Dual-mode hybrid power cycle rocket engine

Abstract

The invention relates to the technical field of rocket engines, in particular to a dual-mode hybrid power cycle rocket engine which comprises a first power control structure and a second power control structure, the first power control structure is arranged on the second power control structure in a limiting mode, and the first power control structure communicates with the second power control structure; the first power control structure is used for hovering treatment, the three third hydraulic control rods are used for changing the positions of the first control unit, the second control unit and the third control unit on the regulation and control groove seat, the engine controls and cooperates with the key shaft to rotate, and driving control over the first control unit, the second control unit and the third control unit is conducted. The protection butt joint seat is communicated with the first regulation and control valve seat and can provide operation power for the engine; and the second power control structure is used for jet type driving. And through the arrangement of the structure, rocket driving work is facilitated.

Description

Technical Field

[0001] The present invention relates to the technical field of rocket engines, and specifically, to a dual-mode hybrid cycle rocket engine. Background Art

[0002] A dual-mode hybrid cycle rocket engine can switch between two power cycle modes according to different stages or requirements of a flight mission. For example, it can adopt a high-thrust mode during rocket takeoff or acceleration, and switch to another high specific impulse mode during orbit entry or cruise, thereby optimizing the overall performance.

[0003] According to Chinese Patent Publication No. CN119687734A, which relates to the technical field of loitering munitions, and particularly to a hybrid power system, a control method, and a loitering munition, including a rotary engine, a rocket engine, an electric motor, a battery, and a control unit; the rotary engine is connected to a propeller; the rocket engine is arranged at the tail of the loitering munition, including a propellant supply chamber, an ignition device, a flameout device, and a Laval nozzle, and can selectively ignite sub-combustion chambers with different cross-sections or different amounts of propellant, thereby achieving precise adjustment of the thrust of the rocket engine. The battery and the control unit respectively provide power and precise control for each electromechanical structure, realizing the power combination of the rotary engine and the rocket engine, enabling the loitering munition to perform long-time, long-distance, and different-route loitering reconnaissance flights, and also to strike quickly and accurately. It solves the problem in the prior art that the power system cannot simultaneously meet the requirements of long-distance loitering reconnaissance and rapid strike of the loitering munition.

[0004] Currently, for the existing dual-mode hybrid cycle rocket engines and the above-mentioned case, during use, it is inconvenient to conduct regulation during power switching and unable to change the aerodynamic design, resulting in waste of power. Therefore, improvements are made for the above problems. Summary of the Invention

[0005] In view of the problems in the prior art, the present invention provides a dual-mode hybrid cycle rocket engine.

[0006] The technical solution adopted by the present invention to solve its technical problems is: a dual-mode hybrid cycle rocket engine, including a first power control structure and a second power control structure. The first power control structure is limitedly arranged on the second power control structure, and the first power control structure and the second power control structure are connected and arranged in communication;

[0007] The first power control structure is used for hovering processing, and there are three third liquid control rods. By changing the positions of the first control unit, the second control unit, and the third control unit on the regulation slot base, and with the cooperation of the engine control and the rotation of the key shaft, the driving control of the first control unit, the second control unit, and the third control unit is carried out. Moreover, the protection docking seat is communicated with the first regulation valve seat, and can provide operating power for the engine;

[0008] The second power control structure is used for jet drive. The fuel storage seat is communicated with the combustion chamber through the second regulating valve seat, and power injection is carried out in the conical nozzle to control the movement of the first power control structure and the second power control structure.

[0009] Specifically, the first power control structure includes a regulating component and a power control component. The regulating component is arranged on the upper limit of the power control component. The regulating component can change the angle, and the power control component is used for driving and controlling the work.

[0010] Specifically, the regulating component includes an adjustment processing mechanism, a first hydraulic control rod, a docking protection ring and a second hydraulic control rod. The second hydraulic control rod controls the telescopic adjustment of the adjustment processing mechanism through a bearing, and the first hydraulic control rod is installed on the adjustment processing mechanism through the docking protection ring.

