CN116215888B - Spacecraft integrated fluid system based on linear Joule engine - Google Patents
Spacecraft integrated fluid system based on linear Joule engine Download PDFInfo
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- CN116215888B CN116215888B CN202310048769.XA CN202310048769A CN116215888B CN 116215888 B CN116215888 B CN 116215888B CN 202310048769 A CN202310048769 A CN 202310048769A CN 116215888 B CN116215888 B CN 116215888B
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- 239000012530 fluid Substances 0.000 title claims abstract description 14
- 239000001257 hydrogen Substances 0.000 claims abstract description 173
- 229910052739 hydrogen Inorganic materials 0.000 claims abstract description 173
- 238000003860 storage Methods 0.000 claims abstract description 143
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims abstract description 138
- 239000001301 oxygen Substances 0.000 claims abstract description 134
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 134
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 123
- 239000007789 gas Substances 0.000 claims abstract description 119
- 239000007788 liquid Substances 0.000 claims abstract description 89
- 238000002485 combustion reaction Methods 0.000 claims abstract description 87
- 238000007906 compression Methods 0.000 claims abstract description 79
- 230000006835 compression Effects 0.000 claims abstract description 77
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 claims abstract description 45
- 150000002431 hydrogen Chemical class 0.000 claims abstract description 22
- 238000006073 displacement reaction Methods 0.000 claims description 15
- 230000008016 vaporization Effects 0.000 claims description 6
- 239000003795 chemical substances by application Substances 0.000 claims description 5
- 239000007921 spray Substances 0.000 claims description 4
- 239000003380 propellant Substances 0.000 description 53
- 239000000446 fuel Substances 0.000 description 26
- 238000000034 method Methods 0.000 description 9
- 230000008569 process Effects 0.000 description 8
- 238000004519 manufacturing process Methods 0.000 description 5
- 230000007246 mechanism Effects 0.000 description 4
- 230000009467 reduction Effects 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 230000003139 buffering effect Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 239000002826 coolant Substances 0.000 description 2
- 239000002828 fuel tank Substances 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 230000033001 locomotion Effects 0.000 description 2
- 230000005486 microgravity Effects 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000020169 heat generation Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 230000001960 triggered effect Effects 0.000 description 1
- 230000005514 two-phase flow Effects 0.000 description 1
- 239000002918 waste heat Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/244—Spacecraft control systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automation & Control Theory (AREA)
- Radar, Positioning & Navigation (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
The invention provides a spacecraft integrated fluid system based on a linear Joule engine, and belongs to the field of aerospace. The device comprises a linear generator, a free piston expander, a free piston compressor, an external combustion chamber, a hydrogen heat exchanger, an oxygen heat exchanger, an exhaust submerged nozzle, a high-pressure oxygen storage cylinder, a high-pressure hydrogen storage cylinder, a gesture control engine, a submerged engine, a track engine, a liquid oxygen storage tank and a liquid hydrogen storage tank, wherein the free piston compressor, the free piston expander and the linear generator are connected through a shaft, pistons in the free piston compressor and the free piston expander are fixed on the shaft, the liquid oxygen storage tank and the liquid hydrogen storage tank are respectively connected with a left compression cylinder oxygen supply valve and a right compression cylinder hydrogen supply valve of the free piston compressor, and gas and oxygen hydrogen compressed by the free piston compressor are respectively discharged through a left compression cylinder oxygen discharge valve and a right compression cylinder hydrogen discharge valve. It is mainly used for spacecraft integrated fluid systems.
Description
Technical Field
The invention belongs to the field of aerospace, and particularly relates to a spacecraft integrated fluid system based on a linear Joule engine.
Background
In order to achieve attitude control and orbit maneuver of the spacecraft during space voyage, it is required that the spacecraft must deliver oxyhydrogen fuel propellant from a fuel tank to an attitude control engine and an orbit maneuver engine for combustion. The realization method is as follows: the high-pressure gas carried by the spacecraft or the device capable of generating the high-pressure gas generates the high-pressure gas, then the high-pressure gas is conveyed into the oxyhydrogen fuel storage tank, the pressure in the storage tank is increased, the fuel in the storage tank is further pumped out, and the high-pressure gas is conveyed into the attitude control engine and the orbital maneuver engine for combustion after the temperature and the pressure are regulated. In the process of realizing the requirement, the pressurization of the storage tank, the temperature and pressure regulation of the extruding propellant and the combustion of the engine are all provided with a controller, and the spacecraft carries various electronic devices such as a computer, a transponder and the like, so that the spacecraft is required to be provided with an electric power supply device to meet the normal operation of all electronic devices while meeting the pressurization of the storage tank. In addition, the orbital motor burns the liquid fuel in the tank and the spacecraft operates under microgravity conditions, so that the concentration of the liquid fuel in the vicinity of the output pipeline when the liquid fuel is output from the fuel tank must be ensured, and the output liquid fuel is ensured not to be mixed with gas.
