Water reaction cross-medium rocket engine based on metal fuel

Abstract

The invention relates to the technical field of rocket engines, in particular to a metal fuel based water reaction cross-medium rocket engine which comprises a rocket structure, a direction adjusting control structure, a first combustion cylinder and a second combustion cylinder, the first combustion cylinder and the second combustion cylinder are fixedly connected, and the rocket structure is fixedly connected to the upper end of the first combustion cylinder and the upper end of the second combustion cylinder. A direction adjusting control structure is mounted on the rocket structure; the rocket structure is used for starting treatment work, the lower ends of the first water ramjet engine and the second water ramjet engine communicate with the second communicating spray pipe, the first communicating spray pipe and the conical spray pipe for underwater starting, and the first ramjet engine and the second ramjet engine communicate with the first combustion cylinder and the second combustion cylinder through the butt-joint combustion chamber for air starting; and the third water ramjet engine is communicated with the communicating valve seat and the communicating pipe through the communicating guide seat to provide running power for steering. And through the arrangement of the structure, rocket starting work is facilitated.

Description

Technical Field

[0001] The present invention relates to the technical field of rocket engines, in particular to a water-reaction cross-medium rocket engine based on metal fuel. Background Art

[0002] The water-reaction cross-medium rocket engine based on metal fuel is an innovative power system that enables the aircraft to autonomously switch between the dual media of air and underwater. It uses metal fuel (such as aluminum, boron, magnesium, etc.) as the core, uses oxidants in water or air to undergo chemical reactions to generate thrust, and combines supersonic ramjet, water ramjet power and supercavitation drag reduction technology to achieve the aircraft's cross-medium high-speed penetration (supersonic speed in the air, high speed underwater) and maneuverable strike capability.

[0003] According to Chinese patent publication number CN114352436B, a metal powder fuel air-water cross-medium engine and its control method are proposed. This engine is capable of multi-frequency water-to-air jumps, flight speeds from Ma0 to 4.0, and high-speed underwater operation. The metal powder fuel air-water cross-medium engine organically integrates the modes of an air-turbine rocket engine, a subsonic ramjet engine, and a water ramjet engine. Through engine flow channel adjustment, it can operate in both water and air mediums and can autonomously switch operating modes according to the external environment, giving the engine a wide speed range and high performance.

[0004] At present, the existing rocket engines and the above-mentioned cases cannot be used for macro-directional control and angle adjustment with higher precision to facilitate direction adjustment in water. Therefore, improvements are made to address the above-mentioned problems. Summary of the Invention

[0005] In view of the problems in the prior art, the present invention provides a water-reaction cross-medium rocket engine based on metal fuel.

[0006] The technical solution adopted by the present invention to solve the technical problem is: a water-reaction cross-medium rocket engine based on metal fuel, comprising a rocket structure, a directional control structure, a first combustion tube and a second combustion tube, the first combustion tube and the second combustion tube are fixedly connected, the upper ends of the first combustion tube and the second combustion tube are fixedly connected to the rocket structure, and the directional control structure is installed on the rocket structure;

[0007] The rocket structure is used for launching and processing work. The lower ends of the first and second water ramjets are connected to the second connecting nozzle, the first connecting nozzle, and the conical nozzle for underwater launching. The first and second ramjets are connected to the first and second combustion tubes through the docking combustion chamber for air launching. The third water ramjets are connected to the connecting valve seat and the connecting pipe through the connecting guide seat to provide operating power for steering. Through the structural setting of the propulsion control component, four main engines are provided. The first and second ramjets have the same structure and are used for air launching. The first and second water ramjets are used for underwater launching. The first injection pipe and the second injection pipe are respectively connected to the first ramjets, the second ramjets, the first water ramjets, and the second water ramjets to introduce different reactants. The water introduced is high-pressure water vapor for launching the reaction. The setting of the third water ramjets can introduce high-pressure water flow through the connecting guide seat and the connecting valve seat, thereby providing operating power for direction adjustment.