[0011] Specifically, the adjustment processing mechanism includes a first control unit, a matching hinge frame, a third hydraulic control rod, a combined end frame, a matching telescopic sleeve frame, a second control unit and a third control unit. The matching telescopic sleeve frame adopts a telescopic design. The top of the matching telescopic sleeve frame is fixedly connected with the combined end frame. The third hydraulic control rod is hinged on the combined end frame. The upper end of the third hydraulic control rod is hinged with the matching hinge frame, and the first control unit is fixedly connected to the matching hinge frame.

[0012] Specifically, there are three of the matching hinge frames and the third hydraulic control rods, and they are evenly distributed around the combined end frame. The matching hinge frame and the third hydraulic control rod on one side are connected to the second control unit, and the matching hinge frame and the third hydraulic control rod on the other side are connected to the third control unit, and the three third hydraulic control rods are controlled by a unified hydraulic system.

[0013] Specifically, the first control unit, the second control unit and the third control unit have the same structure. The first control unit includes a propeller, a first fixed end block, a first adaptor connecting shaft, a second adaptor connecting shaft and a second fixed end block. The rear end of the first adaptor connecting shaft is fixedly connected to the second adaptor connecting shaft. The first adaptor connecting shaft is fixedly arranged on the first fixed end block, and the second adaptor connecting shaft is fixedly arranged on the second fixed end block. The propeller is hinged on the first adaptor connecting shaft and the second adaptor connecting shaft.

[0014] Specifically, the power control component includes a combined top sleeve, a regulation groove seat, a mating key shaft, an engine, and a protection docking seat. An engine is connected to the protection docking seat in a communicating manner. A mating key shaft is drivingly connected to the engine. A regulation groove seat is fixedly connected to the mating key shaft. A combined top sleeve is fixedly connected to the regulation groove seat. Through the structural arrangement of the regulation component, it is convenient to carry out regulation work. Among them, the second hydraulic control rod can control the movement of the combined end frame and the mating telescopic sleeve frame, so that the mating telescopic sleeve frame is limited in telescopic adjustment on the mating key shaft, changing the height of the combined end frame and the mating telescopic sleeve frame, so as to carry out regulation work. At the same time, the third hydraulic control rod can be telescopically adjusted. The third hydraulic control rod is hingedly arranged with the first control unit through a mating hinge frame, and can make the propeller hingedly arranged around the first adaptor connecting shaft and the second adaptor connecting shaft, changing the angular position of the propeller, so as to facilitate the regulation work in cooperation with aerodynamics. The engine can control the rotation of the regulation groove seat through the mating key shaft, so that the first control unit, the second control unit, and the third control unit rotate and cooperate to carry out hovering work.

[0015] Specifically, the second power control structure includes a fuel storage seat, a first regulation valve seat, a second regulation valve seat, a conical nozzle, a combustion chamber, and a guiding control pipe. The upper end of the conical nozzle is connected to the combustion chamber in a communicating manner. The upper end of the combustion chamber is connected to the second regulation valve seat in a communicating manner. The upper end of the second regulation valve seat is connected to the fuel storage seat in a communicating manner, and the center of the second regulation valve seat is also connected to the guiding control pipe in a communicating manner. The upper center of the guiding control pipe is connected to the first regulation valve seat in a communicating manner.

[0016] Specifically, the second regulation valve seat can divert and transmit the fuel on the fuel storage seat. The fuel storage seat can be connected to the combustion chamber through the second regulation valve seat. The fuel storage seat can also be connected to the protection docking seat through the second regulation valve seat, the guiding control pipe, and the first regulation valve seat. The lower end of the protection docking seat is fixedly connected to the first regulation valve seat in a communicating manner. Through the structural arrangement of the second power control structure, the fuel storage seat is connected to the second regulation valve seat and the combustion chamber. Through fuel injection and ignition, drive control work is carried out to achieve guiding and propulsion work. At the same time, the second regulation valve seat can be connected to the protection docking seat through the guiding control pipe and the first regulation valve seat, so as to guide the fuel into the engine, and the engine controls the rotation of the mating key shaft, so as to carry out the control operation work of the first control unit, the second control unit, and the third control unit.

