Aircraft energy supply method and system

Abstract

The invention relates to the technical field of electric aircrafts, in particular to an aircraft energy supply method and system. The method comprises the following steps: on the basis that the power demand of the power unit is less than or equal to a demand threshold, the storage unit supplies methanol and water to the hydrogen production unit; methanol and water are supplied to the hydrogen production unit based on the material storage unit, a reaction chamber of the hydrogen production unit supplies hydrogen to a first battery of the power generation unit, and the gas supply unit supplies air to the first battery; hydrogen is supplied to the first battery based on the reaction chamber, the air supply unit supplies air to the first battery, and the first battery supplies electric energy to the power utilization unit at first power; electric energy is supplied to the power utilization unit at first power based on the first battery, and first tail gas flows through a first heat exchanger of the hydrogen production unit and is conveyed to the inerting unit; first tail gas flows through the first heat exchanger and is conveyed to the inerting unit, and the inerting unit inputs inert gas into the methanol tank and inputs water into the water tank. Therefore, the problem of how to safely store and use methanol on the aircraft is solved.

Description

Technical Field

[0001] The present invention relates to the technical field of electric aircraft, and in particular to an aircraft energy supply method and system. Background Art

[0002] At present, aircraft mainly use aviation fuel as fuel, which is not only highly dependent on oil resources, but also has an impact on the climate due to the nitrogen oxides and hydrocarbons emitted, and also produces ultrafine particulate pollution and heavy metal lead pollution. In order to save energy and reduce emissions, electric aircraft have become an optional way. Electric aircraft are mainly powered by fuel cells. Fuel cells are energy conversion devices that can directly convert the chemical energy of gasified fuel into electrical energy and thermal energy. They have energy conversion efficiency far exceeding that of internal combustion engines and have broad application prospects. Among them, hydrogen is currently recognized as the best fuel for fuel cells, so these batteries that use hydrogen as fuel are also called hydrogen fuel cells, which are currently the most widely used type of fuel cells.

[0003] Since the safe and efficient storage of hydrogen on aircraft is a technical bottleneck, the existing high-pressure gaseous hydrogen storage, low-temperature liquid hydrogen storage and solid hydrogen storage methods have major problems in terms of safety, economy and energy density, which greatly limits the application of hydrogen fuel cells on aircraft. Therefore, hydrogen production through the catalytic reforming reaction of methanol and water has become an optional economical method, but in the high-altitude and low-pressure environment of aircraft, the auto-ignition point of methanol is low. If the pressure in the methanol tank is too low, it is easy for methanol to gasify, which is flammable and explosive, and there are certain safety hazards. As an aircraft fuel, methanol needs to consider how to store it safely in the flight environment to avoid the problem of methanol explosion. Summary of the invention

[0004] In order to solve the problem of how to safely store and use methanol on an aircraft, the present invention provides an aircraft energy supply method and system.

[0005] In a first aspect, the present invention provides an aircraft power supply method, the aircraft power supply method comprising:

[0006] Step S10, based on the electricity demand of the electricity consumption unit being less than or equal to the demand threshold, the material storage unit supplies methanol at a first flow rate and water at a second flow rate to the hydrogen production unit;

[0007] Step S20, based on the material storage unit supplying methanol at the first flow rate and water at the second flow rate to the hydrogen production unit, the reaction chamber of the hydrogen production unit supplies hydrogen to the first battery of the power generation unit, and the gas supply unit supplies air to the first battery;

[0008] Step S30, based on the reaction chamber supplying hydrogen to the first battery and the gas supply unit supplying air to the first battery, the first battery supplies electric energy to the power consumption unit at a first power;

[0009] Step S40, based on the first battery supplying electric energy to the power-consuming unit at the first power, the first tail gas is transported to the inerting unit through the first heat exchanger of the hydrogen production unit; wherein the first tail gas includes carbon dioxide and water discharged from the combustion of methanol in the combustion chamber of the hydrogen production unit, and inert gas discharged from the reaction of hydrogen in the first battery with air;

[0010] Step S50, based on the first tail gas flowing through the first heat exchanger and being transported to the inerting unit, the inerting unit inputs inert gas into the methanol tank of the storage unit and inputs water into the water tank of the storage unit.

[0011] In some embodiments, step S20 includes:

[0012] Step S21, based on the material storage unit supplying methanol at the first flow rate and water at the second flow rate to the hydrogen production unit, the first heater is heated to a first temperature threshold and the second heater is heated to a second temperature threshold;

[0013] Step S22, based on the first heater being heated to the first temperature threshold and the second heater being heated to the second temperature threshold, methanol flows through the first evaporation chamber to complete vaporization and water flows through the second evaporation chamber to complete vaporization;

[0014] Step S23, based on the methanol flowing through the first evaporation chamber to complete vaporization, the water flowing through the second evaporation chamber to complete vaporization, the vaporized methanol flows into the reaction chamber and the combustion chamber respectively, and the vaporized water flows into the reaction chamber;

[0015] Step S24, based on the vaporized methanol flowing into the reaction chamber and the combustion chamber respectively and the vaporized water flowing into the reaction chamber, the reaction chamber supplies hydrogen to the first battery of the power generation unit, and the air supply unit supplies air to the first battery.

[0016] In some embodiments, step S40 includes:

[0017] Step S41, supplying electric energy to the power-consuming unit at the first power based on the first battery, and the first battery discharges residual hydrogen and inert gas after the reaction;

[0018] Step S42, based on the residual hydrogen and inert gas discharged from the first battery after the reaction, the residual hydrogen after the reaction flows into the combustion chamber of the hydrogen production unit for combustion, and the first exhaust gas flows through the first heat exchanger of the hydrogen production unit and is transported to the inerting unit; wherein the first exhaust gas includes carbon dioxide and water discharged from the combustion of methanol in the combustion chamber of the hydrogen production unit, and inert gas discharged from the reaction of hydrogen in the first battery with air.

