Double-medium self-adaptive pre-pressurization rocket engine

Abstract

The invention relates to the technical field of rocket engines, in particular to a double-medium self-adaptive pre-pressurization rocket engine which comprises an engine part, a rocket barrel is arranged outside the engine part, the engine part is fixedly arranged in the rocket barrel, a rocket front cover is fixedly connected to the upper end of the rocket barrel, and nozzles are evenly distributed at the bottom end of the rocket barrel. According to the invention, dual-medium cooperative driving is adopted, a high-pressure gas starting stage and a high-pressure liquid such as liquid oxygen steady-state stage are adopted for dual-medium driving of the pre-booster pump, the mass of a starting gas cylinder for storing fuel and an oxidizing agent is reduced, and the effective load is improved; seamless switching between a gas turbine and a liquid turbine is achieved, the pressure of a combustion chamber is ensured to be stable by adjusting supercharging pressure in real time, combustion efficiency reduction caused by pressure fluctuation is avoided, and the engine can operate efficiently under different working conditions such as take-off, cruise or orbital transfer.

Description

Technical Field

[0001] The invention relates to the technical field of rocket engine end covers, in particular to a dual-medium self-adaptive pre-pressurized rocket engine. Background Art

[0002] A rocket engine is a jet engine that uses its own fuel and oxidizer and does not rely on external air to operate. Its core structure includes a combustion chamber and a nozzle. The propellant burns to produce high-temperature, high-pressure combustion gas, which is accelerated by the nozzle to generate thrust. This characteristic makes it the only power device for space flight and can operate freely inside and outside the Earth's atmosphere. The propellant (fuel + oxidizer) undergoes a chemical reaction in the combustion chamber, releasing chemical energy and converting it into the kinetic energy of the high-temperature combustion gas. The combustion gas expands and accelerates through the nozzle, ejecting it at supersonic speed, generating reverse thrust to propel the rocket forward. For example, a liquid rocket engine uses a turbopump to inject propellants such as liquid oxygen and kerosene into the combustion chamber, where the mixed combustion generates thrust.

[0003] When starting a traditional cryogenic liquid rocket engine, it relies on high-pressure gas cylinders to provide an instantaneous high-flow gas to drive the turbopump, resulting in a high proportion of gas cylinder mass and a large system volume. In addition, when the existing rocket engine is running, the propellant has no initial pressure or insufficient initial pressure, and it needs to overcome pipeline resistance, which cannot fully ensure that the propellant enters the main turbopump smoothly and cannot ensure the full operation of the engine. Therefore, a dual-medium adaptive pre-boost rocket engine is needed to improve the above-mentioned problems. This engine is driven by dual media in a coordinated manner, using high-pressure gas in the starting phase and high-pressure liquid, such as liquid oxygen, in the steady-state phase to drive the pre-boost pump. This reduces the mass of the starting gas cylinders storing fuel and oxidizer and increases the payload. Through the provision of pressure sensors and flow rate sensors combined with the provision of pressure thresholds and flow matching algorithms, seamless switching between the gas turbine and the liquid turbine is achieved. In addition, by adjusting the boost pressure in real time, the combustion chamber pressure is ensured to be stable, avoiding the decrease in combustion efficiency due to pressure fluctuations, so that the engine can maintain efficient operation under different operating conditions such as takeoff, cruising or trajectory change. Summary of the Invention

[0004] In response to the problems in the prior art, the present invention provides a dual-medium adaptive pre-boost rocket engine.

[0005] The technical solution adopted by the present invention to solve its technical problems is: a dual-medium adaptive pre-boost rocket engine, including an engine part, a rocket launcher is arranged on the outside of the engine part, and the engine part is fixedly arranged inside the rocket launcher, the upper end of the rocket launcher is fixedly connected to the rocket front cover, and the bottom end of the rocket launcher is evenly distributed with nozzles.

[0006] Preferably, the engine portion includes a dual-medium adaptive pre-boost body and an engine body, and the engine body is arranged at the bottom end of the dual-medium adaptive pre-boost body.

