CN116526590B - Electric heating integrated system of on-board high-power equipment and management method - Google Patents
Electric heating integrated system of on-board high-power equipment and management method Download PDFInfo
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- CN116526590B CN116526590B CN202310752840.2A CN202310752840A CN116526590B CN 116526590 B CN116526590 B CN 116526590B CN 202310752840 A CN202310752840 A CN 202310752840A CN 116526590 B CN116526590 B CN 116526590B
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- 238000007726 management method Methods 0.000 title claims abstract description 70
- 238000005485 electric heating Methods 0.000 title claims abstract description 14
- 239000000446 fuel Substances 0.000 claims abstract description 96
- 239000000295 fuel oil Substances 0.000 claims abstract description 61
- 230000017525 heat dissipation Effects 0.000 claims abstract description 45
- 239000001257 hydrogen Substances 0.000 claims abstract description 18
- 229910052739 hydrogen Inorganic materials 0.000 claims abstract description 18
- 238000001833 catalytic reforming Methods 0.000 claims abstract description 17
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims abstract description 14
- 239000007788 liquid Substances 0.000 claims description 58
- 238000000034 method Methods 0.000 claims description 52
- 238000005338 heat storage Methods 0.000 claims description 49
- 239000003507 refrigerant Substances 0.000 claims description 36
- 238000010248 power generation Methods 0.000 claims description 26
- 230000001276 controlling effect Effects 0.000 claims description 21
- 238000002485 combustion reaction Methods 0.000 claims description 13
- 238000001816 cooling Methods 0.000 claims description 13
- 239000007789 gas Substances 0.000 claims description 13
- 238000012546 transfer Methods 0.000 claims description 12
- 239000000126 substance Substances 0.000 claims description 9
- 238000010438 heat treatment Methods 0.000 claims description 7
- 238000010521 absorption reaction Methods 0.000 claims description 6
- 238000007599 discharging Methods 0.000 claims description 6
- 239000002828 fuel tank Substances 0.000 claims description 6
- 230000005611 electricity Effects 0.000 claims description 5
- 230000001105 regulatory effect Effects 0.000 claims description 5
- 229910000831 Steel Inorganic materials 0.000 claims description 4
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 4
- 239000003638 chemical reducing agent Substances 0.000 claims description 4
- 150000002431 hydrogen Chemical class 0.000 claims description 4
- 239000007800 oxidant agent Substances 0.000 claims description 4
- 239000001301 oxygen Substances 0.000 claims description 4
- 229910052760 oxygen Inorganic materials 0.000 claims description 4
- 239000010959 steel Substances 0.000 claims description 4
- 239000003570 air Substances 0.000 description 75
- 238000013461 design Methods 0.000 description 6
- 239000012080 ambient air Substances 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 230000006978 adaptation Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 230000005662 electromechanics Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 230000014509 gene expression Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M8/00—Fuel cells; Manufacture thereof
- H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
- H01M8/04007—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids related to heat exchange
- H01M8/04029—Heat exchange using liquids
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
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- G—PHYSICS
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- G06Q10/00—Administration; Management
- G06Q10/06—Resources, workflows, human or project management; Enterprise or organisation planning; Enterprise or organisation modelling
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- G06Q10/0631—Resource planning, allocation, distributing or scheduling for enterprises or organisations
- G06Q10/06312—Adjustment or analysis of established resource schedule, e.g. resource or task levelling, or dynamic rescheduling
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- G06Q—INFORMATION AND COMMUNICATION TECHNOLOGY [ICT] SPECIALLY ADAPTED FOR ADMINISTRATIVE, COMMERCIAL, FINANCIAL, MANAGERIAL OR SUPERVISORY PURPOSES; SYSTEMS OR METHODS SPECIALLY ADAPTED FOR ADMINISTRATIVE, COMMERCIAL, FINANCIAL, MANAGERIAL OR SUPERVISORY PURPOSES, NOT OTHERWISE PROVIDED FOR
- G06Q50/00—Information and communication technology [ICT] specially adapted for implementation of business processes of specific business sectors, e.g. utilities or tourism
- G06Q50/06—Energy or water supply
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M8/00—Fuel cells; Manufacture thereof
- H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
- H01M8/04007—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids related to heat exchange
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J4/00—Circuit arrangements for mains or distribution networks not specified as ac or dc
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0614—Environmental Control Systems with subsystems for cooling avionics
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J2310/00—The network for supplying or distributing electric power characterised by its spatial reach or by the load
- H02J2310/40—The network being an on-board power network, i.e. within a vehicle
- H02J2310/44—The network being an on-board power network, i.e. within a vehicle for aircrafts
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Abstract
The invention provides an on-board high-power equipment electric heating integrated system and a management method, comprising the following steps: s1, judging whether the engine has enough fuel oil, if so, adopting the fuel oil as a heat sink to perform heat management and executing the step S2, otherwise, executing the step S3; s2, judging whether the flying height is larger than a value alpha 1 If yes, using an auxiliary power device and a generator to supply power, otherwise, using a fuel catalytic reforming reactor and a hydrogen fuel cell to supply power; s3, judging whether the flying speed is greater than a value alpha 2 If yes, the ram air turbine and the generator are used for power supply and the ram air is used as a heat sink for heat management, otherwise, the compressed air turbine and the generator are used for power supply and the compressed air is used as the heat sink for heat management; the problem that the power supply and heat dissipation requirements of high-power equipment cannot be met on the machine is solved.
Description
Technical Field
The invention relates to the technical field of aviation electromechanics, in particular to an on-board high-power equipment electric heating integrated system and a management method.
