Solid-liquid mixed combined ramjet engine

Abstract

The invention relates to the technical field of rocket engines, in particular to a solid-liquid mixed combined type ramjet engine which comprises a rocket body, supporting parts are fixedly installed at the front end of the rocket body and distributed annularly, and a spray pipe system is fixedly installed at the front end of each supporting part and connected with the rocket body. The supporting part comprises a positioning device, a transmission device and a displacement device, the displacement device is slidably inserted into the inner center of the positioning device, and the transmission device is fixedly installed in the positioning device and located above the displacement device; the positioning device comprises a positioning cavity, a combustion chamber, a heat insulation sleeve layer, a solid fuel column, a guide sleeve, a connecting base frame, a driving motor, a transmission worm, a movable hole and a limiting groove, the combustion chamber is fixedly installed at the front end of the positioning cavity, the heat insulation sleeve layer is fixedly installed on the inner wall of the combustion chamber, and the solid fuel column is fixedly installed on the inner wall of the heat insulation sleeve layer. And through the arrangement of the supporting component, the purpose that an oxidizing agent can be injected into different areas in the combustion column is achieved.

Description

Technical Field

[0001] This invention relates to the field of rocket engine technology, specifically to a solid-liquid hybrid ramjet rocket engine. Background Technology

[0002] A rocket engine is a jet engine that carries its own propellant. It does not rely on external air and can operate in space beyond the dense atmosphere. Rocket engines operate on the impulse principle, converting the reactants (propellant) within the propellant tank or launch vehicle into a high-speed jet, generating thrust according to Newton's third law of motion. Energy is converted into the kinetic energy of the working medium within the rocket engine, forming a high-speed jet that is then expelled, thus producing thrust.

[0003] Rocket engines have wide applications in the aerospace field, including launch vehicles, spacecraft propulsion, and missiles. With the continuous development of aerospace technology, rocket engines are also constantly being improved and innovated. For example, China has achieved new breakthroughs in reusable rocket engines, and the hydraulic test of the turbopump of the Liqing-2 needle-bolt engine was a complete success. Furthermore, new propellants, new engine structures, and advanced control systems are constantly emerging, injecting new vitality into the development of rocket engines.

[0004] For example, the rocket engine with Chinese patent publication number CN105822459B has a combustion chamber at the tail of the casing, and a nozzle is provided on the nozzle of the combustion chamber. Inside the casing, there are a propellant tank, an oxidizer tank, a propellant delivery pump assembly, and an oxidizer delivery pump assembly. The outlet of the propellant tank is connected to the inlet of the propellant delivery pump assembly via a first propellant delivery pipe. A second propellant delivery pipe is installed on the outlet of the propellant delivery pump assembly. The outlet of the oxidizer tank is connected to the inlet of the oxidizer delivery pump assembly via a first oxidizer delivery pipe. A second oxidizer delivery pipe is installed on the outlet of the oxidizer delivery pump assembly.

[0005] Currently, existing solid-liquid hybrid rocket engines suffer from incomplete combustion because the internal fuel column needs to work with the oxidizer during combustion, and the oxidizer usually only enters the interior of the combustion chamber. As a result, the oxidizer cannot make uniform contact with the fuel column, leading to incomplete combustion of the fuel column and oxidizer. Therefore, an improved device is needed to address these issues. Summary of the Invention

[0006] To address the problems in the prior art, the present invention provides a solid-liquid hybrid combined ramjet rocket engine.