The existing spacecraft system scheme capable of realizing pressurization of the fuel storage tank and meeting the requirements of supplying power to spacecraft equipment and not clamping air during liquid outflow is as follows: the integrated fluid system for spacecraft based on oxyhydrogen internal combustion engine is characterized by that it utilizes the heated and evaporated gas propellant in liquid hydrogen-liquid oxygen storage tank and existent liquid propellant, and makes them pass through compressor to make pressurization, then makes them pass through heat-exchange circulation formed from heat exchanger, oxyhydrogen internal combustion engine heat-exchange jacket and recirculated oil to form high-temp. high-pressure gas, and these gases are divided into four portions, and the first portion is directly fed into attitude control engine for attitude control, and the second portion is fed back into storage tank to make pressurization, so that the propellant can be extruded, and a portion of extruded liquid propellant is fed into orbital engine to implement orbital maneuver, and the extruded gas propellant and another portion of liquid propellant can be pressurized and heat-exchanged again, and a portion is directly fed into attitude control engine for attitude control, and a portion is fed back into storage tank to make pressurization so as to repeatedly implement operation. And secondly, the system comprises an oxyhydrogen internal combustion engine, a third part of high-temperature and high-pressure gas generated by pressurizing and heat exchanging gas and liquid propellant is conveyed into the oxyhydrogen internal combustion engine to do combustion work, a generator connected with the internal combustion engine through a crank connecting rod mechanism is driven to generate power, and the oxyhydrogen internal combustion engine supplies power for various electronic devices on a spacecraft such as an electric motor, a system master controller and a storage box controller for driving a compressor. Finally, the system conveys the fourth part of the high-temperature high-pressure gas generated by pressurizing and heat exchanging the gas and liquid propellant to the submerged engine to burn and match with an exhaust submerged nozzle of the oxyhydrogen internal combustion engine to generate liquid fuel submerged thrust so as to meet the requirement that gas cannot be mixed in the liquid fuel when the fuel storage tank outputs the liquid fuel under the microgravity condition. The spacecraft system scheme is wide in system task adaptability, high in integration level and light in weight, and is a mainstream system scheme for realizing the attitude control function of the spacecraft at present.
However, current systems still have problems in terms of reliability, lifetime, system complexity, manufacturing difficulty, and overall thermal efficiency and cost of the system. In the propellant compression process of the prior system scheme, the same compressor is adopted for compressing the gas and liquid propellant. The compressor compresses working media with different phases at the same time, the requirement on the performance of the compressor is high, the difficulty of the working condition adjustment and control of the compressor is high, the design cost of the compressor is increased, the service life of the compressor is shortened, and therefore the service life of a spacecraft is shortened, and the reliability of the spacecraft is lowered. Secondly, in the heat exchange process of the oxyhydrogen internal combustion engine in the prior system scheme, the heat exchange is carried out by matching a heat exchange jacket of the internal combustion engine with the intermediate heat exchange agent recycle oil. The use of the heat exchange jacket can lead to complex internal combustion engine structure pipelines, the use of the intermediate heat exchange agent can lead to the loss of part of heat in the intermediate heat exchange process of the traditional system, the heat exchange efficiency of the system is lower than that of the propellant when the propellant exchanges heat with the internal combustion engine directly, so that the overall heat efficiency of the system is reduced, and the waste heat generation caused by intermittent work of the internal combustion engine is a discontinuous and discontinuous process, which inevitably leads to the unbalanced condition of part of high temperature and part of low temperature after the heat exchange of the intermediate heat exchange agent, further leads to the condition of part of high temperature and part of low temperature fluctuation of the propellant, and finally leads to the reduction of stability and reliability of the spacecraft when executing tasks. Finally, in the high-temperature and high-pressure gas conveying process of the prior system scheme, the pressurized and heated gas propellant in the system is directly conveyed into the attitude control engine, the bottom engine, the internal combustion engine and the storage tank, no gas buffer device is arranged in the middle for buffering to reduce fluctuation of temperature and pressure of the gas propellant, no intermediate transition device is arranged for integrating pipelines and distributing flow, and each pipeline is required to be provided with a separate flow control valve and a separate pressure control valve, so that the fuel supply requirement of each conveying terminal device is stricter and finer, the control difficulty is higher, the conveying pipeline is complex, the arrangement difficulty is high, the safety and the reliability of the system are influenced, and the design and manufacturing difficulty and the cost are improved.
Disclosure of Invention
The invention provides a spacecraft integrated fluid system based on a linear Joule engine, which aims to solve the problems in the prior art.
In order to achieve the above purpose, the present invention adopts the following technical scheme: a spacecraft integrated fluid system based on a linear Joule engine comprises a linear generator, a free piston expander, a free piston compressor, an external combustion chamber, a hydrogen heat exchanger, an oxygen heat exchanger, an exhaust submerged nozzle, a high-pressure oxygen storage cylinder, a high-pressure hydrogen storage cylinder, a posture control engine, a submerged engine, a rail engine, a liquid oxygen storage tank and a liquid hydrogen storage tank, wherein the free piston compressor, the free piston expander and the linear generator are connected through a shaft, pistons in the free piston compressor and the free piston expander are fixed on the shaft, the liquid oxygen storage tank and the liquid hydrogen storage tank are respectively connected with a left compression cylinder oxygen supply valve and a right compression cylinder hydrogen supply valve of the free piston compressor, gas and oxygen hydrogen compressed by the free piston compressor are respectively discharged through a left compression cylinder oxygen discharge valve and a right compression cylinder hydrogen discharge valve, the liquid hydrogen storage tank is connected with a liquid hydrogen booster pump, the liquid oxygen storage tank is connected with a liquid oxygen booster pump, the outlet of the liquid oxygen booster pump is connected with the heat exchanger inlet of the hydrogen heat exchanger, the outlet of the liquid oxygen booster pump is connected with the heat exchanger inlet of the oxygen heat exchanger, the outlet of the hydrogen heat exchanger is connected with the inlet of a high-pressure hydrogen storage cylinder, the outlet of the oxygen heat exchanger is connected with the inlet of the high-pressure oxygen storage cylinder, the high-pressure hydrogen storage cylinder is connected with a gas-hydrogen splitting device, the high-pressure oxygen storage cylinder is connected with the gas-oxygen splitting device, the gas-hydrogen splitting device and the gas-oxygen splitting device are respectively connected with a posture control engine, a bottom engine and a storage tank booster controller, the storage tank booster controller is connected with the liquid oxygen storage tank and the liquid hydrogen storage tank, the bottoms of the liquid oxygen storage tank and the liquid hydrogen storage tank are connected with a track engine, the gas-hydrogen splitting device and the gas-oxygen splitting device are connected with an external combustion chamber, the external combustion chamber is connected with a left expansion cylinder air inlet valve and a right expansion cylinder air inlet valve of the free piston expander, exhaust gas exhausted from a left expansion cylinder air outlet valve and a right expansion cylinder air outlet valve of the free piston expander is divided into two paths to respectively enter the hydrogen heat exchanger and the oxygen heat exchanger, exhaust gas after heat exchange enters the exhaust submerged nozzle, a compressor displacement sensor is arranged at the top of a cylinder of the free piston compressor, and an expander displacement sensor is arranged at the top of the cylinder of the free piston expander.
