Satellite composite propulsion system and method based on Brayton cycle

Abstract

The invention relates to the technical field of satellite attitude control and orbital maneuver, in particular to a Brayton cycle-based satellite composite propulsion system and method. The composite propulsion system comprises a propellant storage unit which comprises a gaseous oxygen storage tank and a gaseous hydrogen storage tank; the turbocharging unit comprises an oxygen first-stage gas compressor and an oxygen second-stage gas compressor which are coaxially connected in series, a hydrogen first-stage gas compressor and a hydrogen second-stage gas compressor which are coaxially connected in series, and a turbine; the oxygen first-stage gas compressor, the oxygen second-stage gas compressor, the hydrogen first-stage gas compressor and the hydrogen second-stage gas compressor are coaxially connected with the turbine; an oxidant inlet of the fuel gas generator is communicated with an outlet of the oxygen secondary gas compressor, a fuel inlet of the fuel gas generator is communicated with an outlet of the hydrogen secondary gas compressor, and a fuel gas outlet of the fuel gas generator is communicated with an inlet of the turbine. A two-stage coaxial series-connection gas compressor structure is adopted, exhaust gas generated after a turbine does work is still kept to be higher than the pressure of a main thrust chamber, the exhaust gas can smoothly flow back to the main thrust chamber for afterburning, and full utilization of energy in a system is achieved.

Description

Technical Field

[0001] This invention relates to the field of satellite attitude control and orbital maneuvering technology, specifically to a satellite composite propulsion system and method based on the Brayton cycle. Background Technology

[0002] With the continuous development of aerospace technology, the mission requirements of satellites in orbit are becoming increasingly complex, and the performance requirements for propulsion systems are also constantly increasing. Hydrogen-oxygen propellants have the advantages of high specific impulse and no pollution, making them an ideal power source for satellite orbital maneuvers.

[0003] However, existing hydrogen-oxygen propulsion systems for satellites in orbit have many shortcomings: Firstly, after hydrogen and oxygen are output from the high-pressure storage tank, the pressure decreases as the remaining propellant in the tank decreases, leading to unstable hydrogen-oxygen mixture pressure entering the thrust chamber, affecting combustion efficiency and thrust output stability. Secondly, if the mixing ratio is not properly controlled during hydrogen-oxygen combustion, excessively high temperatures can easily occur, severely damaging thruster components and shortening the service life of the propulsion system. In addition, the remaining propellant after combustion in traditional propulsion systems is usually directly discharged, resulting in resource waste and reducing the overall utilization rate of propellant.

[0004] Currently, although there is research on related hydrogen-oxygen thrusters and propellant supply systems, such as some studies proposing catalytic ignition hydrogen-oxygen thruster structures or propellant supply pipeline designs, none of them have solved the integrated problems of unstable output pressure of high-pressure storage tanks, hydrogen-rich combustion control, and residual oxygen recovery and utilization.

[0005] Therefore, there is an urgent need to design an on-orbit satellite hydrogen-oxygen propulsion system that can achieve stable hydrogen-oxygen pressurization, safe hydrogen-rich combustion, and recovery and utilization of residual oxygen. Existing systems typically rely on a single extrusion-type gas supply, leading to insufficient pressure in the storage tank later on, or rely solely on electric pump pressurization, resulting in system complexity. Summary of the Invention

[0006] Therefore, the technical problem to be solved by the present invention is to overcome the problems of tank pressure decay and low propellant utilization in the prior art, thereby providing a satellite composite propulsion system and method based on the Brayton cycle.

[0007] To address the aforementioned technical problems, this invention provides a satellite composite propulsion system based on the Brayton cycle, comprising: a propellant storage unit, including a gaseous oxygen storage tank and a gaseous hydrogen storage tank; a turbocharger unit, including an oxygen primary compressor and an oxygen secondary compressor coaxially connected in series, a hydrogen primary compressor and a hydrogen secondary compressor coaxially connected in series, and a turbine; the oxygen primary compressor, oxygen secondary compressor, hydrogen primary compressor, and hydrogen secondary compressor are coaxially connected to the turbine; and a gas generator, with an oxidant inlet connected to the outlet of the oxygen secondary compressor and a fuel inlet connected to the outlet of the hydrogen secondary compressor. The turbine is connected to the gas outlet to generate high-temperature, high-pressure gas to drive the turbine; the bypass delivery unit includes an oxygen bypass pipeline and a hydrogen bypass pipeline, with the oxygen bypass pipeline located between the gaseous oxygen storage tank and the thrust chamber, and the hydrogen bypass pipeline located between the gaseous hydrogen storage tank and the thrust chamber; the thrust chamber has an oxidizer inlet connected to the outlet of the oxygen first-stage compressor and the outlet of the oxygen bypass pipeline, a fuel inlet connected to the outlet of the hydrogen first-stage compressor and the outlet of the hydrogen bypass pipeline, and a gas combustion inlet connected to the turbine outlet; and an ion thruster connected to the outlet of the gaseous oxygen storage tank.

