A cryogenic propellant integrated fluid system based on energy-fluid matching design

Abstract

A cryogenic propellant integrated fluid system based on energy-fluid matching design, wherein a hydrogen tank module and an oxygen tank module are used to store liquid hydrogen and liquid oxygen respectively, and realize the self-pressurization function of hydrogen and oxygen at the same time; a hydrogen fluid pump module and an oxygen fluid pump module are used to extract liquid hydrogen and liquid oxygen from the tanks and increase their pressures to supply heat exchangers; a hydrogen bottle module and an oxygen bottle module are used to store gaseous hydrogen and gaseous oxygen respectively, and can provide gaseous hydrogen and gaseous oxygen for an internal combustion engine module, a thruster module, a hydrogen tank module, and an oxygen tank module; a hydrogen-oxygen combined heat exchanger module is used to exchange heat between liquid hydrogen, liquid oxygen and an internal combustion engine coolant, so that liquid hydrogen and liquid oxygen are vaporized into gaseous hydrogen and gaseous oxygen and stored in gas cylinders; an internal combustion engine module is used to burn gaseous hydrogen and gaseous oxygen and drive a generator to generate electricity, which is stored in a battery, and the cylinder wall is cooled by the internal combustion engine coolant at the same time; a thruster module is used to burn gaseous hydrogen and gaseous oxygen to provide thrust, and realize the attitude control of the aircraft.

Description

Technical Field

[0001] The invention relates to a cryogenic propellant integrated fluid system based on energy-fluid matching design, belonging to the technical field of propellant integrated fluid systems. Background Art

[0002] The cryogenic propellant integrated fluid system integrates the functions of attitude and orbit control, power generation, and pressurization through the integrated management of cryogenic propellants, which can reduce the design margin of each independent system and thus achieve the goal of optimizing the system. The integrated fluid system uses high-specific impulse hydrogen-oxygen thrusters and hydrogen-oxygen internal combustion engine-based power generation systems to replace traditional auxiliary power systems, large battery systems, and helium pressurization systems. It can break through the limitations of hydrazine propellant usage, battery capacity, and helium usage, improve the efficiency of the transportation system, increase on-orbit time, and expand mission capabilities. In addition, the use of an integrated fluid system can significantly reduce the types of propellants that are refilled on-orbit, which is conducive to the future development of reusable space transportation systems based on liquid hydrogen and liquid oxygen on-orbit refueling technology.

[0003] Integrated fluid systems contain many components, complex working parameters, and strong mutual coupling between different components, which brings great difficulties to the design and parameter optimization of integrated fluid systems. Existing integrated fluid system design methods usually require all specific aspects of the flight mission to be clarified in advance, and targeted parameter design must be carried out from scratch. It is difficult to make timely adjustments according to changes in the space environment and flight missions, and the mission adaptability is poor. Summary of the invention

[0004] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, to provide a cryogenic propellant integrated fluid system based on energy-fluid matching design, to improve the mission adaptability of the integrated fluid system, and at the same time to improve the reliability and operating efficiency of the integrated fluid system.

[0005] The technical solution of the present invention is: a cryogenic propellant integrated fluid system based on energy-fluid matching design, including a hydrogen tank module, an oxygen tank module, a hydrogen fluid pump module, an oxygen fluid pump module, a hydrogen bottle module, an oxygen bottle module, a hydrogen-oxygen combined heat exchanger module, an internal combustion engine module, and a thruster module;

[0006] The hydrogen tank module and the oxygen tank module are used to store liquid hydrogen and liquid oxygen respectively, and realize the self-pressurization function of hydrogen and oxygen at the same time;

[0007] The hydrogen fluid pump module and the oxygen fluid pump module are used to extract liquid hydrogen and liquid oxygen from the storage tank and increase their pressure to supply the heat exchanger respectively;

[0008] The hydrogen cylinder module and the oxygen cylinder module are used to store gaseous hydrogen and gaseous oxygen respectively, and can provide gaseous hydrogen and gaseous oxygen for the internal combustion engine module, the thruster module, the hydrogen tank module, and the oxygen tank module;

[0009] The hydrogen-oxygen combined heat exchanger module is used to perform heat exchange on liquid hydrogen, liquid oxygen and internal combustion engine coolant, so that liquid hydrogen and liquid oxygen are vaporized into gaseous hydrogen and gaseous oxygen and stored in gas cylinders;

[0010] The internal combustion engine module is used to burn gaseous hydrogen and gaseous oxygen and drive the generator to generate electricity, which is stored in the battery, and the cylinder wall is cooled by the internal combustion engine coolant;

[0011] The thruster module is used to burn gaseous hydrogen and gaseous oxygen to provide thrust and realize attitude control of the aircraft.

