CN115649492A - Low-temperature propellant integrated fluid system based on energy-fluid matching design - Google Patents
Low-temperature propellant integrated fluid system based on energy-fluid matching design Download PDFInfo
- Publication number
- CN115649492A CN115649492A CN202211339092.7A CN202211339092A CN115649492A CN 115649492 A CN115649492 A CN 115649492A CN 202211339092 A CN202211339092 A CN 202211339092A CN 115649492 A CN115649492 A CN 115649492A
- Authority
- CN
- China
- Prior art keywords
- oxygen
- hydrogen
- module
- gas
- combustion engine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Abstract
A low-temperature propellant integrated fluid system based on energy-fluid matching design is characterized in that a hydrogen storage tank module and an oxygen storage tank module are respectively used for storing liquid hydrogen and liquid oxygen and realizing the self-generation pressurization function of hydrogen and oxygen; the hydrogen fluid pump module and the oxygen fluid pump module are respectively used for pumping liquid hydrogen and liquid oxygen from the storage tank and increasing the pressure of the liquid hydrogen and the liquid oxygen to supply the liquid hydrogen and the liquid oxygen to the heat exchanger; the hydrogen cylinder module and the oxygen cylinder module are respectively used for storing gas hydrogen and gas oxygen and can provide the gas hydrogen and the gas oxygen for the internal combustion engine module, the thruster module, the hydrogen storage tank module and the oxygen storage tank module; the hydrogen-oxygen combined heat exchanger module is used for exchanging heat for liquid hydrogen, liquid oxygen and cooling liquid of the internal combustion engine, so that the liquid hydrogen and the liquid oxygen are gasified and changed into gas hydrogen and gas oxygen which are stored in a gas cylinder; the internal combustion engine module is used for combusting hydrogen and oxygen and driving the generator to generate electricity, storing the electricity in the storage battery, and cooling the cylinder wall through internal combustion engine cooling liquid; the thruster module is used for providing thrust for combustion gas hydrogen and gas oxygen to realize attitude control of the aircraft.
Description
Technical Field
The invention relates to a low-temperature propellant integrated fluid system based on an energy-fluid matching design, and belongs to the technical field of propellant integrated fluid systems.
Background
The low-temperature propellant integrated fluid system integrates the functions of attitude and orbit control, power generation, pressurization and the like into a whole by integrally managing the low-temperature propellant, so that the design margin of each independent system can be reduced, and the purpose of optimizing the system is further achieved. The integrated fluid system adopts a high-specific-impulse hydrogen-oxygen thruster and a hydrogen-oxygen-based internal combustion engine power generation system to replace a traditional auxiliary power system, a large-scale battery system and a helium pressurization system, so that the limitations of hydrazine propellant consumption, battery capacity, helium consumption and the like can be broken through, the efficiency of a transportation system is improved, the on-orbit time is increased, and the task capacity is expanded. In addition, the integrated fluid system can remarkably reduce the types of propellants for on-rail filling, and is favorable for developing a reusable space transportation system based on a liquid hydrogen, liquid oxygen and on-rail filling technology in the future.
The integrated fluid system has a large number of components and complex working parameters, and different components have strong mutual coupling relation, which brings great difficulty to the scheme design and parameter optimization of the integrated fluid system. The existing integrated fluid system design method usually needs to clearly define all specific links of a flight task in advance, develops targeted parameter design from the beginning, is difficult to adjust in time according to the change of a space environment and the flight task, and has poor task adaptability.
Disclosure of Invention
The invention solves the technical problems that: the defects in the prior art are overcome, the low-temperature propellant integrated fluid system based on the energy-fluid matching design is provided, the task adaptability of the integrated fluid system is improved, and meanwhile, the reliability and the operation efficiency of the integrated fluid system are improved.