[0017] Specifically, the mating telescopic sleeve frame is slidably connected to the mating key shaft. The first fixed end block and the second fixed end block are fixedly connected to the regulation groove seat. The mating hinge frame is fixed on the propeller. The first hydraulic control rod is fixed on the lower side of the regulation groove seat. The second hydraulic control rod is fixed on the upper side of the protection docking seat. A groove for the movement of the propeller is provided on the regulation groove seat.

[0018] Advantages of the present invention:

[0019] First, through the structural settings of the control components, the present invention facilitates the control work. Among them, the second hydraulic control rod can control the combined end frame and cooperate with the telescopic sleeve frame to move, enabling the telescopic sleeve frame to be limited and telescoped on the mating key shaft, changing the height of the combined end frame and the telescopic sleeve frame, thereby carrying out the control work. At the same time, the third hydraulic control rod can be telescopically adjusted. The third hydraulic control rod is hinged to the first control unit through the mating hinge frame, enabling the propeller to be hinged around the first adaptor connecting shaft and the second adaptor connecting shaft, changing the angular position of the propeller, thus facilitating the control work in cooperation with aerodynamics. The engine can control the rotation of the control groove seat through the mating key shaft, enabling the first control unit, the second control unit, and the third control unit to rotate and cooperate in hovering work.

[0020] Second, through the structural settings of the second power control structure, the fuel storage seat is connected to the second control valve seat and the combustion chamber, and is driven and controlled by fuel injection and ignition to achieve guiding and propulsion work. At the same time, the second control valve seat can be connected to the protection docking seat through the guiding control pipe and the first control valve seat, thereby guiding the fuel into the engine. The engine controls the rotation of the mating key shaft to carry out the control operation of the first control unit, the second control unit, and the third control unit. Description of the Drawings

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

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

[0023] Figure 2 It is an exploded view of the main body in the present invention;

[0024] Figure 3 It is a three-dimensional view of the first power control structure in the present invention;

[0025] Figure 4 It is a three-dimensional view of the control components in the present invention;

[0026] Figure 5 It is a three-dimensional view of the adjustment and processing mechanism in the present invention;

[0027] Figure 6 It is an exploded view of the first control unit in the present invention;

[0028] Figure 7 It is a three-dimensional structure schematic diagram of the power control components in the present invention;

[0029] Figure 8 It is a three-dimensional structure schematic diagram of the second power control structure in the present invention.

[0030] In the figure: 1 - First power control structure, 2 - Second power control structure, 3 - Regulation component, 4 - Power control component, 5 - Adjustment processing mechanism, 6 - First hydraulic control rod, 7 - Docking protection ring, 8 - Second hydraulic control rod, 9 - First control unit, 10 - Matching hinge frame, 11 - Third hydraulic control rod, 12 - Combined end frame, 13 - Matching telescopic sleeve frame, 14 - Second control unit, 15 - Third control unit, 16 - Propeller, 17 - First fixed end block, 18 - First adapter connecting shaft, 19 - Second adapter connecting shaft, 20 - Second fixed end block, 21 - Combined top sleeve, 22 - Regulation groove seat, 23 - Matching key shaft, 24 - Engine, 25 - Protection docking seat, 26 - Fuel storage seat, 27 - First regulation valve seat, 28 - Second regulation valve seat, 29 - Conical nozzle, 30 - Combustion chamber, 31 - Guide control pipe. Detailed implementation manner

[0031] In order to enable those skilled in the art of the present 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 of the embodiments. Based on the embodiments in this application, all other embodiments obtained by those of ordinary skill in the art without making creative efforts shall fall within the protection scope of this application.

[0032] The present invention will be further described below in conjunction with the accompanying drawings.