[0007] The technical solution adopted by this invention to solve its technical problem is: a solid-liquid hybrid combined ramjet rocket engine, comprising a rocket body, a support component fixedly installed at the front end of the rocket body, the support component being arranged in a ring, a nozzle system fixedly installed at the front end of the support component, the support component including a positioning device, a transmission device, and a displacement device, the displacement device being slidably inserted into the internal center of the positioning device, the transmission device being fixedly installed inside the positioning device and located above the displacement device, the positioning device including a positioning cavity, a combustion chamber, a heat insulation layer, a solid fuel column, and a combustion chamber. The system comprises a guide sleeve, a connecting base frame, a drive motor, a transmission worm gear, a movable hole, and a limiting groove. The combustion chamber is fixedly installed at the front end of the positioning cavity. The heat insulation sleeve is fixedly installed on the inner wall of the combustion chamber. The solid fuel column is fixedly installed on the inner wall of the heat insulation sleeve. The connecting base frame is symmetrically fixedly installed inside the positioning cavity. The guide sleeve is fixedly installed between two connecting base frames. The movable hole is opened at the inner center of the guide sleeve. The limiting groove is symmetrically opened on both sides of the movable hole. The drive motor is symmetrically fixedly installed at the top front end of the guide sleeve. The transmission worm gear is fixedly installed at the center front end of the drive motor.

[0008] Specifically, the transmission device includes a contact swing arm, an extension side frame, a connecting shaft, a photoelectric sensor, a first gear, a second gear, an extension front frame, a transmission worm gear, and a support side frame. The transmission worm gear is rotatably mounted on the outside of the extension front frame, the second gear is fixedly mounted between the two transmission worm gears, the extension side frame is fixedly mounted at the front end of the extension front frame, the photoelectric sensor is fixedly mounted on the side end of the extension side frame near the second gear, the support side frame is fixedly mounted at the top end of the extension side frame, the connecting shaft is rotatably mounted between the two support side frames, the first gear is symmetrically fixedly mounted on the outer ring of the connecting shaft, and the contact swing arm is fixedly mounted on the side end of the first gear away from the second gear.

[0009] Specifically, the displacement device includes a guide nozzle, an alignment nozzle, a sealing circular plate, a contact rack, a connecting pipe joint, a solenoid valve, and a limiting crossbeam. The solenoid valve is fixedly installed at the rear end of the guide nozzle, the connecting pipe joint is fixedly installed at the rear end of the solenoid valve, the limiting crossbeam is fixedly installed on both sides of the guide nozzle, the contact rack is fixedly installed at the top center of the guide nozzle, the sealing circular plate is fixedly installed at the front end of the outer ring of the guide nozzle, and the alignment nozzle is fixedly installed on the outer ring of the guide nozzle near the sealing circular plate, and the alignment nozzle is arranged in a ring.

[0010] Specifically, the positioning cavity is fixedly installed at the front end of the rocket body, the extended front frame is fixedly installed at the front end of the guide sleeve, and the extended front frame is located below the drive motor, with the second gear meshing with the first gear.

[0011] Specifically, the transmission worm gear meshes with the transmission worm, the guide nozzle is slidably inserted into the interior of the movable hole, and the first gear and the second gear are flush with the side ends near the transmission worm gear.

[0012] Specifically, the alignment nozzle is vertically aligned with the inner wall of the solid fuel column, the second gear meshes with the contact rack, the two sides of the second gear are spaced 2 cm apart from the inner wall of the extended front frame, and the limiting crossbar is slidably inserted into the inside of the limiting groove.

[0013] Specifically, the guide nozzle is hollow inside and is interconnected with the solenoid valve. The outer surface of the sealing disc is in contact with the inner wall of the solid fuel column. The transmission ratio between the second gear and the first gear is 1:10. The photoelectric sensor and the solenoid valve are connected by a wireless signal.

[0014] Specifically, the nozzle system is fixedly installed at the front end of the combustion chamber, the alignment nozzle is internally connected to the guide nozzle, and the connecting pipe joint is internally connected to the solenoid valve.

[0015] Specifically, the positioning cavity also includes a wire collection groove and a limiting side plate. The wire collection groove is fixedly installed inside the rear end of the positioning cavity, and the limiting side plate is symmetrically fixedly installed on both sides inside the wire collection groove.

[0016] Specifically, the top of the opposite sides of the limiting side plates are inclined at 45°, and the two limiting side plates are spaced 5 centimeters apart.