The technical solution of the invention is as follows: a low-temperature propellant integrated fluid system based on energy-fluid matching design comprises a hydrogen storage tank module, an oxygen storage 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 storage tank module and the oxygen storage tank module are respectively used for storing liquid hydrogen and liquid oxygen and realizing the self-generation pressurization function of hydrogen and oxygen;
the hydrogen fluid pump module and the oxygen fluid pump module are respectively used for pumping liquid hydrogen and liquid oxygen from the storage tank and increasing the pressure of the liquid hydrogen and the liquid oxygen to supply the liquid hydrogen and the liquid oxygen to the heat exchanger;
the hydrogen cylinder module and the oxygen cylinder module are respectively used for storing gas hydrogen and gas oxygen and can provide gas hydrogen and gas oxygen for the internal combustion engine module, the thruster module, the hydrogen storage tank module and the oxygen storage tank module;
the hydrogen-oxygen combined heat exchanger module is used for exchanging heat for liquid hydrogen, liquid oxygen and cooling liquid of the internal combustion engine, so that the liquid hydrogen and the liquid oxygen are gasified and changed into gas hydrogen and gas oxygen which are stored in a gas cylinder;
the internal combustion engine module is used for combusting hydrogen and oxygen and driving the generator to generate electricity, storing the electricity in the storage battery, and cooling the cylinder wall through internal combustion engine cooling liquid;
the thruster module is used for providing thrust for combustion gas hydrogen and gas oxygen to realize attitude control of the aircraft.
Furthermore, the hydrogen fluid pump module and the oxygen fluid pump module adopt a plunger pump mode driven by a motor, the change of fluid flow is realized through a real-time control instruction, and the pressure after the pump is ensured to be kept stable.
Furthermore, the oxyhydrogen combined heat exchanger module distributes heat provided by the cooling liquid between liquid hydrogen and liquid oxygen, and realizes the flow regulation of the gas hydrogen and the gas oxygen on the premise of ensuring that the temperature of the gas hydrogen and the gas oxygen at the outlet of the heat exchanger is not changed.
Furthermore, the internal combustion engine module adopts a hydrogen-rich combustion mode, the gas hydrogen used for combustion is derived from the gas hydrogen evaporated by the hydrogen storage tank, the gas oxygen used for combustion is derived from the gas oxygen supplied by the oxygen cylinder, and the adjustment of electric power and thermal power is realized by adjusting the flow rate of the gas oxygen.
Furthermore, the thruster module adopts a direct current impact type or pintle type injector, the gas hydrogen used for combustion is from the gas hydrogen supplied by a hydrogen cylinder, and the gas oxygen used for combustion is from the gas oxygen supplied by the hydrogen cylinder, so that the thruster module has the capability of starting multiple ignitions.
Further, the energy and fluid of the fluid system are regulated according to requirements, and the fluid system works in at least three different modes.
And further, the internal combustion engine operates in one working condition mode, the internal combustion engine operates at the lowest power, the oxygen cylinder supplies oxygen to the internal combustion engine, and the oxygen flow is the minimum value of the internal combustion engine.
And further, the internal combustion engine operates in one working condition mode, the internal combustion engine runs at the highest power, the oxygen cylinder supplies oxygen to the internal combustion engine, and the oxygen flow is the maximum value of the internal combustion engine.
And further, the internal combustion engine works in one working condition mode, the internal combustion engine runs between the lowest power and the highest power according to the pressure of the hydrogen-oxygen cylinder and the electric quantity requirement of the storage battery, the oxygen cylinder supplies oxygen to the internal combustion engine, and the oxygen flow is dynamically adjusted according to the requirement.
According to the method for realizing the adjustment of the energy and the fluid of the system according to the requirement by the low-temperature propellant integrated fluid system based on the energy-fluid matching design, the method comprises the following steps:
(1) Reading the evaporation capacity of liquid hydrogen, the pressure of a hydrogen and oxygen cylinder and the electric quantity of a storage battery at the current moment;
(2) Judging whether the pressure of the oxyhydrogen gas bottle is lower than a set value, if so, executing the step (3), and if not, executing the step (4);
(3) The oxygen cylinder supplies oxygen to the internal combustion engine, the oxygen flow is dynamically adjusted according to the requirement, the internal combustion engine runs at medium power, and the step (1) is executed at the next moment;
(4) Judging whether the electric quantity of the storage battery is lower than a set value, if so, executing the step (3), and if not, executing the step (5);
(5) Judging whether a pressurization command is received, if so, executing the step (6), and if not, executing the step (7);
(6) The oxyhydrogen gas bottle supplies gas to the oxyhydrogen storage tank respectively, the oxygen bottle supplies oxygen to the internal-combustion engine, the oxygen flow is the maximum value of the internal-combustion engine, the internal-combustion engine runs at the maximum power, and the next moment returns to execute the step (1);
(7) Judging whether a thruster starting instruction is received or not, if so, executing step (8), and if not, executing step (9);
(8) The oxygen cylinder supplies oxygen to the internal combustion engine, the oxygen flow is dynamically adjusted according to the requirement, and then the step (9) is executed;
(9) And (3) supplying oxygen to the internal combustion engine by the oxygen cylinder, wherein the oxygen flow is the minimum value of the internal combustion engine, the internal combustion engine runs at the minimum power, and the step (1) is executed in the next moment.