Background
The high-power equipment greatly improves the airborne energy demand, and simultaneously, a large amount of heat can be generated when the high-power equipment operates. However, the current on-board power supply system and thermal management system cannot meet the power supply and thermal management requirements of high-power equipment, and the requirements are mainly expressed in the aspects of extremely high power consumption, extremely high volume and weight, low efficiency and the like. If the power supply and thermal management system designed by the high-power equipment (such as a laser system and the like) is the same as the conventional mode, the design system with independent functional structures is adopted respectively, and meanwhile, the maximum electric power and the maximum refrigerating capacity of the system are required to be not less than the peak electric energy requirement and the peak thermal load requirement of the laser system, so that the volume and the weight of the power supply and thermal management system are more huge.
In an airborne environment, cooling resources are deficient, energy sources, effective loads and space are very limited, so that a power supply and thermal management system of airborne high-power equipment is required to meet the power supply and thermal management requirements of high loads, the energy consumption, weight and volume of the power supply and thermal management system and the dispatching of the airborne resources are reduced as much as possible, the integrated design of power supply and thermal management is required, and a design system with independent functional structures of the existing power supply and thermal management system is broken.
Disclosure of Invention
The invention aims to overcome the defects of the technology, and provides an on-board high-power equipment electric heating integrated management method for solving the problem that the on-board high-power equipment power supply and heat dissipation requirements cannot be met.
The invention provides an on-board high-power equipment electric heating integrated management method, which comprises the following steps: the control method comprises the following steps: s1, judging whether the engine has enough fuel oil, if so, adopting the fuel oil as a heat sink to perform heat management and executing the step S2, otherwise, executing the step S3; s2, judging whether the flying height is larger than a numerical valueα 1 If yes, using an auxiliary power device and a generator to supply power, otherwise, using a fuel catalytic reforming reactor and a hydrogen fuel cell to supply power; s3, judging whether the flying speed is greater than a value alpha 2 If so, power is supplied with the ram air turbine and generator and heat management is performed using ram air as a heat sink, otherwise, power is supplied with the compressed air turbine and generator and heat management is performed using compressed air as a heat sink.
In some embodiments, the determination of whether there is sufficient fuel on the machine is made using the following conditions: when m is Total (S) -m Flying ≥m Power supply And m is Total (S) -m Flying ≥m Heat dissipation When the engine is in operation, enough fuel oil is arranged on the engine to supply power and heat management for high-power equipment; wherein m is Total (S) M is the total weight of the fuel oil on the machine Flying M for maintaining the weight of fuel in normal flight Power supply Total weight of fuel oil needed to be consumed for supplying power to high-power equipment on board, m Heat dissipation The total weight of fuel oil which is required to be consumed for heat dissipation of the high-power equipment on the machine.
In some embodiments, the total weight m of fuel oil needed to be consumed by the power supply of the on-board high-power equipment Power supply Calculated by the following method: s11, combustion heat value H based on fuel u And fuel consumption rate M generated by power generation of fuel power generation device f The chemical energy released by the fuel oil of the fuel oil power generation device is: q (Q) f =H u ·M f The method comprises the steps of carrying out a first treatment on the surface of the S12, chemical energy Q released based on fuel oil of fuel oil power generation device f And the total power generation efficiency eta of the fuel chemical energy converted into electric energy by the fuel power generation device 1 The total power generated by the fuel oil power generation device is as follows: w=q f ·η 1 The method comprises the steps of carrying out a first treatment on the surface of the S13, based on power supply power requirement W of on-board high-power equipment Apparatus and method for controlling the operation of a device To meet the power supply requirement, W is more than or equal to W Apparatus and method for controlling the operation of a device The required fuel consumption rate is:the method comprises the steps of carrying out a first treatment on the surface of the S14, integrating the required fuel consumption rate based on the service time t of the on-board high-power equipment to obtain the power supply of the on-board high-power equipmentTotal fuel weight to be consumed:。
in some embodiments, the total weight of fuel consumed for heat dissipation by the on-board high power device, mrower, is calculated by the following method: s21, working efficiency eta based on-board high-power equipment 2 And obtaining heating power generated after the on-board high-power equipment operates: q (Q) Apparatus and method for controlling the operation of a device =W Apparatus and method for controlling the operation of a device ·(1-η 2 ) The method comprises the steps of carrying out a first treatment on the surface of the S22, based on specific heat capacity C of fuel, temperature rise delta T of fuel caused by absorbing heat productivity of high-power equipment and fuel consumption rate M h The total heat dissipation power of the fuel oil used as a heat sink is obtained: q=c·m h ΔT; s23, heat dissipation power requirement Q based on-board high-power equipment Apparatus and method for controlling the operation of a device To meet the heat dissipation requirement, obtain Q is more than or equal to Q Apparatus and method for controlling the operation of a device The required fuel consumption rate:the method comprises the steps of carrying out a first treatment on the surface of the S24, based on the use time t of the on-board high-power equipment, integrating the required fuel consumption rate to obtain the total weight of fuel required to be consumed by heat dissipation of the on-board high-power equipment: />。
In some embodiments, thermally managing using fuel as a heat sink and powering using the auxiliary power unit and the generator includes: s31, fuel oil in the fuel tank flows through the phase-change heat storage heat exchanger to absorb heat stored by the phase-change heat storage heat exchanger, the fuel oil with raised temperature after heat absorption is conveyed to the auxiliary power device to be mixed with air for combustion, high-temperature gas is generated to impact the turbine, the turbine rotates to generate mechanical energy, and the generator is driven to rotate to generate electric energy to supply power for high-power equipment on the aircraft; s32, generating a large amount of heat when the high-power equipment operates, and transmitting the heat to the liquid-cooled circulating refrigerating medium through the heat-dissipating cold plate; s33, in the liquid cooling circulation, the secondary refrigerant in the liquid storage tank flows through the heat dissipation cold plate under the drive of the liquid pump, absorbs heat generated by the operation of high-power equipment on the machine, and the secondary refrigerant with the increased temperature flows through the phase-change heat storage heat exchanger to transfer the heat to the phase-change heat storage heat exchanger, and the secondary refrigerant with the reduced temperature returns to the liquid storage tank to complete the circulation.