[0008] Furthermore, an oxygen bypass control valve is provided on the oxygen bypass pipeline, and a hydrogen bypass control valve is provided on the hydrogen bypass pipeline.

[0009] Furthermore, it also includes an oxygen main pipeline, which connects the oxygen storage tank and the thrust chamber, and the oxygen primary compressor is located on the oxygen main pipeline.

[0010] Furthermore, the oxygen main pipeline is equipped with an oxygen booster branch main valve and an oxygen main pipeline control valve.

[0011] Furthermore, an oxygen branch pipeline is provided between the oxygen primary compressor and the oxygen secondary compressor, and the oxygen branch pipeline is equipped with an oxygen secondary branch control valve.

[0012] Furthermore, it also includes a main hydrogen pipeline, which connects the gaseous hydrogen storage tank and the thrust chamber, and the hydrogen primary compressor is located on the main hydrogen pipeline.

[0013] Furthermore, the main hydrogen pipeline is equipped with a main hydrogen booster branch valve and a main hydrogen pipeline control valve.

[0014] Furthermore, a hydrogen branch pipeline is provided between the hydrogen primary compressor and the hydrogen secondary compressor, and the hydrogen branch pipeline is equipped with a hydrogen secondary branch control valve.

[0015] Furthermore, it also includes a connecting pipeline that connects the oxygen bypass pipeline to the ion thruster, and the connecting pipeline is equipped with a thruster control valve.

[0016] The present invention also provides a method for operating a satellite composite propulsion system based on the Brayton cycle, comprising: Turbocharging mode: The oxygen bypass line and hydrogen bypass line are closed. A small amount of hydrogen and oxygen are pressurized twice by passing through the oxygen primary compressor and oxygen secondary compressor, the hydrogen primary compressor and hydrogen secondary compressor, respectively, and then enter the gas generator for ignition and combustion, producing high-temperature and high-pressure gas. The high-temperature and high-pressure gas drives the turbine to rotate at high speed. The turbine coaxially drives the oxygen primary compressor and hydrogen primary compressor. The low-pressure oxygen and hydrogen are pressurized to the preset pressure by passing through the oxygen primary compressor and hydrogen primary compressor respectively. Then, the hydrogen passes through the hydrogen main control valve and the gas generator for combustion. The remaining hydrogen is injected into the thrust chamber through the turbine. The exhaust gas after the turbine does work still maintains a pressure higher than that of the thrust chamber combustion chamber and is smoothly injected into the thrust chamber to mix and combust with the propellant in the oxygen main line and hydrogen main line lines.

[0017] The technical solution of this invention has the following advantages: The Brayton cycle-based satellite composite propulsion system provided by this invention features a dual-mode gas supply: the composite propulsion system has a pressurization branch and a direct bypass connected in parallel between the storage tank and the thrust chamber. During the initial mission phase, the high pressure of the storage tank itself is used for direct gas supply, reducing the operating time of rotating components and improving system reliability. When the tank pressure decreases after propellant consumption, the system switches to turbocharging mode to ensure stable input pressure in the thrust chamber.

[0018] Staged pressurized closed-loop afterburning cycle: It adopts a two-stage coaxial compressor structure. The outlet of the first-stage compressor is divided into two paths. The main path supplies the main thrust chamber, and the branch path supplies the gas generator after secondary pressurization by the second-stage compressor. This significantly increases the turbine inlet pressure and reserves sufficient pressure drop margin. The exhaust gas after the turbine does power is still maintained at a pressure higher than that of the main thrust chamber, and can flow back to the main thrust chamber for afterburning, realizing full utilization of energy within the system.