[0007] Preferably, the dual-medium adaptive pre-boost body includes a first delivery pipe, a second delivery pipe, a mixing turbine pump, a third delivery pipe, a fourth delivery pipe, a fifth delivery pipe, a fuel storage tank and an oxidizer storage tank. The mixing turbine pump is fixedly connected to the bottom end of the third delivery pipe, the second delivery pipe and the fourth delivery pipe are symmetrically distributed, and the bottom ends of the second delivery pipe and the fourth delivery pipe are respectively fixedly connected to the two sides of the upper end of the third delivery pipe, the first delivery pipe is fixedly connected to the upper end of the second delivery pipe, and the fifth delivery pipe is fixedly connected to the upper end of the fourth delivery pipe. The bottom ends of the fuel storage tank and the oxidizer storage tank are respectively fixedly connected to the upper ends of the fifth delivery pipe and the first delivery pipe through a valve body. During the operation of the engine body, the high-pressure fuel and oxygen stored in the fuel storage tank and the oxidizer storage tank will be transported to the interior of the third delivery pipe through the fifth delivery pipe and the first delivery pipe, and then mixed through the mixing turbine pump. Under the action of the mixing turbine pump, the fuel and oxygen can be fully transported for operation.

[0008] Preferably, the first delivery pipe is connected to the interior of the second delivery pipe, the second delivery pipe is connected to the interior of the third delivery pipe, the fifth delivery pipe is connected to the interior of the fourth delivery pipe, and the fourth delivery pipe is connected to the interior of the third delivery pipe.

[0009] Preferably, the fuel storage tank and the oxidizer storage tank are respectively provided with a third clamping connecting frame and a fourth clamping connecting frame, and the fuel storage tank is fixedly mounted on the third clamping connecting frame, the oxidizer storage tank is fixedly mounted on the fourth clamping connecting frame, and fixing holes are evenly opened on the third clamping connecting frame and the fourth clamping connecting frame.

[0010] Preferably, the outer end of the first delivery pipe is fixedly connected to the first pressurized delivery pipe, the upper end of the first pressurized delivery pipe is fixedly connected to the first turbine outer frame, the first turbine outer frame has a first turbine rotatably mounted inside, and the upper end of the first turbine outer frame is fixedly connected to the first high-pressure storage tank.

[0011] Preferably, the outer end of the fifth delivery pipe is fixedly connected to the second pressurized delivery pipe, the upper end of the second pressurized delivery pipe is fixedly connected to the second turbine outer frame, the second turbine outer frame has a second turbine rotatably mounted inside, and the upper end of the second turbine outer frame is fixedly connected to the second high-pressure storage tank.

[0012] Preferably, solenoid valves are fixedly installed between the second high-pressure storage tank and the second turbine outer frame and between the first high-pressure storage tank and the first turbine outer frame, the second pressurized delivery pipe is connected to the fifth delivery pipe, and the first pressurized delivery pipe is connected to the first delivery pipe. A second clamping connection frame and a first clamping connection frame are provided on the outside of the second high-pressure storage tank and the first high-pressure storage tank, and the second high-pressure storage tank is fixedly installed on the second clamping connection frame, and the first high-pressure storage tank is fixedly installed on the first clamping connection frame, and fixing holes are provided on the first clamping connection frame and the mixing turbine pump.

[0013] Preferably, the bottom end of the mixing turbine pump is connected to the interior of the engine body through a third delivery pipe, the interior of the first high-pressure storage tank stores high-pressure gas, and the interior of the second high-pressure storage tank stores high-pressure liquid.

[0014] Preferably, a third pressure sensor and a third flow sensor are installed on the third delivery pipe. The flow rate and pressure of the mixture of the fuel and the oxidizer can be detected by the third pressure sensor and the third flow sensor, so as to indirectly control and adjust the solenoid valve to control the flow rate and flow of the gas or liquid injected into the first high-pressure storage tank and the second high-pressure storage tank according to the detected data, thereby fully adapting to play the role of precise pre-pressurization.