[0019] In some embodiments, step S50 includes:

[0020] Step S51, based on the first tail gas flowing through the first heat exchanger and being transported to the inerting unit, the second heat exchanger cools the first tail gas;

[0021] Step S52, cooling the first tail gas by the second heat exchanger is completed, and the first tail gas flows into a first separator for gas-liquid separation;

[0022] Step S53, based on the first tail gas flowing into the first separator to complete gas-liquid separation, the water in the first separator is transported to the water tank of the storage unit, and the mixed gas in the first separator is transported to the filter; wherein the mixed gas includes carbon dioxide, inert gas, and oxygen;

[0023] Step S54, obtaining the oxygen content of the mixed gas based on the mixed gas flowing through the filter;

[0024] Step S55: Based on the oxygen content of the mixed gas being less than a first threshold, the mixed gas is transported to the methanol tank of the storage unit.

[0025] In some embodiments, the step S50 further includes:

[0026] Step S56, based on the oxygen content of the mixed gas being greater than or equal to the first threshold, conveying the mixed gas to a second separator;

[0027] Step S57, based on the mixed gas being delivered to the second separator, the second separator delivers the oxygen separated from the mixed gas to the first battery and delivers the mixed gas from which oxygen is removed to the methanol tank.

[0028] In some embodiments, the step S50 further includes:

[0029] Step S58, obtaining the pressure in the methanol tank based on the mixed gas being delivered to the methanol tank;

[0030] Step S59, based on the pressure in the methanol tank being greater than or equal to a first pressure threshold, stop delivering the mixed gas to the methanol tank and store the remaining mixed gas in an inerting tank.

[0031] In some embodiments, the aircraft power supply method further includes:

[0032] Step S11: based on the power demand of the power consumption unit being greater than the demand threshold, the first battery supplies electric energy to the power consumption unit at a second power; wherein the second power is greater than the first power;

[0033] Step S12, based on the first battery supplying electric energy to the power-consuming unit at the second power, the first exhaust gas flows through the first heat exchanger and is transported to the inerting unit;

[0034] Step S13, based on the first tail gas flowing through the first heat exchanger and being transported to the inerting unit, obtaining the amount of inerting gas in the inerting unit and the pressure in the methanol tank;

[0035] Step S14, based on the inert gas amount in the inertization unit being less than a set gas threshold and the pressure in the methanol tank being less than a second pressure threshold, disconnecting the gas supply machine from the first battery and controlling the third separator of the gas supply unit to separate oxygen and inert gas from the air supplied by the gas supply machine;

[0036] Step S15, separating oxygen and inert gas from the air supplied by the air supply machine based on the third separator, and the third separator transports the oxygen to the first battery and transports the inert gas to the methanol tank.

[0037] In some embodiments, the step S11 includes:

[0038] Step S111, based on the electricity demand of the electricity consumption unit being greater than the demand threshold, the material storage unit supplies methanol at a third flow rate and water at a fourth flow rate to the hydrogen production unit; wherein the third flow rate is greater than the first flow rate; and the fourth flow rate is greater than the second flow rate;

[0039] Step S112, based on the material storage unit supplying methanol at the third flow rate and water at the fourth flow rate to the hydrogen production unit, the reaction chamber supplies hydrogen to the first battery, and the gas supply machine supplies air to the first battery;

[0040] Step S113, based on the reaction chamber supplying hydrogen to the first battery and the gas supply machine supplying air to the first battery, the first battery supplies electric energy to the power consumption unit at a second power and the second battery supplies electric energy to the power consumption unit; wherein the second power is greater than the first power; the power generation unit includes the first battery, the second battery, a first converter, and a second converter; the first battery is electrically connected to the power consumption unit through the first converter; the second battery is electrically connected to the power consumption unit through the second converter.

[0041] In a second aspect, the present invention provides an aircraft energy supply system, the aircraft energy supply system is applied to an aircraft energy supply method described in any one of the above embodiments, and the aircraft energy supply system includes:

[0042] A material storage unit, the material storage unit comprises a methanol tank, a methanol pump, a water tank, and a water pump; the input end of the methanol pump is connected to the output end of the methanol tank; the input end of the water pump is connected to the output end of the water tank;

[0043] A hydrogen production unit, the hydrogen production unit comprises a reaction chamber, a combustion chamber, a first evaporation chamber, a second evaporation chamber, a first heater, a second heater, and a first heat exchanger; the outer peripheral wall of the reaction chamber abuts against the inner peripheral wall of the combustion chamber; the inner peripheral wall of the first evaporation chamber abuts against part of the outer peripheral wall of the combustion chamber; the inner peripheral wall of the second evaporation chamber abuts against part of the outer peripheral wall of the combustion chamber; the first evaporation chamber and the second evaporation chamber are arranged at intervals; the first heater is arranged in the inner chamber of the first evaporation chamber; the second heater is arranged in the inner chamber of the second evaporation chamber; the inner peripheral wall of the first heat exchanger abuts against the outer peripheral wall of the first evaporation chamber and the outer peripheral wall of the second evaporation chamber respectively; the input end of the first evaporation chamber is connected to the output end of the methanol pump; the output end of the first evaporation chamber is connected to the input end of the reaction chamber and the input end of the combustion chamber respectively through pipelines; the input end of the second evaporation chamber is connected to the output end of the water pump; the output end of the second evaporation chamber is connected to the input end of the reaction chamber through a pipeline; the output end of the combustion chamber is connected to the input end of the first heat exchanger;