[0019] Joint propulsion: During the cruise / position-keeping phase, when high-thrust maneuvering is not required, the remaining low-pressure oxygen in the storage tank is introduced into the ion thruster. Electrical energy is used to ionize and accelerate the oxygen, providing high specific impulse position-keeping thrust and maximizing propellant utilization.

[0020] The summary section is provided to present the chosen concepts in a simplified form, which will be further described in the detailed description below. The summary section is not intended to identify essential or necessary features of this disclosure, nor is it intended to limit the scope of this disclosure. Attached Figure Description

[0021] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0022] Figure 1 A schematic diagram of the structure of a satellite composite propulsion system based on the Brayton cycle provided by the present invention.

[0023] Explanation of reference numerals in the attached figures: 1. Oxygen storage tank; 2. Hydrogen storage tank; 3. Oxygen primary compressor; 3-1. Oxygen secondary compressor; 4. Hydrogen primary compressor; 4-1. Hydrogen secondary compressor; 5. Turbine; 6. Gas generator; 7. Thrust chamber; 8. Ion thruster; 9. Oxygen booster branch main valve; 10. Hydrogen booster branch main valve; 11. Oxygen secondary branch control valve; 12. Hydrogen secondary branch control valve; 13. Hydrogen main line control valve; 14. Oxygen main line control valve; 15. Hydrogen bypass control valve; 16. Oxygen bypass control valve; 17. Thruster control valve; 18. Oxygen bypass pipeline; 19. Hydrogen bypass pipeline; 20. Oxygen main line pipeline; 21. Hydrogen main line pipeline; 22. Oxygen branch pipeline; 23. Hydrogen branch pipeline; 24. Connecting pipeline. Detailed Implementation

[0024] In the following description, only certain exemplary embodiments are briefly described. As those skilled in the art will recognize, the described embodiments can be modified in various ways without departing from the spirit or scope of this disclosure. Therefore, the drawings and description are to be considered exemplary in nature and not restrictive.

[0025] The preferred embodiments of this disclosure are described below with reference to the accompanying drawings. It should be understood that the preferred embodiments described herein are for illustration and explanation only and are not intended to limit this disclosure.

[0026] Please see Figure 1As shown, this invention provides a satellite composite propulsion system based on the Brayton cycle, comprising: a propellant storage unit, including a gaseous oxygen storage tank 1 and a gaseous hydrogen storage tank 2; a turbine 5 booster unit, including an oxygen first-stage compressor 3 and an oxygen second-stage compressor 3-1 arranged coaxially in series, a hydrogen first-stage compressor 4 and a hydrogen second-stage compressor 4-1 arranged coaxially in series, and a turbine 5; the oxygen first-stage compressor 3, the oxygen second-stage compressor 3-1, the hydrogen first-stage compressor 4, and the hydrogen second-stage compressor 4-1 are coaxially connected to the turbine 5; a gas generator 6, with an oxidizer inlet connected to the outlet of the oxygen second-stage compressor 3-1 and a fuel inlet connected to the outlet of the hydrogen second-stage compressor 4-1. The gas outlet is connected to the inlet of turbine 5 to generate high-temperature, high-pressure gas to drive turbine 5; the bypass delivery unit includes an oxygen bypass pipeline 18 and a hydrogen bypass pipeline 19. The oxygen bypass pipeline 18 is located between the gaseous oxygen storage tank 1 and the thrust chamber 7, and the hydrogen bypass pipeline 19 is located between the gaseous hydrogen storage tank 2 and the thrust chamber 7; the oxidizer inlet of the thrust chamber 7 is connected to the outlet of the oxygen first-stage compressor 3 and the outlet of the oxygen bypass pipeline 18, respectively; the fuel inlet is connected to the outlet of the hydrogen first-stage compressor 4 and the outlet of the hydrogen bypass pipeline 19, respectively; and the gas combustion inlet is connected to the outlet of turbine 5; the ion thruster 8 is connected to the outlet of the gaseous oxygen storage tank 1.

[0027] The design pressure ratio of the second-stage compressor is higher than that of the first-stage compressor, which makes the inlet pressure of turbine 5 much higher than the working pressure of thrust chamber 7, and the outlet pressure of turbine 5 after doing work is still higher than the combustion chamber pressure of thrust chamber 7.