[0015] Beneficial effects of the present invention:

[0016] 1. The present invention adopts dual-medium synergistic drive, using both high-pressure gas in the starting phase and high-pressure liquid, such as liquid oxygen, in the steady-state phase to drive the pre-boost pump. This reduces the mass of the starting gas cylinders storing fuel and oxidizer, thereby increasing the payload. The pressure sensor and flow rate sensor, combined with the set pressure threshold and flow matching algorithm, achieve seamless switching between the gas turbine and the liquid turbine. Furthermore, by adjusting the boost pressure in real time, the combustion chamber pressure is ensured to be stable, avoiding the reduction in combustion efficiency due to pressure fluctuations. This allows the engine to maintain efficient operation under different operating conditions such as takeoff, cruising, or trajectory changes, thereby improving overall thrust performance. Adaptive pre-boost technology can reduce dependence on external high-pressure gas cylinders and achieve pressure regulation through an internal boost mechanism, thereby simplifying the system structure and reducing weight.

[0017] 2. During the operation of the engine body of the present invention, the high-pressure fuel and oxygen stored in the fuel storage tank and the oxidant storage tank will be transported to the interior of the third delivery pipe through the fifth delivery pipe and the first delivery pipe, and then mixed and passed through the mixing turbine pump. Under the action of the mixing turbine pump, the fuel and oxygen can be fully transported and operated. In the process of transporting the fuel and oxygen, the flow rate and pressure of the transported fuel and oxygen can be detected and monitored in real time through the second delivery pipe and the first flow sensor and the second pressure sensor and the second flow sensor. When the fuel and oxygen are initially transported and supplied, the gas stored in the first high-pressure storage tank is transported to the interior of the first turbine outer frame under the control of the solenoid valve, driving the first The turbine rotates at high speed and then pressurizes the oxygen, which is then transported to the interior of the first delivery pipe through the first pressure delivery pipe, thereby pressurizing the oxygen transported inside the first delivery pipe and quickly delivering and replenishing it. In the whole process, the first flow sensor and the first pressure sensor provided can detect the flow rate and pressure in real time, thereby indirectly controlling the control state of the solenoid valve at the bottom of the first high-pressure storage tank. Similarly, the second high-pressure storage tank can be provided, and the high-pressure liquid therein, such as liquid oxygen, can be used to pressurize the oxygen in the fuel storage tank and fully deliver it to the interior of the third delivery pipe through the fifth delivery pipe and the fourth delivery pipe, thereby effectively overcoming pipeline resistance and automatically performing detection and realizing automatic adjustment and control in the whole process. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The present invention will be further described below with reference to the accompanying drawings and examples.

[0019] Figure 1 This is a schematic diagram of the three-dimensional structure of the main body of the present invention from the front perspective;

[0020] Figure 2 Schematic diagram of the internal structure of the bazooka of the present invention;

[0021] Figure 3 This is a schematic diagram of the bottom structure of the rocket launcher in the present invention;

[0022] Figure 4 Schematic diagram of the internal structure of the engine part in the present invention;

[0023] Figure 5 It is a schematic diagram of the three-dimensional structure of the engine part in the present invention from a side view;

[0024] Figure 6 This is a schematic diagram of the dual-medium adaptive pre-boosting main structure of the present invention;

[0025] Figure 7 This is a schematic side view of the three-dimensional structure of the dual-medium adaptive pre-boosting body in the present invention;

[0026] Figure 8This is a schematic structural diagram of the second embodiment of the main body of the present invention.