[0008] The direction adjustment control structure is connected to the connecting pipe, and the first electrically controlled hydraulic rod is extended and retracted to make the rotating shaft and the docking adjustment seat rotate on the nested pipe, thereby changing the position of the jet pipe. The jet pipe is connected to the connecting pipe through the docking movable connecting pipe, thereby performing jet direction adjustment processing.

[0009] Specifically, the rocket structure includes a propulsion control component, a direction adjustment connecting component and a protective top plate. The lower end of the propulsion control component is fixedly connected with the direction adjustment connecting component, and the propulsion control component is provided with a protective top plate.

[0010] Specifically, the propulsion control component includes a first ramjet, a second ramjet and a first water ramjet. The second ramjet and the first ramjet have the same structure, and the first water ramjet and the second water ramjet have the same structure. The first ramjet, the second ramjet, the first water ramjet and the second water ramjet are all installed on a protective seat, and the first ramjet, the second ramjet, the first water ramjet and the second water ramjet are all connected to the first injection pipe and the second injection pipe. Metal fuel and reactants are introduced through the first injection pipe and the second injection pipe. The lower end of the protective seat is fixedly connected to the docking combustion chamber.

[0011] Specifically, the directional connection component includes a third water ramjet engine, a connecting guide seat and a connecting valve seat. The lower end of the third water ramjet engine is connected to a connecting guide seat, the lower end of the connecting guide seat is connected to a connecting valve seat, and a connecting pipe is provided on the connecting valve seat. The center of the connecting valve seat is fixedly installed with a second connecting nozzle, the lower end of the first connecting nozzle is connected to the first connecting nozzle, and the lower end of the first connecting nozzle is connected to a conical nozzle.

[0012] Specifically, the direction adjustment control structure includes a socket plate and an articulated seat. The lower end of the socket plate is fixedly connected to the articulated seat. The articulated seat is hingedly provided with a first electrically-controlled hydraulic rod. The lower end of the first electrically-controlled hydraulic rod is fixed to the first docking hinge plate, and the lower end of the first docking hinge plate is hingedly provided with the first docking hinge rod. The first docking hinge rod is provided on the front end side of the docking adjustment seat, and the front end of the docking adjustment seat is connected to a jet pipe, and the docking adjustment seat is connected to a docking movable connecting pipe.

[0013] Specifically, the rear end of the docking adjustment seat is fixedly connected to the rotating shaft, the nested tube is sleeved on the rotating shaft, the rotating shaft is rotated and adjusted on the nested tube, and the nested tube is fixed to the connecting valve seat. The first electrically controlled hydraulic rod is extended and retracted, so that the docking adjustment seat is rotated and adjusted on the nested tube through the rotating shaft.

[0014] Specifically, the socket plate is connected to the upper end of the docking combustion chamber, the first ramjet engine and the second ramjet engine are connected to the docking combustion chamber, and the lower end of the docking combustion chamber is connected to the first combustion tube and the second combustion tube. The first injection pipe and the second injection pipe are provided in four groups, each group has two, which can introduce different reactants and metal fuels.

[0015] Specifically, the protection seat limits the upper parts of the first ramjet engine, the second ramjet engine, the first water ramjet engine, and the second water ramjet engine through the protection top plate, and the first combustion cylinder and the second combustion cylinder are fixed to the lower end of the connecting valve seat.

[0016] Specifically, the side end of the first docking hinge rod is hinged with a second docking hinge plate, the lower end of the second docking hinge plate is fixedly provided with a second electrically-controlled hydraulic rod, the lower end of the second electrically-controlled hydraulic rod is hinged with a second docking hinge rod, and the second docking hinge rod is fixedly connected to a chassis, and the chassis is fixedly connected to the outer sides of the first combustion tube and the second combustion tube. The structural setting of the direction adjustment control structure facilitates the direction control work. The first electrically-controlled hydraulic rod acts on the first docking hinge rod through extension and contraction to provide an adjustment steering force, so that the rotating shaft rotates and adjusts on the nested tube to change the position of the docking adjustment seat. At this time, the docking movable connecting pipe cooperates with the docking adjustment seat to extend and contract, and the docking movable connecting pipe drives the jet pipe to adjust its position. The connecting pipe is connected to the jet pipe through the docking movable connecting pipe to provide steering power, so that the rocket structure, the direction adjustment control structure, the first combustion tube and the second combustion tube can be adjusted in the water as a whole.