In some embodiments, thermally managing and powering with the fuel catalytic reforming reactor and the hydrogen fuel cell using fuel as a heat sink comprises: s41, enabling fuel in a fuel tank to flow through a phase-change heat storage heat exchanger to absorb heat stored by the phase-change heat storage heat exchanger, conveying the fuel with increased temperature after heat absorption to a catalytic reforming reactor, decomposing the fuel into hydrogen by the catalytic reforming reactor, and injecting the hydrogen serving as a reducing agent and oxygen serving as an oxidizing agent into a fuel cell to generate electricity so as to supply power for high-power equipment on the aircraft; s42, generating a large amount of heat when the high-power equipment operates, and transmitting the heat to the liquid-cooled circulating refrigerating medium through the heat-dissipating cold plate; s43, in the liquid cooling circulation, the secondary refrigerant in the liquid storage tank flows through the heat dissipation cold plate under the drive of the liquid pump, absorbs heat generated by the operation of high-power equipment on the machine, and the secondary refrigerant with the increased temperature flows through the phase-change heat storage heat exchanger to transfer the heat to the phase-change heat storage heat exchanger, and the secondary refrigerant with the reduced temperature returns to the liquid storage tank to complete the circulation.
In some embodiments, thermally managing with ram air as a heat sink and powering with a ram air turbine and generator includes: s51, ram air flows in from a ram air door, pushes a turbine to rotate after passing through an inner duct to convert kinetic energy of high-speed gas into mechanical energy, and drives a generator to rotate to generate electric energy so as to supply power for high-power equipment on the aircraft; s52, performing turbine expansion work, enabling the ram air with the temperature and pressure reduced to flow through a phase-change heat storage heat exchanger, absorbing heat stored in the phase-change heat storage heat exchanger, and discharging the heat out of the machine; s53, generating a large amount of heat when the high-power equipment operates, and transmitting the heat to the liquid-cooled circulating refrigerating medium through the heat-dissipating cold plate; s54, in the liquid cooling circulation, the secondary refrigerant in the liquid storage tank flows through the heat dissipation cold plate under the drive of the liquid pump, absorbs heat generated by the operation of high-power equipment on the machine, and the secondary refrigerant with the increased temperature flows through the phase-change heat storage heat exchanger to transfer the heat to the phase-change heat storage heat exchanger, and the secondary refrigerant with the reduced temperature returns to the liquid storage tank to complete the circulation.
In some embodiments, thermally managing with compressed air as a heat sink and powering with a compressed air turbine and generator includes: s61, flowing the liquid compressed air loaded in the steel cylinder through the phase-change heat storage heat exchanger after passing through the regulating valve, absorbing heat stored in the phase-change heat storage heat exchanger, gasifying the liquid compressed air into gaseous compressed air, driving the power turbine to rotate to generate mechanical energy, driving the generator to rotate to generate electric energy, and supplying power for high-power equipment on the machine; s62, discharging the gaseous compressed air after the work is done out of the machine; s63, generating a large amount of heat when the high-power equipment operates, and transmitting the heat to the liquid-cooled circulating refrigerating medium through the heat-dissipating cold plate; s64, in the liquid cooling circulation, the secondary refrigerant in the liquid storage tank flows through the heat dissipation cold plate under the drive of the liquid pump, absorbs heat generated by the operation of high-power equipment on the machine, and the secondary refrigerant with the increased temperature flows through the phase-change heat storage heat exchanger to transfer the heat to the phase-change heat storage heat exchanger, and the secondary refrigerant with the reduced temperature returns to the liquid storage tank to complete the circulation.
In a second aspect, the invention provides an on-board high-power equipment electric heating integrated system, which adopts the on-board high-power equipment electric heating integrated management method to perform power supply management and thermal management.
The technical scheme provided by the invention has the following beneficial effects:
according to the invention, fuel oil, ram air or compressed air is used as a power source and a heat sink at the same time, and the power supply and heat sink integrated high-power equipment power supply and heat management architecture design integrates a power supply system and a heat management system on the premise of ensuring power supply and heat dissipation requirements, so that the problems of limited carrying space, limited power supply and insufficient heat sink of the high-power equipment are solved.
The invention enhances autonomy and flexibility of the power supply and thermal management system, is separated from the power supply and thermal management system of the on-board platform, has no difference of power supply system and heat sink selection, can be flexibly matched with the on-board platform, and expands the application range.
According to the invention, whether the aircraft has enough fuel oil or not is judged, whether the flying height exceeds a critical value or not is judged, whether the flying speed is higher than the critical value or not is judged, and different power sources and heat sink integrated power supply and heat management architecture schemes are adopted for different on-board platforms, so that the power supply and heat dissipation requirements of high-power equipment installed on the aircraft can be met.
The invention provides different power source and heat sink integrated schemes aiming at different flying heights and flying speeds, ensures the power supply and heat dissipation requirements of high-power equipment on the basis of small volume and weight and less power source and heat sink use, and reduces the influence of the high-power equipment on the performance of an aircraft platform as much as possible.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the invention as claimed.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the disclosure and together with the description, serve to explain the principles of the disclosure.
FIG. 1 shows a schematic flow chart of an on-board high-power equipment electric heating integrated management method of the invention;
FIG. 2 shows a schematic diagram of an on-board high-power equipment electrothermal integrated management system architecture according to the present invention;
FIG. 3 is a schematic diagram of another embodiment of an on-board high power device electrothermal integrated management architecture according to the present invention;
FIG. 4 is a schematic diagram of another embodiment of the on-board high power device electrothermal integrated management architecture of the present invention;
fig. 5 shows a schematic diagram of another embodiment of the electrothermal integrated management architecture of the on-board high-power device of the present invention.