[0012] Furthermore, the hydrogen fluid pump module and the oxygen fluid pump module adopt the form of motor-driven plunger pumps, which realize the change of fluid flow rate through real-time control instructions, while ensuring that the pressure after the pump remains stable.

[0013] Furthermore, the hydrogen-oxygen combined heat exchanger module distributes the heat provided by the coolant between liquid hydrogen and liquid oxygen, and achieves flow regulation of gaseous hydrogen and gaseous oxygen under the premise of ensuring that the temperatures of gaseous hydrogen and gaseous oxygen at the heat exchanger outlet remain unchanged.

[0014] Furthermore, the internal combustion engine module adopts a hydrogen-rich combustion mode, the gaseous hydrogen used for combustion comes from the gaseous hydrogen evaporated from the hydrogen tank, and the gaseous oxygen used for combustion comes from the gaseous oxygen supplied by the oxygen cylinder, and the regulation of electric power and thermal power is achieved by adjusting the flow rate of gaseous oxygen.

[0015] Furthermore, the thruster module adopts a DC impact type or pintle type injector, the hydrogen used for combustion comes from the hydrogen supplied by the hydrogen cylinder, and the oxygen used for combustion comes from the oxygen supplied by the hydrogen cylinder, and has the ability of multiple ignition and starting.

[0016] Furthermore, the energy and fluid of the fluid system are adjusted according to demand to operate in at least three different modes.

[0017] Furthermore, in one of the operating modes, the internal combustion engine operates at the lowest power, the oxygen cylinder supplies oxygen to the internal combustion engine, and the oxygen flow rate is the minimum value of the internal combustion engine.

[0018] Furthermore, in one of the operating modes, the internal combustion engine operates at the highest power, the oxygen cylinder supplies oxygen to the internal combustion engine, and the oxygen flow rate is the maximum value of the internal combustion engine.

[0019] Furthermore, in one of the operating modes, the internal combustion engine operates between the minimum power and the maximum power according to the pressure of the hydrogen and oxygen cylinders and the battery power requirements, the oxygen cylinder supplies oxygen to the internal combustion engine, and the oxygen flow rate is dynamically adjusted as needed.

[0020] According to the cryogenic propellant integrated fluid system based on energy-fluid matching design, a method for adjusting the energy and fluid of the system according to demand includes:

[0021] (1) Read the current amount of liquid hydrogen evaporation, hydrogen and oxygen cylinder pressure, and battery power;

[0022] (2) Determine whether the pressure of the hydrogen and oxygen cylinder is lower than the set value. If yes, execute step (3); if not, execute step (4);

[0023] (3) The oxygen cylinder supplies oxygen to the internal combustion engine, and the oxygen flow rate is dynamically adjusted according to needs. The internal combustion engine operates at medium power, and the next moment returns to step (1);

[0024] (4) Determine whether the battery power is lower than the set value. If yes, execute step (3); if no, execute step (5);

[0025] (5) Determine whether a boost command is received, if yes, execute step (6), if no, execute step (7);

[0026] (6) The hydrogen and oxygen cylinders supply gas to the hydrogen and oxygen storage tanks respectively, and the oxygen cylinder supplies oxygen to the internal combustion engine. The oxygen flow rate is the maximum value of the internal combustion engine, and the internal combustion engine operates at maximum power. At the next moment, the process returns to step (1);

[0027] (7) determining whether a thruster start command has been received, if so, executing step (8), if not, executing step (9);

[0028] (8) The oxygen cylinder supplies oxygen to the internal combustion engine, and the oxygen flow rate is dynamically adjusted as needed, and then step (9) is executed;

[0029] (9) The oxygen cylinder supplies oxygen to the internal combustion engine, the oxygen flow rate is the minimum value of the internal combustion engine, the internal combustion engine operates at minimum power, and the next moment returns to execute step (1).

[0030] The advantages of the present invention compared with the prior art are:

[0031] (1) The present invention provides an energy-fluid matching design method for a cryogenic propellant integrated fluid system, which overcomes the poor mission adaptability of the prior art. The system operation state can be adjusted in time according to changes in the space environment and flight mission, and the energy and fluid can be matched, thereby improving the mission adaptability of the integrated fluid system.