[0027] In the figure: 1-rocket front cover, 2-bazooka, 3-nozzle, 4-engine part, 5-dual-medium adaptive pre-boost body, 6-engine body, 7-first high-pressure storage tank, 8-first fixed connecting frame, 9-first turbine outer frame, 10-first turbine, 11-first pressurized delivery pipe, 12-first delivery pipe, 13-second delivery pipe, 14-first flow sensor, 15-first pressure sensor, 16-mixing turbine pump, 17-third delivery pipe, 18-second pressure sensor, 19-second flow sensor, 20-fourth delivery pipe, 21-fifth delivery pipe, 22-second pressurized delivery pipe, 23-second turbine, 24-second turbine outer frame, 25-second high-pressure storage tank, 26-second fixed connecting frame, 27-solenoid valve, 28-fuel storage tank, 29-third fixed connecting frame, 30-oxidizer storage tank, 31-fourth fixed connecting frame, 32-third pressure sensor, 33-third flow sensor. DETAILED DESCRIPTION

[0028] Example 1

[0029] In order to enable people skilled in the art to better understand the solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work should fall within the scope of protection of this application.

[0030] It should be noted that the terms "first", "second", etc. in the specification and claims of this application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the data used in this way can be interchanged where appropriate, so as to describe the embodiments of the present application described herein. In addition, the terms "including" and "having" and any variations thereof are intended to cover non-exclusive inclusions. For example, a process, method, system, product or apparatus that includes a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or apparatuses.

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

[0032] like Figure 1-5As shown, the dual-medium adaptive pre-boost rocket engine of the present invention includes an engine part 4, a rocket launcher 2 is arranged outside the engine part 4, and the engine part 4 is fixedly arranged inside the rocket launcher 2, the upper end of the rocket launcher 2 is fixedly connected to the rocket front cover 1, and the bottom end of the rocket launcher 2 is evenly distributed with nozzles 3, the engine part 4 includes a dual-medium adaptive pre-boost main body 5 and an engine main body 6, and the engine main body 6 is arranged at the bottom end of the dual-medium adaptive pre-boost main body 5. The dual-medium adaptive pre-boost main body 5 can be used to fully supplement the interior of the engine main body 6 with sufficient fuel and oxidant, so that the engine main body 6 can operate fully, and the dual-medium synergistic drive adopts high-pressure gas to start The dual-medium driven pre-boost pump in the dynamic stage and the steady-state stage of high-pressure liquid, such as liquid oxygen, reduces the mass of the starting gas cylinders storing fuel and oxidizer, increases the effective load, and realizes seamless switching between the gas turbine and the liquid turbine through the set pressure sensor and flow rate sensor combined with the set pressure threshold and flow matching algorithm. In addition, the boost pressure is adjusted in real time to ensure the stability of the combustion chamber pressure and avoid the reduction of combustion efficiency due to pressure fluctuations, so that the engine can maintain efficient operation under different working conditions such as take-off, cruising or trajectory change, thereby improving the overall thrust performance. The adaptive pre-boost technology may reduce the dependence on external high-pressure gas cylinders and achieve pressure regulation through the internal boost mechanism, thereby simplifying the system structure and reducing weight.