Detailed Description
The disclosure will now be discussed with reference to several exemplary embodiments. It should be understood that these embodiments are discussed only to enable those of ordinary skill in the art to better understand and thus practice the present disclosure, and are not meant to imply any limitation on the scope of the present disclosure.
As used herein, the term "comprising" and variants thereof are to be interpreted as meaning "including but not limited to" open-ended terms. The term "based on" is to be interpreted as "based at least in part on". The terms "one embodiment" and "an embodiment" are to be interpreted as "at least one embodiment. The term "another embodiment" is to be interpreted as "at least one other embodiment".
The increased power demands of high power devices are met by additional energy storage devices and generators of greater bulk and weight that can adversely affect engine performance. The limited on-board heat sink also cannot meet the heat dissipation requirements of high-power devices. By adopting a design system with independent functional structures, the weight of an airplane can be increased, the available installation volume is reduced, the overall performance is greatly reduced, the onboard high-power equipment system needs to work normally, the problem of integrated integration with a carrier platform is firstly to be realized, constraints such as space, weight, power supply and heat dissipation which can be provided by the carrier platform need to be comprehensively considered, high-efficiency stable operation of the high-power equipment is ensured, the influence of the high-power equipment on the carrier is reduced, and the volume, weight, energy supply and heat management of the onboard high-power equipment power supply and heat management system need to be developed for optimization design.
In order to solve the above technical problems, an embodiment of the present invention discloses an electrothermal integrated management method for on-board high-power equipment, as shown in fig. 1, the control method includes: s1, judging whether the engine has enough fuel oil, if so, adopting the fuel oil as a heat sink to perform heat management and executing the step S2, otherwise, executing the step S3; s2, judging whether the flying height is greater than 12km, if so, using an auxiliary power device and a generator to supply power, otherwise, using a fuel catalytic reforming reactor and a hydrogen fuel cell to supply power; and S3, judging whether the flying speed is greater than 0.8Ma, if so, using the ram air turbine and the generator to supply power and using ram air as a heat sink for heat management, otherwise, using the compressed air turbine and the generator to supply power and using compressed air as the heat sink for heat management.
In the embodiment, whether the aircraft has enough fuel oil or not is judged, whether the flying height exceeds a critical value or not is judged, whether the flying speed is higher than a critical value or not is judged, and different power source and heat sink integrated power supply and heat management architecture schemes are adopted for different on-board platforms, so that the power supply and heat dissipation requirements of high-power equipment installed on the aircraft can be met.
In the embodiment, fuel oil is selected as a power source and a heat sink at the same time, and compared with ram air which is used as the power source and the heat sink at the same time, the ram air tuyere is not required to be additionally arranged, so that the flight resistance can be reduced, and the additional compensation loss caused by the ram air resistance is avoided; compared with compressed air which is used as a power source and a heat sink at the same time, the technology of applying fuel is more mature, the reliability is higher, the application feasibility is higher, and meanwhile, a steel cylinder for loading liquid compressed air and a regulating valve are not required to be additionally added, so that compensation loss caused by weight can be reduced, and therefore, when the engine has enough fuel, the fuel is preferred as the heat sink.
In this embodiment, the setting criteria for the flying height are as follows: the method mainly aims at the height requirement of the auxiliary power device, fuel oil is conveyed to the auxiliary power device and is combusted in the combustion chamber after being mixed with air, in order that the ignition system can ignite the oil-gas mixed gas in the combustion chamber, the requirement that the pressure of the air entering the combustion chamber is not lower than a critical value is met, the air can be reversely pushed until the pressure of the ambient air is not lower than the critical value, and finally the height critical value is obtained; based on auxiliary power unit combustion chamber air pressure critical value P m And the pressure ratio pi of the auxiliary power unit compressor, the critical value of the ambient air pressure is as follows:
；
when the altitude H <11.0km, the relation between the ambient air pressure and the altitude is:
；
namely, the height needs to satisfy:
；
when the altitude H >11.0km, the relation between the ambient air pressure and the altitude is:
；
namely, the height needs to satisfy:
；
in the present embodiment, the setting criteria for the flying speed are as follows: the speed requirement of the ram air turbine is mainly met, the ram air turbine blows blades to rotate by means of the air kinetic energy of ram air, the connected shaft is driven to rotate at a high speed, the kinetic energy of high-speed gas is converted into mechanical energy, and the generator is driven to generate electricity. In order to meet the power demand, the kinetic energy of the gas needs to meet a threshold value, which can be pushed back to the ram air speed threshold value, i.e. the flight speed threshold value. When a mass point with mass m moves at a speed v, the kinetic energy is: e=0.5 mv 2 The method comprises the steps of carrying out a first treatment on the surface of the For an inner ducted ram air turbine, the ducted cross-sectional area is A and the velocity of the passing ram air is v Stamping When the ram air density is ρ, the mass flow rate of the ram air flowing through is: m is m Stamping =ρ·A·v Stamping The method comprises the steps of carrying out a first treatment on the surface of the The total kinetic energy of the flowing ram air is: e (E) Stamping =0.5m Stamping ·v Stamping 2 =0.5ρ·A·v Stamping 3 The method comprises the steps of carrying out a first treatment on the surface of the The ram air turbine converts the total kinetic energy of ram air into electrical energy with a total power generation efficiency η 3 The total power generated by the ram air turbine: w (W) Stamping =0.5ρ·A·v Stamping 3 ·η 3 The method comprises the steps of carrying out a first treatment on the surface of the The power supply power requirement of the high-power equipment on the machine is W Apparatus and method for controlling the operation of a device To meet the power supply requirement, obtain W Stamping ≥W Apparatus and method for controlling the operation of a device The ram air speed (i.e. the flight speed) required is then:。
in this embodiment, 12km and 0.8Ma are calculated based on the above formula.