[0032] (2) The present invention achieves regulation of the electrical power and thermal power of the internal combustion engine by regulating the oxygen flow of the internal combustion engine, which is beneficial to the precise matching of fluid and energy in the integrated fluid system and improves the reliability of the integrated fluid system.

[0033] (3) The present invention achieves regulation of the hydrogen and oxygen flow rates by regulating the hydrogen-oxygen heat distribution of the hydrogen-oxygen combined heat exchanger, so that the filling ratios of the hydrogen cylinder and the oxygen cylinder remain consistent, thereby improving the operating efficiency of the integrated fluid system. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 is a system structure diagram of the present invention;

[0035] Figure 2 It is the work flow chart of the present invention. DETAILED DESCRIPTION

[0036] In order to better understand the above technical scheme, the technical scheme of the present application is described in detail below through the accompanying drawings and specific embodiments. It should be understood that the embodiments of the present application and the specific features in the embodiments are detailed descriptions of the technical scheme of the present application, rather than limitations on the technical scheme of the present application. In the absence of conflict, the embodiments of the present application and the technical features in the embodiments can be combined with each other.

[0037] The following is a further detailed description of a cryogenic propellant integrated fluid system based on energy-fluid matching design provided by an embodiment of the present application in conjunction with the accompanying drawings of the specification. The specific implementation method may include (eg Figures 1-2 shown):

[0038] In the solution provided in the embodiment of the present application, Figure 1 As shown, a method for designing energy-fluid matching of a cryogenic propellant integrated fluid system includes a hydrogen tank module, an oxygen tank module, a hydrogen fluid pump module, an oxygen fluid pump module, a hydrogen bottle module, an oxygen bottle module, a hydrogen-oxygen combined heat exchanger module, an internal combustion engine module, and a thruster module.

[0039] Hydrogen tank module, oxygen tank module, hydrogen fluid pump module, oxygen fluid pump module, hydrogen cylinder module, oxygen cylinder module, hydrogen-oxygen combined heat exchanger module, internal combustion engine module, thruster module;

[0040] The hydrogen tank module and oxygen tank module are used to store liquid hydrogen and liquid oxygen respectively, and realize the self-pressurization function of hydrogen and oxygen at the same time;

[0041] The hydrogen fluid pump module and the oxygen fluid pump module are used to extract liquid hydrogen and liquid oxygen from the tank and increase their pressure to supply the heat exchanger. It is characterized by adopting a motor-driven plunger pump, which can realize the change of fluid flow through real-time control instructions, while ensuring that the pressure after the pump remains stable;

[0042] The hydrogen cylinder module and the oxygen cylinder module are used to store gaseous hydrogen and gaseous oxygen respectively, and can provide gaseous hydrogen and gaseous oxygen for the internal combustion engine module, the thruster module, the hydrogen tank module, and the oxygen tank module;

[0043] The hydrogen-oxygen combined heat exchanger module is used to exchange heat between liquid hydrogen, liquid oxygen and internal combustion engine coolant, so that liquid hydrogen and liquid oxygen are vaporized into gaseous hydrogen and gaseous oxygen and stored in gas cylinders. It is characterized in that the heat provided by the coolant can be distributed between liquid hydrogen and liquid oxygen, and the flow rate of gaseous hydrogen and gaseous oxygen can be adjusted under the premise of ensuring that the temperature of gaseous hydrogen and gaseous oxygen at the heat exchanger outlet remains unchanged.

[0044] The internal combustion engine module is used to burn gaseous hydrogen and gaseous oxygen and drive the generator to generate electricity, which is stored in the battery, and the cylinder wall is cooled by the internal combustion engine coolant. It is characterized by adopting a hydrogen-rich combustion method, the gaseous hydrogen burned comes from the gaseous hydrogen evaporated from the hydrogen storage tank, and the gaseous oxygen comes from the gaseous oxygen supplied by the hydrogen cylinder, and the electric power and thermal power can be adjusted by adjusting the flow of gaseous oxygen.

[0045] The thruster module is used to burn gaseous hydrogen and gaseous oxygen to provide thrust, so as to realize functions such as attitude control of the aircraft.