[0033] like Figure 6-7As shown, the dual-medium adaptive pre-boost body 5 includes a first delivery pipe 12, a second delivery pipe 13, a mixing turbine pump 16, a third delivery pipe 17, a fourth delivery pipe 20, a fifth delivery pipe 21, a fuel storage tank 28 and an oxidizer storage tank 30. The mixing turbine pump 16 is fixedly connected to the bottom end of the third delivery pipe 17. The second delivery pipe 13 and the fourth delivery pipe 20 are symmetrically distributed, and the bottom ends of the second delivery pipe 13 and the fourth delivery pipe 20 are respectively fixedly connected to both sides of the upper end of the third delivery pipe 17. The first delivery pipe 12 is fixedly connected to the upper end of the second delivery pipe 13, the fifth delivery pipe 21 is fixedly connected to the upper end of the fourth delivery pipe 20, and the bottom ends of the fuel storage tank 28 and the oxidizer storage tank 30 are respectively connected to the fifth delivery pipe 17 through the valve body. 21 is fixedly connected to the upper end of the first delivery pipe 12, the first delivery pipe 12 is communicated with the interior of the second delivery pipe 13, the second delivery pipe 13 is communicated with the interior of the third delivery pipe 17, the fifth delivery pipe 21 is communicated with the interior of the fourth delivery pipe 20, and the fourth delivery pipe 20 is communicated with the interior of the third delivery pipe 17. The fuel storage tank 28 and the oxidizer storage tank 30 are respectively provided with a third clamping connection frame 29 and a fourth clamping connection frame 31, and the fuel storage tank 28 is fixedly mounted on the third clamping connection frame 29, and the oxidizer storage tank 30 is fixedly mounted on the fourth clamping connection frame 31, and fixing holes are evenly opened on the third clamping connection frame 29 and the fourth clamping connection frame 31. The outer end of the first delivery pipe 12 is fixedly connected to the first pressurized delivery pipe 1 The upper end of the first pressurized delivery pipe 11 is fixedly connected to the first turbine outer frame 9, the first turbine outer frame 9 is rotatably mounted with the first turbine 10, the upper end of the first turbine outer frame 9 is fixedly connected to the first high-pressure storage tank 7, the outer end of the fifth delivery pipe 21 is fixedly connected to the second pressurized delivery pipe 22, the upper end of the second pressurized delivery pipe 22 is fixedly connected to the second turbine outer frame 24, the second turbine outer frame 24 is rotatably mounted with the second turbine 23, the upper end of the second turbine outer frame 24 is fixedly connected to the second high-pressure storage tank 25, the high-pressure fuel and oxygen stored in the fuel storage tank 28 and the oxidant storage tank 30 will be delivered to the interior of the third delivery pipe 17 through the fifth delivery pipe 21 and the first delivery pipe 12 and then mixed. The turbine pump 16 is provided, and under the action of the mixing turbine pump 16, the fuel and oxygen can be fully transported and operated. During the process of transporting the fuel and oxygen, the flow rate and pressure of the transported fuel and oxygen can be detected and monitored in real time through the second delivery pipe 13, the first flow sensor 14, the second pressure sensor 18, and the second flow sensor 19. When the fuel and oxygen are initially transported and supplied, the gas stored in the first high-pressure storage tank 7 is transported to the inside of the first turbine outer frame 9 under the control of the solenoid valve 27, driving the first turbine 10 to rotate at high speed and pressurize, and then transported to the inside of the first delivery pipe 12 through the first pressurized delivery pipe 11, thereby pressurizing the oxygen transported in the first delivery pipe 12 and quickly transporting and replenishing it.Throughout the entire process, the first flow sensor 14 and first pressure sensor 15 can monitor flow rate and pressure in real time, thereby indirectly controlling the state of the solenoid valve 27 at the bottom of the first high-pressure storage tank 7. Similarly, the second high-pressure storage tank 25 can utilize the high-pressure liquid, such as liquid oxygen, contained therein to pressurize the oxygen in the fuel storage tank 28 and fully deliver it through the fifth and fourth delivery pipes 21 and 20 to the interior of the third delivery pipe 17, effectively overcoming pipeline resistance and enabling automatic detection and adjustment control throughout the entire process.

[0034] Solenoid valves 27 are fixedly installed between the second high-pressure storage tank 25 and the second turbine outer frame 24, and between the first high-pressure storage tank 7 and the first turbine outer frame 9. The second pressurized delivery pipe 22 is connected to the fifth delivery pipe 21, and the first pressurized delivery pipe 11 is connected to the first delivery pipe 12. A second fixed connecting frame 26 and a first fixed connecting frame 8 are provided on the outside of the second high-pressure storage tank 25 and the first high-pressure storage tank 7, and the second high-pressure storage tank 25 is fixedly installed on the second fixed connecting frame 26, and the first high-pressure storage tank 7 is fixedly installed on the first fixed connecting frame 8. Fixing holes are provided on the first fixed connecting frame 8 and the mixing turbine pump 16, which can conveniently realize fixed, disassembled, installed and used.