[0044] A power generation unit, the power generation unit comprising a first battery and a first converter; the input end of the first battery is connected to the output end of the reaction chamber; the output end of the first battery is electrically connected to the input end of the first converter; the output end of the first battery is connected to the input end of the combustion chamber;

[0045] An inerting unit, the inerting unit comprising a second heat exchanger, a first separator, a second separator, a first valve, a second valve, a filter, a sensor, and an inerting tank; the output end of the second heat exchanger is connected to the input end of the first separator; the output end of the first separator is respectively connected to the input end of the water tank and the input end of the filter; the output end of the filter is connected to the input end of the first valve; the output end of the first valve is respectively connected to the input end of the second separator and the input end of the second valve; the sensor is arranged on the pipeline between the filter and the first valve; the input end of the second heat exchanger is connected to the output end of the first heat exchanger; the output end of the second separator is respectively connected to the input end of the first battery and the input end of the second valve; the output end of the second valve is connected to the input end of the methanol tank; the inerting tank is connected to the input end of the methanol tank through the second valve;

[0046] an air supply unit, wherein an output end of the air supply unit is connected to an input end of the first battery;

[0047] An electric unit, wherein an input end of the electric unit is electrically connected to an output end of the first converter.

[0048] In some embodiments, the power generation unit also includes a second battery and a second converter; the second battery is electrically connected to the input end of the power consumption unit through the second converter; the gas supply unit includes a gas supply machine and a third separator; the input end of the gas supply machine is connected to the external space; the output end of the gas supply machine is respectively connected to the input end of the third separator and the input end of the first battery; the output end of the third separator is respectively connected to the input end of the first battery and the input end of the methanol tank.

[0049] In order to solve the problem of how to safely store and use methanol on an aircraft, the present invention has the following advantages:

[0050] Methanol and water enter the reaction chamber for catalytic reforming reaction to produce hydrogen, and the hydrogen is transported to the first battery to react with air, thereby providing electricity for the power unit. The first tail gas discharged is recycled and reused through the inertization unit, and the inert gas separated from the first tail gas is input into the methanol tank as a protective gas for methanol, while ensuring that the pressure in the methanol tank is stable to avoid the explosion of methanol in the methanol tank. The water separated from the first tail gas is input into the water tank for storage. In this way, energy recycling can be achieved and the waste of aircraft fuel resources can be reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0051] Figure 1 A schematic diagram of a flow chart of an aircraft energy supply method according to an embodiment is shown;

[0052] Figure 2A schematic diagram of an aircraft energy supply system according to an embodiment is shown.

[0053] Figure numerals: 01 storage unit; 11 methanol tank; 12 methanol pump; 13 water tank; 14 water pump; 02 hydrogen production unit; 21 reaction chamber; 22 combustion chamber; 23 first evaporation chamber; 24 second evaporation chamber; 25 first heater; 26 second heater; 27 first heat exchanger; 03 power generation unit; 31 first battery; 32 first converter; 33 second battery; 34 second converter; 04 inerting unit; 41 second heat exchanger; 42 first separator; 43 second separator; 44 first valve; 45 second valve; 46 filter; 47 sensor; 48 inerting tank; 05 gas supply unit; 51 gas supply machine; 52 third separator; 06 power consumption unit. DETAILED DESCRIPTION

[0054] The present disclosure will now be discussed with reference to several exemplary embodiments. It should be understood that these embodiments are discussed only to enable those skilled in the art to better understand and thus implement the present disclosure, rather than implying any limitation on the scope of the present disclosure.

[0055] As used herein, the term "including" and its variants are to be interpreted as open-ended terms meaning "including but not limited to". 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 orientation or position relationship indicated by the terms "upper", "lower", "left", "right", "front", "back", "top", "bottom", "inner", "outer", "vertical", "horizontal", "lateral", "longitudinal" and the like is based on the orientation or position relationship shown in the accompanying drawings. These terms are mainly for better describing the present application and its embodiments, and are not used to limit the indicated devices, elements or components to have a specific orientation, or to be constructed and operated in a specific orientation. In addition, in addition to being used to indicate an orientation or position relationship, some of the above terms may also be used to indicate other meanings, such as the term "upper" may also be used to indicate a certain dependency or connection relationship in some cases. For those of ordinary skill in the art, the specific meanings of these terms in this application can be understood according to the specific circumstances. In addition, the terms "install", "set", "provided with", "connected" and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral structure; it can be a mechanical connection, or an electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, or it can be an internal connection between two devices, elements or components. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to the specific circumstances. In addition, the terms "first", "second", etc. are mainly used to distinguish different devices, elements or components (the specific types and structures may be the same or different), and are not used to indicate or imply the relative importance and quantity of the indicated devices, elements or components. Unless otherwise specified, "plurality" means two or more.

[0056] In this embodiment, the electric aircraft can produce hydrogen through the catalytic reforming reaction of methanol and water, and then transport the hydrogen to the hydrogen fuel cell to supply electricity. The excess reaction gas produced by the hydrogen production and the excess reaction gas produced in the process of converting chemical energy into electricity in the hydrogen fuel cell are often discharged to the external space, resulting in a waste of resources. However, in the high-altitude and low-pressure environment of the aircraft, the auto-ignition point of methanol is low, and the low pressure in the methanol tank 11 can easily cause methanol to gasify, making methanol flammable and explosive, posing certain safety hazards. In order to solve the above problems, this embodiment discloses a method for supplying energy to an aircraft, such as Figure 1 As shown, the aircraft energy supply method may include steps S10 to S50, and the above steps are described in detail below:

[0057] Step S10, based on the electricity demand of the electricity consumption unit 06 being less than or equal to the demand threshold, the storage unit 01 supplies methanol at a first flow rate and water at a second flow rate to the hydrogen production unit 02, so as to facilitate the subsequent operation of the hydrogen production unit 02.

