozzle 15, then enters the deflector 17 after controlling the injection amount through the first stop valve 16, and finally is ejected from each of the first injection adjustment main bodies 18, thereby pushing the rocket to fly. During the flight, the second motors 37 in each of the first injection adjustment main bodies 18 drive the adjustment shafts 38 to rotate, which can control the orientation and running angle of each adjustment nozzle 36, so as to accurately adjust and change the flight angle and position of the rocket.

[0034] As Figure 7 and Figure 8As shown, the auxiliary propulsion system 14 includes a second fixed connection plate 20, a storage tank 22, a delivery pipe 27, a reaction chamber 28, a second injection adjustment body 29, and a one-way pneumatic combination valve 30. The second fixed connection plate 20 is evenly and fixedly installed on the upper edge of the storage tank 22. The reaction chamber 28 is arranged directly below the storage tank 22. The delivery pipe 27 is evenly and fixedly connected between the storage tank 22 and the reaction chamber 28. The one-way pneumatic combination valve 30 is fixedly installed on the delivery pipe 27. The second injection adjustment body 29 is evenly arranged on the bottom edge of the reaction chamber 28. A first air pump 21 is evenly and fixedly arranged on the upper end of the storage tank 22. The first air pump 21 is communicated with the inside of the storage tank 22. The second injection adjustment body 29 has the same structure as the first injection adjustment body 18. Fixed brackets 26 are evenly distributed on the outside of the reaction chamber 28. A second air pump 23 is fixedly installed on the upper end of the fixed bracket 26. A water storage tank 24 is fixedly installed inside the fixed bracket 26. Liquid level sensors 25 are evenly and fixedly installed on the water storage tank 24. The bottom end of the second air pump 23 is communicated with the upper end inside of the water storage tank 24. A sealing cover 31 is arranged in a threaded manner on the outer side of the upper end of the water storage tank 24. When the first air pump 21 operates, the magnesium powder or aluminum powder stored in the storage tank 22 is sprayed into the inside of the reaction chamber 28 through the delivery pipe 27, and the spraying speed and spraying amount can be controlled through the one-way pneumatic combination valve 30. At this time, the second air pump 23 transports the clear water stored inside the water storage tank 24 into the inside of the reaction chamber 28 through the delivery pipe. After the clear water is transported into the inside of the reaction chamber 28, it reacts with the aluminum powder and magnesium powder transported into the reaction chamber 28 to release a large amount of heat energy and gas.

[0035] As Figure 9 shown, both the first injection adjustment body 18 and the second injection adjustment body 29 include a fixed plate 33, an adjustment nozzle 36, a second motor 37, an adjustment shaft 38, and a delivery connection metal bellows 39. The fixed plates 33 are symmetrically arranged. The adjustment shaft 38 is rotatably clamped between the fixed plates 33. The adjustment nozzle 36 is fixedly installed in the middle of the adjustment shaft 38. The delivery connection metal bellows 39 is fixedly connected to the middle of the upper end of the adjustment nozzle 36. The second motor 37 is fixedly installed on the outer end of the fixed plate 33. The driving end of the second motor 37 is fixedly connected to the middle of the adjustment shaft 38. The second motor 37 can drive the adjustment shaft 38 and the adjustment nozzle 36 to rotate and adjust the angle.

[0036] A control valve 35 is fixedly installed in the middle of the outer end of the adjustment nozzle 36, which can control the spraying efficiency. An angle sensor 34 is fixedly installed on the outer end of the fixed plate 33 without the second motor 37. The angle sensor 34 is connected to the end of the adjustment shaft 38. Through the angle sensor 34, the angle of the forward and reverse rotation of the adjustment shaft 38 can be accurately detected, and the angle of the adjustment nozzle 36 can be indirectly and accurately controlled.

[0037] The conveying nozzle 15 passes through the middle of the storage tank 22 and the reaction chamber 28. The conveying connecting metal bellows 39 in the second injection adjustment body 29 is fixedly connected to the reaction chamber 28, and the conveying connecting metal bellows 39 is internally communicated with the reaction chamber 28. The conveying connecting metal bellows 39 in the first injection adjustment body 18 is internally communicated with the inside of the guide disk 17, playing a role in connecting and conveying.

[0038] As Figure 1 , Figure 2 and Figure 3 shown, a water-air cross-medium rocket includes a conical top cover 1, an installation bin 2 and a propulsion bin 3. The installation bin 2 is fixedly connected to the bottom end of the conical top cover 1 by bolts, and the propulsion bin 3 is fixedly connected to the bottom end of the installation bin 2 by bolts. The first fixed connecting plate 9 is fixedly installed inside the propulsion bin 3 by bolts, and the second fixed connecting plate 20 is fixedly installed inside the second protective sleeve 12 by bolts. The first protective sleeve 11 and the second protective sleeve 12 are located inside the propulsion bin 3. A control system is arranged inside the installation bin 2. The control system is used to ensure the normal flight of the launch vehicle along the predetermined ballistic trajectory. It consists of three major parts: a guidance system, an attitude control system, and a power supply and distribution and timing control system. The task of the guidance system is to control the rocket to move along the predetermined ballistic trajectory and accurately send the payload into the predetermined space position.

