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CN-122009531-A - Satellite composite propulsion system and method based on Brayton cycle

CN122009531ACN 122009531 ACN122009531 ACN 122009531ACN-122009531-A

Abstract

The invention relates to the technical field of satellite attitude control and orbital maneuver, in particular to a satellite composite propulsion system and method based on Brayton cycle. The composite propulsion system comprises a propellant storage unit, a gas generator, an oxidant inlet and a fuel outlet, wherein the propellant storage unit comprises an oxygen primary compressor and an oxygen secondary compressor which are coaxially and serially arranged, a hydrogen primary compressor and a hydrogen secondary compressor which are coaxially and serially arranged, and a turbine, the oxygen primary compressor, the oxygen secondary compressor, the hydrogen primary compressor and the hydrogen secondary compressor are coaxially connected with the turbine, the oxidant inlet is communicated with an outlet of the oxygen secondary compressor, the fuel inlet is communicated with an outlet of the hydrogen secondary compressor, and the fuel outlet is communicated with an inlet of the turbine. By adopting a two-stage coaxial series compressor structure, the exhaust gas after the turbine does work still keeps higher than the pressure of the main thrust chamber, and can smoothly flow back to the main thrust chamber for afterburning, thereby realizing the full utilization of energy in the system.

Inventors

  • CHENG KUNLIN
  • SONG MINGYU
  • QIN JIANG
  • JI YONGBIN

Assignees

  • 哈尔滨工业大学

Dates

Publication Date
20260512
Application Date
20260327

Claims (10)

  1. 1. A brayton cycle based satellite hybrid propulsion system comprising: a propellant storage unit comprising a gas oxygen storage tank (1) and a gas hydrogen storage tank (2); The turbocharging unit comprises an oxygen primary compressor (3) and an oxygen secondary compressor (3-1) which are coaxially and serially arranged, a hydrogen primary compressor (4) and a hydrogen secondary compressor (4-1) which are coaxially and serially arranged and a turbine (5), wherein the oxygen primary compressor (3), the oxygen secondary compressor (3-1), the hydrogen primary compressor (4) and the hydrogen secondary compressor (4-1) are coaxially connected with the turbine (5); A gas generator (6) with an oxidant inlet communicated with the outlet of the oxygen secondary compressor (3-1), a fuel inlet communicated with the outlet of the hydrogen secondary compressor (4-1), and a gas outlet communicated with the inlet of the turbine (5) for generating high-temperature and high-pressure gas to drive the turbine (5); The bypass conveying unit comprises an oxygen bypass pipeline (18) and a hydrogen bypass pipeline (19), wherein the oxygen bypass pipeline (18) is arranged between the gas-oxygen storage tank (1) and the thrust chamber (7), and the hydrogen bypass pipeline (19) is arranged between the gas-hydrogen storage tank (2) and the thrust chamber (7); The thrust chamber (7) is respectively communicated with an outlet of the oxygen primary compressor (3) and an outlet of the oxygen bypass pipeline (18), the fuel inlet is respectively communicated with an outlet of the hydrogen primary compressor (4) and an outlet of the hydrogen bypass pipeline (19), and the fuel gas afterburning inlet is communicated with an outlet of the turbine (5); And the ion propeller (8) is connected with the outlet of the air-oxygen storage tank (1).
  2. 2. The brayton cycle-based satellite hybrid propulsion system of claim 1, wherein an oxygen bypass control valve (16) is provided on the oxygen bypass line (18), and a hydrogen bypass control valve (15) is provided on the hydrogen bypass line (19).
  3. 3. The brayton cycle-based satellite composite propulsion system according to claim 1, further comprising an oxygen main line (20), wherein the oxygen main line (20) connects the gas-oxygen storage tank (1) and the thrust chamber (7), and wherein the oxygen primary compressor (3) is provided on the oxygen main line (20).
  4. 4. A brayton cycle based satellite hybrid propulsion system according to claim 3, wherein the oxygen main circuit (20) is provided with an oxygen pressurization branch total valve (9) and an oxygen main circuit control valve (14).
  5. 5. The brayton cycle-based satellite composite propulsion system according to claim 4, wherein an oxygen bypass line (22) is provided between the oxygen primary compressor (3) and the oxygen secondary compressor (3-1), the oxygen bypass line (22) being provided with an oxygen secondary bypass control valve (11).
  6. 6. The brayton cycle based satellite composite propulsion system according to any of claims 1-5, further comprising a hydrogen main line (21), said hydrogen main line (21) connecting said gas hydrogen storage tank (2) and thrust chamber (7), said hydrogen primary compressor (4) being provided on the hydrogen main line (21).
  7. 7. The brayton cycle-based satellite composite propulsion system according to claim 6, wherein the hydrogen main line (21) is provided with a hydrogen pressurization branch master valve (10) and a hydrogen main line control valve (13).
  8. 8. The brayton cycle-based satellite composite propulsion system according to claim 7, wherein a hydrogen bypass line (23) is provided between the hydrogen primary compressor (4) and the hydrogen secondary compressor (4-1), the hydrogen bypass line (23) being provided with a hydrogen secondary bypass control valve (12).
  9. 9. The brayton cycle-based satellite composite propulsion system according to claim 8, further comprising a communication line (24), wherein the communication line (24) connects the oxygen bypass line (18) with an ion thruster, and wherein a thruster control valve (17) is provided on the communication line (24).
  10. 10. A method of operation using a brayton cycle based satellite composite propulsion system according to any of claims 1-9, comprising: in the turbo-charging mode, an oxygen bypass pipeline (18) and a hydrogen bypass pipeline (19) are closed, a small amount of hydrogen and oxygen are respectively combusted by an oxygen primary compressor (3) and an oxygen secondary compressor (3-1), a hydrogen primary compressor (4) and a hydrogen secondary compressor (4-1), the secondary pressurized hydrogen enters a gas generator (6) to be ignited and combusted to generate high-temperature high-pressure gas, the high-temperature high-pressure gas drives a turbine (5) to rotate at a high speed, the turbine (5) coaxially drives the oxygen primary compressor (3) and the hydrogen primary compressor (4), the low-pressure oxygen and the low-pressure hydrogen are respectively pressurized to preset pressures by the oxygen primary compressor (3) and the hydrogen primary compressor (4), then the residual hydrogen is injected into a thrust chamber (7) by the turbine (5) after being combusted by a hydrogen main path control valve (13) and the gas generator (6), the exhaust gas after the turbine (5) is still kept higher than the pressure of the combustion chamber, and is smoothly injected into the thrust chamber (7) to be mixed with a propellant of an oxygen main pipeline (20) and a hydrogen main pipeline (21).