[0017] Specifically, the first docking hinge and the second docking hinge are coaxially arranged, and are both connected to the docking adjustment seat through the first docking hinge rod, and the first electrically controlled hydraulic rod and the second electrically controlled hydraulic rod form a triangular structure.

[0018] Beneficial effects of the present invention:

[0019] First, the present invention has four main engines through the structural arrangement of the propulsion control component. The first ramjet and the second ramjet have the same structure and are used for aerial launching. The first water ramjet and the second water ramjet are used for underwater launching. The first injection pipe and the second injection pipe are respectively connected to the first ramjet, the second ramjet, the first water ramjet, and the second water ramjet to introduce different reactants. The water introduced is high-pressure water vapor for launching the reaction. The third water ramjet is set up to introduce high-pressure water flow through the connecting guide seat and the connecting valve seat, thereby providing operating power for directional adjustment.

[0020] Second, the present invention facilitates direction control through the structural setting of the direction control structure. The first electrically controlled hydraulic rod acts on the first docking hinge rod through extension and retraction to provide steering force, so that the rotating shaft rotates and adjusts on the nested tube to change the position of the docking adjustment seat. At this time, the docking movable connecting pipe cooperates with the docking adjustment seat to extend and retract, and the docking movable connecting pipe drives the jet pipe to adjust its position. The connecting pipe is connected to the jet pipe through the docking movable connecting pipe to provide steering power, so that the rocket structure, direction control structure, first combustion tube and second combustion tube can be adjusted as a whole in the water. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The present invention will be further described below with reference to the accompanying drawings and examples.

[0022] Figure 1 This is a schematic diagram of the three-dimensional structure of the main body of the present invention from the front perspective;

[0023] Figure 2 This is a split diagram of the main body of the present invention;

[0024] Figure 3 A perspective view of the rocket structure of the present invention;

[0025] Figure 4 This is a disassembled diagram of the rocket structure of the present invention;

[0026] Figure 5 A perspective view of a propulsion control component in the present invention;

[0027] Figure 6 A perspective view of the direction-adjusting connecting component of the present invention;

[0028] Figure 7 A perspective view of the steering control structure of the present invention;

[0029] Figure 8 This is a disassembled diagram of the direction adjustment control structure in the present invention;

[0030] Figure 9 It is a three-dimensional diagram of a second embodiment of the main body of the present invention.

[0031] In the figure: 1-rocket structure, 2-direction control structure, 3-first combustion tube, 4-second combustion tube, 5-propulsion control component, 6-direction connection component, 7-protective top plate, 8-first ramjet, 9-second ramjet, 10-first water ramjet, 11-protective seat, 12-first injection pipe, 13-second injection pipe, 14-docking combustion chamber, 15-second water ramjet, 16-third water ramjet, 17-connecting guide seat, 18- Connecting valve seat, 19-connecting pipe, 20-conical nozzle, 21-first connecting nozzle, 22-second connecting nozzle, 23-sleeve plate, 24-hinge seat, 25-first electrically-controlled hydraulic rod, 26-first docking hinge, 27-rotating shaft, 28-nested pipe, 29-first docking hinge, 30-injection pipe, 31-docking adjustment seat, 32-docking movable connecting pipe, 33-second docking hinge, 34-second electrically-controlled hydraulic rod, 35-second docking hinge, 36-chassis. DETAILED DESCRIPTION

[0032] In order to enable those skilled in the art to better understand the present invention, the following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts should fall within the scope of protection of this application.

[0033] The present invention will be further described below with reference to the accompanying drawings.

[0034] Example 1

[0035] like Figure 1-8 As shown, the metal fuel-based water-reactive cross-medium rocket engine of the present invention includes a rocket structure 1, a directional control structure 2, a first combustion tube 3 and a second combustion tube 4. The first combustion tube 3 and the second combustion tube 4 are fixedly connected. The upper ends of the first combustion tube 3 and the second combustion tube 4 are fixedly connected to the rocket structure 1, and the directional control structure 2 is installed on the rocket structure 1.