[0058] In step S20, based on the storage unit 01 supplying methanol at a first flow rate and water at a second flow rate to the hydrogen production unit 02, the reaction chamber 21 of the hydrogen production unit 02 supplies hydrogen to the first battery 31 of the power generation unit 03, and the gas supply unit 05 supplies air to the first battery 31; the first battery 31 can be a high-temperature proton exchange membrane hydrogen fuel cell, which has a high tolerance to carbon monoxide and the proton exchange membrane is not easily poisoned.

[0059] Step S30, based on the reaction chamber 21 supplying hydrogen to the first battery 31 and the gas supply unit 05 supplying air to the first battery 31, the first battery 31 supplies electric energy to the power consumption unit 06 at a first power;

[0060] Step S40, based on the first battery 31 supplying electric energy to the power consumption unit 06 at a first power, the first exhaust gas flows through the first heat exchanger 27 of the hydrogen production unit 02 and is transported to the inerting unit 04; wherein the first exhaust gas includes carbon dioxide and water discharged from the combustion of methanol in the combustion chamber 22 of the hydrogen production unit 02, and inert gas discharged from the reaction of hydrogen and air in the first battery 31; by utilizing the first heat exchanger 27 to absorb heat in the first exhaust gas, the heat can be used to help vaporize methanol and water, thereby improving the efficiency of catalytic reforming hydrogen production.

[0061] Step S50, based on the first tail gas flowing through the first heat exchanger 27 and being transported to the inerting unit 04, the inerting unit 04 inputs inert gas to the methanol tank 11 of the storage unit 01 and inputs water to the water tank 13 of the storage unit 01. The first tail gas is recovered and separated by the inerting unit 04, water is added to the water tank 13, and inert gas is filled into the methanol tank 11 as a protective gas for methanol, ensuring that the pressure of the methanol tank 11 is stable, thereby reducing the risk of methanol explosion. At the same time, the recycling of aircraft fuel resources is achieved to a certain extent, reducing energy waste.

[0062] In this embodiment, step S20 may include:

[0063] Step S21, based on the material storage unit 01 supplying methanol at a first flow rate and water at a second flow rate to the hydrogen production unit 02, the first heater 25 is heated to a first temperature threshold, and the second heater 26 is heated to a second temperature threshold;

[0064] In step S22, based on the first heater 25 being heated to the first temperature threshold and the second heater 26 being heated to the second temperature threshold, methanol flows through the first evaporation chamber 23 to complete vaporization and water flows through the second evaporation chamber 24 to complete vaporization; thus, the first heater 25 and the second heater 26 can be used for heating, so that methanol and water can be vaporized faster, thereby improving the efficiency of catalytic reforming hydrogen production.

[0065] In step S23, methanol flows through the first evaporation chamber 23 to complete vaporization, and water flows through the second evaporation chamber 24 to complete vaporization. The vaporized methanol flows into the reaction chamber 21 and the combustion chamber 22 respectively, and the vaporized water flows into the reaction chamber 21; thereby, the combustion of methanol in the combustion chamber 22 can provide heat for the reaction of methanol and water in the reaction chamber 21. At the same time, the combustion of methanol in the combustion chamber 22 can also provide heat for the first evaporation chamber 23 and the second evaporation chamber 24, accelerate the vaporization process of methanol and water, and thus improve the utilization rate of thermal energy and reduce energy waste.

[0066] In step S24, based on the vaporized methanol flowing into the reaction chamber 21 and the combustion chamber 22 respectively and the vaporized water flowing into the reaction chamber 21, the reaction chamber 21 supplies hydrogen to the first battery 31 of the power generation unit 03, and the air supply machine 51 of the air supply unit 05 supplies air to the first battery 31.

[0067] In this embodiment, step S40 may include:

[0068] Step S41, based on the first battery 31 supplying electric energy to the power consumption unit 06 at a first power, the first battery 31 discharges residual hydrogen and inert gas after the reaction;

[0069] Step S42, based on the residual hydrogen and inert gas discharged from the first battery 31 after the reaction, the residual hydrogen after the reaction flows into the combustion chamber 22 of the hydrogen production unit 02 for combustion, and the first tail gas flows through the first heat exchanger 27 of the hydrogen production unit 02 and is transported to the inerting unit 04; wherein, the first tail gas includes carbon dioxide and water discharged from the combustion of methanol in the combustion chamber 22 of the hydrogen production unit 02, and inert gas discharged from the reaction of hydrogen and air in the first battery 31. The residual hydrogen after the reaction of the first battery 31 is transported to the combustion chamber 22 for combustion, so as to provide sufficient heat for the first evaporation chamber 23, the second evaporation chamber 24, and the reaction chamber 21, and further improve the efficiency of catalytic reforming hydrogen production. At the same time, energy waste is reduced and costs are saved.

[0070] In this embodiment, step S50 may include:

[0071] Step S51, based on the first tail gas flowing through the first heat exchanger 27 and being transported to the inerting unit 04, the second heat exchanger 41 cools the first tail gas, so as to facilitate the subsequent gas-liquid separation of the first tail gas.

[0072] Step S52, after the cooling of the first tail gas is completed by the second heat exchanger 41, the first tail gas flows into the first separator 42 for gas-liquid separation; thereby, the water in the first tail gas can be recycled and reused, reducing energy waste.

[0073] Step S53, based on the first exhaust gas flowing into the first separator 42 to complete gas-liquid separation, the water in the first separator 42 is transported to the water tank 13 of the storage unit 01, and the mixed gas in the first separator 42 is transported to the filter 46; wherein the mixed gas includes carbon dioxide, inert gas, and oxygen; thereby, impurities in the mixed gas can be filtered out, facilitating the subsequent reuse of the mixed gas.