[0017] The beneficial effects of this invention are:

[0018] When this device is in use, the drive motor starts, which drives the transmission worm gear to rotate. The rotation of the worm gear, in turn, drives the second gear to rotate. This second gear, in turn, displaces the contact rack, allowing the positioning nozzle to move within the solid fuel column. Simultaneously, the rotation of the second gear intermittently drives the contact swing arm to rotate until it contacts the photoelectric sensor. This causes the photoelectric sensor to intermittently close the solenoid valve, preventing oxidizer waste. Furthermore, the sealing plate's contact with the inner wall of the solid fuel column prevents the positioning nozzle from moving backward during oxidizer injection. The self-locking mechanism between the transmission worm gear and the transmission worm wheel prevents the contact rack from slipping. The limiting crossarm's movement within the limiting groove supports the guide nozzle's linear displacement within the solid fuel column, ensuring the positioning nozzle uniformly sprays oxidizer into different areas within the solid fuel column. Attached Figure Description

[0019] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0020] Figure 1 This is a three-dimensional structural diagram of the main body from a frontal perspective in this invention;

[0021] Figure 2 This is a partial cross-sectional schematic diagram of the support component in this invention;

[0022] Figure 3 This is a three-dimensional structural diagram of the support component from a frontal view in this invention;

[0023] Figure 4 This is a partial cross-sectional schematic diagram of the positioning device in this invention;

[0024] Figure 5 In this invention Figure 4 A magnified view of part A;

[0025] Figure 6 This is a three-dimensional structural diagram of the transmission device from the front view in this invention;

[0026] Figure 7 This is a partial cross-sectional schematic diagram of the displacement device in this invention;

[0027] Figure 8 This is a rear-view three-dimensional structural diagram of the second embodiment of the positioning cavity in this invention.

[0028] In the diagram: 1-Supporting component, 2-Nozzle system, 3-Rocket body, 4-Positioning device, 5-Transmission device, 6-Displacement device, 7-Positioning cavity, 8-Combustion chamber, 9-Insulation jacket, 10-Solid fuel column, 11-Guide sleeve, 12-Connecting base frame, 13-Drive motor, 14-Transmission worm gear, 15-Moving hole, 16-Limiting groove, 17-Contact swing arm, 18-Extension side frame, 19-Connecting shaft, 20-Photoelectric sensor, 21-First gear, 22-Second gear, 23-Extension front frame, 24-Transmission worm gear, 25-Supporting side frame, 26-Guide nozzle, 27-Alignment nozzle, 28-Sealing circular plate, 29-Contact rack, 30-Connecting pipe joint, 31-Solenoid valve, 32-Limiting cross frame, 33-Collection trough, 34-Limiting side plate. Detailed Implementation

[0029] To enable those skilled in the art to better understand the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present application, and not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative effort should fall within the scope of protection of the present application.

[0030] The invention will be further described below with reference to the accompanying drawings.

[0031] Example 1

[0032] like Figure 1 , Figure 2 , Figure 3 , Figure 4 and Figure 5 As shown, a solid-liquid hybrid combined ramjet rocket engine of the present invention includes a rocket body 3. A support component 1 is fixedly installed at the front end of the rocket body 3, and the support component 1 is arranged in a ring. A nozzle system 2 is fixedly installed at the front end of the support component 1. The support component 1 includes a positioning device 4, a transmission device 5, and a displacement device 6. The displacement device 6 is slidably inserted into the center of the positioning device 4. The transmission device 5 is fixedly installed inside the positioning device 4 and is located above the displacement device 6. The positioning device 4 includes a positioning cavity 7, a combustion chamber 8, a heat insulation layer 9, a solid fuel column 10, a guide sleeve 11, a connecting base frame 12, and a drive unit. The drive motor 13, transmission worm gear 14, movable hole 15, and limiting groove 16 are provided. The combustion chamber 8 is fixedly installed at the front end of the positioning cavity 7. The heat insulation sleeve 9 is fixedly installed on the inner wall of the combustion chamber 8. The solid fuel column 10 is fixedly installed on the inner wall of the heat insulation sleeve 9. The connecting base frame 12 is symmetrically fixedly installed inside the positioning cavity 7. The guide sleeve 11 is fixedly installed between the two connecting base frames 12. The movable hole 15 is opened in the inner center of the guide sleeve 11. The limiting groove 16 is symmetrically opened on both sides of the movable hole 15. The drive motor 13 is symmetrically fixedly installed at the front top of the guide sleeve 11. The transmission worm gear 14 is fixedly installed in the front center of the drive motor 13.