Further, the liquid hydrogen discharged from the liquid hydrogen storage tank is connected with a liquid hydrogen booster pump through a liquid pump hydrogen supply valve.
Further, the liquid oxygen discharged from the liquid oxygen storage tank is connected with the liquid oxygen booster pump through a liquid pump oxygen supply valve.
Furthermore, the hydrogen after absorbing heat and vaporizing from the outlet of the hydrogen heat exchanger and the hydrogen discharged by the hydrogen discharge valve of the right compression cylinder are mixed before the inlet of the high-pressure hydrogen storage cylinder and then flow into the high-pressure hydrogen storage cylinder together.
Further, the oxygen after absorbing heat and vaporizing from the outlet of the oxygen heat exchanger and the oxygen discharged by the oxygen discharge valve of the left compression cylinder are mixed before the inlet of the high-pressure oxygen storage cylinder and then flow into the high-pressure oxygen storage cylinder together.
Further, the tank pressurizing controller is connected with the liquid oxygen tank and the liquid hydrogen tank through a hydrogen tank pressurizing valve and an oxygen tank pressurizing valve respectively.
Further, the gas-oxygen diversion device is connected with the external combustion chamber through an external combustion chamber oxygen supply valve.
Further, the gas-hydrogen split device is connected with the external combustion chamber through an external combustion chamber hydrogen supply valve.
Further, the exhaust gas after heat exchange of the hydrogen heat exchanger and the oxygen heat exchanger is converged before the exhaust gas bottom spray pipe and then enters the exhaust gas bottom spray pipe.
Further, the external combustion chamber, the storage tank pressurizing controller and all valves are connected with a master controller, and the linear generator is connected with a rechargeable battery.
Compared with the prior art, the invention has the beneficial effects that:
1. the compression device used in the existing system comprises a hydrogen compressor and an oxygen compressor which are driven by an electric motor, the compression energy transmission process comprises the steps that chemical energy of fuel is converted into internal energy of gas in a cylinder through combustion, the gas in the cylinder pushes a piston to do work to convert the internal energy into kinetic energy of the piston, a crank-link mechanism transmits the kinetic energy to a generator, the kinetic energy is converted into electric energy through the generator, and the electric energy is converted into kinetic energy of the compressor through the motor. The system provided by the invention uses the compression device to be a free piston compressor and a liquid booster pump in a linear Joule engine, the liquid booster pump is also driven by an electric motor, the energy conversion process is the same as that of the existing system, but the free piston compressor shares the gas compression part of the two-phase compressor in the existing system and is not driven by the electric motor, the compression energy transmission process comprises the conversion of chemical energy of fuel into internal energy of gas in a cylinder, the internal energy is converted into kinetic energy of horizontal motion of a shaft left and right by pushing the piston to do work by the gas in the cylinder, and the kinetic energy of the shaft is directly transferred to the compression gas of the compressor to do work by the connection of the compressor piston and the shaft.
2. The existing system sends a part of the gas propellant into the oxyhydrogen internal combustion engine to perform combustion work, the combustion and the work of the internal combustion engine are integrated and are not mutually independent, the combustion of fuel influences the work of the piston, and the limiting conditions for the smooth combustion of the hydrogen internal combustion engine are quite large due to the characteristics of the hydrogen fuel. The linear Joule engine adopted by the system provided by the invention adopts the external combustion chamber matched with the free piston expander to complete the combustion and the working of fuel, the combustion and the working are mutually independent, the energy for working is externally input to the expander, and the adverse effect possibly occurring in the combustion process hardly affects the movement of the piston in the whole cylinder, so that the range of various parameters of the external combustion chamber capable of combusting hydrogen is wider, the range of power provided by the expander is also larger, the task adaptability of the whole spacecraft is further improved, and more tasks under different conditions can be executed.
3. The existing system adopts an oxyhydrogen internal combustion engine to burn fuel to do work, the internal combustion engine is connected with a generator through a crank-link mechanism, and kinetic energy is converted into electric energy through the generator to supply various electronic devices. The system provided by the invention adopts the linear Joule engine, the free piston expander of the linear Joule engine is directly connected with the linear generator through the shaft, and a crank-link mechanism is not arranged, so that the friction loss generated by the internal combustion engine in the existing system can be effectively reduced, and the overall energy utilization rate and the power generation efficiency of the system are improved.