[0074] Step S54 , based on the mixed gas flowing through the filter 46 , the oxygen content of the mixed gas is obtained; the oxygen concentration of the mixed gas can be determined by the sensor 47 .

[0075] Step S55: Based on the oxygen content of the mixed gas being less than the first threshold, the mixed gas is delivered to the methanol tank 11 of the storage unit 01. This can reduce energy waste and avoid the increased risk of methanol explosion due to excessively high oxygen content in the mixed gas.

[0076] In this embodiment, step S50 may further include:

[0077] Step S56, based on the oxygen content of the mixed gas being greater than or equal to the first threshold, delivering the mixed gas to the second separator 43;

[0078] In step S57 , based on the mixed gas being delivered to the second separator 43 , the second separator 43 delivers the oxygen separated from the mixed gas to the first battery 31 and delivers the mixed gas from which oxygen is removed to the methanol tank 11 .

[0079] In this embodiment, step S50 may further include:

[0080] Step S58, based on the mixed gas being delivered to the methanol tank 11, obtaining the pressure in the methanol tank 11;

[0081] Step S59, based on the pressure in the methanol tank 11 being greater than or equal to the first pressure threshold, stop delivering the mixed gas to the methanol tank 11 and store the remaining mixed gas in the inerting tank 48. During the flight of the aircraft, the chemical reaction in the hydrogen production unit 02 and the first battery 31 always exists, but the demand for the mixed gas in the methanol tank 11 is changing. When the demand for the mixed gas is small, the mixed gas can be stored, so that when the demand for the mixed gas increases sharply, the mixed gas in the inerting tank 48 can be input into the methanol tank 11, ensuring the safety of the methanol storage in the methanol tank 11. At the same time, it is prevented that the mixed gas is directly discharged into the external space to reduce resource waste.

[0082] In this embodiment, the aircraft energy supply method may further include:

[0083] Step S11, based on the fact that the power demand of the power unit 06 is greater than the demand threshold, the first battery 31 supplies electric energy to the power unit 06 at a second power; wherein the second power is greater than the first power; at this time, the power consumption of the power unit 06 is relatively large, and the first battery 31 needs to increase the output power to meet the power demand of the power unit 06, and the hydrogen production unit 02 needs to consume a large amount of methanol to produce hydrogen.

[0084] Step S12, based on the first battery 31 supplying electric energy to the power consumption unit 06 at the second power, the first exhaust gas flows through the first heat exchanger 27 and is transported to the inerting unit 04;

[0085] Step S13, based on the first tail gas flowing through the first heat exchanger 27 and being transported to the inerting unit 04, the amount of inerting gas in the inerting unit 04 and the pressure in the methanol tank 11 are obtained; thereby, it is convenient to judge whether the subsequent inert gas can meet the use requirement of the methanol tank 11.

[0086] Step S14, based on the fact that the amount of inert gas in the inerting unit 04 is less than the set gas threshold and the pressure in the methanol tank 11 is less than the second pressure threshold, disconnect the connection between the gas supply machine 51 and the first battery 31 and control the third separator 52 of the gas supply unit 05 to separate the air supplied by the gas supply machine 51 into oxygen and inert gas;

[0087] Step S15, based on the third separator 52, the air supplied by the gas supply machine 51 is separated into oxygen and inert gas, and the third separator 52 delivers oxygen to the first battery 31 and delivers inert gas to the methanol tank 11. At this time, due to the large amount of methanol consumed in the hydrogen production unit 02, the pressure in the methanol tank 11 is low, and the risk of methanol explosion is high. The inert gas stored in the inerting tank 48 may not meet the use requirements of the methanol tank 11, so the third separator 52 can be opened to directly separate the air sucked by the gas supply machine 51. The separated inert gas can replenish the inert gas to the methanol tank 11 in time to ensure that the pressure of the methanol tank 11 is greater than or equal to the first pressure threshold (i.e., the methanol safety range value). At the same time, the separated oxygen is delivered to the first battery 31, which can effectively improve the completeness of the reaction in the first battery 31, improve the efficiency of the first battery 31 in converting chemical energy into electrical energy, and ensure the stability of the output power of the first battery 31.

[0088] In this embodiment, step S11 may include:

[0089] Step S111, based on the fact that the electricity demand of the electricity consumption unit 06 is greater than the demand threshold, the storage unit 01 supplies methanol at a third flow rate and water at a fourth flow rate to the hydrogen production unit 02; wherein the third flow rate is greater than the first flow rate; the fourth flow rate is greater than the second flow rate; thereby ensuring that the hydrogen production unit 02 supplies sufficient hydrogen to the first battery 31.

[0090] Step S112, based on the storage unit 01 supplying methanol at a third flow rate and water at a fourth flow rate to the hydrogen production unit 02, the reaction chamber 21 supplies hydrogen to the first battery 31, and the gas supply machine 51 supplies air to the first battery 31;

[0091] Step S113, based on the reaction chamber 21 supplying hydrogen to the first battery 31 and the air supply machine 51 supplying air to the first battery 31, the first battery 31 supplies electric energy to the power unit 06 at the second power and the second battery 33 supplies electric energy to the power unit 06; wherein the second power is greater than the first power; the power generation unit 03 includes the first battery 31, the second battery 33, the first converter 32, and the second converter 34; the first battery 31 is electrically connected to the power unit 06 through the first converter 32; the second battery 33 is electrically connected to the power unit 06 through the second converter 34. Thus, the second battery 33 can be used to supplement electric energy, ensure the power demand of the power unit 06, and buy time for the chemical reaction between the hydrogen production unit 02 and the first battery 31.