[0046] Furthermore, the thruster module adopts a DC impact or pintle injector, the hydrogen used for combustion comes from the hydrogen supplied by the hydrogen cylinder, and the oxygen used for combustion comes from the oxygen supplied by the hydrogen cylinder, and has the ability of multiple ignition and starting.

[0047] Optionally, the energy and fluid of the fluid system are adjusted according to demand to operate in at least three different modes.

[0048] 1. When operating in one of the working modes, the internal combustion engine runs at the lowest power, the oxygen cylinder supplies oxygen to the internal combustion engine, and the oxygen flow rate is the minimum value of the internal combustion engine.

[0049] 2. When operating in one of the working modes, the internal combustion engine runs at the highest power, the oxygen cylinder supplies oxygen to the internal combustion engine, and the oxygen flow rate is the maximum value of the internal combustion engine.

[0050] 3. When operating in one of the working modes, the internal combustion engine operates between the minimum power and the maximum power according to the pressure of the hydrogen and oxygen cylinders and the battery power requirements. The oxygen cylinder supplies oxygen to the internal combustion engine, and the oxygen flow rate is dynamically adjusted as needed.

[0051] A cryogenic propellant integrated fluid system energy-fluid matching design method comprises the following steps:

[0052] (1) Read the current amount of liquid hydrogen evaporation, hydrogen and oxygen cylinder pressure, and battery power;

[0053] (2) Determine whether the pressure of the hydrogen and oxygen cylinder is lower than the set value. If yes, execute step (3); if not, execute step (4);

[0054] (3) The oxygen cylinder supplies oxygen to the internal combustion engine, and the oxygen flow rate is dynamically adjusted according to needs. The internal combustion engine operates at medium power, and the next moment returns to step (1);

[0055] (4) Determine whether the battery power is lower than the set value. If yes, execute step (3); if no, execute step (5);

[0056] (5) Determine whether a boost command is received, if yes, execute step (6), if no, execute step (7);

[0057] (6) The hydrogen and oxygen cylinders supply gas to the hydrogen and oxygen storage tanks respectively, and the oxygen cylinder supplies oxygen to the internal combustion engine. The oxygen flow rate is the maximum value of the internal combustion engine, and the internal combustion engine operates at maximum power. At the next moment, the process returns to step (1);

[0058] (7) determining whether a thruster start command has been received, if so, executing step (8), if not, executing step (9);

[0059] (8) The oxygen cylinder supplies oxygen to the internal combustion engine, and the oxygen flow rate is dynamically adjusted as needed, and then step (9) is executed;

[0060] (9) The oxygen cylinder supplies oxygen to the internal combustion engine, the oxygen flow rate is the minimum value of the internal combustion engine, the internal combustion engine operates at the minimum power, and the next moment returns to execute step (1)

[0061] Obviously, those skilled in the art can make various changes and modifications to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is also intended to include these modifications and variations.

[0062] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. A cryogenic propellant integrated fluid system based on energy-fluid matching design, characterized in that: It includes a hydrogen tank module, an oxygen tank module, a hydrogen fluid pump module, an oxygen fluid pump module, a hydrogen cylinder module, an oxygen cylinder module, a hydrogen-oxygen combined heat exchanger module, an internal combustion engine module, and a thruster module; The hydrogen tank module and the oxygen tank module are used to store liquid hydrogen and liquid oxygen respectively, and realize the self-pressurization function of hydrogen and oxygen at the same time; The hydrogen fluid pump module and the oxygen fluid pump module are used to extract liquid hydrogen and liquid oxygen from the storage tank and increase their pressure to supply the heat exchanger respectively; The hydrogen cylinder module and the oxygen cylinder module are used to store gaseous hydrogen and gaseous oxygen respectively, and can provide gaseous hydrogen and gaseous oxygen for the internal combustion engine module, the thruster module, the hydrogen tank module, and the oxygen tank module; The hydrogen-oxygen combined heat exchanger module is used to perform heat exchange on liquid hydrogen, liquid oxygen and internal combustion engine coolant, so that liquid hydrogen and liquid oxygen are vaporized into gaseous hydrogen and gaseous oxygen and stored in gas cylinders; The internal combustion engine module is used to burn gaseous hydrogen and gaseous oxygen and drive the generator to generate electricity, which is stored in the battery, and the cylinder wall is cooled by the internal combustion engine coolant; The thruster module is used to burn gaseous hydrogen and gaseous oxygen to provide thrust and realize attitude control of the aircraft.

2. The cryogenic propellant integrated fluid system based on energy-fluid matching design according to claim 1, characterized in that: The hydrogen fluid pump module and the oxygen fluid pump module are in the form of motor-driven plunger pumps, which realize the change of fluid flow rate through real-time control instructions while ensuring that the pressure after the pump remains stable.

3. The cryogenic propellant integrated fluid system based on energy-fluid matching design according to claim 1, characterized in that: The hydrogen-oxygen combined heat exchanger module distributes the heat provided by the coolant between liquid hydrogen and liquid oxygen, and achieves flow regulation of gaseous hydrogen and gaseous oxygen on the premise of ensuring that the temperatures of gaseous hydrogen and gaseous oxygen at the heat exchanger outlet remain unchanged.

4. The cryogenic propellant integrated fluid system based on energy-fluid matching design according to claim 1, characterized in that: The internal combustion engine module adopts a hydrogen-rich combustion mode. The gaseous hydrogen used for combustion comes from the gaseous hydrogen evaporated from the hydrogen storage tank, and the gaseous oxygen used for combustion comes from the gaseous oxygen supplied by the oxygen cylinder. The regulation of electric power and thermal power is achieved by adjusting the flow rate of gaseous oxygen.

5. The cryogenic propellant integrated fluid system based on energy-fluid matching design according to claim 1, characterized in that: The thruster module adopts a DC impact or pintle injector. The hydrogen used for combustion comes from the hydrogen supplied by the hydrogen cylinder, and the oxygen used for combustion comes from the oxygen supplied by the hydrogen cylinder. It has the ability of multiple ignition and starting.

6. The cryogenic propellant integrated fluid system based on energy-fluid matching design according to claim 1, characterized in that: The energy and fluid of the fluid system are adjusted according to demand, and it works in at least three different modes.

7. The cryogenic propellant integrated fluid system based on energy-fluid matching design according to claim 6, characterized in that: In one of the working modes, the internal combustion engine operates at the lowest power, the oxygen cylinder supplies oxygen to the internal combustion engine, and the oxygen flow rate is the minimum value of the internal combustion engine.

8. The cryogenic propellant integrated fluid system based on energy-fluid matching design according to claim 6, characterized in that: In one of the operating modes, the internal combustion engine operates at the highest power, the oxygen cylinder supplies oxygen to the internal combustion engine, and the oxygen flow rate is the maximum value of the internal combustion engine.

9. The cryogenic propellant integrated fluid system based on energy-fluid matching design according to claim 6, characterized in that: In one of the operating modes, the internal combustion engine operates between the minimum power and the maximum power according to the pressure of the hydrogen and oxygen cylinders and the battery power requirements. The oxygen cylinder supplies oxygen to the internal combustion engine, and the oxygen flow rate is dynamically adjusted as needed.

10. The method for adjusting the energy and fluid of a cryogenic propellant integrated fluid system according to claim 1 based on energy-fluid matching design is characterized in that: include: (1) Read the current amount of liquid hydrogen evaporation, hydrogen and oxygen cylinder pressure, and battery power; (2) Determine whether the pressure of the hydrogen and oxygen cylinder is lower than the set value. If yes, execute step (3); if not, execute step (4); (3) The oxygen cylinder supplies oxygen to the internal combustion engine, and the oxygen flow rate is dynamically adjusted according to needs. The internal combustion engine operates at medium power, and the next moment returns to step (1); (4) Determine whether the battery power is lower than the set value. If yes, execute step (3); if no, execute step (5); (5) Determine whether a boost command is received, if yes, execute step (6), if no, execute step (7); (6) The hydrogen and oxygen cylinders supply gas to the hydrogen and oxygen storage tanks respectively, and the oxygen cylinder supplies oxygen to the internal combustion engine. The oxygen flow rate is the maximum value of the internal combustion engine, and the internal combustion engine operates at maximum power. At the next moment, the process returns to step (1); (7) determining whether a thruster start command has been received, if so, executing step (8), if not, executing step (9); (8) The oxygen cylinder supplies oxygen to the internal combustion engine, and the oxygen flow rate is dynamically adjusted as needed, and then step (9) is executed; (9) The oxygen cylinder supplies oxygen to the internal combustion engine, the oxygen flow rate is the minimum value of the internal combustion engine, the internal combustion engine operates at minimum power, and the next moment returns to execute step (1).

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