In some embodiments, the determination of whether there is sufficient fuel on the machine is made using the following conditions: when m is Total (S) -m Flying ≥m Power supply And m is Total (S) -m Flying ≥m Heat dissipation When the engine is in operation, enough fuel oil is arranged on the engine to supply power and heat management for high-power equipment; wherein m is Total (S) M is the total weight of the fuel oil on the machine Flying M for maintaining the weight of fuel in normal flight Power supply Total weight of fuel oil needed to be consumed for supplying power to high-power equipment on board, m Heat dissipation The total weight of fuel oil which is required to be consumed for heat dissipation of the high-power equipment on the machine.
In some embodiments, the total weight m of fuel oil needed to be consumed for power supply of the on-board high-power equipment Power supply Calculated by the following method: s11, combustion heat value H based on fuel u And the fuel consumption rate M generated by the power generation of the fuel power generation device (an auxiliary power device drives a generator or a fuel catalytic reforming reactor drives a hydrogen fuel cell) f The chemical energy released by the fuel oil of the fuel oil power generation device is: q (Q) f =H u ·M f The method comprises the steps of carrying out a first treatment on the surface of the S12, chemical energy Q released based on fuel oil of fuel oil power generation device f And the total power generation efficiency eta of the fuel chemical energy converted into electric energy by the fuel power generation device 1 The total power generated by the fuel oil power generation device is as follows: w=q f ·η 1 The method comprises the steps of carrying out a first treatment on the surface of the S13, based on power supply power requirement W of on-board high-power equipment Apparatus and method for controlling the operation of a device To meet the power supply requirement, W is more than or equal to W Apparatus and method for controlling the operation of a device The required fuel consumption rate is:the method comprises the steps of carrying out a first treatment on the surface of the S14, integrating the required fuel consumption rate based on the service time t of the on-board high-power equipment to obtain the total weight of fuel required to be consumed by the on-board high-power equipment for power supply: />。
In some embodiments, the total weight of fuel consumed for heat dissipation by the onboard high power device, mrower, is calculated by: s21, working efficiency eta based on-board high-power equipment 2 And obtaining heating power generated after the on-board high-power equipment operates: q (Q) Apparatus and method for controlling the operation of a device =W Apparatus and method for controlling the operation of a device ·(1-η 2 ) The method comprises the steps of carrying out a first treatment on the surface of the S22, based onSpecific heat capacity C of fuel, rising temperature delta T of fuel caused by absorbing heat productivity of high-power equipment and fuel consumption rate M h The total heat dissipation power of the fuel oil used as a heat sink is obtained: q=c·m h ΔT; s23, heat dissipation power requirement Q based on-board high-power equipment Apparatus and method for controlling the operation of a device To meet the heat dissipation requirement, obtain Q is more than or equal to Q Apparatus and method for controlling the operation of a device The required fuel consumption rate:the method comprises the steps of carrying out a first treatment on the surface of the S24, based on the use time t of the on-board high-power equipment, integrating the required fuel consumption rate to obtain the total weight of fuel required to be consumed by heat dissipation of the on-board high-power equipment: />。
In some embodiments, thermally managing using fuel as a heat sink and powering using the auxiliary power unit and the generator includes: s31, fuel oil in the fuel tank flows through the phase-change heat storage heat exchanger to absorb heat stored by the phase-change heat storage heat exchanger, the fuel oil with raised temperature after heat absorption is conveyed to the auxiliary power device to be mixed with air for combustion, high-temperature gas is generated to impact the turbine, the turbine rotates to generate mechanical energy, and the generator is driven to rotate to generate electric energy to supply power for high-power equipment on the aircraft; s32, generating a large amount of heat when the high-power equipment operates, and transmitting the heat to the liquid-cooled circulating refrigerating medium through the heat-dissipating cold plate; s33, in the liquid cooling circulation, the secondary refrigerant in the liquid storage tank flows through the heat dissipation cold plate under the drive of the liquid pump, absorbs heat generated by the operation of high-power equipment on the machine, and the secondary refrigerant with the increased temperature flows through the phase-change heat storage heat exchanger to transfer the heat to the phase-change heat storage heat exchanger, and the secondary refrigerant with the reduced temperature returns to the liquid storage tank to complete the circulation.
In the embodiment, firstly, an auxiliary power device is adopted to drive a generator to supply power and fuel oil is adopted as a heat sink, wherein a power supply system is an auxiliary power device and a generator; the thermal management system adopts fuel oil as a heat sink; the fuel oil is taken as a power source and a heat sink at the same time, the fuel oil enters a combustion chamber of the auxiliary power device for combustion, and the generated high-temperature gas pushes the turbine to rotate so as to drive the generator to rotate for power generation, so that power is supplied to high-power equipment; at the same time, the fuel may act as a heat sink for the thermal management system.
In some embodiments, thermally managing and powering with the fuel catalytic reforming reactor and the hydrogen fuel cell using fuel as a heat sink comprises: s41, enabling fuel in a fuel tank to flow through a phase-change heat storage heat exchanger to absorb heat stored by the phase-change heat storage heat exchanger, conveying the fuel with increased temperature after heat absorption to a catalytic reforming reactor, decomposing the fuel into hydrogen by the catalytic reforming reactor, and injecting the hydrogen serving as a reducing agent and oxygen serving as an oxidizing agent into a fuel cell to generate electricity so as to supply power for high-power equipment on the aircraft; s42, generating a large amount of heat when the high-power equipment operates, and transmitting the heat to the liquid-cooled circulating refrigerating medium through the heat-dissipating cold plate; s43, in the liquid cooling circulation, the secondary refrigerant in the liquid storage tank flows through the heat dissipation cold plate under the drive of the liquid pump, absorbs heat generated by the operation of high-power equipment on the machine, and the secondary refrigerant with the increased temperature flows through the phase-change heat storage heat exchanger to transfer the heat to the phase-change heat storage heat exchanger, and the secondary refrigerant with the reduced temperature returns to the liquid storage tank to complete the circulation.