[0036] The rocket structure 1 is used for launching and processing work. The lower ends of the first water ramjet engine 10 and the second water ramjet engine 15 are connected to the second connecting nozzle 22, the first connecting nozzle 21, and the conical nozzle 20 for underwater launching. The first ramjet engine 8 and the second ramjet engine 9 are connected to the first combustion tube 3 and the second combustion tube 4 through the docking combustion chamber 14 for aerial launching. The third water ramjet engine 16 is connected to the connecting valve seat 18 and the connecting pipe 19 through the connecting guide seat 17 to provide running power for steering. Fuel and reactants are introduced through the first injection pipe 12 and the second injection pipe 13. When in the air, the first injection pipe 12 and the second injection pipe 13 are introduced into the second ramjet engine 9 and the first ramjet engine 8, mixed and reacted in the first ramjet engine 8 and the second ramjet engine 9, and then ignited in the docking combustion chamber 14 and ejected through the first combustion tube 3 and the second combustion tube 4, thereby driving the overall movement of the rocket structure 1, the direction adjustment control structure 2, the first combustion tube 3, and the second combustion tube 4;

[0037] The direction adjustment control structure 2 is connected to the connecting pipe 19, and the first electrically controlled hydraulic rod 25 is extended and retracted, so that the rotating shaft 27 and the docking adjustment seat 31 rotate on the nesting tube 28, changing the position of the jet pipe 30. The jet pipe 30 is connected to the connecting pipe 19 through the docking movable connecting pipe 32, thereby performing jet direction adjustment processing.

[0038] The rocket structure 1 includes a propulsion control component 5, a direction adjustment connecting component 6 and a protective top plate 7. The lower end of the propulsion control component 5 is fixedly connected with the direction adjustment connecting component 6, and the propulsion control component 5 is provided with a protective top plate 7.

[0039] The propulsion control component 5 includes a first ramjet 8, a second ramjet 9 and a first water ramjet 10. The second ramjet 9 and the first ramjet 8 have the same structure, and the first water ramjet 10 and the second water ramjet 15 have the same structure. The first ramjet 8, the second ramjet 9, the first water ramjet 10 and the second water ramjet 15 are all installed on the protection seat 11, and the first ramjet 8, the second ramjet 9, the first water ramjet 10 and the second water ramjet 15 are all connected to the first injection pipe 12 and the second injection pipe 13. Metal fuel and reactants are introduced through the first injection pipe 12 and the second injection pipe 13. The lower end of the protection seat 11 is fixedly connected to the docking combustion chamber 14.

[0040] The directional control component 6 includes a third water ramjet engine 16, a connecting guide seat 17 and a connecting valve seat 18. When in water, the directional control structure 2 can perform directional operation. At this time, the third water ramjet engine 16 can react. The lower end of the third water ramjet engine 16 is connected to the connecting valve seat 18 through the connecting guide seat 17. The connecting valve seat 18 is connected to the docking movable connecting pipe 32 through the connecting pipe 19. The docking movable connecting pipe 32 is connected to the jet pipe 30 through the docking adjustment seat 31, and can eject high-pressure gas, thereby pushing the rocket structure 1, the directional control structure 2, and the third water ramjet engine 16 to the rocket. The first combustion tube 3 and the second combustion tube 4 are adjusted in direction. The lower end of the third water ramjet engine 16 is connected with a connecting guide seat 17, and the lower end of the connecting guide seat 17 is connected with a connecting valve seat 18, and a connecting pipe 19 is provided on the connecting valve seat 18. The center of the connecting valve seat 18 is fixedly installed with a second connecting nozzle 22, and the lower end of the first connecting nozzle 21 is connected with a first connecting nozzle 21, and the lower end of the first connecting nozzle 21 is connected with a conical nozzle 20. Through the structural setting of the propulsion control component 5, four main engines are provided, the first ramjet engine 8, the second ramjet engine 9, the first ramjet engine 10, the second ramjet engine 11, the first ramjet engine 12 and the second ramjet engine 13. The engine 9 has the same structure and is used for air starting. The first water ramjet engine 10 and the second water ramjet engine 15 are used for underwater starting. The first injection pipe 12 and the second injection pipe 13 are connected to the first ramjet engine 8, the second ramjet engine 9, the first water ramjet engine 10, and the second water ramjet engine 15 respectively to introduce different reactants. The water introduced is high-pressure water vapor for starting the reaction. The third water ramjet engine 16 is set to be able to introduce high-pressure water flow through the connecting guide seat 17 and the connecting valve seat 18, thereby providing operating power for direction adjustment. When in water, the first water ramjet 10 and the second water ramjet 15 are working, and the first injection pipe 12 and the second injection pipe 13 introduce metal fuel and high-pressure water vapor into the first water ramjet 10 and the second water ramjet 15, so that a reaction occurs in the first water ramjet 10 and the second water ramjet 15, and then the second connecting nozzle 22, the first connecting nozzle 21, and the conical nozzle 20 are used for injection and discharge, thereby controlling the rocket structure 1, the direction control structure 2, the first combustion tube 3, and the second combustion tube 4 to operate in the water.