[0028] An oxygen bypass control valve 16 is installed on the oxygen bypass line 18, and a hydrogen bypass control valve 15 is installed on the hydrogen bypass line 19. By setting the oxygen bypass control valve 16 and the hydrogen bypass control valve 15, the flow of oxygen in the oxygen bypass line 18 and the flow of hydrogen in the hydrogen bypass line 19 are controlled, thus achieving precise control.

[0029] The Brayton cycle-based satellite composite propulsion system also includes an oxygen main pipeline 20, which connects the oxygen storage tank 1 and the thrust chamber 7, and the oxygen first-stage compressor 3 is mounted on the oxygen main pipeline 20.

[0030] The main function of the oxygen main pipeline 20 is to transport oxygen so that the oxygen in the oxygen storage tank 1 can smoothly enter the thrust chamber 7.

[0031] Meanwhile, an oxygen booster branch main valve 9 and an oxygen main control valve 14 are provided on the oxygen main pipeline 20. That is, the oxygen booster branch main valve 9 controls the oxygen to enter the oxygen first-stage compressor 3, and the oxygen main control valve 14 controls the oxygen to enter the thrust chamber 7.

[0032] An oxygen branch pipeline 22 is provided between the oxygen primary compressor 3 and the oxygen secondary compressor 3-1, and the oxygen branch pipeline 22 is equipped with an oxygen secondary branch control valve 11.

[0033] The outlet of the oxygen primary compressor 3 is provided with two branches: the main branch is connected to the oxidant inlet of the thrust chamber 7 via the oxygen main branch control valve 14, and the branch is connected to the inlet of the oxygen secondary compressor 3-1 via the oxygen secondary branch control valve 11.

[0034] The Brayton cycle-based satellite composite propulsion system also includes a hydrogen main pipeline 21, which connects the gaseous hydrogen storage tank 2 and the thrust chamber 7, and the hydrogen first-stage compressor 4 is mounted on the hydrogen main pipeline 21.

[0035] The main function of the hydrogen main pipeline 21 is to transport hydrogen so that the hydrogen in the gaseous hydrogen storage tank 2 can smoothly enter the thrust chamber 7.

[0036] Meanwhile, a hydrogen booster branch main valve 10 and a hydrogen main control valve 13 are provided on the hydrogen main pipeline 21. That is, the hydrogen booster branch main valve 10 controls the hydrogen to enter the hydrogen first-stage compressor 4, and the hydrogen main control valve 13 controls the hydrogen to enter the thrust chamber 7.

[0037] A hydrogen branch pipeline 23 is provided between the hydrogen primary compressor 4 and the hydrogen secondary compressor 4-1, and the hydrogen branch pipeline 23 is equipped with a hydrogen secondary branch control valve 12.

[0038] That is, the outlet of the hydrogen primary compressor 4 is provided with two branches: the main branch is connected to the fuel inlet of the thrust chamber 7 via the hydrogen main branch control valve 13, and the branch is connected to the inlet of the hydrogen secondary compressor 4-1 via the hydrogen secondary branch control valve 12.

[0039] The Brayton cycle-based satellite composite propulsion system also includes a connecting pipe 24, which connects the oxygen bypass pipe 18 to the ion thruster 8, and the connecting pipe 24 is equipped with a thruster control valve 17.

[0040] The oxygen bypass line 18 is connected to the ion thruster 8 via the connecting line 24. Oxygen can enter through the oxygen bypass line 18, then enter the connecting line 24, and finally enter the ion thruster 8 through the thruster control valve 17.

[0041] The present invention also provides a method for operating a satellite composite propulsion system based on the Brayton cycle, comprising: Squeeze-through mode: When the propellant reserves in the tank are sufficient at the beginning of the mission or when the tank pressure is higher than the sum of the design combustion chamber pressure and the pipeline pressure drop, the compound propulsion system operates in straight-through mode. At this time, the oxygen booster branch main valve 9, the hydrogen booster branch main valve 10, the oxygen secondary branch control valve 11, the hydrogen secondary branch control valve 12, the oxygen main control valve 14, the hydrogen main control valve 13, and the thruster control valve 17 are all closed; the oxygen bypass control valve 16 and the hydrogen bypass control valve 15 remain open, and oxygen and hydrogen are directly transported to the thrust chamber 7 through the oxygen bypass pipeline 18 and the hydrogen bypass pipeline 19 without passing through the turbo 5 booster unit to perform hydrogen-rich combustion and work.