[0035] The bottom end of the hybrid turbine pump 16 is connected to the interior of the engine body 6 through the third delivery pipe 17. The interior of the first high-pressure storage tank 7 stores high-pressure gas such as inert gas, and the interior of the second high-pressure storage tank 25 stores high-pressure liquid, realizing dual-medium pre-pressurization.

[0036] Working principle: During the operation of the engine body 6, the high-pressure fuel and oxygen stored in the fuel storage tank 28 and the oxidizer storage tank 30 will be transported to the inside of the third delivery pipe 17 through the fifth delivery pipe 21 and the first delivery pipe 12, and then mixed through the mixing turbine pump 16. Under the action of the mixing turbine pump 16, the fuel and oxygen can be fully transported and operated. In the process of transporting fuel and oxygen, the flow rate and pressure of the transported fuel and oxygen can be detected and monitored in real time through the second delivery pipe 13 and the first flow sensor 14 and the second pressure sensor 18 and the second flow sensor 19. At the initial delivery and supply of fuel and oxygen, the gas stored in the first high-pressure storage tank 7 is transported to the inside of the first turbine outer frame 9 under the control of the solenoid valve 27, driving the second high-pressure storage tank 7 to move to the outside of the first turbine outer frame 9. A turbine 10 rotates at high speed and boosts the pressure, which is then transported to the interior of the first delivery pipe 12 through the first pressurized delivery pipe 11, thereby pressurizing the oxygen transported inside the first delivery pipe 12 and quickly delivering and replenishing it. In the whole process, the first flow sensor 14 and the first pressure sensor 15 provided can detect the flow rate and pressure in real time, thereby indirectly controlling the control state of the solenoid valve 27 at the bottom end of the first high-pressure storage tank 7. Similarly, the second high-pressure storage tank 25 can be provided, and the high-pressure liquid therein, such as liquid oxygen, can be used to pressurize the oxygen in the fuel storage tank 28 and fully deliver it to the interior of the third delivery pipe 17 through the fifth delivery pipe 21 and the fourth delivery pipe 20, which can effectively overcome the pipeline resistance and automatically perform detection and realize automatic adjustment and control in the whole process.

[0037] Example 2

[0038] On the basis of Example 1, Figure 8 As shown, a third pressure sensor 32 and a third flow sensor 33 are installed on the third delivery pipe 17 .

[0039] When implementing this embodiment, the third pressure sensor 32 and the third flow sensor 33 can be provided to detect the flow rate and pressure of the mixture of the fuel and the oxidizer, thereby indirectly controlling and adjusting the solenoid valve 27 to control the flow rate and flow of the gas or liquid injected into the first high-pressure storage tank 7 and the second high-pressure storage tank 25 based on the detected data, thereby fully adapting to play the role of precise pre-pressurization.

[0040] 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 dual-medium self-adaptive pre-boost rocket engine, comprising an engine unit (4), characterized in that: A rocket launcher (2) is arranged outside the engine part (4), and the engine part (4) is fixedly arranged inside the rocket launcher (2). The upper end of the rocket launcher (2) is fixedly connected to a rocket front cover (1), and the bottom end of the rocket launcher (2) is evenly distributed with nozzles (3).

2. The dual-medium adaptive pre-boost rocket engine according to claim 1, characterized in that: The engine part (4) comprises a dual-medium adaptive pre-boosting body (5) and an engine body (6), wherein the engine body (6) is arranged at the bottom end of the dual-medium adaptive pre-boosting body (5).