[0041] The direction adjustment control structure 2 includes a sleeve disc 23 and an articulated seat 24. The lower end of the sleeve disc 23 is fixedly connected to the articulated seat 24. A first electrically controlled hydraulic rod 25 is hingedly provided on the articulated seat 24. The lower end of the first electrically controlled hydraulic rod 25 is fixed to the first docking hinge 26, and the lower end of the first docking hinge 26 is hingedly provided with a first docking hinge rod 29. The first docking hinge rod 29 is provided at the front end side of the docking adjustment seat 31, and the front end of the docking adjustment seat 31 is connected to an air jet pipe 30. The docking adjustment seat 31 is connected to a docking activity connecting pipe 32. The structural setting of the direction adjustment control structure 2 facilitates direction adjustment. During the regulation work, the first electrically-controlled hydraulic rod 25 acts on the first docking hinge rod 29 by extending and retracting, providing the adjustment steering force, so that the rotating shaft 27 rotates and adjusts on the nesting tube 28, changing the position of the docking adjustment seat 31. At this time, the docking movable connecting tube 32 cooperates with the docking adjustment seat 31 to extend and retract, and the docking movable connecting tube 32 drives the jet pipe 30 to adjust its position. The connecting tube 19 is connected to the jet pipe 30 through the docking movable connecting tube 32, providing the steering power, so that the rocket structure 1, the direction control structure 2, the first combustion tube 3, and the second combustion tube 4 can adjust the direction as a whole in the water.

[0042] The rear end of the docking adjustment seat 31 is fixedly connected to the rotating shaft 27, the nesting tube 28 is sleeved on the rotating shaft 27, the rotating shaft 27 is rotated and adjusted on the nesting tube 28, and the nesting tube 28 is fixed to the connecting valve seat 18. The first electrically controlled hydraulic rod 25 is extended and retracted, so that the docking adjustment seat 31 is rotated and adjusted on the nesting tube 28 through the rotating shaft 27, and the first electrically controlled hydraulic rod 25 can work. The first electrically controlled hydraulic rod 25 is hinged to the sleeve plate 23 through the hinge seat 24, and the lower end of the first electrically controlled hydraulic rod 25 is connected to the first hinge plate 26 through the first docking hinge plate 27. The docking hinge rod 29 is hingedly arranged, and the angle of the jet pipe 30 and the docking adjustment seat 31 is changed through the telescopic adjustment of the first electrically controlled hydraulic rod 25. The nested tube 28 is fixed to the connecting valve seat 18. The push of the first docking hinge rod 29 causes the jet pipe 30 and the docking adjustment seat 31 to rotate and adjust on the nested tube 28 through the rotating shaft 27, thereby changing the angular position of the jet pipe 30. Along with the jet processing of the jet pipe 30, the push adjustment is performed to change the direction of the rocket structure 1, the direction control structure 2, the first combustion tube 3, and the second combustion tube 4.