In the second embodiment, the fuel catalytic reforming reactor is adopted to drive the hydrogen fuel cell to supply power and the fuel is adopted as a heat sink, wherein the power supply system is the fuel catalytic reforming reactor and the hydrogen fuel cell, and the fuel is adopted as the heat sink by the thermal management system; the fuel oil is used as a power source and a heat sink at the same time, the fuel oil catalytic reforming reactor is used for decomposing the airborne fuel oil into mixed gas mainly comprising hydrogen, the hydrogen is used as a reducing agent after further treatment, and the oxygen is used as an oxidizing agent to be injected into the fuel cell for power generation, so that power is supplied to high-power equipment; at the same time, the fuel may act as a heat sink for the thermal management system.
In some embodiments, thermally managing with ram air as a heat sink and powering with a ram air turbine and generator includes: s51, ram air flows in from a ram air door, pushes a turbine to rotate after passing through an inner duct to convert kinetic energy of high-speed gas into mechanical energy, and drives a generator to rotate to generate electric energy so as to supply power for high-power equipment on the aircraft; s52, performing turbine expansion work, enabling the ram air with the temperature and pressure reduced to flow through a phase-change heat storage heat exchanger, absorbing heat stored in the phase-change heat storage heat exchanger, and discharging the heat out of the machine; s53, generating a large amount of heat when the high-power equipment operates, and transmitting the heat to the liquid-cooled circulating refrigerating medium through the heat-dissipating cold plate; s54, in the liquid cooling circulation, the secondary refrigerant in the liquid storage tank flows through the heat dissipation cold plate under the drive of the liquid pump, absorbs heat generated by the operation of high-power equipment on the machine, and the secondary refrigerant with the increased temperature flows through the phase-change heat storage heat exchanger to transfer the heat to the phase-change heat storage heat exchanger, and the secondary refrigerant with the reduced temperature returns to the liquid storage tank to complete the circulation.
In the third embodiment, the power supply of the generator is driven by the ram air turbine and the ram air is used as a heat sink, wherein the power supply system is the ram air turbine and the generator, and the heat management system uses the ram air as the heat sink; the ram air is used as a power source and a heat sink at the same time, a ram air door is arranged, and the ram air pushes the turbine to rotate so as to drive the generator to rotate for power generation; the ram air after the turbine is doing work directly serves as a heat sink for the thermal management system.
In some embodiments, thermally managing with compressed air as a heat sink and powering with a compressed air turbine and generator includes: s51, flowing the liquid compressed air loaded in the steel cylinder through the phase-change heat storage heat exchanger after passing through the regulating valve, absorbing heat stored in the phase-change heat storage heat exchanger, gasifying the liquid compressed air into gaseous compressed air, driving the power turbine to rotate to generate mechanical energy, driving the generator to rotate to generate electric energy, and supplying power for high-power equipment on the machine; s52, discharging the gaseous compressed air after the work is done out of the machine; s53, generating a large amount of heat when the high-power equipment operates, and transmitting the heat to the liquid-cooled circulating refrigerating medium through the heat-dissipating cold plate; s54, in the liquid cooling circulation, the secondary refrigerant in the liquid storage tank flows through the heat dissipation cold plate under the drive of the liquid pump, absorbs heat generated by the operation of high-power equipment on the machine, and the secondary refrigerant with the increased temperature flows through the phase-change heat storage heat exchanger to transfer the heat to the phase-change heat storage heat exchanger, and the secondary refrigerant with the reduced temperature returns to the liquid storage tank to complete the circulation.
In the fourth embodiment, the compressed air turbine is adopted to drive the generator to supply power and the compressed air is adopted as the heat sink, wherein the power supply system is a compressed air turbine and a generator, and the thermal management system adopts the compressed air as the heat sink; the compressed air is used as a power source and a heat sink at the same time, and after passing through the regulating valve, the liquid compressed air absorbs the heat of the thermal management system and is gasified to become gaseous compressed air which is used as the heat sink of the thermal management system; then, the gas compressed air pushes the turbine to rotate, and drives the generator to rotate for generating electricity.
In the above embodiment, the working medium in the phase change heat storage heat exchanger absorbs the heat of the coolant with higher temperature, and changes from solid state to liquid state; the stored heat is then transferred to a lower temperature heat sink (fuel, ram air, compressed air, etc.) from a liquid state back to a solid state.
Based on the same inventive concept, the invention provides an on-board high-power equipment electric heating integrated system, which adopts the on-board high-power equipment electric heating integrated management method to carry out power supply management and thermal management.
It is understood that the term "plurality" in this disclosure means two or more, and other adjectives are similar thereto. "and/or", describes an association relationship of an association object, and indicates that there may be three relationships, for example, a and/or B, and may indicate: a exists alone, A and B exist together, and B exists alone. The character "/" generally indicates that the context-dependent object is an "or" relationship. The singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise.
It is further understood that the terms "first," "second," and the like are used to describe various information, but such information should not be limited to these terms. These terms are only used to distinguish one type of information from another and do not denote a particular order or importance. Indeed, the expressions "first", "second", etc. may be used entirely interchangeably. For example, first information may also be referred to as second information, and similarly, second information may also be referred to as first information, without departing from the scope of the present disclosure.
It will be further understood that the terms "center," "longitudinal," "transverse," "front," "rear," "upper," "lower," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like, as used herein, refer to an orientation or positional relationship based on that shown in the drawings, merely for convenience in describing the present embodiments and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operate in a particular orientation.