[0033] Embodiment

[0034] As Figure 1-8 shown, a dual-mode hybrid cycle rocket engine of the present invention includes a first power control structure 1 and a second power control structure 2. The first power control structure 1 is limitedly provided on the second power control structure 2, and the first power control structure 1 and the second power control structure 2 are connected and arranged in communication;

[0035] The first power control structure 1 is used for hovering processing, and there are three third hydraulic control rods 11, which change the positions of the first control unit 9, the second control unit 14, and the third control unit 15 on the regulation groove seat 22. The engine 24 controls the rotation of the matching key shaft 23 to perform drive control on the first control unit 9, the second control unit 14, and the third control unit 15. The protection docking seat 25 is communicated with the first regulation valve seat 27 and can provide operating power for the engine 24;

[0036] The second power control structure 2 is used for jet drive. The fuel storage seat 26 is communicated with the combustion chamber 30 through the second regulation valve seat 28, and power injection is performed in the conical nozzle 29 to control the movement of the first power control structure 1 and the second power control structure 2.

[0037] The first power control structure 1 includes a regulation component 3 and a power control component 4. The regulation component 3 is disposed above the power control component 4 in a limiting manner. The regulation component 3 can change its angle, and the power control component 4 is used for driving and controlling the operation.

[0038] The regulation component 3 includes an adjustment processing mechanism 5, a first hydraulic control rod 6, a docking protection ring 7, and a second hydraulic control rod 8. The adjustment processing mechanism 5 is telescopically adjusted by the bearing on the second hydraulic control rod 8, and the first hydraulic control rod 6 is installed on the adjustment processing mechanism 5 through the docking protection ring 7.

[0039] The adjustment processing mechanism 5 includes a first control unit 9, a mating hinge frame 10, a third hydraulic control rod 11, a combined end frame 12, a mating telescopic sleeve frame 13, a second control unit 14, and a third control unit 15. The mating telescopic sleeve frame 13 is designed to be telescopic. The top of the mating telescopic sleeve frame 13 is fixedly connected to the combined end frame 12. The third hydraulic control rod 11 is hingedly provided on the combined end frame 12. The upper end of the third hydraulic control rod 11 is hingedly arranged with the mating hinge frame 10, and the first control unit 9 is fixedly connected to the mating hinge frame 10.

[0040] There are three mating hinge frames 10 and third hydraulic control rods 11, and they are evenly distributed around the combined end frame 12. One side of the mating hinge frames 10 and third hydraulic control rods 11 is connected to the second control unit 14, and the other side of the mating hinge frames 10 and third hydraulic control rods 11 is connected to the third control unit 15. And the three third hydraulic control rods 11 are controlled by a unified hydraulic system.

[0041] The first control unit 9, the second control unit 14, and the third control unit 15 have the same structure. The first control unit 9 includes a propeller 16, a first fixed-end block 17, a first adapter connecting shaft 18, a second adapter connecting shaft 19, and a second fixed-end block 20. The rear end of the first adapter connecting shaft 18 is fixedly connected to the second adapter connecting shaft 19. The first adapter connecting shaft 18 is fixedly arranged on the first fixed-end block 17, and the second adapter connecting shaft 19 is fixedly arranged on the second fixed-end block 20. The propeller 16 is hingedly arranged on the first adapter connecting shaft 18 and the second adapter connecting shaft 19. When propulsion is carried out in the combustion chamber 30, the second adapter connecting shaft 19 should not be in a horizontal state at this time. At this time, the second hydraulic control rod 8 and the first hydraulic control rod 6 control and cooperate with the telescopic sleeve frame 13 to telescopically adjust, changing the telescopic length of the telescopic sleeve frame 13 on the mating key shaft 23. Moreover, the second hydraulic control rod 8 is rotatably connected to the combined end frame 12 and the upper end of the telescopic sleeve frame 13 through bearings, without affecting the rotation of the combined end frame 12 and the telescopic sleeve frame 13. At the same time, the third hydraulic control rod 11 can be telescopically adjusted. The lower end of the third hydraulic control rod 11 is hingedly arranged with the combined end frame 12, and the upper end of the third hydraulic control rod 11 is hingedly arranged with the mating hinge frame 10 to control the rotation of the first control unit 9, the second control unit 14, and the third control unit 15. At this time, the propeller 16 rotates and adjusts on the first adapter connecting shaft 18 and the second adapter connecting shaft 19. The first fixed-end block 17 and the second fixed-end block 20 are fixed to the control groove base 22 to achieve the purpose of installation and fixation, so as to be able to adjust the propeller 16 to a longitudinal state and reduce air resistance.