Drawings
FIG. 1 is a schematic diagram of a spacecraft integrated fluid system based on a linear Joule engine according to the present invention, wherein the thin solid lines are propellant transport;
FIG. 2 is a schematic view of a free piston expander according to the present invention;
fig. 3 is a schematic view of a free piston compressor according to the present invention.
1: master controller, 2: linear generator, 3: rechargeable battery, 4: free piston expander, 5: an external combustion chamber, 6: hydrogen heat exchanger, 7: oxygen heat exchanger, 8: external combustion chamber oxygen supply valve, 9: external combustion chamber hydrogen supply valve, 10: free piston compressor, 11: exhaust submerged nozzle, 12: high-pressure oxygen storage bottle, 13: high pressure hydrogen storage cylinder, 14: attitude control engine, 15: gas-hydrogen splitting device, 16: gas oxygen diverging device, 17: a submersible engine, 18: liquid hydrogen booster pump, 19: liquid oxygen booster pump, 20: tank boost controller, 21: liquid pump hydrogen supply valve, 22: liquid pump oxygen supply valve, 23: hydrogen tank pressurization valve, 24: oxygen tank pressurization valve, 25: liquid oxygen tank, 26: liquid hydrogen tank, 27: orbital motor, 28: left expansion cylinder intake valve, 29: left expansion cylinder exhaust valve, 30: right expansion cylinder intake valve, 31: right expansion cylinder exhaust valve, 32: left compression cylinder oxygen valve, 33: left compression cylinder bleed valve, 34: right compression cylinder hydrogen supply valve, 35: right compression cylinder hydrogen valve, 36: expander displacement sensor, 37: compressor displacement sensor.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.
Referring to fig. 1-3 for illustrating the present embodiment, a spacecraft integrated fluid system based on a linear joule engine comprises a linear generator 2, a free piston expander 4, a free piston compressor 10, an external combustion chamber 5, a hydrogen heat exchanger 6, an oxygen heat exchanger 7, an exhaust submerged nozzle 11, a high-pressure oxygen cylinder 12, a high-pressure hydrogen cylinder 13, a attitude control engine 14, a submerged engine 17, a rail engine 27, a liquid oxygen storage tank 25 and a liquid hydrogen storage tank 26, wherein the free piston compressor 10, the free piston expander 4 and the linear generator 2 are connected through shafts, the pistons in the free piston compressor 10 and the free piston expander 4 are fixed on the shafts, the liquid oxygen storage tank 25 and the liquid hydrogen storage tank 26 are respectively connected with a left compression cylinder oxygen supply valve 32 and a right compression cylinder hydrogen supply valve 34 of the free piston compressor 10, the gas and oxygen hydrogen compressed by the free piston compressor 10 are respectively discharged through a left compression cylinder oxygen discharge valve 33 and a right compression cylinder hydrogen discharge valve 35, the liquid hydrogen storage tank 26 is connected with a liquid hydrogen booster pump 18, the liquid oxygen storage tank 25 is connected with a liquid oxygen booster pump 19, the outlet of the liquid hydrogen booster pump 18 is connected with the heat exchanger inlet of the hydrogen heat exchanger 6, the outlet of the liquid oxygen booster pump 19 is connected with the heat exchanger inlet of the oxygen heat exchanger 7, the outlet of the hydrogen heat exchanger 6 is connected with the inlet of a high-pressure hydrogen storage cylinder 13, the outlet of the oxygen heat exchanger 7 is connected with the inlet of a high-pressure oxygen storage cylinder 12, the high-pressure hydrogen storage cylinder 13 is connected with a gas hydrogen splitting device 15, the high-pressure oxygen storage cylinder 12 is connected with a gas oxygen splitting device 16, the gas hydrogen splitting device 15 and the gas oxygen splitting device 16 are respectively connected with the attitude control engine 14, the bottom engine 17 and the storage tank pressurizing controller 20, the storage tank pressurizing controller 20 is connected with the liquid oxygen storage tank 25 and the liquid hydrogen storage tank 26, the bottoms of the liquid oxygen storage tank 25 and the liquid hydrogen storage tank 26 are connected with the rail engine 27, the gas hydrogen splitting device 15 and the gas oxygen splitting device 16 are connected with the outer combustion chamber 5, the outer combustion chamber 5 is connected with the left expansion cylinder air inlet valve 28 and the right expansion cylinder air inlet valve 30 of the free piston expander 4, the exhaust gas discharged from the left expansion cylinder air outlet valve 29 and the right expansion cylinder air outlet valve 31 of the free piston expander 4 is divided into two paths to respectively enter the hydrogen heat exchanger 6 and the oxygen heat exchanger 7, the exhaust gas after heat exchange enters the exhaust submerged nozzle 11, the free piston compressor 10 is provided with a compressor displacement sensor 37 at the top of the cylinder, and the free piston expander 4 is provided with an expander displacement sensor 36 at the top of the cylinder.