It will be further understood that "connected" includes both direct connection where no other member is present and indirect connection where other element is present, unless specifically stated otherwise.
It will be further understood that although operations are depicted in the drawings in a particular order, this should not be understood as requiring that such operations be performed in the particular order shown or in sequential order, or that all illustrated operations be performed, to achieve desirable results. In certain circumstances, multitasking and parallel processing may be advantageous.
Other embodiments of the disclosure will be apparent to those skilled in the art from consideration of the specification and practice of the disclosure disclosed herein. This disclosure is intended to cover any adaptations, uses, or adaptations of the disclosure following the general principles of the disclosure and including such departures from the present disclosure as come within known or customary practice within the art to which the disclosure pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the disclosure being indicated by the following claims.
It is to be understood that the present disclosure is not limited to the precise arrangements and instrumentalities shown in the drawings, and that various modifications and changes may be effected without departing from the scope thereof. The scope of the present disclosure is limited only by the appended claims.
Claims (8)
1. An on-board high-power equipment electric heating integrated management method is characterized by comprising the following steps:
s1, judging whether the engine has enough fuel oil, if so, adopting the fuel oil as a heat sink to perform heat management and executing the step S2, otherwise, executing the step S3;
s2, judging whether the flying height is larger than a value alpha 1 If yes, the auxiliary power device and the generator are used for supplying power, otherwise, the fuel catalytic reforming reactor and the hydrogen fuel cell are used for supplying power;
s3, judging whether the flying speed is greater than a value alpha 2 If yes, the ram air turbine and the generator are used for power supply and the ram air is used as a heat sink for heat management, otherwise, the compressed air turbine and the generator are used for power supply and the compressed air is used as the heat sink for heat management;
wherein for the value alpha 1 The following method is adopted for calculation:
based on auxiliary power unit combustion chamber air pressure critical value P m And the pressure ratio pi of the auxiliary power device compressor, calculatingThe method comprises the steps of carrying out a first treatment on the surface of the Obtaining alpha 1 Minimum value of (2) ， If at this time alpha 1 And (c) satisfies a minimum of less than 11km 1 Taking alpha 1 Is the minimum of (2); if not, calculate ++>The method comprises the steps of carrying out a first treatment on the surface of the Obtaining alpha 1 If at this time alpha 1 The maximum value of the alpha is more than 11km 1 Taking alpha 1 Is the maximum value of (2);
for the value alpha 2 The following formula is used for calculation:
；
wherein W is Apparatus and method for controlling the operation of a device For the power supply requirement of the high-power equipment on the machine, A is the sectional area of the duct, ρ is the density of the ram air, η 3 The total kinetic energy of the ram air is converted into the total power generation efficiency of the electrical energy for the ram air turbine.
2. An on-board high power device as claimed in claim 1, wherein the power source is a power sourceThe body management method is characterized in that whether the machine has enough fuel oil is judged by adopting the following conditions: when m is Total (S) -m Flying ≥m Power supply And m is Total (S) -m Flying ≥m Heat dissipation When the engine is in operation, enough fuel oil is arranged on the engine to supply power and heat management for high-power equipment; wherein m is Total (S) M is the total weight of the fuel oil on the machine Flying M for maintaining the weight of fuel in normal flight Power supply Total weight of fuel oil needed to be consumed for supplying power to high-power equipment on board, m Heat dissipation The total weight of fuel oil which is required to be consumed for heat dissipation of the high-power equipment on the machine.
3. The method for integrated management of electric heating of on-board high-power equipment according to claim 2, wherein the total weight m of fuel oil required to be consumed for power supply of the on-board high-power equipment is Power supply Calculated by the following method:
s11, combustion heat value H based on fuel u And fuel consumption rate M generated by power generation of fuel power generation device f The chemical energy released by the fuel oil of the fuel oil power generation device is: q (Q) f =H u ·M f ；
S12, chemical energy Q released based on fuel oil of fuel oil power generation device f And the total power generation efficiency eta of the fuel chemical energy converted into electric energy by the fuel power generation device 1 The total power generated by the fuel oil power generation device is as follows: w=q f ·η 1 ；
S13, based on power supply power requirement W of on-board high-power equipment Apparatus and method for controlling the operation of a device To meet the power supply requirement, W is more than or equal to W Apparatus and method for controlling the operation of a device The required fuel consumption rate is:；
s14, integrating the required fuel consumption rate based on the service time t of the on-board high-power equipment to obtain the total weight of fuel required to be consumed by the on-board high-power equipment for power supply:。
4. the method for integrated management of electric heating of on-board high-power equipment according to claim 3, wherein the total weight m of fuel oil required to be consumed for heat dissipation of the on-board high-power equipment is Heat dissipation Calculated by the following method:
s21, working efficiency eta based on-board high-power equipment 2 And obtaining heating power generated after the on-board high-power equipment operates: q (Q) Apparatus and method for controlling the operation of a device =W Apparatus and method for controlling the operation of a device ·(1-η 2 )；
S22, based on specific heat capacity C of fuel, temperature rise delta T of fuel caused by absorbing heat productivity of high-power equipment and fuel consumption rate M h The total heat dissipation power of the fuel oil used as a heat sink is obtained: q=c·m h ·ΔT；
S23, heat dissipation power requirement Q based on-board high-power equipment Apparatus and method for controlling the operation of a device To meet the heat dissipation requirement, obtain Q is more than or equal to Q Apparatus and method for controlling the operation of a device The required fuel consumption rate:；
s24, based on the use time t of the on-board high-power equipment, integrating the required fuel consumption rate to obtain the total weight of fuel required to be consumed by heat dissipation of the on-board high-power equipment:。
5. the method for integrated management of electrical heating of on-board high power equipment according to claim 1, wherein using fuel as a heat sink for thermal management and using auxiliary power means and a generator for power supply comprises:
s31, fuel oil in the fuel tank flows through the phase-change heat storage heat exchanger to absorb heat stored by the phase-change heat storage heat exchanger, the fuel oil with raised temperature after heat absorption is conveyed to the auxiliary power device to be mixed with air for combustion, high-temperature gas is generated to impact the turbine, the turbine rotates to generate mechanical energy, and the generator is driven to rotate to generate electric energy to supply power for high-power equipment on the aircraft;
s32, generating a large amount of heat when the high-power equipment operates, and transmitting the heat to the liquid-cooled circulating refrigerating medium through the heat-dissipating cold plate;
s33, in the liquid cooling circulation, the secondary refrigerant in the liquid storage tank flows through the heat dissipation cold plate under the drive of the liquid pump, absorbs heat generated by the operation of high-power equipment on the machine, and the secondary refrigerant with the increased temperature flows through the phase-change heat storage heat exchanger to transfer the heat to the phase-change heat storage heat exchanger, and the secondary refrigerant with the reduced temperature returns to the liquid storage tank to complete the circulation.