[0039] The working principle of Embodiment 1 is as follows: When the rocket is running in water, at this time, each first air pump 21 operates, so that the magnesium powder or aluminum powder stored in the storage tank 22 is sprayed into the inside of the reaction chamber 28 through the conveying pipe 27, and the spraying speed and spraying amount can be controlled by the one-way pneumatic combination valve 30. At this time, the second air pump 23 conveys the clear water stored inside the water storage tank 24 to the inside of the reaction chamber 28 through the conveying pipe. After the clear water is conveyed into the reaction chamber 28, it reacts with the aluminum powder and magnesium powder conveyed into the reaction chamber 28 to release a large amount of heat energy and gas, and then is conveyed to the adjustment nozzle 36 through the conveying connecting metal bellows 39 in the second injection adjustment body 29 and sprayed out from the inside of each adjustment nozzle 36 to push the rocket to move and run in water. Starting the second motor 37 can adjust the spraying angle of the adjustment nozzle 36, and the angle sensor 34 can accurately detect the use position and angle of the adjustment nozzle 36, so that the rocket can change the moving direction in water. By setting the liquid level sensor 25, the amount of clear water stored inside the water storage tank 24 can be detected, and it can be added in time. The cover plate fixedly arranged at the upper end of the storage tank 22 by bolts can be removed, so that the inside of the storage tank 22 can be conveniently filled with aluminum powder or magnesium powder;

[0040] When the rocket is in flight, the auxiliary propulsion system 14 stops operating as a whole. At this time, the liquid rocket engine 13 operates, causing the thermal energy generated in the liquid rocket engine 13 to be delivered to the delivery nozzle 15. Then, after controlling the injection volume through the first shut-off valve 16, it enters the deflector 17 and is finally ejected from each first injection adjustment body 18, thereby propelling the rocket to fly. During the flight, the second electric motor 37 in each first injection adjustment body 18 drives the adjustment shaft 38 to rotate, which can control the orientation and operating angle of each adjustment nozzle 36, enabling precise adjustment and change of the flight angle and position of the rocket.

[0041] Embodiment 2

[0042] Based on Embodiment 1, as Figure 1 and Figure 2 shown, swing support arms 6 are evenly and rotatably installed at the outer ends of the propulsion chamber 3. An adjustment support leg 7 is slidably clamped inside the swing support arm 6. A first electric push rod 5 is fixedly installed at the upper end of the swing support arm 6, and the driving end of the first electric push rod 5 is fixedly connected to the upper front part of the adjustment support leg 7. First electric motors 4 are evenly and fixedly installed on the propulsion chamber 3, and the driving ends of the first electric motors 4 are fixedly connected to the upper side parts of the swing support arms 6.

[0043] When implementing this embodiment, by starting the first electric motors 4, each swing support arm 6 can be controlled to rotate outward and open. By starting the swing support arm 6, each adjustment support leg 7 can be controlled to telescopically move along the swing support arm 6, so that the opened swing support arms 6 and adjustment support legs 7 can stably support the rocket, facilitating the recycling of the rocket. Moreover, according to different landing locations, the opening angles of the swing support arms 6 and adjustment support legs 7, as well as the supporting positions and heights of the swing support arms 6 and adjustment support legs 7, can be adaptively adjusted and controlled, enabling the rocket to be stably supported and recycled on different terrains.

[0044] Although the embodiments of the present invention have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A water-to-air medium-spanning rocket engine, comprising a propulsion body (8), characterized in that: The propulsion body (8) comprises a first fixed connection plate (9), a fixed installation plate (10), a first protective sleeve (11), a second protective sleeve (12), a liquid rocket engine (13), an auxiliary propulsion system (14), a delivery nozzle (15), a first stop valve (16), a guide plate (17) and a first injection adjustment body (18), wherein the first fixed connection plate (9) is fixedly connected to both sides of the fixed installation plate (10), the first protective sleeve (11) is fixedly connected to the bottom end of the fixed installation plate (10), the second protective sleeve (12) is fixedly connected to the bottom end of the first protective sleeve (11) by bolts, and the liquid The rocket engine (13) is fixedly installed inside the first protective sleeve (11) by bolts, the auxiliary propulsion system (14) is arranged inside the second protective sleeve (12), and the liquid rocket engine (13) is arranged at the upper end of the auxiliary propulsion system (14), the delivery nozzle (15) is fixedly connected to the bottom end of the liquid rocket engine (13), the first stop valve (16) is fixedly connected to the bottom end of the delivery nozzle (15), the guide plate (17) is fixedly connected to the bottom end of the first stop valve (16), and the first injection adjustment body (18) is evenly fixedly arranged at the bottom end of the guide plate (17).

2. A water-to-air medium-spanning rocket engine according to claim 1, characterized in that: The auxiliary propulsion system (14) comprises a second fixed connection plate (20), a storage box (22), a delivery pipe (27), a reaction chamber (28), a second injection regulating body (29) and a one-way pneumatic combination valve (30), wherein the second fixed connection plate (20) is evenly fixedly installed on the upper edge of the storage box (22), the reaction chamber (28) is arranged directly below the storage box (22), the delivery pipe (27) is evenly fixedly connected between the storage box (22) and the reaction chamber (28), the one-way pneumatic combination valve (30) is fixedly installed on the delivery pipe (27), and the second injection regulating body (29) is evenly arranged on the bottom edge of the reaction chamber (28).

3. A water-to-air medium-spanning rocket engine according to claim 2, characterized in that: A first air pump (21) is evenly and fixedly arranged at the upper end of the storage box (22); the first air pump (21) is connected to the interior of the storage box (22); and the second injection regulating body (29) has the same structure as the first injection regulating body (18).

4. A water-to-air medium-spanning rocket engine according to claim 3, characterized in that: Fixed brackets (26) are evenly distributed on the outside of the reaction chamber (28), a second air pump (23) is fixedly mounted on the upper end of the fixed bracket (26), a water storage tank (24) is fixedly mounted inside the fixed bracket (26), a liquid level sensor (25) is evenly fixedly mounted on the water storage tank (24), the bottom end of the second air pump (23) is connected to the inside of the upper end of the water storage tank (24), and a sealing cover (31) is threadedly arranged on the outer side of the upper end of the water storage tank (24).

5. A water-to-air medium-spanning rocket engine according to claim 4, characterized in that: The first injection regulating body (18) and the second injection regulating body (29) both comprise a fixed plate (33), an adjusting nozzle (36), a second motor (37), an adjusting shaft (38) and a conveying connection metal bellows (39); the fixed plates (33) are symmetrically arranged; the adjusting shaft (38) is rotatably clamped between the fixed plates (33); the adjusting nozzle (36) is fixedly mounted in the middle of the adjusting shaft (38); the conveying connection metal bellows (39) is fixedly connected to the middle of the upper end of the adjusting nozzle (36); the second motor (37) is fixedly mounted on the outer end of the fixed plate (33); and the driving end of the second motor (37) is fixedly connected to the middle of the adjusting shaft (38).

6. A water-to-air medium-spanning rocket engine according to claim 5, characterized in that: A control valve (35) is fixedly mounted in the middle of the outer end of the regulating nozzle (36), and an angle sensor (34) is fixedly mounted on the outer end of the fixed plate (33) not provided with the second motor (37), and the angle sensor (34) is connected to the end of the regulating shaft (38).

7. The water-to-air medium-spanning rocket engine according to claim 6, characterized in that: The delivery nozzle (15) passes through the middle of the storage box (22) and the reaction chamber (28); the delivery connection metal bellows (39) in the second injection adjustment body (29) is fixedly connected to the reaction chamber (28), and the delivery connection metal bellows (39) is communicated with the interior of the reaction chamber (28); the delivery connection metal bellows (39) in the first injection adjustment body (18) is communicated with the interior of the guide plate (17).

8. A water-to-air medium-spanning rocket, suitable for the water-to-air medium-spanning rocket engine according to claim 7, characterized in that: It comprises a conical top cover (1), a mounting chamber (2) and a propulsion chamber (3), wherein the mounting chamber (2) is fixedly connected to the bottom end of the conical top cover (1) by means of bolts, and the propulsion chamber (3) is fixedly connected to the bottom end of the mounting chamber (2) by means of bolts.

9. A water-to-air medium-spanning rocket according to claim 8, characterized in that: The first fixed connecting plate (9) is fixedly mounted inside the propulsion chamber (3) by means of bolts, and the second fixed connecting plate (20) is fixedly mounted inside the second protective sleeve (12) by means of bolts. The first protective sleeve (11) and the second protective sleeve (12) are located inside the propulsion chamber (3).

10. A water-to-air medium-spanning rocket according to claim 9, characterized in that: A swing support arm (6) is evenly and rotatably mounted on the outer end of the propulsion bin (3), an adjustment support leg (7) is slidably engaged inside the swing support arm (6), a first electric push rod (5) is fixedly mounted on the upper end of the swing support arm (6), and a driving end of the first electric push rod (5) is fixedly connected to the upper front end of the adjustment support leg (7), a first motor (4) is evenly and fixedly mounted on the propulsion bin (3), and a driving end of the first motor (4) is fixedly connected to the upper side end of the swing support arm (6).

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