[0033] like Figure 6 The transmission device 5 includes a contact swing arm 17, an extension side frame 18, a connecting shaft 19, a photoelectric sensor 20, a first gear 21, a second gear 22, an extension front frame 23, a transmission worm gear 24, and a support side frame 25. The transmission worm gear 24 is rotatably mounted on the outside of the extension front frame 23, the second gear 22 is fixedly mounted between the two transmission worm gears 24, the extension side frame 18 is fixedly mounted on the front end of the extension front frame 23, the photoelectric sensor 20 is fixedly mounted on the side end of the extension side frame 18 near the second gear 22, the support side frame 25 is fixedly mounted on the top end of the extension side frame 18, and the connecting shaft 19 is rotatably mounted on... Between the two support side frames 25, the first gear 21 is symmetrically fixedly mounted on the outer ring of the connecting shaft 19, and the contact swing arm 17 is fixedly mounted on the side end of the first gear 21 away from the second gear 22. When the transmission worm gear 24 rotates, it can drive the contact rack 29 to move through the second gear 22, so that the alignment nozzle 27 can spray oxidant at different positions inside the solid fuel column 10. Furthermore, when the second gear 22 rotates, it can drive the contact swing arm 17 to intermittently pass over the surface of the photoelectric sensor 20 through the first gear 21, which facilitates the intermittent release of oxidant.

[0034] like Figure 7 The displacement device 6 includes a guide nozzle 26, an alignment nozzle 27, a sealing circular plate 28, a contact rack 29, a connecting pipe joint 30, a solenoid valve 31, and a limiting crossbeam 32. The solenoid valve 31 is fixedly installed at the rear end of the guide nozzle 26, the connecting pipe joint 30 is fixedly installed at the rear end of the solenoid valve 31, the limiting crossbeam 32 is fixedly installed on both sides of the guide nozzle 26, the contact rack 29 is fixedly installed at the center of the top end of the guide nozzle 26, the sealing circular plate 28 is fixedly installed at the front end of the outer ring of the guide nozzle 26, and the alignment nozzle 27 is fixedly installed... On the outer ring of the guide nozzle 26 near the sealing disc 28, and with the alignment nozzles 27 arranged in a ring, the outer ring surface of the sealing disc 28 is in contact with the inner ring surface of the solid fuel column 10, so that the oxidant can be prevented from splashing to the rear end of the inner wall of the solid fuel column 10. At the same time, through the interconnection between the connecting pipe joint 30, the solenoid valve 31, the guide nozzle 26 and the alignment nozzles 27, the solenoid valve 31 can push the oxidant into the interior of the guide nozzle 26 when it is running, and finally spray it onto the inner wall of the solid fuel column 10 by the alignment nozzles 27.