[0042] Turbocharged mode: As propellant is consumed, when the pressure sensor detects that the pressure in oxygen tank 1 and hydrogen tank 2 is lower than the set threshold, the compound propulsion system automatically switches to pressurization mode. Start-up process: Oxygen bypass control valve 16 and hydrogen bypass control valve 15 are closed, while oxygen booster branch main valve 9, hydrogen booster branch main valve 10, oxygen secondary branch control valve 11, hydrogen secondary branch control valve 12, oxygen main control valve 14, and hydrogen main control valve 13 are opened; a small amount of hydrogen and oxygen are pressurized twice by the two-stage compressor and then enter the gas generator 6 for ignition and combustion, producing high-temperature and high-pressure gas; Pressurization process: High-temperature and high-pressure gas drives turbine 5 to rotate at high speed. Turbine 5 coaxially drives oxygen primary compressor 3 and hydrogen primary compressor 4. Low-pressure oxygen and hydrogen are pressurized to preset pressures by oxygen primary compressor 3 and hydrogen primary compressor 4 respectively. Then, the hydrogen is burned by hydrogen main control valve 13 and gas generator 6. The remaining hydrogen is injected into thrust chamber 7 through turbine 5. The exhaust gas after turbine 5 does work still maintains a pressure higher than that of the combustion chamber of thrust chamber 7 and is smoothly injected into thrust chamber 7 to mix with the main hydrogen-oxygen propellant for afterburning, forming a closed-loop afterburning cycle. When the satellite is not in orbit change period, thruster control valve 17 is activated to switch the oxygen flow channel to ion thruster 8, ionize the oxygen and accelerate its ejection for long-term orbit maintenance.

[0043] Position hold / cruise mode: When the satellite completes its orbital maneuver and enters the long-term on-orbit cruise and orbit maintenance phase, the composite propulsion system switches to electric propulsion mode. At this time, the thrust chamber 7 and the turbine 5 booster unit are all shut down, the thruster control valve 17 is opened, and the oxygen in the oxygen storage tank 1 is directly introduced into the ion thruster 8. The oxygen is ionized and ejected at high speed using the electrical energy converted from the solar energy absorbed by the satellite, providing high specific impulse micro-thrust to complete long-term orbit maintenance and attitude control.

[0044] This mode makes full use of the remaining low-pressure oxygen working fluid in the composite propulsion system, eliminating the need for an additional electric propulsion working fluid storage tank, and significantly improving the integration of the propulsion system and the propellant utilization rate.

[0045] The thrust chamber 7 adopts a hydrogen-rich combustion mode, which uses excess hydrogen to reduce the combustion temperature and protect the nozzle structure; the ion thruster 8 operates in position hold / cruise mode, at which time the thrust chamber 7 is closed, and the oxygen in the oxygen storage tank 1 is introduced into the ion thruster 8 through the ion thruster 8 control valve.

[0046] The thrust chamber 7 adopts catalytic ignition, with a platinum-based metal catalytic bed set in the front section of the combustion chamber, which allows some of the hydrogen-oxygen premixed gas to ignite at low temperature, thus igniting the mixed gas in the main combustion chamber.

[0047] Obviously, the above embodiments are merely illustrative examples for clear explanation and are not intended to limit the implementation. Those skilled in the art will recognize that other variations or modifications can be made based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. However, obvious variations or modifications derived therefrom are still within the scope of protection of this invention.