The liquid hydrogen discharged from the liquid hydrogen storage tank 26 is connected with the liquid hydrogen booster pump 18 through the liquid pump hydrogen supply valve 21, the liquid oxygen discharged from the liquid oxygen storage tank 25 is connected with the liquid oxygen booster pump 19 through the liquid pump oxygen supply valve 22, the endothermic vaporized hydrogen discharged from the outlet of the hydrogen heat exchanger 6 and the hydrogen discharged from the right compression cylinder hydrogen discharge valve 35 are mixed before the inlet of the high-pressure hydrogen storage tank 13 and then flow into the high-pressure hydrogen storage tank 13, the endothermic vaporized oxygen discharged from the outlet of the oxygen heat exchanger 7 and the oxygen discharged from the left compression cylinder oxygen discharge valve 33 are mixed before the inlet of the high-pressure oxygen storage tank 12 and then flow into the high-pressure oxygen storage tank 12, the storage tank booster controller 20 is connected with the liquid oxygen storage tank 25 and the liquid hydrogen storage tank 26 through the hydrogen storage tank booster valve 23 and the oxygen storage tank booster valve 24 respectively, the gas oxygen splitting device 16 is connected with the external combustion chamber 5 through the external combustion chamber oxygen supply valve 8, the gas splitting device 15 is connected with the external combustion chamber 5 through the external combustion chamber hydrogen supply valve 9, the endothermic vaporized oxygen discharged from the outlet of the oxygen heat exchanger 7 and the oxygen storage tank 6 and the oxygen storage tank 11 are mixed before the inlet of the high-pressure oxygen storage tank 12 and then flow into the oxygen storage tank 11 and the exhaust gas storage tank 2, and the exhaust gas is connected with the exhaust gas collector 11 and the exhaust gas collector 2 through the exhaust valve 2, and the exhaust valve 2 and the exhaust valve is connected with the exhaust gas collector and the exhaust valve 2.
The embodiment can utilize the hydrogen and oxygen which are heated and evaporated from the low-temperature storage tank, compressed by the compressor, mixed with the high-temperature and high-pressure gas hydrogen and oxygen which are pressurized by the hydraulic pump and heated by the heat exchanger, and then stored in the gas cylinder together for being supplied to the external combustion chamber 5, the attitude control engine 14 and the submerged engine 17 for combustion work and supercharging of the oxyhydrogen storage tank. The shaft work output by the free piston expander 4 is used for driving the linear generator 2 to generate power and the free piston compressor 10 to compress, and redundant electric energy is stored in the rechargeable battery 3 to cope with the change of electric power demand, and the exhaust gas after the work is subjected to heat exchange by the heat exchanger can be used for a thrust device to generate sinking thrust so as to assist the sinking of liquid fuel in the storage tank.
Specifically, as shown in fig. 1-3, a spacecraft integrated fluid system based on a linear joule engine comprises a hydrogen heat exchanger 6, an oxygen heat exchanger 7, a free piston compressor 10, a liquid hydrogen booster pump 18, a liquid oxygen booster pump 19, a liquid pump hydrogen supply valve 21, a liquid pump oxygen supply valve 22, a liquid oxygen storage tank 25, a liquid hydrogen storage tank 26, a left compression cylinder oxygen supply valve 32, a left compression cylinder oxygen discharge valve 33, a right compression cylinder hydrogen supply valve 34, a right compression cylinder hydrogen discharge valve 35, a high-pressure hydrogen storage cylinder 12 and a high-pressure oxygen storage cylinder 13, so that when high-temperature high-pressure gas in the cylinder is insufficient, the gas is supplemented to the cylinder through pressurizing and heating the gas-liquid fuel in the storage tank.
The gas oxygen discharged from the liquid oxygen storage tank 25 and the gas hydrogen discharged from the liquid hydrogen storage tank 26 are connected with the free piston compressor 10 through the left compression cylinder oxygen supply valve 32 and the right compression cylinder hydrogen supply valve 34, and the compressed gas oxygen hydrogen is discharged through the left compression cylinder oxygen discharge valve 33 and the right compression cylinder hydrogen discharge valve 35; liquid hydrogen discharged from the hydrogen storage tank 26 is connected to the liquid hydrogen booster pump 18 through the liquid pump hydrogen supply valve 21, and liquid oxygen discharged from the oxygen storage tank 25 is connected to the liquid oxygen booster pump 19 through the liquid pump oxygen supply valve 22; the compressed liquid hydrogen is connected with the heat exchanger inlet of the hydrogen heat exchanger 6 through the outlet of the liquid hydrogen booster pump 18, and the compressed liquid oxygen is connected with the heat exchanger inlet of the oxygen heat exchanger 7 through the outlet of the liquid oxygen booster pump 19; the outlet of the hydrogen heat exchanger 6 is connected with the inlet of the high-pressure hydrogen storage bottle 13, and the outlet of the oxygen heat exchanger 7 is connected with the inlet of the high-pressure oxygen storage bottle 12; the hydrogen after absorbing heat and vaporizing from the outlet of the hydrogen heat exchanger 6 and the hydrogen discharged from the hydrogen discharge valve 35 of the right compression cylinder are mixed before the inlet of the high-pressure hydrogen storage cylinder 13 and flow into the high-pressure hydrogen storage cylinder 13 together; the oxygen after absorbing heat and vaporizing from the outlet of the oxygen heat exchanger 7 is mixed with the oxygen discharged from the left compression cylinder oxygen discharge valve 33 before the inlet of the high-pressure oxygen storage cylinder 12 and flows into the high-pressure oxygen storage cylinder 12 together
The integrated fluid system of the spacecraft based on the linear Joule engine further comprises an attitude control engine 14, a gas-hydrogen splitting device 15, a gas-oxygen splitting device 16, a bottom engine 17, a tank pressurizing controller 20, a hydrogen tank pressurizing valve 23, an oxygen tank pressurizing valve 24 and an orbit maneuver engine 27, so that the attitude control, liquid fuel bottom sinking and orbit maneuver required by the spacecraft are met.