[0042] The power control component 4 includes a combined top sleeve 21, a regulation groove seat 22, a mating key shaft 23, an engine 24, and a protection docking seat 25. When reaching the designated position, the second regulation valve seat 28 can control the fuel and oxidant to be guided onto the guiding control pipe 31, and then guided to the inside of the protection docking seat 25 through the first regulation valve seat 27, and then transmitted into the engine 24. Ignition occurs inside the engine 24, thereby controlling the rotation of the mating key shaft 23. At this time, the mating key shaft 23 can control the rotation of the first control unit 9, the second control unit 14, and the third control unit 15 through the regulation groove seat 22, thereby performing hovering control and lifting operations. The protection docking seat 25 is communicatively connected with the engine 24. The engine 24 is drivingly connected with the mating key shaft 23. The mating key shaft 23 is fixedly connected with the regulation groove seat 22. The regulation groove seat 22 is fixedly connected with the combined top sleeve 21. Through the structural arrangement of the regulation component 3, it is convenient to carry out regulation work. Among them, the second hydraulic control rod 8 can control the movement of the combined end frame 12 and the mating telescopic sleeve frame 13, so that the mating telescopic sleeve frame 13 is limited in telescopic adjustment on the mating key shaft 23, changing the heights of the combined end frame 12 and the mating telescopic sleeve frame 13, thereby carrying out regulation work. At the same time, the third hydraulic control rod 11 can be telescopically adjusted. The third hydraulic control rod 11 is hingedly arranged with the first control unit 9 through the mating hinge frame 10, and can make the propeller 16 be hingedly arranged around the first adapter connecting shaft 18 and the second adapter connecting shaft 19, changing the angular position of the propeller 16, thereby facilitating the regulation work in cooperation with aerodynamics. The engine 24 can control the rotation of the regulation groove seat 22 through the mating key shaft 23, making the first control unit 9, the second control unit 14, and the third control unit 15 rotate, and cooperating to perform hovering work.

[0043] The second power control structure 2 includes a fuel storage seat 26, a first regulation valve seat 27, a second regulation valve seat 28, a conical nozzle 29, a combustion chamber 30, and a guiding control pipe 31. The upper end of the conical nozzle 29 is communicatively connected with the combustion chamber 30. The upper end of the combustion chamber 30 is communicatively connected with the second regulation valve seat 28. The upper end of the second regulation valve seat 28 is communicatively connected with the fuel storage seat 26, and the center of the second regulation valve seat 28 is also communicatively connected with the guiding control pipe 31. The upper center of the guiding control pipe 31 is communicatively connected with the first regulation valve seat 27. Through the fuel storage seat 26, fuel and oxidant can be guided, so that the fuel and oxidant are guided into the second regulation valve seat 28. The second regulation valve seat 28 can control the guiding direction. When the second regulation valve seat 28 controls the fuel and oxidant to be guided into the combustion chamber 30, ignition can occur inside the combustion chamber 30, and thus the flame is ejected through the conical nozzle 29 to perform guiding and driving work.

[0044] The second regulating valve seat 28 can divert and transfer the fuel on the fuel storage seat 26. The fuel storage seat 26 can communicate with the combustion chamber 30 through the second regulating valve seat 28. The fuel storage seat 26 can also communicate with the protection docking seat 25 through the second regulating valve seat 28, the guiding control pipe 31, and the first regulating valve seat 27. The lower end of the protection docking seat 25 is fixedly connected and communicated with the first regulating valve seat 27.

[0045] It is slidably connected with the cooperating telescopic sleeve frame 13 on the cooperating key shaft 23. The first fixed end block 17 and the second fixed end block 20 are fixedly connected to the regulating groove seat 22. The cooperating hinge frame 10 is fixed on the propeller 16. The first hydraulic control rod 6 is fixed on the lower side of the regulating groove seat 22. The second hydraulic control rod 8 is fixed on the upper side of the protection docking seat 25. The regulating groove seat 22 is provided with a groove for the movement of the propeller 16.