[0035] The positioning cavity 7 is fixedly installed at the front end of the rocket body 3, and the extended front frame 23 is fixedly installed at the front end of the guide sleeve 11, with the extended front frame 23 located below the drive motor 13. The second gear 22 meshes with the first gear 21, the transmission worm gear 24 meshes with the transmission worm 14, and the guide nozzle 26 is slidably inserted into the interior of the movable hole 15. The sides of the first gear 21 and the second gear 22 are flush with the sides of the transmission worm gear 24. The alignment nozzle 27 is vertically aligned with the inner wall of the solid fuel column 10. The second gear 22 meshes with the contact rack 29, and the two sides of the second gear 22 are flush with the inner walls of the extended front frame 23. The walls are spaced 2 cm apart. The limiting crossbar 32 is slidably inserted into the limiting groove 16. The inside of the guide nozzle 26 is hollow and is interconnected with the inside of the solenoid valve 31. The outer surface of the sealing plate 28 is in contact with the inner wall surface of the solid fuel column 10. The transmission ratio of the second gear 22 to the first gear 21 is 1:10. There is a wireless signal connection between the photoelectric sensor 20 and the solenoid valve 31. The nozzle system 2 is fixedly installed at the front end of the combustion chamber 8. The alignment nozzle 27 is interconnected with the inside of the guide nozzle 26. The connecting pipe joint 30 is interconnected with the inside of the solenoid valve 31.

[0036] The working principle of Example 1 is as follows: In use, the connecting pipe joint 30 is first connected to the oxidizer storage device inside the rocket body 3. An igniter is installed at the front end of the combustion chamber 8, igniting the solid fuel column 10. Simultaneously, when the solid fuel column 10 is ignited, the pump in the oxidizer storage device is activated, allowing the pump to deliver the oxidizer from the connecting pipe joint 30 and the solenoid valve 31 to the interior of the guide nozzle 26. At the same time, the alignment nozzle 27 communicates with the interior of the guide nozzle 26, allowing the alignment nozzle 27 to spray the oxidizer onto the inner wall of the solid fuel column 10. Meanwhile, by ensuring the outer surface of the sealing disc 28 is in contact with the inner wall surface of the solid fuel column 10, oxidizer splashing onto the solid fuel column is prevented. At the rear end of the inner wall of 10, the drive motor 13 can be started to drive the transmission worm 14 to rotate. The transmission worm 14 meshes with the transmission worm wheel 24, so that the transmission worm 14 can drive the transmission worm wheel 24 to rotate. When the transmission worm wheel 24 rotates, it can drive the contact rack 29 to move through the second gear 22, so that the contact rack 29 can drive the guide nozzle 26 to move to the rear end inside the solid fuel column 10. Thus, according to the combustion speed of the solid fuel column 10, the positioning nozzle 27 can be moved to the corresponding position, which can ensure sufficient contact between the oxidant and the solid fuel column 10. In addition, the guide nozzle 26 can be supported to move in a straight line by the sliding of the limiting crossbar 32 inside the limiting groove 16. At the same time, the oxygen is connected through the connecting pipe joint 30. A flexible hose is installed between the pump bodies in the oxidizer storage device to facilitate the rearward displacement of the guide nozzle 26. A self-locking mechanism between the transmission worm gear 14 and the transmission worm wheel 24 prevents the guide nozzle 26 from shifting again. Simultaneously, when the second gear 22 rotates, it also drives the first gear 21 to rotate. When the first gear 21 rotates, it drives the contact arm 17 past the photoelectric sensor 20. When the contact arm 17 contacts the photoelectric sensor 20, it closes the solenoid valve 31, temporarily stopping the oxidizer injection. Subsequently, when the contact arm 17 passes the photoelectric sensor 20, the solenoid valve 31 reopens, allowing it to continuously supply oxidizer to the interior of the guide nozzle 26, preventing the oxidizer from being discharged. To avoid excessive waste, this device, during use, allows the guide nozzle 26 to slide within the movable hole 15, enabling it to move rearward. Simultaneously, the second gear 22 quickly drives the first gear 21 to rotate, preventing prolonged contact between the contact arm 17 and the photoelectric sensor 20, thus avoiding insufficient fuel supply within the solid fuel column 10. Furthermore, the fact that the side end of the contact arm 17 is flush with the surface of the photoelectric sensor 20 facilitates contact between them. Additionally, the gap between the contact arm 17 and the extended front frame 23 prevents interference between the contact arm 17 and the extended front frame 23 during rotation. During operation, the device is activated by the drive motor 13.The transmission worm gear 14 drives the transmission worm wheel 24 to rotate. When the transmission worm wheel 24 rotates, the second gear 22 drives the contact rack 29 to move rearward, allowing the guide nozzle 26 to move the alignment nozzle 27 to a designated position inside the solid fuel column 10. This ensures that the oxidizer is injected at the designated combustion position of the solid fuel column 10. Furthermore, during operation, the nozzle system 2 accelerates the ejection of the combusted gas to generate thrust, completing the combustion of the solid fuel column 10 and the oxidizer. During displacement, the guide nozzle 26 drives the first gear 21 to rotate via the second gear 22, allowing the contact swing arm 17 to intermittently pass over the surface of the photoelectric sensor 20. This intermittently operates the solenoid valve 31, preventing the alignment nozzle 27 from injecting excessive oxidizer and reducing oxidizer waste.