The high-pressure hydrogen storage bottle 13 is connected with the gas-hydrogen splitting device 15, and the high-pressure oxygen storage bottle 12 is connected with the gas-oxygen splitting device 16; the gas and oxygen are respectively connected with the attitude control engine 14, the bottom engine 17 and the storage tank pressurizing controller 20 through the gas and oxygen splitting device 16; the gas and hydrogen are respectively connected with the attitude control engine 14, the bottom sinking engine 17 and the storage tank pressurizing controller 20 through the gas and hydrogen splitting device 15; the tank pressurizing controller 20 is connected with a hydrogen tank 26 and an oxygen tank 25 through a hydrogen tank pressurizing valve 23 and an oxygen tank pressurizing valve 24; the hydrogen storage tank 26 and the oxygen storage tank 25 are connected with a rail motor 27 through pipes at the bottoms.
The integrated fluid system of the spacecraft based on the linear Joule engine further comprises an external combustion chamber 5, an external combustion chamber hydrogen supply valve 8, an external combustion chamber oxygen supply valve 9, a master controller 1, an exhaust sinking nozzle 11 of the free piston expander 4, a left expansion cylinder air inlet valve 28 and a right expansion cylinder air inlet valve 30, so that the power supply and control of the system are realized.
The gas-oxygen splitting device 16 is connected with the external combustion chamber oxygen supply valve 8, the gas-hydrogen splitting device 15 is connected with the external combustion chamber hydrogen supply valve 9, gas, hydrogen and oxygen enter the external combustion chamber 5 for combustion, and combustion gas discharged from the external combustion chamber 5 is connected with the free piston expander 4 through the left expansion cylinder air inlet valve 28 and the right expansion cylinder air inlet valve 30; the exhaust gas discharged from the expander is divided into two paths and respectively enters the hydrogen heat exchanger 6 and the oxygen heat exchanger 7; the exhaust gas after heat exchange is converged before the exhaust sinking nozzle 11 and enters the nozzle for discharge; the main controller 1 controls the ignition of the external combustion chamber 5, and the operation of the storage tank pressurizing controller 20 and the on-off of all valves ensure the normal operation of the whole system; the tank gas pressure is controlled to be within a normal range.
The free piston compressor 10 is provided with displacement sensors at the top of the cylinder (both left and right sides), and the compressor displacement sensor 37 feeds back to the master controller 1 for valve timing adjustment according to the displacement and the speed of the piston. The upper dead center and the lower dead center of the left compression cylinder are adopted as the convention of the patent, confusion of alternating properties of the upper dead center and the upper dead center of the left compression cylinder and the right compression cylinder during operation is eliminated, and the piston is provided with a compression end point at each of the left compression cylinder and the right compression cylinder according to a preset compression ratio, and the compression end point of the left compression cylinder and the compression end point of the right compression cylinder. The displacement sensor converts the position and the speed of the piston into signals at any time and transmits the signals to the master controller 1. When the piston moves to the compression end point of the left compression cylinder, the master controller 1 commands the left compression cylinder oxygen discharge valve 33 to open, discharges compressed gas, when the piston moves to the top dead center of the left compression cylinder and the speed is zero, the master controller 1 commands the left compression cylinder oxygen discharge valve 33 to close, the left compression cylinder oxygen supply valve 32 to open, after that, the piston moves from left to right, when the piston moves to the middle point of the compressor stroke, the left compression cylinder oxygen supply valve 32 to close, when the piston moves to the compression end point of the right compression cylinder, the right compression cylinder hydrogen discharge valve 35 to open, discharges compressed gas, when the piston moves to the bottom dead center of the left compression cylinder and the speed is zero, the right compression cylinder hydrogen discharge valve 35 to close, the right compression cylinder hydrogen supply valve 34 to open, and thus the compression of the gas hydrogen and the gas oxygen is repeatedly performed.
The free piston expander 4 is provided with displacement sensors at the top of the cylinder (both left and right sides), and the expander displacement sensor 36 feeds back to the master controller 1 for valve timing adjustment according to the displacement and the speed of the piston. The top dead center and the bottom dead center of the left expansion cylinder are adopted as the convention of the patent. When the piston moves to top dead center of the left expansion cylinder and the speed is zero, the left expansion cylinder intake valve 28 opening command and the right expansion cylinder exhaust valve 31 opening command are triggered, and the intake valve is closed when the piston moves to the stroke midpoint. When the piston moves to the bottom dead center of the left expansion cylinder and the piston speed is zero, the exhaust valve 31 of the right expansion cylinder is closed, the intake valve 30 is opened, and the exhaust valve 29 of the left expansion cylinder is opened, whereby expansion work of the gas is repeatedly performed.
When the rechargeable battery is used, firstly, the high-pressure gas cylinder is filled with high-temperature and high-pressure hydrogen and oxygen in the ground preparation stage, and the rechargeable battery is fully charged in the ground preparation stage. The high-temperature high-pressure hydrogen and oxygen flow out of the high-pressure gas cylinder due to the pressure gradient, flow into the gas splitting device for splitting, flow is regulated and distributed through the gas splitting device, and the gas splitting device is respectively connected with the attitude control engine, the submerged engine, the external combustion chamber of the linear Joule engine and the storage tank pressurization controller.
When the spacecraft is required to be subjected to attitude control, the master controller controls the high-temperature high-pressure gas propellant to enter the attitude control engine through the gas splitting device to burn and do work so as to realize attitude control.