[0043] The socket disc 23 is connected to the upper end of the docking combustion chamber 14, the first ramjet engine 8 and the second ramjet engine 9 are connected to the docking combustion chamber 14, and the lower end of the docking combustion chamber 14 is connected to the first combustion tube 3 and the second combustion tube 4. The first injection pipe 12 and the second injection pipe 13 are provided in four groups, each group is provided with two, which can introduce different reactants and metal fuels.

[0044] The protection seat 11 limits the upper parts of the first ramjet engine 8, the second ramjet engine 9, the first water ramjet engine 10, and the second water ramjet engine 15 by protecting the top plate 7, and the first combustion tube 3 and the second combustion tube 4 are fixed to the lower end of the connecting valve seat 18.

[0045] The working principle is as follows: when in use, fuel and reactants are introduced through the first injection pipe 12 and the second injection pipe 13. When in the air, the first injection pipe 12 and the second injection pipe 13 are used to introduce the fuel and reactants into the second ramjet engine 9 and the first ramjet engine 8, where they are mixed and reacted. After that, they are ignited in the docking combustion chamber 14 and ejected through the first combustion tube 3 and the second combustion tube 4, thereby driving the overall movement of the rocket structure 1, the direction control structure 2, the first combustion tube 3, and the second combustion tube 4.

[0046] When in water, the first water ramjet 10 and the second water ramjet 15 are working. The first injection pipe 12 and the second injection pipe 13 introduce metal fuel and high-pressure steam into the first water ramjet 10 and the second water ramjet 15, so that a reaction occurs in the first water ramjet 10 and the second water ramjet 15. Then, the second connecting nozzle 22, the first connecting nozzle 21, and the conical nozzle 20 are used for injection and discharge, thereby controlling the rocket structure 1, the direction control structure 2, the first combustion tube 3, and the second combustion tube 4 to operate in water.

[0047] When in water, the direction adjustment control structure 2 can perform direction adjustment work. At this time, the third water ramjet engine 16 can react. The lower end of the third water ramjet engine 16 is connected to the connecting valve seat 18 through the connecting guide seat 17. The connecting valve seat 18 is connected to the docking movable connecting pipe 32 through the connecting pipe 19. The docking movable connecting pipe 32 is connected to the jet pipe 30 through the docking adjustment seat 31. High-pressure gas can be ejected, thereby pushing the rocket structure 1, the direction adjustment control structure 2, the first combustion tube 3, and the second combustion tube 4 to adjust the direction;

[0048] At this time, the first electrically-controlled hydraulic rod 25 is able to work. The first electrically-controlled hydraulic rod 25 is hinged to the socket plate 23 through the hinge seat 24. The lower end of the first electrically-controlled hydraulic rod 25 is hinged to the first docking hinge 29 through the first docking hinge 26. Through the telescopic adjustment of the first electrically-controlled hydraulic rod 25, the angle of the jet pipe 30 and the docking adjustment seat 31 is changed, and the nested tube 28 is fixed to the connecting valve seat 18. The push of the first docking hinge 29 causes the jet pipe 30 and the docking adjustment seat 31 to rotate and adjust on the nested tube 28 through the rotating shaft 27, thereby changing the angular position of the jet pipe 30. Along with the jet processing of the jet pipe 30, the push adjustment is performed to change the direction of the rocket structure 1, the adjustment control structure 2, the first combustion tube 3, and the second combustion tube 4 to complete the work.

[0049] Example 2

[0050] On the basis of Example 1, Figure 9 As shown, the side end of the first docking hinge 29 is hinged with a second docking hinge 33, the lower end of the second docking hinge 33 is fixedly provided with a second electro-hydraulic rod 34, the lower end of the second electro-hydraulic rod 34 is hinged with a second docking hinge 35, and the second docking hinge 35 is fixedly connected to a chassis 36, and the chassis 36 is fixedly connected to the outer sides of the first combustion tube 3 and the second combustion tube 4. The second docking hinge 33 is docked with the first docking hinge 29 and the first docking hinge 26. When the first electro-hydraulic rod 25 is telescopically adjusted, the second electro-hydraulic rod 34 cooperates to perform telescopic adjustment, and the lower end of the second electro-hydraulic rod 34 is hinged with the chassis 36 through the second docking hinge 35, and can also follow the angle adjustment, thereby improving the stability performance of the docking adjustment seat 31 during rotation. The first electro-hydraulic rod 25 and the second electro-hydraulic rod 34 form a triangular structure, which can perform rotation adjustment more stably.