Compared with the prior art, the invention has the advantages that:
(1) The invention provides an energy-fluid matching design method for a low-temperature propellant integrated fluid system, overcomes the characteristic of poor task adaptability in the prior art, can adjust the running state of the system in time according to the change of space environment and flight task, matches energy with fluid, and improves the task adaptability of the integrated fluid system.
(2) The invention realizes the regulation of the electric power and the thermal power of the internal combustion engine by regulating the oxygen flow of the internal combustion engine, is beneficial to the accurate matching of the fluid and the energy of the integrated fluid system, and improves the reliability of the integrated fluid system.
(3) The invention realizes the adjustment of the flow of hydrogen, oxygen and oxygen by the distribution and adjustment of the hydrogen and oxygen heat of the hydrogen and oxygen combined heat exchanger, so that the charging proportion of the hydrogen cylinder and the oxygen cylinder is kept consistent, and the running efficiency of the integrated fluid system is improved.
Drawings
FIG. 1 is a block diagram of the system of the present invention;
fig. 2 is a flow chart of the operation of the present invention.
Detailed Description
In order to better understand the technical solutions, the technical solutions of the present application are described in detail below with reference to the drawings and specific embodiments, and it should be understood that the specific features in the embodiments and examples of the present application are detailed descriptions of the technical solutions of the present application, and are not limitations of the technical solutions of the present application, and the technical features in the embodiments and examples of the present application may be combined with each other without conflict.
The low-temperature propellant integrated fluid system based on the energy-fluid matching design provided by the embodiments of the present application is further described in detail below with reference to the accompanying drawings, and specific implementations may include (as shown in fig. 1 to 2):
in the solution provided in the embodiment of the present application, as shown in fig. 1, 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 cylinder module, an oxygen cylinder module, a combined hydrogen and oxygen heat exchanger module, an internal combustion engine module, and a thruster module.
The hydrogen storage tank module, the oxygen storage tank module, the hydrogen fluid pump module, the oxygen fluid pump module, the hydrogen cylinder module, the oxygen cylinder module, the hydrogen and oxygen combined heat exchanger module, the internal combustion engine module and the thruster module;
the hydrogen storage tank module and the oxygen storage tank module are respectively used for storing liquid hydrogen and liquid oxygen and realizing the self-generation pressurization function of hydrogen and oxygen;
the hydrogen fluid pump module and the oxygen fluid pump module are respectively used for extracting liquid hydrogen and liquid oxygen from the storage tank and raising the pressure of the liquid hydrogen and the liquid oxygen to supply to the heat exchanger. The method is characterized in that a plunger pump driven by a motor is adopted, so that the change of the flow of the fluid can be realized through a real-time control instruction, and the pressure after the pump is kept stable;
the hydrogen cylinder module and the oxygen cylinder module are respectively used for storing gas hydrogen and gas oxygen and can provide gas hydrogen and gas oxygen for the internal combustion engine module, the thruster module, the hydrogen storage tank module and the oxygen storage tank module;
the hydrogen-oxygen combined heat exchanger module is used for exchanging heat for liquid hydrogen, liquid oxygen and cooling liquid of the internal combustion engine, so that the liquid hydrogen and the liquid oxygen are gasified and changed into gas hydrogen and gas oxygen which are stored in the gas cylinder. The method is characterized in that heat provided by cooling liquid can be distributed between liquid hydrogen and liquid oxygen, and the flow regulation of gas hydrogen and gas oxygen is realized on the premise of ensuring that the temperature of the gas hydrogen and the gas oxygen at the outlet of the heat exchanger is not changed.
The internal combustion engine module is used for combusting hydrogen and oxygen and driving a generator to generate electricity, is stored in a storage battery, and simultaneously cools the cylinder wall through internal combustion engine cooling liquid. The hydrogen-rich combustion mode is adopted, the combusted gas hydrogen comes from the gas hydrogen evaporated by the hydrogen storage tank, the gas oxygen comes from the gas oxygen supplied by the hydrogen cylinder, and the adjustment of electric power and thermal power can be realized by adjusting the flow of the gas oxygen.