3. The dual-medium adaptive pre-boost rocket engine according to claim 2, characterized in that: The dual-medium adaptive pre-boosting body (5) comprises a first delivery pipe (12), a second delivery pipe (13), a mixing turbine pump (16), a third delivery pipe (17), a fourth delivery pipe (20), a fifth delivery pipe (21), a fuel storage tank (28) and an oxidant storage tank (30), wherein the mixing turbine pump (16) is fixedly connected to the bottom end of the third delivery pipe (17), the second delivery pipe (13) and the fourth delivery pipe (20) are symmetrically distributed, and the bottom ends of the second delivery pipe (13) and the fourth delivery pipe (20) are respectively fixedly connected to the upper ends of the third delivery pipe (17), the first delivery pipe (12) is fixedly connected to the upper end of the second delivery pipe (13), the fifth delivery pipe (21) is fixedly connected to the upper end of the fourth delivery pipe (20), and the bottom ends of the fuel storage tank (28) and the oxidant storage tank (30) are respectively fixedly connected to the upper ends of the fifth delivery pipe (21) and the first delivery pipe (12) through valve bodies.

4. The dual-medium adaptive pre-boost rocket engine according to claim 3, characterized in that: The first delivery pipe (12) is connected to the interior of the second delivery pipe (13), the second delivery pipe (13) is connected to the interior of the third delivery pipe (17), the fifth delivery pipe (21) is connected to the interior of the fourth delivery pipe (20), and the fourth delivery pipe (20) is connected to the interior of the third delivery pipe (17).

5. The dual-medium adaptive pre-boost rocket engine according to claim 4, characterized in that: The fuel storage tank (28) and the oxidant storage tank (30) are respectively provided with a third clamping connection frame (29) and a fourth clamping connection frame (31), and the fuel storage tank (28) is fixedly mounted on the third clamping connection frame (29), and the oxidant storage tank (30) is fixedly mounted on the fourth clamping connection frame (31), and fixing holes are evenly opened on the third clamping connection frame (29) and the fourth clamping connection frame (31).

6. The dual-medium adaptive pre-boost rocket engine according to claim 5, characterized in that: The outer end of the first delivery pipe (12) is fixedly connected to the first pressurized delivery pipe (11), the upper end of the first pressurized delivery pipe (11) is fixedly connected to the first turbine outer frame (9), the first turbine (10) is rotatably mounted inside the first turbine outer frame (9), and the upper end of the first turbine outer frame (9) is fixedly connected to the first high-pressure storage tank (7).

7. The dual-medium adaptive pre-boost rocket engine according to claim 6, characterized in that: The outer end of the fifth delivery pipe (21) is fixedly connected to a second pressurized delivery pipe (22), the upper end of the second pressurized delivery pipe (22) is fixedly connected to a second turbine outer frame (24), a second turbine (23) is rotatably mounted inside the second turbine outer frame (24), and the upper end of the second turbine outer frame (24) is fixedly connected to a second high-pressure storage tank (25).

8. The dual-medium adaptive pre-boost rocket engine according to claim 7, characterized in that: A solenoid valve (27) is fixedly installed between the second high-pressure storage tank (25) and the second turbine outer frame (24), and between the first high-pressure storage tank (7) and the first turbine outer frame (9). The second pressurized delivery pipe (22) is connected to the fifth delivery pipe (21), and the first pressurized delivery pipe (11) is connected to the first delivery pipe (12). A second clamping connection frame (26) and a first clamping connection frame (8) are provided on the outside of the second high-pressure storage tank (25) and the first high-pressure storage tank (7). The second high-pressure storage tank (25) is fixedly installed on the second clamping connection frame (26), and the first high-pressure storage tank (7) is fixedly installed on the first clamping connection frame (8). Fixing holes are provided on the first clamping connection frame (8) and the mixing turbine pump (16).

9. The dual-medium adaptive pre-boost rocket engine according to claim 8, characterized in that: The bottom end of the mixing turbine pump (16) is connected to the interior of the engine body (6) through a third delivery pipe (17), the interior of the first high-pressure storage tank (7) stores high-pressure gas, and the interior of the second high-pressure storage tank (25) stores high-pressure liquid.

10. The dual-medium adaptive pre-boost rocket engine according to claim 9, characterized in that: A third pressure sensor (32) and a third flow sensor (33) are installed on the third delivery pipe (17).

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