Description

Satellite composite propulsion system and method based on Brayton cycle Technical Field The invention relates to the technical field of satellite attitude control and orbital maneuver, in particular to a satellite composite propulsion system and method based on Brayton cycle. Background With the continuous development of aerospace technology, the task requirements of on-orbit satellites are increasingly complex, and the performance requirements of propulsion systems are also continuously improved. The oxyhydrogen propellant has the advantages of high specific impulse and no pollution, and is an ideal power source for satellite orbit maneuver. However, the conventional hydrogen-oxygen propulsion system of the in-orbit satellite has a plurality of defects that on one hand, after hydrogen and oxygen are output from a high-pressure storage tank, the pressure can be reduced along with the reduction of the residual amount of the propellant in the storage tank, so that the hydrogen-oxygen mixing pressure entering a thrust chamber is unstable, the combustion efficiency and the stability of thrust output are affected, on the other hand, if the mixing ratio is controlled improperly in the hydrogen-oxygen combustion process, the condition of overhigh temperature easily occurs, the parts of the thruster are seriously damaged, the service life of the propulsion system is shortened, and in addition, the residual propellant after combustion in the conventional propulsion system is usually discharged directly, so that the resource waste is caused, and the overall utilization rate of the propellant is reduced. At present, although researches on related oxyhydrogen thrusters and propellant supply systems are provided, such as partial researches propose a catalytic ignition oxyhydrogen thruster structure or a propellant supply pipeline design, but all the problems of unstable output pressure of a high-pressure storage tank, hydrogen-rich combustion control and integration of residual oxygen recycling are not solved. Therefore, there is a need to design an on-orbit satellite oxyhydrogen power propulsion system capable of realizing stable oxyhydrogen pressurization, hydrogen-rich safe combustion and recycling of residual oxygen. Existing systems typically rely on only a single squeeze supply of air, resulting in a tank with insufficient pressure at a later stage, or rely on only an electric pump to boost pressure, resulting in a complex system. Disclosure of Invention Therefore, the technical problem to be solved by the invention is to overcome the problems of pressure decay of a storage tank and low utilization rate of propellant in the prior art, so as to provide a satellite composite propulsion system and a satellite composite propulsion method based on the Brayton cycle. The invention provides a satellite composite propulsion system based on Brayton cycle, which comprises a propellant storage unit, a turbocharging unit, a bypass conveying unit and a bypass conveying unit, wherein the propellant storage unit comprises an oxygen primary compressor and an oxygen secondary compressor which are coaxially arranged in series, the hydrogen primary compressor and the hydrogen secondary compressor are coaxially arranged in series, the turbine is connected with the oxygen primary compressor, the oxygen secondary compressor, the hydrogen primary compressor and the hydrogen secondary compressor coaxially, an oxidant inlet is communicated with an outlet of the oxygen secondary compressor, a fuel inlet is communicated with an outlet of the hydrogen secondary compressor, a fuel outlet is communicated with an inlet of the turbine and is used for generating high-temperature and high-pressure gas to drive the turbine, the bypass conveying unit comprises an oxygen bypass pipeline and a hydrogen bypass pipeline, the oxygen bypass pipeline is arranged between the oxygen storage tank and a thrust chamber, the hydrogen bypass pipeline is arranged between the oxygen hydrogen storage tank and the thrust chamber, the thrust chamber is respectively communicated with an outlet of the oxygen primary compressor and an outlet of the oxygen bypass pipeline, the fuel inlet is respectively communicated with an outlet of the hydrogen primary compressor and an outlet of the hydrogen bypass pipeline, the fuel inlet is respectively communicated with an outlet of the hydrogen bypass pipeline, and an outlet of the turbine is communicated with an outlet of the oxygen bypass pipeline and is communicated with an outlet of the oxygen storage tank. Further, an oxygen bypass control valve is arranged on the oxygen bypass pipeline, and a hydrogen bypass control valve is arranged on the hydrogen bypass pipeline. Further, the device also comprises an oxygen main pipeline, wherein the oxygen main pipeline is connected with the gas-oxygen storage tank and the thrust chamber, and the oxygen primary compressor is arranged on the oxygen main pipeline. Further, an oxygen pressur