When the orbit engine of the spacecraft needs liquid propellant for orbit control, the master controller controls the gas propellant to enter the storage tank pressurizing controller through the gas dividing device for pressure adjustment, and then the gas propellant is input into the liquid hydrogen-liquid oxygen storage tank to press the liquid propellant out of the storage tank and is conveyed into the orbit engine for combustion work.
Because each electronic device of the spacecraft needs to continuously and stably supply power, the master controller controls the gas propellant to enter an external combustion chamber of the linear joule engine through the gas splitting device, the external combustion chamber is used for combusting hydrogen and oxygen to generate high-energy gas, and then the high-energy gas enters a free piston expander to perform expansion work in two ways to push a piston to move left and right so as to drive the linear generator to generate power. Some of this power is used to power the electronics of the spacecraft, and the remainder is stored in a rechargeable battery to cope with changes in power demand.
When the high-temperature high-pressure gas propellant in the high-pressure gas cylinder is insufficient, the master controller controls the gas propellant to enter the storage tank pressurization controller through the gas splitting device for pressure adjustment, then the gas propellant is input into the liquid hydrogen liquid oxygen storage tank to be pressed out of the storage tank into a free piston compressor of the linear Joule engine for gas compression, the liquid propellant in the storage tank is pressed into the liquid booster pump for liquid pressurization, the pressurized liquid propellant and the exhaust gas which does work in the free piston expander are subjected to heat exchange and temperature rise in the oxyhydrogen heat exchanger, and then the pressurized liquid propellant and the gas propellant which is compressed by the free piston compressor are converged and mixed before the high-pressure gas cylinder, and then the gas propellant and the gas propellant are filled into the gas cylinder for buffering and storage.
When the liquid hydrogen liquid oxygen propellant storage tank needs to sink the liquid propellant, the system proposal provided by the invention realizes the sinking of the liquid propellant in two ways. Firstly, a master controller controls a gas propellant to enter a submerged engine through a gas flow dividing device to burn and do work to provide a submerged thrust so as to realize liquid fuel submerged; secondly, the exhaust gas after heat exchange by the heat exchanger still has certain pressure, and the exhaust gas is discharged into space by utilizing the sinking nozzle, so that certain sinking thrust can be obtained to help the sinking of the liquid fuel.
The system provided by the invention changes the compression of the gas propellant and the liquid propellant from the compression of the two-phase flow in the existing system through one compressor into the separate single-phase compression of the gas propellant and the liquid booster pump by the free piston compressor, wherein the compression of the gas propellant and the compression of the liquid propellant are carried out by the separate single-phase compression by the free piston compressor, and the problems of the reduction of the service life, the reduction of the safety reliability and the manufacturing cost of the spacecraft, which are caused by high performance requirements and high control difficulty of the compressor in the compression process of the propellant of the existing system are solved. Compared with the prior art, the compression mode simplifies the compression working conditions of the compressor and the hydraulic pump, reduces the difficulty in adjusting and controlling the compression working conditions, reduces the requirements on the performances of the compressor and the pump, prolongs the service life of the compressor and the pump, and reduces the manufacturing cost. Further, the reliability of the whole system is improved, and the operation life of the spacecraft carrying the system is prolonged.
The system provided by the invention provides a linear joule engine to replace the oxyhydrogen internal combustion engine in the existing system, aiming at the problems of low system heat efficiency and high complexity caused by the use of a heat exchange jacket and an intermediate heat exchange agent in the heat exchange process of the oxyhydrogen internal combustion engine in the existing system and the problem of reduced safety and reliability of a spacecraft caused by discontinuous work of the internal combustion engine. Firstly, the problem of complex structure of the internal combustion engine caused by the adoption of the heat exchange jacket of the internal combustion engine is solved, and the system provided by the invention does not have the problem of complex structure of the internal combustion engine caused by the adoption of the oxyhydrogen internal combustion engine, so that the heat exchange facilities adopted instead are a hydrogen heat exchanger and an oxygen heat exchanger, and compared with the arrangement of the heat exchange jacket, the arrangement of the heat exchangers is more flexible and simple, the arrangement positions are changeable, the complexity of the whole system is reduced, and the design and the manufacture of the system are facilitated. Secondly, regarding the problem of low heat exchange efficiency caused by the fact that the existing system uses the intermediate coolant to circularly exchange heat between the internal combustion engine and the propellant, the system provided by the invention does not use the intermediate coolant, but directly introduces exhaust gas which does work and the propellant into the heat exchanger to directly exchange heat, so that the heat exchange efficiency is improved, the temperature of the propellant after heat exchange is higher, and compared with the existing system, the heat efficiency of the engine can be improved by conveying the propellant with higher temperature to the engine for combustion. Finally, regarding the problem of temperature fluctuation of the propellant caused by the use of the internal combustion engine in the prior art, the linear joule engine used in the system provided by the invention provides an external combustion chamber capable of continuously burning and a free piston expander capable of continuously providing exhaust gas, so that the supply of heat in the heat exchanger is stable and does not fluctuate, the problem is effectively solved, and the reliability of the whole system is further improved.
The system provided by the invention solves the problem that the fluctuation of the temperature and pressure of the gas propellant is reduced by arranging one high-pressure gas cylinder after two oxyhydrogen heat exchangers respectively, wherein the high-pressure gas cylinder is arranged in the middle of the process of conveying the high-temperature and high-pressure gas to each engine, and can store a part of propellant when the fluctuation of the temperature and the pressure of the propellant is reduced, so that the engines can have sufficient and stable fuel supply when the power is changed and the pressure in a storage tank is insufficient, and the reliability of the whole system and the whole spacecraft is further improved. Meanwhile, the system provided by the invention adopts a flow dividing device arranged behind the high-pressure gas cylinder to integrate and distribute the gas fuel to the attitude control engine, the submerged engine, the external combustion chamber and the pressurizing controller, so that the flow of the propellant entering each engine, the combustion chamber and the storage tank pressurizing controller is easier to control, and the integration level of a conveying pipeline of the whole system is higher and simpler.