[0046] The working principle is as follows: When in use, the fuel storage seat 26 can guide the fuel and the oxidant, so that the fuel and the oxidant are guided into the second regulating valve seat 28. The second regulating valve seat 28 can control the guiding direction. When the second regulating valve seat 28 controls the fuel and the oxidant to be guided into the combustion chamber 30, ignition can occur in the combustion chamber 30, and then the flame is ejected through the conical nozzle 29 to perform the guiding and driving work.

[0047] When reaching the designated position, at this time, the second regulating valve seat 28 can control the fuel and the oxidant to be guided onto the guiding control pipe 31, and then guided into the interior of the protection docking seat 25 through the first regulating valve seat 27, and then transmitted into the engine 24, where ignition occurs in the engine 24, so as to control the rotation of the cooperating key shaft 23. At this time, the cooperating key shaft 23 can control the rotation of the first control unit 9, the second control unit 14, and the third control unit 15 through the regulating groove seat 22, so as to perform hovering control and lifting operations.

[0048] When the propulsion is carried out in the combustion chamber 30, the second adaptively connected shaft 19 should not be in a horizontal state at this time. At this time, the second hydraulic control rod 8 and the first hydraulic control rod 6 control and cooperate with the telescopic sleeve frame 13 to telescopically adjust, changing the telescopic length of the telescopic sleeve frame 13 on the mating key shaft 23. Moreover, the second hydraulic control rod 8 is rotationally connected to the combined end frame 12 and the upper end of the telescopic sleeve frame 13 through bearings, without affecting the rotation of the combined end frame 12 and the telescopic sleeve frame 13. At the same time, the third hydraulic control rod 11 can be telescopically controlled, and the lower end of the third hydraulic control rod 11 is hinged to the combined end frame 12, and the upper end of the third hydraulic control rod 11 is hinged to the mating hinge frame 10 to control the rotation of the first control unit 9, the second control unit 14, and the third control unit 15. At this time, the propeller 16 rotates and adjusts on the first adaptively connected shaft 18 and the second adaptively connected shaft 19. The first fixed end block 17 and the second fixed end block 20 are fixed to the control groove seat 22 to achieve the purpose of installation and fixation, so that the propeller 16 can be adjusted to a longitudinal state, reducing air resistance and completing the work.

[0049] 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 dual-mode hybrid cycle rocket engine, characterized in that: It includes a first power control structure (1) and a second power control structure (2). The first power control structure (1) is disposed at the upper limit of the second power control structure (2), and the first power control structure (1) and the second power control structure (2) are connected and arranged. The first power control structure (1) is used for hovering processing, and there are three third liquid control rods (11). It changes the positions of the first control unit (9), the second control unit (14), and the third control unit (15) on the control groove seat (22), and the engine (24) controls the rotation of the key shaft (23) to drive and control the first control unit (9), the second control unit (14), and the third control unit (15). Moreover, the protection docking seat (25) is communicated with the first control valve seat (27) and can provide operating power for the engine (24). The second power control structure (2) is used for jet drive. The fuel storage seat (26) is communicated with the combustion chamber (30) through the second control valve seat (28), and power injection is carried out in the conical nozzle (29) to control the movement of the first power control structure (1) and the second power control structure (2).

2. A dual-mode hybrid cycle rocket engine according to claim 1, characterized in that: The first power control structure (1) includes a control component (3) and a power control component (4). The control component (3) is disposed at the upper limit of the power control component (4), and the control component (3) can change the angle, and the power control component (4) is used for driving and controlling the work.

3. The dual-mode hybrid cycle rocket engine according to claim 2, wherein: The control component (3) includes an adjustment processing mechanism (5), a first hydraulic control rod (6), a docking protection ring (7), and a second hydraulic control rod (8). The second hydraulic control rod (8) controls the telescopic adjustment of the adjustment processing mechanism (5) through a bearing, and the first hydraulic control rod (6) is installed on the adjustment processing mechanism (5) through the docking protection ring (7).