6. The method for integrated management of electrical heating of on-board high power equipment according to claim 1, wherein the thermal management using fuel as a heat sink and the power supply using a fuel catalytic reforming reactor and a hydrogen fuel cell comprises:
s41, enabling fuel in a fuel tank to flow through a phase-change heat storage heat exchanger to absorb heat stored by the phase-change heat storage heat exchanger, conveying the fuel with increased temperature after heat absorption to a catalytic reforming reactor, decomposing the fuel into hydrogen by the catalytic reforming reactor, and injecting the hydrogen serving as a reducing agent and oxygen serving as an oxidizing agent into a fuel cell to generate electricity so as to supply power for high-power equipment on the aircraft;
s42, generating a large amount of heat when the high-power equipment operates, and transmitting the heat to the liquid-cooled circulating refrigerating medium through the heat-dissipating cold plate;
s43, in the liquid cooling circulation, the secondary refrigerant in the liquid storage tank flows through the heat dissipation cold plate under the drive of the liquid pump, absorbs heat generated by the operation of high-power equipment on the machine, and the secondary refrigerant with the increased temperature flows through the phase-change heat storage heat exchanger to transfer the heat to the phase-change heat storage heat exchanger, and the secondary refrigerant with the reduced temperature returns to the liquid storage tank to complete the circulation.
7. The method of integrated management of electrical heating of high power equipment on board as claimed in claim 1, wherein using ram air as a heat sink for thermal management and using a ram air turbine and a generator for power supply comprises:
s51, ram air flows in from a ram air door, pushes a turbine to rotate after passing through an inner duct, converts kinetic energy of high-speed gas into mechanical energy, and drives a generator to rotate to generate electric energy so as to supply power for high-power equipment on the aircraft;
s52, performing turbine expansion work, enabling the ram air with the temperature and pressure reduced to flow through a phase-change heat storage heat exchanger, absorbing heat stored in the phase-change heat storage heat exchanger, and discharging the heat out of the machine;
s53, generating a large amount of heat when the high-power equipment operates, and transmitting the heat to the liquid-cooled circulating refrigerating medium through the heat-dissipating cold plate;
s54, in the liquid cooling circulation, the secondary refrigerant in the liquid storage tank flows through the heat dissipation cold plate under the drive of the liquid pump, absorbs heat generated by the operation of high-power equipment on the machine, and the secondary refrigerant with the increased temperature flows through the phase-change heat storage heat exchanger to transfer the heat to the phase-change heat storage heat exchanger, and the secondary refrigerant with the reduced temperature returns to the liquid storage tank to complete the circulation.
8. The method of integrated management of electrical heating of on-board high power equipment of claim 1, wherein thermally managing with compressed air as a heat sink and powering with a compressed air turbine and a generator comprises:
s61, flowing the liquid compressed air loaded in the steel cylinder through the phase-change heat storage heat exchanger after passing through the regulating valve, absorbing heat stored in the phase-change heat storage heat exchanger, gasifying the liquid compressed air into gaseous compressed air, driving the power turbine to rotate to generate mechanical energy, driving the generator to rotate to generate electric energy, and supplying power for high-power equipment on the machine;
s62, discharging the gaseous compressed air after the work is done out of the machine;
s63, generating a large amount of heat when the high-power equipment operates, and transmitting the heat to the liquid-cooled circulating refrigerating medium through the heat-dissipating cold plate;
s64, in the liquid cooling circulation, the secondary refrigerant in the liquid storage tank flows through the heat dissipation cold plate under the drive of the liquid pump, absorbs heat generated by the operation of high-power equipment on the machine, and the secondary refrigerant with the increased temperature flows through the phase-change heat storage heat exchanger to transfer the heat to the phase-change heat storage heat exchanger, and the secondary refrigerant with the reduced temperature returns to the liquid storage tank to complete the circulation.
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| CN117775295B (en) * | 2023-12-22 | 2024-06-11 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Electromechanical system for electrohydraulic thermal complementation based on compressed working medium |
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| CN106970523A (en) * | 2017-03-01 | 2017-07-21 | 南京航空航天大学 | A kind of energy management strategies of aircraft self-adapting power and heat management system |
| CN112623233A (en) * | 2020-12-24 | 2021-04-09 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Self-adaptive power and heat management system for airplane |
| CN114154242A (en) * | 2021-12-01 | 2022-03-08 | 北京航空航天大学 | Aircraft thermal management system optimization method and system |
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| CN106970523A (en) * | 2017-03-01 | 2017-07-21 | 南京航空航天大学 | A kind of energy management strategies of aircraft self-adapting power and heat management system |
| CN112623233A (en) * | 2020-12-24 | 2021-04-09 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Self-adaptive power and heat management system for airplane |
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