[0037] Example 2

[0038] Based on Example 1, such as Figure 8 As shown, the positioning cavity 7 also includes a wire collection groove 33 and a limiting side plate 34. The wire collection groove 33 is fixedly installed inside the rear end of the positioning cavity 7, and the limiting side plate 34 is symmetrically fixedly installed on both sides inside the wire collection groove 33. The top of the opposite side ends of the limiting side plate 34 is inclined at 45°, and the two limiting side plates 34 are spaced 5 cm apart.

[0039] In this embodiment, when the solenoid valve 31 moves the hose on the pump body of the oxidant storage device, the solenoid valve 31 is aligned with the inner center of the collection trough 33, allowing the hose to be placed inside the collection trough 33 for collection and restriction, preventing the hose from contacting the inner wall of the positioning cavity 7. At the same time, the top of the limiting side plate 34 is inclined at 45°, ensuring that the hose is always located in the inner center of the collection trough 33, preventing the hose from becoming disordered. In addition, the plastic layer installed on the surface of the limiting side plate 34 prevents excessive friction between the hose and the collection trough 33, improving the service life of the hose and completing the work of protecting and placing the hose.

[0040] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A solid-liquid hybrid combined ramjet rocket engine, comprising a rocket body (3), wherein a support component (1) is fixedly installed at the front end of the rocket body (3), and the support component (1) is arranged in a ring shape, and a nozzle system (2) is fixedly installed at the front end of the support component (1), characterized in that: The supporting component (1) includes a positioning device (4), a transmission device (5), and a displacement device (6). The displacement device (6) is slidably inserted into the center of the positioning device (4). The transmission device (5) is fixedly installed inside the positioning device (4) and is located above the displacement device (6). The positioning device (4) includes a positioning cavity (7), a combustion chamber (8), a heat insulation sleeve (9), a solid fuel column (10), a guide sleeve (11), a connecting base frame (12), a drive motor (13), a transmission worm gear (14), a movable hole (15), and a limiting groove (16). The combustion chamber (8) is fixedly installed in the positioning cavity (7). At the front end of the combustion chamber (8), the heat insulation sleeve (9) is fixedly installed on the inner wall of the combustion chamber (8), the solid fuel column (10) is fixedly installed on the inner wall of the heat insulation sleeve (9), the connecting base (12) is symmetrically fixedly installed inside the positioning cavity (7), the guide sleeve (11) is fixedly installed between the two connecting bases (12), the movable hole (15) is opened in the inner center of the guide sleeve (11), the limiting groove (16) is symmetrically opened on both sides inside the movable hole (15), the drive motor (13) is symmetrically fixedly installed at the front end top of the guide sleeve (11), and the transmission worm (14) is fixedly installed at the front end center of the drive motor (13).