[0051] The first docking hinge plate 26 and the second docking hinge plate 33 are coaxially arranged and are connected to the docking adjustment seat 31 through the first docking hinge rod 29 , and the first electrically controlled hydraulic rod 25 and the second electrically controlled hydraulic rod 34 form a triangular structure.

[0052] When in use, the second docking hinge 33 is docked with the first docking hinge 29 and the first docking hinge 26. When the first electro-hydraulic rod 25 is telescopically adjusted, the second electro-hydraulic rod 34 cooperates to perform telescopic adjustment, and the lower end of the second electro-hydraulic rod 34 is hinged to the chassis 36 through the second docking hinge 35, and can also follow the angle adjustment, thereby improving the stability of the docking adjustment seat 31 during rotation. The first electro-hydraulic rod 25 and the second electro-hydraulic rod 34 form a triangular structure, which makes the rotation adjustment work more stable.

[0053] While embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions, and variations may be made to these embodiments without departing from the principles and spirit of the invention, and that the scope of the invention is defined by the appended claims and their equivalents.

Claims

1. A water-reactive cross-medium rocket engine based on metal fuel, characterized by: The rocket structure (1) comprises a rocket structure (1), a direction adjustment control structure (2), a first combustion tube (3) and a second combustion tube (4); the first combustion tube (3) and the second combustion tube (4) are fixedly connected; the upper ends of the first combustion tube (3) and the second combustion tube (4) are fixedly connected to the rocket structure (1); and the direction adjustment control structure (2) is installed on the rocket structure (1); The rocket structure (1) is used for starting and processing work. The lower ends of the first water ramjet engine (10) and the second water ramjet engine (15) are connected to the second connecting nozzle (22), the first connecting nozzle (21), and the conical nozzle (20) to perform underwater starting. The first ramjet engine (8) and the second ramjet engine (9) are connected to the first combustion tube (3) and the second combustion tube (4) through the docking combustion chamber (14) to perform aerial starting. The third water ramjet engine (16) is connected to the connecting valve seat (18) and the connecting pipe (19) through the connecting guide seat (17) to provide operating power for steering. The direction adjustment control structure (2) is connected to the connecting pipe (19), and the first electrically controlled hydraulic rod (25) is extended and retracted, so that the rotating shaft (27) and the docking adjustment seat (31) rotate on the nesting pipe (28), thereby changing the position of the jet pipe (30). The jet pipe (30) is connected to the connecting pipe (19) through the docking movable connecting pipe (32), thereby performing jet direction adjustment processing.

2. The metal fuel-based water-reactive cross-medium rocket engine according to claim 1, characterized in that: The rocket structure (1) comprises a propulsion control component (5), a direction-adjusting connecting component (6) and a protective top plate (7); the lower end of the propulsion control component (5) is fixedly connected to the direction-adjusting connecting component (6), and the protective top plate (7) is provided on the propulsion control component (5).

3. The metal fuel-based water-reactive cross-medium rocket engine according to claim 2, characterized in that: The propulsion control component (5) comprises a first ramjet (8), a second ramjet (9) and a first water ramjet (10); the second ramjet (9) and the first ramjet (8) have the same structure; the first water ramjet (10) and the second water ramjet (15) have the same structure; the first ramjet (8), the second ramjet (9), the first water ramjet (10) and the second water ramjet (15) are all mounted on a protective seat (11); and the first ramjet (8), the second ramjet (9), the first water ramjet (10) and the second water ramjet (15) are all connected to a first injection pipe (12) and a second injection pipe (13); metal fuel and reactants are introduced through the first injection pipe (12) and the second injection pipe (13); and the lower end of the protective seat (11) is fixedly connected to a docking combustion chamber (14).