The foregoing has outlined rather broadly the more detailed description of the invention in order that the detailed description of the principles and embodiments of the invention may be better understood, and in order that the present invention may be better understood; meanwhile, as those skilled in the art will have variations in the specific embodiments and application scope in accordance with the ideas of the present invention, the present description should not be construed as limiting the present invention in view of the above.
Claims (1)
1. A spacecraft integrated fluid system based on a linear joule engine, characterized by: the device comprises a linear generator (2), a free piston expander (4), a free piston compressor (10), an external combustion chamber (5), a hydrogen heat exchanger (6), an oxygen heat exchanger (7), an exhaust bottom jet pipe (11), a high-pressure oxygen storage cylinder (12), a high-pressure hydrogen storage cylinder (13), a posture control engine (14), a bottom engine (17), a rail engine (27), a liquid oxygen storage tank (25) and a liquid hydrogen storage tank (26), wherein the free piston compressor (10), the free piston expander (4) and the linear generator (2) are connected through a shaft, pistons in the free piston compressor (10) and the free piston expander (4) are fixed on the shaft, the liquid oxygen storage tank (25) and the liquid hydrogen storage tank (26) are respectively connected with a left compression cylinder oxygen supply valve (32) and a right compression cylinder hydrogen supply valve (34) of the free piston compressor (10), gas and oxygen hydrogen compressed by the free piston compressor (10) are respectively discharged through a left compression cylinder oxygen discharge valve (33) and a right compression hydrogen discharge valve (35), the liquid hydrogen storage tank (26) is connected with a hydrogen storage tank (18) of the booster pump (18) through a booster pump (18), the outlet of the liquid oxygen booster pump (19) is connected with the heat exchange agent inlet of the oxygen heat exchanger (7), the outlet of the hydrogen heat exchanger (6) is connected with the inlet of the high-pressure hydrogen storage cylinder (13), the outlet of the oxygen heat exchanger (7) is connected with the inlet of the high-pressure oxygen storage cylinder (12), the high-pressure hydrogen storage cylinder (13) is connected with the gas-hydrogen splitting device (15), the high-pressure oxygen storage cylinder (12) is connected with the gas-oxygen splitting device (16), the gas-hydrogen splitting device (15) and the gas-oxygen splitting device (16) are respectively connected with the attitude control engine (14), the countersunk engine (17) and the storage tank pressurizing controller (20), the storage tank pressurizing controller (20) is connected with the liquid oxygen storage tank (25) and the liquid hydrogen storage tank (26), the bottoms of the liquid oxygen storage tank (25) are connected with the track engine (27), the gas-hydrogen splitting device (15) and the gas-oxygen splitting device (16) are respectively connected with the external combustion chamber (5), the gas-hydrogen splitting device (5) is respectively connected with the left expansion cylinder (4) and the right expansion cylinder (4) and the expansion cylinder (4) from the left expansion cylinder (4) and the expansion cylinder (29 respectively, the exhaust gas after heat exchange enters an exhaust gas submerged nozzle (11), a compressor displacement sensor (37) is arranged at the top of a cylinder of the free piston compressor (10), and an expander displacement sensor (36) is arranged at the top of the cylinder of the free piston expander (4);
the liquid hydrogen discharged from the liquid hydrogen storage tank (26) is connected with a liquid hydrogen booster pump (18) through a liquid pump hydrogen supply valve (21);
the liquid oxygen discharged from the liquid oxygen storage tank (25) is connected with a liquid oxygen booster pump (19) through a liquid pump oxygen supply valve (22);
the hydrogen after absorbing heat and vaporizing from the outlet of the hydrogen heat exchanger (6) and the hydrogen discharged by the hydrogen discharge valve (35) of the right compression cylinder are mixed before the inlet of the high-pressure hydrogen storage cylinder (13) and then flow into the high-pressure hydrogen storage cylinder (13);
the oxygen after absorbing heat and vaporizing from the outlet of the oxygen heat exchanger (7) and the oxygen discharged by the left compression cylinder oxygen discharge valve (33) are mixed before the inlet of the high-pressure oxygen storage cylinder (12) and then flow into the high-pressure oxygen storage cylinder (12) together;
the storage tank pressurizing controller (20) is respectively connected with the liquid oxygen storage tank (25) and the liquid hydrogen storage tank (26) through a hydrogen storage tank pressurizing valve (23) and an oxygen storage tank pressurizing valve (24);
the gas-oxygen diversion device (16) is connected with the external combustion chamber (5) through an external combustion chamber oxygen supply valve (8);
the gas-hydrogen split device (15) is connected with the external combustion chamber (5) through an external combustion chamber hydrogen supply valve (9);
the exhaust gas after heat exchange of the hydrogen heat exchanger (6) and the oxygen heat exchanger (7) is converged before the exhaust gas bottom spray pipe (11) and then enters the exhaust gas bottom spray pipe (11);
the external combustion chamber (5), the storage tank pressurizing controller (20) and all valves are connected with the master controller (1), and the linear generator (2) is connected with the rechargeable battery (3).
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