2. The solid-liquid hybrid combined ramjet rocket engine according to claim 1, characterized in that: The transmission device (5) includes a contact swing arm (17), an extension side frame (18), a connecting shaft (19), a photoelectric sensor (20), a first gear (21), a second gear (22), an extension front frame (23), a transmission worm gear (24), and a support side frame (25). The transmission worm gear (24) is rotatably mounted on the outside of the extension front frame (23), and the second gear (22) is fixedly mounted between the two transmission worm gears (24). The extension side frame (18) is fixedly mounted on the extension front frame (25). At the front end of 23), the photoelectric sensor (20) is fixedly installed on the side end of the extension side frame (18) near the second gear (22), the support side frame (25) is fixedly installed on the top end of the extension side frame (18), the connecting shaft (19) is rotatably installed between the two support side frames (25), the first gear (21) is symmetrically fixedly installed on the outer ring of the connecting shaft (19), and the contact swing arm (17) is fixedly installed on the side end of the first gear (21) away from the second gear (22).

3. The solid-liquid hybrid combined ramjet rocket engine according to claim 2, characterized in that: The displacement device (6) includes a guide nozzle (26), an alignment nozzle (27), a sealing disc (28), a contact rack (29), a connecting pipe joint (30), a solenoid valve (31), and a limiting crossbar (32). The solenoid valve (31) is fixedly installed at the rear end of the guide nozzle (26), the connecting pipe joint (30) is fixedly installed at the rear end of the solenoid valve (31), the limiting crossbar (32) is fixedly installed on both sides of the guide nozzle (26), the contact rack (29) is fixedly installed at the top center of the guide nozzle (26), the sealing disc (28) is fixedly installed at the front end of the outer ring of the guide nozzle (26), and the alignment nozzle (27) is fixedly installed on the outer ring of the guide nozzle (26) near the sealing disc (28), and the alignment nozzle (27) is arranged in a ring.

4. A solid-liquid hybrid combined ramjet rocket engine according to claim 3, characterized in that: The positioning cavity (7) is fixedly installed at the front end of the rocket body (3), the extension front frame (23) is fixedly installed at the front end of the guide sleeve (11), and the extension front frame (23) is located below the drive motor (13). The second gear (22) meshes with the first gear (21).

5. A solid-liquid hybrid combined ramjet rocket engine according to claim 4, characterized in that: The transmission worm gear (24) meshes with the transmission worm (14), the guide nozzle (26) is slidably inserted into the interior of the movable hole (15), and the first gear (21) and the second gear (22) are flush with the side ends of the transmission worm gear (24).

6. A solid-liquid hybrid combined ramjet rocket engine according to claim 5, characterized in that: The alignment nozzle (27) is vertically aligned with the inner wall of the solid fuel column (10), the second gear (22) meshes with the contact rack (29), the two sides of the second gear (22) are spaced 2 cm apart from the inner wall of the extension front frame (23), and the limiting cross frame (32) is slidably inserted into the inside of the limiting groove (16).

7. A solid-liquid hybrid combined ramjet rocket engine according to claim 6, characterized in that: The interior of the guide nozzle (26) is hollow, and the guide nozzle (26) is interconnected with the interior of the solenoid valve (31). The outer surface of the sealing disc (28) is in contact with the inner wall surface of the solid fuel column (10). The transmission ratio between the second gear (22) and the first gear (21) is 1:

10. There is a wireless signal connection between the photoelectric sensor (20) and the solenoid valve (31).

8. A solid-liquid hybrid combined ramjet rocket engine according to claim 7, characterized in that: The nozzle system (2) is fixedly installed at the front end of the combustion chamber (8). The alignment nozzle (27) is internally connected to the guide nozzle (26), and the connecting pipe joint (30) is internally connected to the solenoid valve (31).

9. A solid-liquid hybrid combined ramjet rocket engine according to claim 8, characterized in that: The positioning cavity (7) also includes a wire collection groove (33) and a limiting side plate (34). The wire collection groove (33) is fixedly installed inside the rear end of the positioning cavity (7), and the limiting side plate (34) is symmetrically fixedly installed on both sides inside the wire collection groove (33).

10. A solid-liquid hybrid combined ramjet rocket engine according to claim 9, characterized in that: The top of the opposite side ends of the limiting side plates (34) are inclined at 45°, and the two limiting side plates (34) are spaced 5 cm apart.

Images