The thruster module is used for combusting gas hydrogen and gas oxygen to provide thrust so as to realize functions of attitude control and the like of the aircraft.
Furthermore, the thruster module adopts a direct current impact type or pintle type injector, the gas hydrogen used for combustion is from the gas hydrogen supplied by a hydrogen cylinder, and the gas oxygen used for combustion is from the gas oxygen supplied by the hydrogen cylinder, so that the thruster module has the capability of starting multiple ignitions.
Optionally, the energy and the fluid of the fluid system are adjusted according to the requirements, and the fluid system operates in at least three different modes.
1. The oxygen cylinder supplies oxygen to the internal combustion engine, and the oxygen flow is the minimum value of the internal combustion engine.
2. The oxygen cylinder supplies oxygen to the internal combustion engine, and the oxygen flow is the maximum value of the internal combustion engine.
3. The internal combustion engine operates in one working condition mode, the internal combustion engine operates between the lowest power and the highest power according to the pressure of the hydrogen and oxygen cylinder and the electric quantity requirement of the storage battery, the oxygen cylinder supplies oxygen to the internal combustion engine, and the oxygen flow is dynamically adjusted according to the requirement.
A low-temperature propellant integrated fluid system energy-fluid matching design method comprises the following steps:
(1) Reading the evaporation capacity of liquid hydrogen, the pressure of a hydrogen-oxygen gas bottle and the electric quantity of a storage battery at the current moment;
(2) Judging whether the pressure of the oxyhydrogen gas bottle is lower than a set value, if so, executing the step (3), and if not, executing the step (4);
(3) The oxygen cylinder supplies oxygen to the internal combustion engine, the oxygen flow is dynamically adjusted according to the requirement, the internal combustion engine runs at medium power, and the step (1) is executed again at the next moment;
(4) Judging whether the electric quantity of the storage battery is lower than a set value, if so, executing the step (3), and if not, executing the step (5);
(5) Judging whether a pressurization command is received, if so, executing the step (6), and if not, executing the step (7);
(6) The oxyhydrogen gas bottle supplies gas to the oxyhydrogen storage tank respectively, the oxygen bottle supplies oxygen to the internal-combustion engine, the oxygen flow is the maximum value of the internal-combustion engine, the internal-combustion engine runs at the maximum power, and the next moment returns to execute the step (1);
(7) Judging whether a thruster starting instruction is received or not, if so, executing the step (8), and if not, executing the step (9);
(8) The oxygen cylinder supplies oxygen to the internal combustion engine, the oxygen flow is dynamically adjusted according to the requirement, and then the step (9) is executed;
(9) The oxygen cylinder supplies oxygen to the internal combustion engine, the oxygen flow is the minimum value of the internal combustion engine, the internal combustion engine runs at the minimum power, and the next time returns to the step (1)
It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such 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 intended to include such modifications and variations as well.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are not particularly limited to the specific examples described herein.
Claims (10)
1. A low-temperature propellant integrated fluid system based on energy-fluid matching design is characterized by comprising a hydrogen storage tank module, an oxygen storage 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 storage tank module and the oxygen storage tank module are respectively used for storing liquid hydrogen and liquid oxygen and realizing the self-generation pressurization function of hydrogen and oxygen;
the hydrogen fluid pump module and the oxygen fluid pump module are respectively used for pumping liquid hydrogen and liquid oxygen from the storage tank and increasing the pressure of the liquid hydrogen and the liquid oxygen to supply the liquid hydrogen and the liquid oxygen to the heat exchanger;
the hydrogen cylinder module and the oxygen cylinder module are respectively used for storing gas hydrogen and gas oxygen and can provide gas hydrogen and gas oxygen for the internal combustion engine module, the thruster module, the hydrogen storage tank module and the oxygen storage tank module;
the hydrogen-oxygen combined heat exchanger module is used for exchanging heat for liquid hydrogen, liquid oxygen and cooling liquid of the internal combustion engine, so that the liquid hydrogen and the liquid oxygen are gasified and changed into gas hydrogen and gas oxygen which are stored in a gas cylinder;
the internal combustion engine module is used for combusting hydrogen and oxygen and driving the generator to generate electricity, storing the electricity in the storage battery, and cooling the cylinder wall through internal combustion engine cooling liquid;
the thruster module is used for providing thrust by combusting gas hydrogen and gas oxygen to realize the attitude control of the aircraft.