4. A dual-mode hybrid cycle rocket engine according to claim 3, characterized in that: The adjustment processing mechanism (5) includes a first control unit (9), a mating hinge frame (10), a third liquid control rod (11), a combined end frame (12), a mating telescopic sleeve frame (13), a second control unit (14), and a third control unit (15). The mating telescopic sleeve frame (13) adopts a telescopic design. The top of the mating telescopic sleeve frame (13) is fixedly connected to the combined end frame (12). The third liquid control rod (11) is hinged on the combined end frame (12). The upper end of the third liquid control rod (11) is hinged to the mating hinge frame (10), and the first control unit (9) is fixedly connected to the mating hinge frame (10).

5. A dual-mode hybrid cycle rocket engine according to claim 4, characterized in that: There are three of the mating hinge frames (10) and the third liquid control rods (11), and they are evenly distributed around the combined end frame (12). One side of the mating hinge frame (10) and the third liquid control rod (11) is connected to the second control unit (14), and the other side of the mating hinge frame (10) and the third liquid control rod (11) is connected to the third control unit (15), and the three third liquid control rods (11) are controlled by a unified hydraulic system.

6. A dual-mode hybrid cycle rocket engine according to claim 5, characterized in that: The first control unit (9), the second control unit (14), and the third control unit (15) have the same structure. The first control unit (9) includes a propeller (16), a first fixed end block (17), a first mating connecting shaft (18), a second mating connecting shaft (19), and a second fixed end block (20). The rear end of the first mating connecting shaft (18) is fixedly connected to the second mating connecting shaft (19). The first mating connecting shaft (18) is fixedly arranged on the first fixed end block (17), and the second mating connecting shaft (19) is fixedly arranged on the second fixed end block (20). The propeller (16) is hingedly arranged on the first mating connecting shaft (18) and the second mating connecting shaft (19).

7. A dual-mode hybrid cycle rocket engine according to claim 6, characterized in that: The power control component (4) includes a combined top sleeve (21), a regulating groove seat (22), a mating key shaft (23), an engine (24), and a protection docking seat (25). The engine (24) is communicated and arranged on the protection docking seat (25). The mating key shaft (23) is drivingly connected to the engine (24). The regulating groove seat (22) is fixedly connected to the mating key shaft (23), and the combined top sleeve (21) is fixedly connected to the regulating groove seat (22).

8. A dual-mode hybrid cycle rocket engine according to claim 7, characterized in that: The second power control structure (2) includes a fuel storage seat (26), a first regulating valve seat (27), a second regulating valve seat (28), a conical nozzle (29), a combustion chamber (30), and a guiding control pipe (31). The upper end of the conical nozzle (29) is communicated with the combustion chamber (30). The upper end of the combustion chamber (30) is communicated with the second regulating valve seat (28). The upper end of the second regulating valve seat (28) is communicated with the fuel storage seat (26), and the center of the second regulating valve seat (28) is also communicated with the guiding control pipe (31). The upper center of the guiding control pipe (31) is communicated with the first regulating valve seat (27).

9. A dual-mode hybrid cycle rocket engine according to claim 8, characterized in that: The second regulating valve seat (28) can split and transmit the fuel on the fuel storage seat (26). The fuel storage seat (26) can be communicated with the combustion chamber (30) through the second regulating valve seat (28). The fuel storage seat (26) can also be communicated with the protection docking seat (25) through the second regulating valve seat (28), the guiding control pipe (31), and the first regulating valve seat (27). The lower end of the protection docking seat (25) is fixedly and communicatively arranged with the first regulating valve seat (27).

10. A dual-mode hybrid cycle rocket engine according to claim 9, characterized in that: The mating telescopic sleeve frame (13) is slidably connected to the mating key shaft (23). The first fixed end block (17) and the second fixed end block (20) are fixedly connected to the regulating groove seat (22). The mating hinge frame (10) is fixed to the propeller (16). The first hydraulic control rod (6) is fixed to the lower side of the regulating groove seat (22), and the second hydraulic control rod (8) is fixed to the upper side of the protection docking seat (25). The regulating groove seat (22) is provided with a groove for the movement of the propeller (16).

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