4. The metal fuel-based water-reactive cross-medium rocket engine according to claim 3, characterized in that: The direction-adjusting connecting component (6) comprises a third water ramjet engine (16), a connecting guide seat (17) and a connecting valve seat (18); the lower end of the third water ramjet engine (16) is connected to the connecting guide seat (17); the lower end of the connecting guide seat (17) is connected to the connecting valve seat (18); a connecting pipe (19) is provided on the connecting valve seat (18); a second connecting nozzle (22) is fixedly installed at the center of the connecting valve seat (18); the lower end of the first connecting nozzle (21) is connected to the first connecting nozzle (21); and the lower end of the first connecting nozzle (21) is connected to the conical nozzle (20).

5. The metal fuel-based water-reactive cross-medium rocket engine according to claim 4, characterized in that: The direction adjustment control structure (2) comprises a sleeve disc (23) and an articulated seat (24). The lower end of the sleeve disc (23) is fixedly connected to the articulated seat (24). A first electrically controlled hydraulic rod (25) is hingedly provided on the articulated seat (24). The lower end of the first electrically controlled hydraulic rod (25) is fixed to a first docking hinge (26), and the lower end of the first docking hinge (26) is hingedly provided to a first docking hinge rod (29). The first docking hinge rod (29) is provided at the front end side of the docking adjustment seat (31), and the front end of the docking adjustment seat (31) is connected to an air jet pipe (30). The docking adjustment seat (31) is connected to a docking movable connecting pipe (32).

6. The metal fuel-based water-reactive cross-medium rocket engine according to claim 5, characterized in that: The rear end of the docking adjustment seat (31) is fixedly connected to the rotating shaft (27), the nesting tube (28) is sleeved on the rotating shaft (27), the rotating shaft (27) is rotated and adjusted on the nesting tube (28), and the nesting tube (28) is fixed to the connecting valve seat (18). The first electrically controlled hydraulic rod (25) is extended and retracted, so that the docking adjustment seat (31) is rotated and adjusted on the nesting tube (28) through the rotating shaft (27).

7. The metal fuel-based water-reactive cross-medium rocket engine according to claim 6, characterized in that: The socket disc (23) is connected to the upper end of the docking combustion chamber (14); the first ramjet engine (8) and the second ramjet engine (9) are connected to the docking combustion chamber (14); the lower end of the docking combustion chamber (14) is connected to the first combustion tube (3) and the second combustion tube (4); the first injection pipe (12) and the second injection pipe (13) are provided with four groups, each group having two, capable of introducing different reactants and metal fuels.

8. The metal fuel-based water-reactive cross-medium rocket engine according to claim 7, characterized in that: The protection seat (11) limits the upper positions of the first ramjet (8), the second ramjet (9), the first water ramjet (10), and the second water ramjet (15) through the protection top plate (7); the first combustion cylinder (3) and the second combustion cylinder (4) are fixed to the lower end of the connecting valve seat (18).

9. The metal fuel-based water-reactive cross-medium rocket engine according to claim 8, characterized in that: The side end of the first butt hinge rod (29) is hingedly provided with a second butt hinge plate (33), the lower end of the second butt hinge plate (33) is fixedly provided with a second electrically controlled hydraulic rod (34), the lower end of the second electrically controlled hydraulic rod (34) is hingedly provided with a second butt hinge rod (35), the second butt hinge rod (35) is fixedly connected with a chassis (36), and the chassis (36) is fixedly connected to the outer sides of the first combustion cylinder (3) and the second combustion cylinder (4).

10. The metal fuel-based water-reactive cross-medium rocket engine according to claim 9, characterized in that: The first docking hinge (26) and the second docking hinge (33) are coaxially arranged and are both connected to the docking adjustment seat (31) via a first docking hinge rod (29), and the first electrically controlled hydraulic rod (25) and the second electrically controlled hydraulic rod (34) form a triangular structure.

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