2. The low-temperature propellant integrated fluid system based on the energy-fluid matching design as claimed in claim 1, wherein the hydrogen fluid pump module and the oxygen fluid pump module are in the form of motor-driven plunger pumps, and the change of fluid flow is realized through real-time control instructions, and meanwhile, the pressure after the pumps is ensured to be stable.
3. The cryogenic propellant integrated fluid system based on energy-fluid matching design as claimed in claim 1, wherein the oxyhydrogen heat exchanger module distributes heat provided by cooling liquid between liquid hydrogen and liquid oxygen, and realizes flow regulation of gas hydrogen and gas oxygen under the premise of ensuring constant temperature of gas hydrogen and gas oxygen at the outlet of the heat exchanger.
4. The cryogenic propellant integrated fluid system based on the energy-fluid matching design as claimed in claim 1, wherein the internal combustion engine module adopts a hydrogen-rich combustion mode, hydrogen used for combustion is derived from hydrogen evaporated from a hydrogen storage tank, oxygen used for combustion is derived from oxygen supplied from an oxygen cylinder, and the adjustment of electric power and thermal power is realized by adjusting the flow of the oxygen.
5. The low-temperature propellant integrated fluid system based on the energy-fluid matching design as claimed in claim 1, wherein the thruster module is a direct current impact type or pintle type injector, the combustion gas hydrogen is from the gas hydrogen supplied by a hydrogen cylinder, and the combustion gas oxygen is from the gas oxygen supplied by the hydrogen cylinder, and the system has multiple ignition starting capability.
6. The cryogenic propellant integrated fluid system of claim 1 wherein the energy and fluid in the fluid system are regulated on demand to operate in at least three different modes.
7. The low-temperature propellant integrated fluid system based on the energy-fluid matching design as claimed in claim 6, wherein in one of the operating modes, the internal combustion engine is operated at the lowest power, the oxygen cylinder supplies oxygen to the internal combustion engine, and the oxygen flow is the minimum of the internal combustion engine.
8. The low-temperature propellant integrated fluid system based on the energy-fluid matching design as claimed in claim 6, wherein in one of the operating modes, the internal combustion engine is operated at the highest power, the oxygen cylinder supplies oxygen to the internal combustion engine, and the oxygen flow is the maximum of the internal combustion engine.
9. The cryogenic propellant integrated fluid system of claim 6 wherein the internal combustion engine is operated in one of the operating modes between a minimum power and a maximum power based on the pressure of the oxyhydrogen gas cylinder and the battery charge requirement, the cylinder supplies oxygen to the internal combustion engine, and the flow of oxygen is dynamically adjusted as required.
10. The method for realizing the adjustment of the energy and the fluid of the system according to the requirement of the low-temperature propellant integrated fluid system based on the energy-fluid matching design is characterized by comprising the following steps of:
(1) Reading the evaporation capacity of liquid hydrogen, the pressure of a hydrogen and oxygen cylinder and the electric quantity of a storage battery at the current moment;
(2) Judging whether the pressure of the oxyhydrogen gas bottle is lower than a set value, if so, executing the step (3), and if not, executing the step (4);
(3) The oxygen cylinder supplies oxygen to the internal combustion engine, the oxygen flow is dynamically adjusted according to the requirement, the internal combustion engine runs at medium power, and the step (1) is executed again at the next moment;
(4) Judging whether the electric quantity of the storage battery is lower than a set value, if so, executing the step (3), and if not, executing the step (5);
(5) Judging whether a pressurization instruction is received or not, if so, executing the step (6), and if not, executing the step (7);
(6) The oxyhydrogen gas bottle supplies gas to the oxyhydrogen storage tank respectively, the oxygen bottle supplies oxygen to the internal-combustion engine, the oxygen flow is the maximum value of the internal-combustion engine, the internal-combustion engine runs at the maximum power, and the next moment returns to execute the step (1);
(7) Judging whether a thruster starting instruction is received or not, if so, executing the step (8), and if not, executing the step (9);