Claims

1. A satellite composite propulsion system based on the Brayton cycle, characterized in that, include: The propellant storage unit includes a gaseous oxygen storage tank (1) and a gaseous hydrogen storage tank (2). The turbocharger unit includes an oxygen primary compressor (3) and an oxygen secondary compressor (3-1) arranged coaxially in series, a hydrogen primary compressor (4) and a hydrogen secondary compressor (4-1) arranged coaxially in series, and a turbine (5); the oxygen primary compressor (3), the oxygen secondary compressor (3-1), the hydrogen primary compressor (4), the hydrogen secondary compressor (4-1) and the turbine (5) are coaxially connected. The gas generator (6) has an oxidant inlet connected to the outlet of the oxygen secondary compressor (3-1), a fuel inlet connected to the outlet of the hydrogen secondary compressor (4-1), and a gas outlet connected to the inlet of the turbine (5), for generating high-temperature and high-pressure gas to drive the turbine (5). Bypass delivery unit: includes oxygen bypass pipeline (18) and hydrogen bypass pipeline (19). The oxygen bypass pipeline (18) is located between the gaseous oxygen storage tank (1) and the thrust chamber (7), and the hydrogen bypass pipeline (19) is located between the gaseous hydrogen storage tank (2) and the thrust chamber (7). The thrust chamber (7) has an oxidizer inlet connected to the outlet of the oxygen first-stage compressor (3) and the outlet of the oxygen bypass pipeline (18), respectively. The fuel inlet is connected to the outlet of the hydrogen first-stage compressor (4) and the outlet of the hydrogen bypass pipeline (19), respectively. The gas combustion supplement inlet is connected to the outlet of the turbine (5). The ion thruster (8) is connected to the outlet of the oxygen storage tank (1).

2. The satellite composite propulsion system based on the Brayton cycle according to claim 1, characterized in that, The oxygen bypass pipeline (18) is equipped with an oxygen bypass control valve (16), and the hydrogen bypass pipeline (19) is equipped with a hydrogen bypass control valve (15).

3. The satellite composite propulsion system based on the Brayton cycle according to claim 1, characterized in that, It also includes an oxygen main pipeline (20), which connects the oxygen storage tank (1) and the thrust chamber (7), and the oxygen primary compressor (3) is installed on the oxygen main pipeline (20).

4. The satellite composite propulsion system based on the Brayton cycle according to claim 3, characterized in that, The oxygen main pipeline (20) is equipped with an oxygen booster branch main valve (9) and an oxygen main control valve (14).

5. The satellite composite propulsion system based on the Brayton cycle according to claim 4, characterized in that, An oxygen branch pipeline (22) is provided between the oxygen primary compressor (3) and the oxygen secondary compressor (3-1), and the oxygen branch pipeline (22) is provided with an oxygen secondary branch control valve (11).

6. The satellite composite propulsion system based on the Brayton cycle according to any one of claims 1-5, characterized in that, It also includes a hydrogen main pipeline (21), which connects the gaseous hydrogen storage tank (2) and the thrust chamber (7), and the hydrogen primary compressor (4) is installed on the hydrogen main pipeline (21).

7. The satellite composite propulsion system based on the Brayton cycle according to claim 6, characterized in that, The main hydrogen pipeline (21) is equipped with a main hydrogen booster branch valve (10) and a main hydrogen pipeline control valve (13).

8. The satellite composite propulsion system based on the Brayton cycle according to claim 7, characterized in that, A hydrogen branch pipeline (23) is provided between the hydrogen primary compressor (4) and the hydrogen secondary compressor (4-1), and the hydrogen branch pipeline (23) is provided with a hydrogen secondary branch control valve (12).

9. The satellite composite propulsion system based on the Brayton cycle according to claim 8, characterized in that, It also includes a connecting pipe (24), which connects the oxygen bypass pipe (18) to the ion thruster, and the connecting pipe (24) is provided with a thruster control valve (17).

10. A method for operating a satellite composite propulsion system based on the Brayton cycle as described in any one of claims 1-9, characterized in that, include: Turbocharging mode: The oxygen bypass line (18) and hydrogen bypass line (19) are closed. A small amount of hydrogen and oxygen are respectively passed through the oxygen primary compressor (3) and oxygen secondary compressor (3-1), hydrogen primary compressor (4) and hydrogen secondary compressor (4-1), and after secondary pressurization, they enter the gas generator (6) for ignition and combustion, producing high-temperature and high-pressure gas. The high-temperature and high-pressure gas drives the turbine (5) to rotate at high speed. The turbine (5) coaxially drives the oxygen primary compressor (3) and hydrogen primary compressor (4). Low-pressure oxygen and hydrogen are pressurized to preset pressure by oxygen primary compressor (3) and hydrogen primary compressor (4), respectively. Then, hydrogen is burned by hydrogen main control valve (13) and gas generator (6). The remaining hydrogen is injected into thrust chamber (7) by turbine (5). The exhaust gas after turbine (5) does work is still higher than the pressure of the combustion chamber of thrust chamber (7) and is smoothly injected into thrust chamber (7) to mix and burn with propellant in oxygen main pipeline (20) and hydrogen main pipeline (21).

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