[0092] In this embodiment, this embodiment discloses an aircraft energy supply system, which can be applied to any one of the aircraft energy supply methods in the above embodiments. The aircraft energy supply system may include: a storage unit 01, a hydrogen production unit 02, a power generation unit 03, an inerting unit 04, an air supply unit 05, and an electricity consumption unit 06.

[0093] The storage unit 01 may include a methanol tank 11, a methanol pump 12, a water tank 13, and a water pump 14. The input end of the methanol pump 12 may be connected to the output end of the methanol tank 11, so as to facilitate the delivery of the methanol stored in the methanol tank 11 to the hydrogen production unit 02. The input end of the water pump 14 may be connected to the output end of the water tank 13, so as to facilitate the delivery of the water stored in the water tank 13 to the hydrogen production unit 02.

[0094] The hydrogen production unit 02 may include a reaction chamber 21, a combustion chamber 22, a first evaporation chamber 23, a second evaporation chamber 24, a first heater 25, a second heater 26, and a first heat exchanger 27. The outer peripheral wall of the reaction chamber 21 may abut against the inner peripheral wall of the combustion chamber 22, and when methanol burns in the combustion chamber 22, heat may be provided for the methanol and water in the reaction chamber 21 to react. The inner peripheral wall of the first evaporation chamber 23 abuts against part of the outer peripheral wall of the combustion chamber 22, so that the heat of methanol burning in the combustion chamber 22 provides heat for the vaporization of methanol in the first evaporation chamber 23. The inner peripheral wall of the second evaporation chamber 24 abuts against part of the outer peripheral wall of the combustion chamber 22, so that the heat of methanol burning in the combustion chamber 22 provides heat for the vaporization of water in the second evaporation chamber 24. The first evaporation chamber 23 and the second evaporation chamber 24 are spaced apart. The first heater 25 is provided in the inner chamber of the first evaporation chamber 23, so that the vaporization of methanol in the first evaporation chamber 23 can be accelerated. The second heater 26 is arranged in the inner chamber of the second evaporation chamber 24, so as to accelerate the vaporization of water in the second evaporation chamber 24. The inner peripheral wall of the first heat exchanger 27 is respectively in contact with the outer peripheral wall of the first evaporation chamber 23 and the outer peripheral wall of the second evaporation chamber 24, so that the heat after the heat exchange between the first heat exchanger 27 and the first tail gas is transferred to the first evaporation chamber 23 and the second evaporation chamber 24, so as to accelerate the vaporization of methanol and water. The input end of the first evaporation chamber 23 is connected with the output end of the methanol pump 12, so as to facilitate the input of methanol into the first evaporation chamber 23 for vaporization. The output end of the first evaporation chamber 23 is respectively connected with the input end of the reaction chamber 21 and the input end of the combustion chamber 22 through pipelines, so as to facilitate the vaporized part of the methanol to flow into the reaction chamber 21 for reaction and the part of the methanol to flow into the combustion chamber 22 for combustion. The input end of the second evaporation chamber 24 is connected with the output end of the water pump 14, so as to facilitate the input of water into the first evaporation chamber 23 for vaporization. The output end of the second evaporation chamber 24 is connected with the input end of the reaction chamber 21 through a pipeline, so as to facilitate the vaporized water to enter the reaction chamber 21 for reaction. The output end of the combustion chamber 22 is connected to the input end of the first heat exchanger 27, so that the gas generated after the combustion of methanol flows into the first heat exchanger 27 for further heat exchange. Through the above arrangement, the heat energy generated during the operation of the hydrogen production unit 02 can be reasonably distributed and utilized to reduce energy waste.

[0095] The power generation unit 03 may include a first battery 31 and a first converter 32. The input end of the first battery 31 is connected to the output end of the reaction chamber 21, so that the hydrogen produced by the reaction chamber 21 is input into the first battery 31. The output end of the first battery 31 is electrically connected to the input end of the first converter 32, so that the first battery 31 can stably output electrical energy to the power consumption unit 06 through the first converter 32. The output end of the first battery 31 can be connected to the input end of the combustion chamber 22, so that the residual hydrogen after the reaction in the first battery 31 is transported to the combustion chamber 22 for combustion and heat release to provide heat for the vaporization of methanol and water and the catalytic reforming reaction of methanol and water, thereby reducing resource waste.

[0096] The inerting unit 04 may include a second heat exchanger 41, a first separator 42, a second separator 43, a first valve 44, a second valve 45, a filter 46, a sensor 47, and an inerting tank 48. The output end of the second heat exchanger 41 is connected to the input end of the first separator 42, so that the first tail gas after cooling is separated into gas and liquid in the first separator 42. The output end of the first separator 42 is connected to the input end of the water tank 13 and the input end of the filter 46, respectively, so that the separated water can be recycled and the impurities in the separated mixed gas can be filtered to reduce resource waste. The output end of the filter 46 is connected to the input end of the first valve 44. The output end of the first valve 44 is connected to the input end of the second separator 43 and the input end of the second valve 45, respectively. The sensor 47 is arranged on the pipeline between the filter 46 and the first valve 44, so as to obtain the oxygen content of the mixed gas. The input end of the second heat exchanger 41 is connected to the output end of the first heat exchanger 27, so that the first tail gas can be input into the inerting unit 04. The output end of the second separator 43 is connected to the input end of the first battery 31 and the input end of the second valve 45, respectively, so that the second separator 43 can separate the oxygen and inert gas in the mixed gas, and avoid the inert gas delivered to the methanol tank 11. The output end of the second valve 45 is connected to the input end of the methanol tank 11. The inerting tank 48 can be connected to the input end of the methanol tank 11 through the second valve 45, so that the inerting tank 48 can store excess mixed gas. The output end of the gas supply unit 05 is connected to the input end of the first battery 31. The input end of the power unit 06 is electrically connected to the output end of the first converter 32.

[0097] In this embodiment, the power generation unit 03 may also include a second battery 33 and a second converter 34. The second battery 33 is electrically connected to the input end of the power consumption unit 06 through the second converter 34. When the electric energy output by the first battery 31 cannot meet the power demand of the power consumption unit 06, the second battery 33 can supplement the electric energy within a certain period of time to play an emergency role. The gas supply unit 05 may include a gas supply machine 51 and a third separator 52. The input end of the gas supply machine 51 is connected to the external space. The output end of the gas supply machine 51 is respectively connected to the input end of the third separator 52 and the input end of the first battery 31. The output end of the third separator 52 is respectively connected to the input end of the first battery 31 and the input end of the methanol tank 11. When the electricity demand of the power consumption unit 06 is too large, the hydrogen production unit 02 needs to consume a large amount of methanol. The excessive methanol consumption leads to an increased demand for inert gas in the methanol tank 11. When the inert gas in the inerting unit 04 is insufficient, the oxygen and inert gas in the air can be separated by the third separator 52, and then the gas supply unit 05 supplies inert gas to the methanol tank 11 and oxygen to the first battery 31, ensuring the safe storage of methanol and stable pressure in the methanol tank 11, and ensuring the stable output of electricity by the first battery 31.

[0098] Those skilled in the art will appreciate that the above-mentioned embodiments are specific examples for implementing the present disclosure, and in actual applications, various changes may be made thereto in form and detail without departing from the scope of the present disclosure.

Claims

1. A method for supplying energy to an aircraft, characterized in that: The aircraft energy supply method comprises: Step S10, based on the electricity demand of the electricity consumption unit being less than or equal to the demand threshold, the material storage unit supplies methanol at a first flow rate and water at a second flow rate to the hydrogen production unit; Step S20, based on the material storage unit supplying methanol at the first flow rate and water at the second flow rate to the hydrogen production unit, the reaction chamber of the hydrogen production unit supplies hydrogen to the first battery of the power generation unit, and the gas supply unit supplies air to the first battery; Step S30, based on the reaction chamber supplying hydrogen to the first battery and the gas supply unit supplying air to the first battery, the first battery supplies electric energy to the power consumption unit at a first power; Step S40, based on the first battery supplying electric energy to the power-consuming unit at the first power, the first tail gas is transported to the inerting unit through the first heat exchanger of the hydrogen production unit; wherein the first tail gas includes carbon dioxide and water discharged from the combustion of methanol in the combustion chamber of the hydrogen production unit, and inert gas discharged from the reaction of hydrogen in the first battery with air; Step S50, based on the first tail gas flowing through the first heat exchanger and being transported to the inerting unit, the inerting unit inputs inert gas into the methanol tank of the storage unit and inputs water into the water tank of the storage unit.

2. The aircraft energy supply method according to claim 1, characterized in that: The step S20 comprises: Step S21, based on the material storage unit supplying methanol at the first flow rate and water at the second flow rate to the hydrogen production unit, the first heater is heated to a first temperature threshold and the second heater is heated to a second temperature threshold; Step S22, based on the first heater being heated to the first temperature threshold and the second heater being heated to the second temperature threshold, methanol flows through the first evaporation chamber to complete vaporization and water flows through the second evaporation chamber to complete vaporization; Step S23, based on the methanol flowing through the first evaporation chamber to complete vaporization, the water flowing through the second evaporation chamber to complete vaporization, the vaporized methanol flows into the reaction chamber and the combustion chamber respectively, and the vaporized water flows into the reaction chamber; Step S24, based on the vaporized methanol flowing into the reaction chamber and the combustion chamber respectively and the vaporized water flowing into the reaction chamber, the reaction chamber supplies hydrogen to the first battery of the power generation unit, and the air supply unit supplies air to the first battery.

3. The aircraft energy supply method according to claim 1, characterized in that: The step S40 comprises: Step S41, supplying electric energy to the power-consuming unit at the first power based on the first battery, and the first battery discharges residual hydrogen and inert gas after the reaction; Step S42, based on the residual hydrogen and inert gas discharged from the first battery after the reaction, the residual hydrogen after the reaction flows into the combustion chamber of the hydrogen production unit for combustion, and the first exhaust gas flows through the first heat exchanger of the hydrogen production unit and is transported to the inerting unit; wherein the first exhaust gas includes carbon dioxide and water discharged from the combustion of methanol in the combustion chamber of the hydrogen production unit, and inert gas discharged from the reaction of hydrogen in the first battery with air.

4. The aircraft energy supply method according to claim 1, characterized in that: The step S50 comprises: Step S51, based on the first tail gas flowing through the first heat exchanger and being transported to the inerting unit, the second heat exchanger cools the first tail gas; Step S52, cooling the first tail gas by the second heat exchanger is completed, and the first tail gas flows into a first separator for gas-liquid separation; Step S53, based on the first tail gas flowing into the first separator to complete gas-liquid separation, the water in the first separator is transported to the water tank of the storage unit, and the mixed gas in the first separator is transported to the filter; wherein the mixed gas includes carbon dioxide, inert gas, and oxygen; Step S54, obtaining the oxygen content of the mixed gas based on the mixed gas flowing through the filter; Step S55: Based on the oxygen content of the mixed gas being less than a first threshold, the mixed gas is transported to the methanol tank of the storage unit.

5. The aircraft energy supply method according to claim 4, characterized in that: The step S50 further includes: Step S56, based on the oxygen content of the mixed gas being greater than or equal to the first threshold, conveying the mixed gas to a second separator; Step S57, based on the mixed gas being delivered to the second separator, the second separator delivers the oxygen separated from the mixed gas to the first battery and delivers the mixed gas from which oxygen is removed to the methanol tank.

6. The aircraft energy supply method according to claim 5, characterized in that: The step S50 further includes: Step S58, obtaining the pressure in the methanol tank based on the mixed gas being delivered to the methanol tank; Step S59, based on the pressure in the methanol tank being greater than or equal to a first pressure threshold, stop delivering the mixed gas to the methanol tank and store the remaining mixed gas in an inerting tank.

7. The aircraft energy supply method according to claim 1, characterized in that: The aircraft energy supply method further comprises: Step S11: based on the power demand of the power consumption unit being greater than the demand threshold, the first battery supplies electric energy to the power consumption unit at a second power; wherein the second power is greater than the first power; Step S12, based on the first battery supplying electric energy to the power-consuming unit at the second power, the first exhaust gas flows through the first heat exchanger and is transported to the inerting unit; Step S13, based on the first tail gas flowing through the first heat exchanger and being transported to the inerting unit, obtaining the amount of inerting gas in the inerting unit and the pressure in the methanol tank; Step S14, based on the inert gas amount in the inertization unit being less than a set gas threshold and the pressure in the methanol tank being less than a second pressure threshold, disconnecting the gas supply machine from the first battery and controlling the third separator of the gas supply unit to separate oxygen and inert gas from the air supplied by the gas supply machine; Step S15, separating oxygen and inert gas from the air supplied by the air supply machine based on the third separator, and the third separator transports the oxygen to the first battery and transports the inert gas to the methanol tank.

8. The aircraft energy supply method according to claim 7, characterized in that: The step S11 comprises: Step S111, based on the electricity demand of the electricity consumption unit being greater than the demand threshold, the material storage unit supplies methanol at a third flow rate and water at a fourth flow rate to the hydrogen production unit; wherein the third flow rate is greater than the first flow rate; and the fourth flow rate is greater than the second flow rate; Step S112, based on the material storage unit supplying methanol at the third flow rate and water at the fourth flow rate to the hydrogen production unit, the reaction chamber supplies hydrogen to the first battery, and the gas supply machine supplies air to the first battery; Step S113, based on the reaction chamber supplying hydrogen to the first battery and the gas supply machine supplying air to the first battery, the first battery supplies electric energy to the power consumption unit at a second power and the second battery supplies electric energy to the power consumption unit; wherein the second power is greater than the first power; the power generation unit includes the first battery, the second battery, a first converter, and a second converter; the first battery is electrically connected to the power consumption unit through the first converter; the second battery is electrically connected to the power consumption unit through the second converter.

9. An aircraft energy supply system, the aircraft energy supply system being applied to an aircraft energy supply method according to any one of claims 1 to 8, characterized in that: The aircraft energy supply system comprises: A material storage unit, the material storage unit comprises a methanol tank, a methanol pump, a water tank, and a water pump; the input end of the methanol pump is connected to the output end of the methanol tank; the input end of the water pump is connected to the output end of the water tank; A hydrogen production unit, the hydrogen production unit comprises a reaction chamber, a combustion chamber, a first evaporation chamber, a second evaporation chamber, a first heater, a second heater, and a first heat exchanger; the outer peripheral wall of the reaction chamber abuts against the inner peripheral wall of the combustion chamber; the inner peripheral wall of the first evaporation chamber abuts against part of the outer peripheral wall of the combustion chamber; the inner peripheral wall of the second evaporation chamber abuts against part of the outer peripheral wall of the combustion chamber; the first evaporation chamber and the second evaporation chamber are arranged at intervals; the first heater is arranged in the inner chamber of the first evaporation chamber; the second heater is arranged in the inner chamber of the second evaporation chamber; the inner peripheral wall of the first heat exchanger abuts against the outer peripheral wall of the first evaporation chamber and the outer peripheral wall of the second evaporation chamber respectively; the input end of the first evaporation chamber is connected to the output end of the methanol pump; the output end of the first evaporation chamber is connected to the input end of the reaction chamber and the input end of the combustion chamber respectively through pipelines; the input end of the second evaporation chamber is connected to the output end of the water pump; the output end of the second evaporation chamber is connected to the input end of the reaction chamber through a pipeline; the output end of the combustion chamber is connected to the input end of the first heat exchanger; A power generation unit, the power generation unit comprising a first battery and a first converter; the input end of the first battery is connected to the output end of the reaction chamber; the output end of the first battery is electrically connected to the input end of the first converter; the output end of the first battery is connected to the input end of the combustion chamber; An inerting unit, the inerting unit comprising a second heat exchanger, a first separator, a second separator, a first valve, a second valve, a filter, a sensor, and an inerting tank; the output end of the second heat exchanger is connected to the input end of the first separator; the output end of the first separator is respectively connected to the input end of the water tank and the input end of the filter; the output end of the filter is connected to the input end of the first valve; the output end of the first valve is respectively connected to the input end of the second separator and the input end of the second valve; the sensor is arranged on the pipeline between the filter and the first valve; the input end of the second heat exchanger is connected to the output end of the first heat exchanger; the output end of the second separator is respectively connected to the input end of the first battery and the input end of the second valve; the output end of the second valve is connected to the input end of the methanol tank; the inerting tank is connected to the input end of the methanol tank through the second valve; an air supply unit, wherein an output end of the air supply unit is connected to an input end of the first battery; An electric unit, wherein an input end of the electric unit is electrically connected to an output end of the first converter.

10. An aircraft energy supply system according to claim 9, characterized in that: The power generation unit also includes a second battery and a second converter; the second battery is electrically connected to the input end of the power consumption unit through the second converter; the gas supply unit includes a gas supply machine and a third separator; the input end of the gas supply machine is connected to the external space; the output end of the gas supply machine is respectively connected to the input end of the third separator and the input end of the first battery; the output end of the third separator is respectively connected to the input end of the first battery and the input end of the methanol tank.

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