(8) The oxygen cylinder supplies oxygen to the internal combustion engine, the oxygen flow is dynamically adjusted according to the requirement, and then the step (9) is executed;
(9) And (3) supplying oxygen to the internal combustion engine by the oxygen cylinder, wherein the oxygen flow is the minimum value of the internal combustion engine, the internal combustion engine runs at the minimum power, and the step (1) is executed in the next moment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211339092.7A CN115649492A (en) | 2022-10-28 | 2022-10-28 | Low-temperature propellant integrated fluid system based on energy-fluid matching design |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211339092.7A CN115649492A (en) | 2022-10-28 | 2022-10-28 | Low-temperature propellant integrated fluid system based on energy-fluid matching design |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115649492A true CN115649492A (en) | 2023-01-31 |
Family
ID=84993194
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211339092.7A Pending CN115649492A (en) | 2022-10-28 | 2022-10-28 | Low-temperature propellant integrated fluid system based on energy-fluid matching design |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115649492A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116215888A (en) * | 2023-02-01 | 2023-06-06 | 哈尔滨工程大学 | Spacecraft integrated fluid system based on linear Joule engine |
| CN117184457A (en) * | 2023-07-25 | 2023-12-08 | 中国科学院力学研究所 | Device and method for stabilizing pressure and liquid level of aerospace craft |
-
2022
- 2022-10-28 CN CN202211339092.7A patent/CN115649492A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116215888A (en) * | 2023-02-01 | 2023-06-06 | 哈尔滨工程大学 | Spacecraft integrated fluid system based on linear Joule engine |
| CN116215888B (en) * | 2023-02-01 | 2023-08-11 | 哈尔滨工程大学 | Spacecraft integrated fluid system based on linear Joule engine |
| CN117184457A (en) * | 2023-07-25 | 2023-12-08 | 中国科学院力学研究所 | Device and method for stabilizing pressure and liquid level of aerospace craft |
| CN117184457B (en) * | 2023-07-25 | 2024-04-09 | 中国科学院力学研究所 | Device and method for stabilizing pressure and liquid level of aerospace craft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN115649492A (en) | Low-temperature propellant integrated fluid system based on energy-fluid matching design | |
| CA2755479C (en) | Continuous flow thermodynamic pump | |
| US8763565B2 (en) | Two engine system with a gaseous fuel stored in liquefied form | |
| CN110979746A (en) | Rocket three-stage solid-liquid main power and attitude control integrated system and method thereof | |
| CN213928583U (en) | Liquid power device based on propellant self-pressurization technology | |
| US11808204B2 (en) | Circuit for supplying fuel to an aeronautical cryogenic turbomachine and associated method | |
| RU2447313C1 (en) | Restartable liquid-propellant engine (versions) | |
| CN114837814B (en) | Thermal management type combined power device | |
| CN109578134B (en) | Hydrogen and oxygen recycling system and application thereof | |
| CN207542327U (en) | Hydrogen cell automobile high-pressure hydrogen storing pressure tank energy retracting device | |
| CN215860603U (en) | Power generation system for realizing new energy storage by carbon dioxide liquefaction | |
| CN117836507A (en) | System for fuel conditioning for supplying an aircraft turbomachine, aircraft and method for using same | |
| CN114087540A (en) | High-efficient portable gas-liquid bimodulus hydrogen fuel filling device | |
| CN113283170A (en) | CCHP system considering operation mode and equipment capacity and model selection optimization method thereof | |
| Zegler | An integrated vehicle propulsion and power system for long duration cryogenic spaceflight | |
| CN116215888B (en) | Spacecraft integrated fluid system based on linear Joule engine | |
| CN103256146A (en) | Internal combustion engine cooling and heat recovery system | |
| CN220856623U (en) | Hydrogen energy conversion system based on solid-state hydrogen storage | |
| CN218587515U (en) | Accurate temperature control cooling sub-equipment | |
| US20230391467A1 (en) | Hydrogen-fuelled aircraft power system | |
| CN112628016B (en) | RBCC engine supply system | |
| CN201045333Y (en) | CO2 power take-off | |
| WO2004111527A1 (en) | Method and apparatus for generating compressed air from liquefied air, for supplying compressed air to an engine | |
| Gordin et al. | Aviation Engines Based on Solid Oxide Fuel Cells For Next Generation Transport Aircraft | |
| Winkler et al. | Differences and synergies between mobile and stationary SOFC-GT designs |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |