Low-altitude aircraft based on solid hydrogen pool and control method

Abstract

The invention relates to the technical field of electric air transportation tools, in particular to a low-altitude aircraft based on a solid hydrogen pool and a control method. The low-altitude aircraft comprises an aircraft body, a flight paddle module, a fuel cell power module, a solid hydrogen pool module and a heat management module, the fuel cell power module comprises a cell stack unit and a tail emission processing unit, the cell stack unit is connected with the flight paddle module, and the solid hydrogen pool module comprises a solid hydrogen storage unit, a water injection unit and a hydrogen conveying buffer unit. The water injection unit is connected with the tail emission treatment unit and the solid hydrogen storage unit, the hydrogen delivery buffer unit is connected with the solid hydrogen storage unit and the cell stack unit, and the heat management module is used for managing heat of the fuel cell power module and the solid hydrogen pool module. Through multi-directional coupling between the fuel cell power module and the solid hydrogen pool module, the overall energy utilization rate is increased, and long cruise of a low-altitude aircraft is met.

Description

Technical Field

[0001] The invention relates to the technical field of electric aerial transport tools, in particular to a low-altitude aircraft based on a solid hydrogen pool and a control method thereof. Background Art

[0002] Conventional low-altitude aircraft all use fuel as energy, causing a lot of air pollution. In recent years, the power system used by new energy low-altitude aircraft is mainly lithium batteries. The mass power density of lithium batteries is limited, which greatly limits the cruising ability of aircraft.

[0003] Hydrogen energy is a renewable secondary energy source and an important resource for solving the future energy crisis. With the continuous reduction of fossil energy and the continuous increase in pollution, hydrogen energy is known as a good carrier for clean and alternative traditional energy. And because hydrogen energy has no pollution, high environmental friendliness and high energy conversion efficiency in the process of energy conversion, especially in the fields of transportation and power generation and energy storage, it is playing a key social role as a substitute for traditional fossil energy to provide a steady stream of electricity and heat energy for the transportation and thermal power fields. The use of hydrogen energy as an energy source is mainly converted into electricity through fuel cells. It can be used in various fields that require the use of electricity, such as sea, land, air, and space, especially in recent years, the application of aerospace has been continuously innovated. Hydrogen fuel cells mainly use gaseous or liquid hydrogen to store the fuel required for power. However, under the condition that the aircraft space and aircraft weight are very limited, it is impossible to carry more fuel, resulting in limited cruising ability of the aircraft, which cannot meet long-distance flights, and the use of high-pressure hydrogen or liquid hydrogen in the aircraft, the safety problem is more prominent.

[0004] At present, solid-state hydrogen storage can achieve high safety and high hydrogen storage density. However, the existing solid-state hydrogen storage methods cannot meet the needs of low-altitude aircraft, especially the hydrogen storage materials with high hydrogen storage density. The hydrogen storage density after hydrolysis reaction is much higher than the existing gaseous, liquid and conventional solid-state hydrogen storage, resulting in the release of hydrogen from this material and the technology that matches the aircraft fuel cell system, which is a key technical problem that needs to be solved at present. Summary of the invention

[0005] The technical problem to be solved by the embodiments of the present invention is to provide a low-altitude aircraft and a control method based on a solid hydrogen pool, so as to solve the problem that the hydrogen energy powered fuel cell in the prior art cannot meet the long cruising requirements of low-altitude aircraft.

[0006] The present invention discloses a low-altitude aircraft based on a solid hydrogen pool, comprising an airframe, a flight propeller module arranged at the front end of the airframe, and a fuel cell power module, a solid hydrogen pool module, and a thermal management module arranged in the airframe; The fuel cell power module includes a battery stack unit and a tail exhaust processing unit, wherein the battery stack unit is connected to the flight propeller module, and the tail exhaust processing unit is connected to the battery stack unit, and is used to draw out the tail exhaust after the reaction in the battery stack unit and perform steam-water separation; The solid-state hydrogen pool module includes a solid-state hydrogen storage unit, a water injection unit and a hydrogen transport buffer unit. The water injection unit is connected to the tail exhaust treatment unit and the solid-state hydrogen storage unit, and is used to quantitatively transport the reaction water after steam-water separation to the solid-state hydrogen storage unit. The hydrogen transport buffer unit is connected to the solid-state hydrogen storage unit and the battery stack unit, and is used to buffer the hydrogen release pressure of the solid-state hydrogen storage unit and transport hydrogen to the battery stack unit. The thermal management module includes a first heat dissipation unit, a second heat dissipation unit and a low-temperature preheating unit. A first medium circulation pipeline is connected between the first heat dissipation unit and the battery stack unit, a second medium circulation pipeline is connected between the second heat dissipation unit and the solid-state hydrogen storage unit, and the low-temperature preheating unit includes a first heat exchanger arranged on the first medium circulation pipeline, and a third medium circulation pipeline is connected between the first heat exchanger and the second medium circulation pipeline.

[0007] Optionally, a second heat exchanger is provided in the battery stack unit, the first heat dissipation unit includes a first water pump, a first radiator and a first three-way valve, and a medium outlet of the second heat exchanger, the first water pump, the first radiator, the first three-way valve, and a medium inlet of the second heat exchanger are connected in sequence through the first medium circulation pipeline; The low-temperature preheating unit further includes a medium bypass, one end of which is connected to the first three-way valve, and the other end of which is connected to the outlet of the first water pump, and the first heat exchanger is arranged on the medium bypass; The thermal management module also includes a first medium compensation tank, a first compensation pipeline is connected between the medium outlet of the first medium compensation tank and the medium inlet of the first water pump, and a first recovery pipeline is connected between the medium inlet of the first medium compensation tank and the medium outlet of the first radiator.

[0008] Optionally, a third heat exchanger is provided in the solid-state hydrogen storage unit, the second heat dissipation unit includes a second water pump, a second radiator and a medium filter, and the medium outlet of the third heat exchanger, the second water pump, the second radiator, the medium filter, and the medium inlet of the third heat exchanger are sequentially connected through the second medium circulation pipeline; The medium inlet of the first heat exchanger is connected to the medium outlet of the third heat exchanger through the third medium circulation pipeline, and the medium outlet of the first heat exchanger is connected to the medium outlet of the second water pump through the third medium circulation pipeline; The thermal management module also includes a second medium compensation tank, a second compensation pipeline is connected between the medium outlet of the second medium compensation tank and the medium inlet of the second water pump, and a second recovery pipeline is connected between the medium inlet of the second medium compensation tank and the medium outlet of the medium filter.

[0009] Optionally, the solid-state hydrogen storage unit includes a hydrogen release pool, and a plurality of solid-state hydrogen storage components arranged in the hydrogen release pool, an independent hydrolysis chamber is arranged in the hydrogen release pool, the water injection unit includes a water storage tank, a third water pump and a water sprayer, and the tail discharge treatment unit, the water storage tank, the third water pump, the water sprayer, and the hydrolysis chamber are connected in sequence; The tail exhaust treatment unit includes a first steam-water separator, and a tail exhaust port is arranged on the battery stack unit at the cathode. The tail exhaust port, the separated water outlet of the first steam-water separator, and the water storage tank are connected in sequence, and a tail exhaust throttle valve is arranged on the connecting pipeline between the tail exhaust port and the first steam-water separator.

[0010] Optionally, an independent hydrogen collection chamber is provided in the hydrogen release pool, the hydrogen transport buffer unit comprises a buffer tank and a pressure sensor, the hydrogen collection chamber, the buffer tank and the battery stack unit are connected in sequence, and the pressure sensor is provided at the outlet side of the buffer tank; A one-way valve is arranged on the communication pipeline between the buffer tank and the hydrogen collecting chamber, and a safety valve and a stop valve are arranged in sequence on the communication pipeline between the buffer tank and the battery stack unit.

[0011] Optionally, the battery stack unit is provided with a hydrogen inlet and a product outlet at the anode respectively; The fuel cell power module further comprises an anode reaction circulation unit, the anode reaction circulation unit comprising an ejector and a second steam-water separator, the ejector is connected to the shut-off valve and the hydrogen inlet of the battery stack unit, and an ejector inlet is provided on the ejector; The second steam-water separator is connected to the product outlet of the battery stack unit, and the separated gas outlet of the second steam-water separator is connected to the ejection inlet of the ejector.

[0012] Optionally, an air inlet is provided on the battery stack unit at the cathode; The fuel cell power module further includes an air intake and exhaust unit, which includes an air filter, an air compressor, an intercooler and a second three-way valve connected in sequence, the second three-way valve is connected to the air inlet of the battery stack unit, and the air filter is provided with an air inlet; The tail exhaust treatment unit also includes a third steam-water separator, the second three-way valve, the separation gas outlet of the first steam-water separator, and the separation gas outlet of the second steam-water separator are respectively connected to the third steam-water separator, the separation water outlet of the third steam-water separator is connected to the water storage tank, and the separation gas outlet of the third steam-water separator is used for external separation gas treatment equipment.

[0013] Optionally, a medium inlet and a medium outlet are provided on the intercooler, the medium inlet of the intercooler is connected to the medium outlet of the first three-way valve, and the medium outlet of the intercooler is connected to the medium inlet of the first water pump.

[0014] Optionally, the low-altitude aircraft further includes a power drive module, a power battery module and a whole machine control module; The fuel cell power module and the thermal management module are arranged at the head end of the engine body, the solid hydrogen pool module and the power battery module are arranged at the tail end of the engine body, and the thermal management module is arranged on the windward side of the engine body; The power drive module includes a DC-DC conversion unit, an all-in-one control unit and a drive unit, the battery stack unit and the power battery module are electrically connected to the all-in-one controller respectively, and the battery stack unit is electrically connected to the all-in-one controller through the DC-DC conversion unit, the all-in-one control unit is electrically connected to the drive unit, and the output end of the drive unit is connected to the flight propeller module; The whole machine control module is respectively communicatively connected with the power drive module, the power battery module, the fuel cell module and the solid-state hydrogen pool module, and is used for closed-loop control of the operation of each module according to the power demand of the low-altitude aircraft.

[0015] The present invention also discloses a control method for controlling the above-mentioned low-altitude aircraft, comprising: In response to the low-altitude aircraft being powered on in standby mode, inspecting the working status of each unit in the fuel cell module, the solid-state hydrogen pool module, and the thermal management module; In response to the working status of each unit being inspected to meet the preset take-off condition, the fuel cell module, the solid-state hydrogen pool module and the thermal management module are controlled to enter a standby state, and the hydrogen pressure state in the hydrogen transport buffer unit is detected; In response to detecting that the hydrogen pressure state in the hydrogen transport buffer unit meets a preset start-up condition, the solid-state hydrogen pool module and the fuel cell module are started in sequence, and the fuel cell module is used to power the flight propeller module until the low-altitude aircraft enters a flight state; According to the flight attitude of the low-altitude aircraft, the output power of the fuel cell module is dynamically adjusted, and according to the adjusted hydrogen demand of the fuel cell module, the hydrogen release rate, hydrogen release pressure and hydrogen release temperature of the solid-state hydrogen pool module are dynamically adjusted; In response to the low-altitude aircraft entering a parking state, the fuel cell module is controlled to enter a cooling and continuous discharge state in sequence until the fuel cell module is shut down, and then the solid-state hydrogen pool module is controlled to enter a stop hydrogen release state until the solid-state hydrogen pool module is shut down.

[0016] Compared with the prior art, the low-altitude aircraft based on the solid hydrogen pool and the control method provided by the embodiment of the present invention have the following beneficial effects: By arranging a fuel cell power module, a solid hydrogen pool module, and a thermal management module in the body of a low-altitude aircraft, a super solid hydrogen pool system is formed by combining the fuel cell power module and the solid hydrogen pool module. The hydrogen produced by hydrolysis in the solid hydrogen storage unit is supplied to the battery stack unit. The hydrogen delivered by the hydrogen transport buffer unit and the air provided separately form an electrochemical reaction in the battery stack unit through electrochemical catalysis to release electrical energy, which is converted into energy for driving the flight propeller module. At the same time, the tail exhaust after the reaction in the battery stack unit is separated into steam and water to provide water for the hydrogen release reaction for the solid hydrogen storage unit, thereby realizing the multi-directional coupling between the fuel cell power module and the solid hydrogen pool module, and realizing the hydrogen supply control with different pressure requirements and different flow requirements. In addition, the heat generated during the release of hydrogen in the solid hydrogen storage unit is transferred to the battery stack unit for circulation through the low-temperature preheating unit, which is used for the low-temperature start of the battery stack unit, which can increase the overall energy utilization rate and further meet the long cruise of the low-altitude aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The technical solution of the present invention will be further described in detail below with reference to the accompanying drawings and embodiments, in which: Figure 1 A schematic diagram of the overall structure of a low-altitude aircraft provided by an embodiment of the present invention; Figure 2 A schematic block diagram of the structure of the coupling between the fuel cell module and the solid-state hydrogen pool module provided in an embodiment of the present invention; Figure 3 A schematic diagram of the structure of the hydrogen transmission line and the air transmission line of the fuel cell module provided in an embodiment of the present invention; Figure 4 A schematic block diagram of the structure of the whole machine control of a low-altitude aircraft provided by an embodiment of the present invention.

[0018] The symbols in the accompanying drawings are as follows: 1. Airframe; 2. Propeller module; 3. Fuel cell power module; 31. Battery stack unit; 32. Tail exhaust treatment unit; 321. First steam-water separator; 322. Tail exhaust throttle valve; 323. Third steam-water separator; 33. Ejector; 34. Second steam-water separator; 35. Air filter; 36. Air compressor; 37. Intercooler; 38. Second three-way valve; 4. Solid-state hydrogen pool module; 41. Solid-state hydrogen storage unit; 411. Hydrogen release pool; 412. Solid-state hydrogen storage component; 42. Water injection unit; 421. Water storage tank; 422. Third water pump; 423. Water sprayer; 43. Hydrogen transport buffer unit; 431. Buffer tank; 432. Pressure sensor; 433. One-way valve; 434. Safety valve; 435. Stop valve; 5. Thermal management module; 51. First heat dissipation unit; 511. First medium circulation pipeline; 512. First water pump; 513. First radiator; 514. First three-way valve; 52. Second heat dissipation unit; 521. Second medium circulation pipeline; 522. Second water pump; 523. Second radiator; 524. Medium filter; 53. Low-temperature preheating unit; 531. First heat exchanger; 532. Third medium circulation pipeline; 533. Medium bypass; 54. First medium compensation tank; 55. Second medium compensation tank; 6. Power drive module; 61. DC-DC conversion unit; 62. All-in-one control unit; 63. Drive unit; 7. Power battery module; 8. Whole machine control module. DETAILED DESCRIPTION

[0019] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application can be combined with each other. Now, in conjunction with the accompanying drawings, the preferred embodiments of the present invention are described in detail.

[0020] The present invention discloses a low-altitude aircraft based on a solid hydrogen pool, such as Figure 1 and Figure 2As shown, it includes a body 1, a flight paddle module 2 arranged at the head end of the body 1, and a fuel cell power module 3, a solid hydrogen pool module 4, and a thermal management module 5 arranged in the body 1. The fuel cell power module 3 includes a battery stack unit 31 and a tail exhaust treatment unit 32. The battery stack unit 31 is connected to the flight paddle module 2, and the tail exhaust treatment unit 32 is connected to the battery stack unit 31, which is used to lead out the tail exhaust after the reaction in the battery stack unit 31 and perform steam-water separation. The solid hydrogen pool module 4 includes a solid hydrogen storage unit 41, a water injection unit 42, and a hydrogen transmission buffer unit 43. The water injection unit 42 connects the tail exhaust treatment unit 32 and the solid hydrogen storage unit 41, and is used to quantitatively transport the reaction water after steam-water separation to the solid hydrogen storage unit 41. The hydrogen transmission buffer unit 43 connects the solid hydrogen storage unit 41 and the battery stack unit 31, and is used to buffer the hydrogen release pressure of the solid hydrogen storage unit 41 and transport hydrogen to the battery stack unit 31. The thermal management module 5 includes a first heat dissipation unit 51, a second heat dissipation unit 52, and a low-temperature preheating unit 53. A first medium circulation pipeline 511 is connected between the first heat dissipation unit 51 and the battery stack unit 31, and a second medium circulation pipeline 521 is connected between the second heat dissipation unit 52 and the solid hydrogen storage unit 41. The low-temperature preheating unit 53 includes a first heat exchanger 531 disposed on the first medium circulation pipeline 511, and a third medium circulation pipeline 532 is connected between the first heat exchanger 531 and the second medium circulation pipeline 521.

[0021] Through the implementation of the above-mentioned low-altitude aircraft embodiment, the super solid hydrogen pool system is formed by combining the fuel cell power module 3 and the solid hydrogen pool module 4. The solid hydrogen storage unit 41 is hydrolyzed to produce hydrogen and then supplied to the battery stack unit 31. The hydrogen delivered by the hydrogen transport buffer unit 43 and the air provided separately form an electrochemical reaction in the battery stack unit 31 through electrochemical catalysis to release electrical energy, and convert it into energy for driving the flight propeller module 2. At the same time, the tail exhaust after the reaction in the battery stack unit 31 is separated into steam and water to provide water for the solid hydrogen storage unit 41 for hydrogen release reaction. On the one hand, the water resources are circulated inside the whole super solid hydrogen pool system to reduce the additional water resource consumption, greatly reduce the cost, reduce the tail exhaust, and reduce the impact on the environment; on the other hand, the water after the electrochemical reaction inside the battery stack unit 31 usually has a higher temperature, which is fed back to the solid hydrogen storage unit 41 for hydrogen release, which can prevent the solid hydrogen storage unit 41 from freezing under winter conditions to ensure that the hydrogen release reaction inside the solid hydrogen storage unit 41 can continue, thereby realizing the multi-directional coupling between the fuel cell power module 3 and the solid hydrogen pool module 4. In addition, the setting of the hydrogen transport buffer unit 43 can have a stable hydrogen storage capacity to ensure that the requirements of the fuel cell power module 3 can be maintained when there is no hydrogen release reaction inside the solid-state hydrogen storage unit 41. On this basis, combined with the thermal management module 5, the first heat dissipation unit 51 performs thermal management on the power generation process of the battery stack unit 31, and the second heat dissipation unit 52 performs thermal management on the hydrogen release process of the solid-state hydrogen storage unit 41, so that the solid-state hydrogen pool module 4 can provide hydrogen with a stable flow, pressure, and temperature for the fuel cell power module 3, thereby dynamically meeting the full operating range requirements of the fuel cell power module 3. In addition, the heat generated during the release of hydrogen in the solid-state hydrogen storage unit 41 is transferred to the battery stack unit 31 for circulation through the low-temperature preheating unit 53, which is used for the low-temperature start-up of the battery stack unit 31, further increasing the overall energy utilization rate, so as to efficiently meet the long cruise of low-altitude aircraft.

[0022] As mentioned above, the battery stack unit 31 usually includes a membrane electrode, a bipolar plate, a seal and a battery pack accessory (BatteryPack). The battery stack unit 31 is the place where air and hydrogen realize electrochemical reactions, and is also the core place for electric energy conversion. It realizes the conversion of chemical energy into electrical energy through external continuous energy supply and heat output. In order to ensure the safe, reliable and stable electrical performance of the system, a battery stack performance detection device is usually provided inside the battery stack unit 31 to monitor the electrical performance of the battery stack, make reasonable judgments on the operation of the battery stack in a timely manner, and avoid safety risks.

[0023] Furthermore, combined with Figure 3As shown, a second heat exchanger is provided in the battery stack unit 31. The first heat dissipation unit 51 includes a first water pump 512, a first radiator 513 and a first three-way valve 514. The medium outlet of the second heat exchanger, the first water pump 512, the first radiator 513, the first three-way valve 514, and the medium inlet of the second heat exchanger are connected in sequence through the first medium circulation pipeline 511. The low-temperature preheating unit 53 also includes a medium bypass 533, one end of the medium bypass 533 is connected to the first three-way valve 514, and the other end of the medium bypass 533 is connected to the outlet of the first water pump 512, and the first heat exchanger 531 is arranged on the medium bypass 533. The thermal management module 5 also includes a first medium compensation tank 54, a first compensation pipeline is connected between the medium outlet of the first medium compensation tank 54 and the medium inlet of the first water pump 512, and a first recovery pipeline is connected between the medium inlet of the first medium compensation tank 54 and the medium outlet of the first radiator 513.

[0024] Through the implementation of the above-mentioned low-altitude aircraft embodiment, the first water pump 512 is a key component of the first heat dissipation unit 51, which is responsible for extracting the heat exchange medium in the second heat exchanger, and after cooling down through the first radiator 513, it enters the second heat exchanger to exchange heat generated by the electrochemical reaction inside the battery stack unit 31 to meet the power supply temperature of the battery stack unit 31 and prevent the battery stack unit 31 from overheating. The first radiator 513 is preferably a device with a cooling fan, which is used to cool the heat exchange medium flowing through the first radiator 513. And by controlling the fan speed of the first radiator 513 and the speed of the first water pump 512, stable control of the exchanged heat is achieved, and heat control during the electrochemical reaction inside the battery stack unit 31 is achieved. In addition, the first medium compensation tank 54 is provided so that when the first medium circulation pipeline 511 is short of heat exchange medium, it can be replenished in time, and when the battery stack unit 31 is about to shut down, the heat exchange medium in the first medium circulation pipeline 511 is recovered to the first medium compensation tank 54 through the first recovery pipeline, so as to avoid medium residue in the first medium circulation pipeline 511.

[0025] In addition, by utilizing the settings of the medium bypass 533 and the first heat exchanger 531, under winter conditions, the first three-way valve 514 is controlled to open the medium bypass 533, so that the heat exchange medium in the second heat exchanger circulates along the medium bypass 533, and the high-temperature medium in the second medium circulation pipeline 521 is introduced into the first heat exchanger 531 through the third medium circulation pipeline 532, so as to preheat the medium in the medium bypass 533 at low temperature, so that the preheated medium enters the second heat exchanger, and the interior of the battery stack unit 31 is continuously heated to ensure that the interior of the entire battery stack unit 31 will not freeze at low temperatures, so that at the whole machine level, the heat of the solid-state hydrogen storage unit 41 for decomposing hydrogen is directly converted to the battery stack unit 31 for reuse, so as to increase the overall energy utilization rate and thereby accelerate the response speed of the low-altitude aircraft power system.

[0026] Preferably, the heat exchange medium is a liquid medium, such as water or other liquid medium.

[0027] Furthermore, a third heat exchanger is provided in the solid hydrogen storage unit 41. The second heat dissipation unit 52 includes a second water pump 522, a second radiator 523 and a medium filter 524, and the medium outlet of the third heat exchanger, the second water pump 522, the second radiator 523, the medium filter 524, and the medium inlet of the third heat exchanger are sequentially connected through the second medium circulation pipeline 521. The medium inlet of the first heat exchanger 531 is connected to the medium outlet of the third heat exchanger through the third medium circulation pipeline 532, and the medium outlet of the first heat exchanger 531 is connected to the medium outlet of the second water pump 522 through the third medium circulation pipeline 532. The thermal management module 5 also includes a second medium compensation tank 55, a second compensation pipeline is connected between the medium outlet of the second medium compensation tank 55 and the medium inlet of the second water pump 522, and a second recovery pipeline is connected between the medium inlet of the second medium compensation tank 55 and the medium outlet of the medium filter 524.

[0028] Through the implementation of the above-mentioned low-altitude aircraft embodiment, the second water pump 522 is a key component in the second heat dissipation unit 52, which is responsible for extracting the heat exchange medium in the third heat exchanger, and after cooling down through the second radiator 523, the impurities in the cooling medium are filtered out by the medium filter 524. The filtered cooling medium then enters the third heat exchanger to exchange heat with the heat generated by the hydrogen release inside the solid hydrogen storage unit 41, so that the temperature of the hydrogen produced by the solid hydrogen storage unit 41 can meet the hydrogen temperature required by the battery stack unit 31. The second radiator 523 is preferably a device with a cooling fan, which is used to cool the heat exchange medium flowing through the second radiator 523. And by controlling the fan speed of the second radiator 523 and the speed of the second water pump 522, stable control of the exchange heat is achieved, and heat management and control during the hydrogen release process are achieved. In addition, the second medium compensation tank 55 is provided so that when the second medium circulation pipeline 521 is short of heat exchange medium, it can be replenished in time, and when the solid-state hydrogen storage unit 41 is about to shut down, the heat exchange medium in the second medium circulation pipeline 521 is recovered to the second medium compensation tank 55 through the second recovery pipeline to avoid medium residue in the second medium circulation pipeline 521.

[0029] Furthermore, the solid-state hydrogen storage unit 41 includes a hydrogen release pool 411, and a plurality of solid-state hydrogen storage components 412 arranged in the hydrogen release pool 411, and an independent hydrolysis chamber is arranged in the hydrogen release pool 411. The water injection unit 42 includes a water storage tank 421, a third water pump 422, and a water sprayer 423. The tail exhaust treatment unit 32, the water storage tank 421, the third water pump 422, the water sprayer 423, and the hydrolysis chamber are connected in sequence. The tail exhaust treatment unit 32 includes a first steam-water separator 321, and a tail exhaust port is arranged at the cathode of the battery stack unit 31. The tail exhaust port, the separated water outlet of the first steam-water separator 321, and the water storage tank 421 are connected in sequence, and a tail exhaust throttle valve 322 is arranged on the connecting pipeline between the tail exhaust port and the first steam-water separator 321.

[0030] Furthermore, an independent hydrogen collection chamber is provided in the hydrogen release pool 411. The hydrogen transmission buffer unit 43 includes a buffer tank 431 and a pressure sensor 432. The hydrogen collection chamber, the buffer tank 431 and the battery stack unit 31 are connected in sequence, and the pressure sensor 432 is arranged at the outlet side of the buffer tank 431. A one-way valve 433 is provided on the connecting pipeline between the buffer tank 431 and the hydrogen collection chamber, and a safety valve 434 and a stop valve 435 are provided in sequence on the connecting pipeline between the buffer tank 431 and the battery stack unit 31.

[0031] Through the implementation of the above-mentioned low-altitude aircraft embodiment, the hydrolysis chamber is a place where the solid hydrogen storage component 412 and the aqueous solution react to hydrolyze hydrogen. The first steam-water separator 321 is used to separate the water vapor discharged after the electrochemical reaction at the cathode in the battery stack unit 31, and the separated water enters the water storage tank 421 for storage. The third water pump 422 is responsible for pumping water from the water storage tank 421 to the water sprayer 423, and by adjusting the opening of the water sprayer 423, the required reaction water can be sprayed into the hydrolysis chamber according to the required amount of water, and sprayed on the solid hydrogen storage component 412 accordingly, so as to control the rate of the hydrogen release reaction. The hydrogen released by hydrolysis is collected in the hydrogen collection chamber on the upper side, and the buffer tank 431 is connected to the hydrogen collection chamber, so that the hydrogen in the hydrogen collection chamber enters the buffer tank 431 for buffer storage, so that the hydrogen released by the solid hydrogen storage component 412 is quantitatively stored by the buffer tank 431, and a stable hydrogen storage amount can be formed in the buffer tank 431 to ensure that the application of the battery stack unit 31 can be maintained when no hydrogen release reaction is carried out in the hydrogen release pool 411. And the pressure change impact caused by the hydrogen release reaction of the solid hydrogen storage component 412 is weakened, and the pressure sensor 432 can monitor the pressure of the hydrogen supply in real time, and the adjustment of the one-way valve 433 can adjust the reaction rate at any time to ensure that the hydrogen provided to the battery stack unit 31 can be in a relatively stable pressure range, so as to dynamically adjust the hydrogen release rate and hydrogen release pressure according to the demand for hydrogen by the battery stack unit 31.

[0032] In addition, the safety valve 434 is provided with a certain pressure jump upper limit to protect the entire system device and ensure that the pressure can be released in time in the case of overpressure. The stop valve 435 is used to cut off the entire hydrogen inlet route.

[0033] As described above, the solid-state hydrogen storage component 412 is preferably composed of hydrogen-filled high-density hydrogen storage materials. The high-density hydrogen storage materials include metal hydrogen storage materials and non-metal hydrogen storage materials, mainly high-density hydrogen storage materials that can release hydrogen by adding water. For example, metal materials such as magnesium (Mg), calcium (Ca), aluminum (Al), hydrogen storage alloys, inorganic ionic compound hydrogen storage materials, carbonaceous hydrogen storage materials, metal organic skeleton compound hydrogen storage materials, etc. Hydrogen storage alloys include binary systems, ternary systems, and multi-element systems, such as lithium hydride (LiH), sodium hydride (NaH), potassium hydride (KH), magnesium dihydride (MgH2O), etc. )、Calcium dihydride( )、Aluminum hydride( ) etc.; Inorganic ionic compound hydrogen storage materials mainly include coordinated hydrides and amino compounds, such as sodium aluminum tetrahydride ( )、lithium borohydride( ) and ammonia borane are both hydrogen storage materials with relatively high hydrogen storage density. In the solid-state hydrogen pool module, a single or multiple hydrogen storage materials with relatively high hydrogen storage density can be selected. Reversible hydrogen storage is not required, only high hydrogen storage density is required. In addition, the multiple solid-state hydrogen storage components 412 in the hydrogen release pool 411 can improve the hydrogen storage density of the solid-state hydrogen pool module 4, and the aqueous solution formed between two adjacent solid-state hydrogen storage components 412 is sprayed into the gap, which can effectively increase the contact area between the hydrogen storage material and the reaction water, and realize the controllability of the contact area between the solid-state hydrogen storage component 412 and the reaction water, thereby realizing the control of the hydrogen release rate and magnitude, and forming an integrated structure with high energy density for the entire solid-state hydrogen pool module 4. In addition, the structure of the solid-state hydrogen pool module 4 is compact, highly integrated, and can be modularized and matrixed. In order to ensure the versatility of storage and replacement of other fuels, the solid-state hydrogen storage unit 41 can also achieve up and down compatibility under different technical conditions. In particular, the multiple solid-state hydrogen storage components 412 arranged in the reaction pool 411 can be quickly replaced.

[0034] Further, the battery stack unit 31 is provided with a hydrogen inlet and a product outlet at the anode. The fuel cell power module 3 also includes an anode reaction circulation unit, which includes an ejector 33 and a second steam-water separator 34. The ejector 33 connects the shut-off valve 435 and the hydrogen inlet of the battery stack unit 31, and an ejector inlet is provided on the ejector 33. The second steam-water separator 34 is connected to the product outlet of the battery stack unit 31, and the separated gas outlet of the second steam-water separator 34 is connected to the ejector inlet of the ejector 33.

[0035] Through the implementation of the above-mentioned low-altitude aircraft embodiment, in the hydrogen fuel cell, the anode is where hydrogen enters, where hydrogen is oxidized to generate current. However, while the electrochemical reaction is carried out in the battery stack unit 31, a part of the reaction products will flow out from the anode, mainly including unreacted hydrogen and a small amount of water vapor. Therefore, the second steam-water separator 34 is used to separate the gas-liquid reaction products flowing out of the anode of the battery stack unit 31 to separate the unreacted hydrogen. And by using the setting of the ejector 33, the hydrogen produced by the solid hydrogen storage unit 41 and flowing at a high speed through the ejector 33 produces a low-pressure area to inhale the hydrogen separated by the second steam-water separator 34 and circulate back to the anode of the battery stack unit 31, thereby optimizing the utilization rate of hydrogen, improving the power supply efficiency and stability of the battery stack unit 31, and reducing the waste of hydrogen.

[0036] Furthermore, an air inlet is provided at the cathode of the battery stack unit 31. The fuel cell power module 3 also includes an air intake and exhaust unit, which includes an air filter 35, an air compressor 36, an intercooler 37 and a second three-way valve 38 connected in sequence. The second three-way valve 38 is connected to the air inlet of the battery stack unit 31, and an air inlet is provided on the air filter 35. The tail exhaust treatment unit 32 also includes a third steam-water separator 323, and the second three-way valve 38, the separation gas outlet of the first steam-water separator 321, and the separation gas outlet of the second steam-water separator 34 are respectively connected to the third steam-water separator 323. The separation water outlet of the third steam-water separator 323 is connected to the water storage tank 421, and the separation gas outlet of the third steam-water separator 323 is used for external separation gas treatment equipment.

[0037] Through the implementation of the above-mentioned low-altitude aircraft embodiment, the air filter 35 is the first line of defense of the air intake and exhaust unit, which is used to filter out dust, impurities and particles in the air to ensure that the air entering the subsequent components and the battery stack unit 31 remains clean. The air compressor 36 is responsible for compressing the filtered air to a certain pressure to provide compressed air for the subsequent cooling process. The intercooler 37 is used to cool the compressed air and allow the cooled air to enter the battery stack unit 31 through the third three-way valve, so as to improve the efficiency of the air and hydrogen mixing reaction in the battery stack unit 31 by lowering the temperature of the air.

[0038] In addition, by using the third steam-water separator 323, the separated gas of the first steam-water separator 321 and the second steam-water separator 34 is further separated into steam and water, so that the excess water vapor at the anode and cathode of the battery stack unit 31 is led out and the aqueous solution is separated by multi-stage steam-water separation, the water extraction rate is improved, and the separated aqueous solution is transported to the water storage tank 421 to fully utilize the water resources in the entire system and ensure that sufficient reaction water is introduced into the solid hydrogen storage unit 41 for water dehydrogenation reaction. Among them, since the air at the outlet of the intercooler 37 is compressed air, the compressed air is introduced into the third steam-water separator 323 through the third three-way valve control to further supplement the amount of water required for the hydrogen release reaction of the solid hydrogen storage unit 41, and the pressure in the third steam-water separator 323 can be balanced.

[0039] Furthermore, the intercooler 37 is provided with a medium inlet and a medium outlet. The medium inlet of the intercooler 37 is connected to the medium outlet of the first three-way valve 514 , and the medium outlet of the intercooler 37 is connected to the medium inlet of the first water pump 512 .

[0040] Through the implementation of the above-mentioned low-altitude aircraft embodiment, the intercooler 37 is used to exchange heat with the first medium circulation pipeline 511, so that the air intake and exhaust unit and the battery stack unit 31 share a set of heat exchange system, that is, the heat-absorbing medium in the intercooler 37 after heat exchange with the air is introduced into the first medium circulation pipeline 511 through the first water pump 512, and is cooled by the first radiator 513, and then returns to the intercooler 37 to continue heat exchange. Considering the small amount of available space on the low-altitude aircraft, the structure of the entire fuel cell power module 3 is compact, highly integrated, and can be modularized and matrixed, ensuring the versatility of storage and replacement of other fuels, thereby contributing to the simplification of the fuel cell power module 3.

[0041] Furthermore, combined with Figure 1 and Figure 4 As shown, the low-altitude aircraft also includes a power drive module 6, a power battery module 7 and a whole machine control module 8. The fuel cell power module 3 and the thermal management module 5 are arranged at the head end of the fuselage 1, the solid-state hydrogen pool module 4 and the power battery module 7 are arranged at the tail of the fuselage 1, and the thermal management module 5 is arranged on the windward side of the fuselage 1. The power drive module 6 includes a DC-DC conversion unit 61, an all-in-one control unit 62 and a drive unit 63. The battery stack unit 31 and the power battery module 7 are electrically connected to the all-in-one controller respectively, and the battery stack unit 31 is electrically connected to the all-in-one controller through the DC-DC conversion unit 61. The all-in-one control unit 62 is electrically connected to the drive unit 63, and the output end of the drive unit 63 is connected to the flight propeller module 2. The whole machine control module 8 is respectively connected to the power drive module 6, the power battery module 7, the fuel cell module and the solid-state hydrogen pool module 4 for closed-loop control of the operation of each module according to the power requirements of the low-altitude aircraft.

[0042] By implementing the above-mentioned low-altitude aircraft embodiment, the fuel cell power module 3 and the thermal management module 5 are arranged at the head end of the body 1, which can provide more space for other positions of the low-altitude aircraft, and the solid hydrogen pool module 4 and the power battery module 7 are arranged at the tail of the body 1, which can protect these high-energy density modules from damage in the event of a collision, thereby improving the safety of the low-altitude aircraft. At the same time, the thermal management module 5 is arranged on the windward side of the body 1, so that the flowing air can more effectively take away the heat, thereby dissipating the heat to the surrounding environment, so as to improve the heat dissipation efficiency of the thermal management module 5.

[0043] In addition, the power battery module 7 is a pure electric battery. By adding the power battery module 7, the power system of the entire low-altitude aircraft adopts a hybrid mode of the fuel cell power module 3 and the power battery module 7, which can achieve rapid load changes and meet the needs of high dynamic response to ensure the flight stability of the low-altitude aircraft. And when the low-altitude aircraft is ready to start, the power battery module 7 can provide the energy required for the entire super-solid hydrogen pool system to start. After the actual fuel cell power module 3 is started, the entire super-solid hydrogen pool system can achieve self-sufficiency without external energy.

[0044] The power drive module 6 is the main part of the entire low-altitude aircraft, responsible for converting electrical energy into mechanical energy, driving the flight propeller module 2 to operate, and thus driving the low-altitude aircraft to fly. Among them, the DC-DC conversion unit 61 converts DC power of different voltages into the required voltage level, so that the DC power generated by the battery stack unit 31 is compatible with the all-in-one control unit 62 through conversion and regulation. The all-in-one control unit 62 can integrate multiple functions, such as a battery management system (Battery Management System, BMS), a motor controller, an inverter, etc., responsible for monitoring and managing the operating status of the battery and the motor. In an embodiment of the present invention, the all-in-one control unit 62 is responsible for simultaneously managing the electrical energy from two different power sources, so that the hybrid mode of the fuel cell module and the power battery module 7 can be achieved to achieve rapid load changes and meet the needs of high dynamic response. The drive unit 63 is preferably a drive motor, etc., which is used to receive the electrical energy transmitted by the all-in-one control unit 62 to achieve different power outputs, thereby adapting to different flight postures of low-altitude aircraft.

[0045] The present invention also discloses a control method for controlling the above-mentioned low-altitude aircraft, comprising: In response to the low-altitude aircraft being powered on in standby mode, inspect the working status of each unit in the fuel cell module, the solid hydrogen pool module 4 and the thermal management module 5; In response to the working status of each unit being inspected to meet the preset take-off condition, the fuel cell module, the solid hydrogen pool module 4 and the thermal management module 5 are controlled to enter the standby state, and the hydrogen pressure state in the hydrogen transport buffer unit 43 is detected; In response to detecting that the hydrogen pressure state in the hydrogen transport buffer unit 43 meets the preset start-up condition, the solid hydrogen pool module 4 and the fuel cell module are started in sequence, and the fuel cell module is used to power the driving of the flight propeller module 2 until the low-altitude aircraft enters the flight state; According to the flight attitude of the low-altitude aircraft, the output power of the fuel cell module is dynamically adjusted, and according to the adjusted hydrogen demand of the fuel cell module, the hydrogen release rate, hydrogen release pressure and hydrogen release temperature of the solid hydrogen pool module 4 are dynamically adjusted; In response to the low-altitude aircraft entering a shutdown state, the fuel cell module is controlled to enter a cooling and continuous discharge state in sequence until the fuel cell module is shut down, and then the solid-state hydrogen pool module 4 is controlled to enter a stop hydrogen release state until the solid-state hydrogen pool module 4 is shut down.

[0046] Through the implementation of the above control method embodiment, in the low-altitude aircraft startup preparation stage, fault detection of each module is carried out, and each module can start the startup stage after detection. The startup of the solid-state hydrogen pool module 4 is better than the fuel cell module as a whole, ensuring the hydrogen supply of the fuel cell module. In addition, since the system power output of the low-altitude aircraft is large during the take-off stage, the hydrogen consumption in the short term is large, so it is necessary to ensure that the hydrogen pressure in the hydrogen transmission buffer unit 43 is higher than the specified limit before the fuel cell module can be turned on. In the normal startup stage of the low-altitude aircraft, the fuel cell module provides different power outputs according to the flight state of the low-altitude aircraft. The solid-state hydrogen pool module 4 recovers the tail water after the reaction of the battery stack unit 31, and adjusts the hydrogen release rate by controlling the opening of the water sprayer 423. A large amount of heat will be released during the hydrogen release reaction of the solid-state hydrogen storage unit 41. This part of the heat is supplied to the battery stack unit 31 through the third medium circulation pipeline 532 for low-temperature startup, thereby improving the efficiency of the power system. In the shutdown stage, the fuel cell module is preferentially shut down by load reduction. After the fuel cell module is shut down, the solid-state hydrogen pool module 4 enters the shutdown program to realize hydrogen storage shutdown.

[0047] The low-altitude aircraft based on the solid hydrogen pool of the present invention has a greatly improved hydrogen storage density of the solid hydrogen storage unit 41, which is 3-10 times the fuel storage energy density of various current technical solutions, and can greatly improve the cruising ability of the aircraft. At the same time, when refueling or quickly replacing the fuel, only the solid hydrogen storage unit 41 needs to be replaced, which is more convenient to operate. Since hydrogen is stored in solid materials, there is no risk of leakage, combustion and explosion, etc., the single transportable base is large, the manufacturing, transportation, and filling links are low-cost, there is no waste in the storage process, and storage in a confined space is allowed. There is no explosion risk during the collision process, which improves intrinsic safety.

[0048] It should be understood that the above embodiments are only used to illustrate the technical solutions of the present invention rather than to limit it. For those skilled in the art, the technical solutions described in the above embodiments can be modified, or some of the technical features therein can be replaced by equivalents; and all these modifications and replacements should fall within the scope of protection of the claims attached to the present invention.

Claims

1. A low-altitude aircraft based on a solid hydrogen pool, characterized in that: The low-altitude aircraft includes an airframe, a flight propeller module arranged at the front end of the airframe, and a fuel cell power module, a solid-state hydrogen pool module, and a thermal management module arranged in the airframe; The fuel cell power module includes a battery stack unit and a tail exhaust processing unit, wherein the battery stack unit is connected to the flight propeller module, and the tail exhaust processing unit is connected to the battery stack unit, and is used to draw out the tail exhaust after the reaction in the battery stack unit and perform steam-water separation; The solid-state hydrogen pool module includes a solid-state hydrogen storage unit, a water injection unit and a hydrogen transport buffer unit. The water injection unit is connected to the tail exhaust treatment unit and the solid-state hydrogen storage unit, and is used to quantitatively transport the reaction water after steam-water separation to the solid-state hydrogen storage unit. The hydrogen transport buffer unit is connected to the solid-state hydrogen storage unit and the battery stack unit, and is used to buffer the hydrogen release pressure of the solid-state hydrogen storage unit and transport hydrogen to the battery stack unit. The thermal management module includes a first heat dissipation unit, a second heat dissipation unit and a low-temperature preheating unit. A first medium circulation pipeline is connected between the first heat dissipation unit and the battery stack unit, a second medium circulation pipeline is connected between the second heat dissipation unit and the solid-state hydrogen storage unit, and the low-temperature preheating unit includes a first heat exchanger arranged on the first medium circulation pipeline, and a third medium circulation pipeline is connected between the first heat exchanger and the second medium circulation pipeline.

2. The low-altitude aircraft according to claim 1, characterized in that: A second heat exchanger is provided in the battery stack unit, the first heat dissipation unit includes a first water pump, a first radiator and a first three-way valve, and a medium outlet of the second heat exchanger, the first water pump, the first radiator, the first three-way valve, and a medium inlet of the second heat exchanger are connected in sequence through the first medium circulation pipeline; The low-temperature preheating unit further includes a medium bypass, one end of which is connected to the first three-way valve, and the other end of which is connected to the outlet of the first water pump, and the first heat exchanger is arranged on the medium bypass; The thermal management module also includes a first medium compensation tank, a first compensation pipeline is connected between the medium outlet of the first medium compensation tank and the medium inlet of the first water pump, and a first recovery pipeline is connected between the medium inlet of the first medium compensation tank and the medium outlet of the first radiator.

3. The low-altitude aircraft according to claim 2, characterized in that: A third heat exchanger is provided in the solid hydrogen storage unit, the second heat dissipation unit includes a second water pump, a second radiator and a medium filter, and the medium outlet of the third heat exchanger, the second water pump, the second radiator, the medium filter, and the medium inlet of the third heat exchanger are connected in sequence through the second medium circulation pipeline; The medium inlet of the first heat exchanger is connected to the medium outlet of the third heat exchanger through the third medium circulation pipeline, and the medium outlet of the first heat exchanger is connected to the medium outlet of the second water pump through the third medium circulation pipeline; The thermal management module also includes a second medium compensation tank, a second compensation pipeline is connected between the medium outlet of the second medium compensation tank and the medium inlet of the second water pump, and a second recovery pipeline is connected between the medium inlet of the second medium compensation tank and the medium outlet of the medium filter.

4. The low-altitude aircraft according to claim 1, characterized in that: The solid-state hydrogen storage unit includes a hydrogen release pool and a plurality of solid-state hydrogen storage components arranged in the hydrogen release pool, an independent hydrolysis chamber is arranged in the hydrogen release pool, the water injection unit includes a water storage tank, a third water pump and a water sprayer, the tail discharge treatment unit, the water storage tank, the third water pump, the water sprayer, and the hydrolysis chamber are connected in sequence; The tail exhaust treatment unit includes a first steam-water separator, and a tail exhaust port is arranged on the battery stack unit at the cathode. The tail exhaust port, the separated water outlet of the first steam-water separator, and the water storage tank are connected in sequence, and a tail exhaust throttle valve is arranged on the connecting pipeline between the tail exhaust port and the first steam-water separator.

5. The low-altitude aircraft according to claim 4, characterized in that: An independent hydrogen collection chamber is provided in the hydrogen release pool, the hydrogen transport buffer unit comprises a buffer tank and a pressure sensor, the hydrogen collection chamber, the buffer tank and the battery stack unit are connected in sequence, and the pressure sensor is provided at the outlet side of the buffer tank; A one-way valve is arranged on the communication pipeline between the buffer tank and the hydrogen collecting chamber, and a safety valve and a stop valve are arranged in sequence on the communication pipeline between the buffer tank and the battery stack unit.

6. The low-altitude aircraft according to claim 5, characterized in that: The battery stack unit is provided with a hydrogen inlet and a product outlet at the anode. The fuel cell power module further comprises an anode reaction circulation unit, the anode reaction circulation unit comprising an ejector and a second steam-water separator, the ejector is connected to the shut-off valve and the hydrogen inlet of the battery stack unit, and an ejector inlet is provided on the ejector; The second steam-water separator is connected to the product outlet of the battery stack unit, and the separated gas outlet of the second steam-water separator is connected to the ejection inlet of the ejector.

7. The low-altitude aircraft according to claim 6, characterized in that: The battery stack unit is provided with an air inlet at the cathode; The fuel cell power module further includes an air intake and exhaust unit, which includes an air filter, an air compressor, an intercooler and a second three-way valve connected in sequence, the second three-way valve is connected to the air inlet of the battery stack unit, and the air filter is provided with an air inlet; The tail exhaust treatment unit also includes a third steam-water separator, the second three-way valve, the separation gas outlet of the first steam-water separator, and the separation gas outlet of the second steam-water separator are respectively connected to the third steam-water separator, the separation water outlet of the third steam-water separator is connected to the water storage tank, and the separation gas outlet of the third steam-water separator is used for external separation gas treatment equipment.

8. The low-altitude aircraft according to claim 7, characterized in that: The intercooler is provided with a medium inlet and a medium outlet. The medium inlet of the intercooler is connected to the medium outlet of the first three-way valve, and the medium outlet of the intercooler is connected to the medium inlet of the first water pump.

9. The low-altitude aircraft according to claim 1, characterized in that: The low-altitude aircraft also includes a power drive module, a power battery module and a whole machine control module; The fuel cell power module and the thermal management module are arranged at the head end of the engine body, the solid hydrogen pool module and the power battery module are arranged at the tail end of the engine body, and the thermal management module is arranged on the windward side of the engine body; The power drive module includes a DC-DC conversion unit, an all-in-one control unit and a drive unit, the battery stack unit and the power battery module are electrically connected to the all-in-one controller respectively, and the battery stack unit is electrically connected to the all-in-one controller through the DC-DC conversion unit, the all-in-one control unit is electrically connected to the drive unit, and the output end of the drive unit is connected to the flight propeller module; The whole machine control module is respectively communicatively connected with the power drive module, the power battery module, the fuel cell module and the solid-state hydrogen pool module, and is used for closed-loop control of the operation of each module according to the power demand of the low-altitude aircraft.

10. A control method, characterized in that: Used to control the low-altitude aircraft according to any one of claims 1 to 9, the control method comprising: In response to the low-altitude aircraft being powered on in standby mode, inspecting the working status of each unit in the fuel cell module, the solid-state hydrogen pool module, and the thermal management module; In response to the working status of each unit being inspected to meet the preset take-off condition, the fuel cell module, the solid-state hydrogen pool module and the thermal management module are controlled to enter a standby state, and the hydrogen pressure state in the hydrogen transport buffer unit is detected; In response to detecting that the hydrogen pressure state in the hydrogen transport buffer unit meets a preset start-up condition, the solid-state hydrogen pool module and the fuel cell module are started in sequence, and the fuel cell module is used to power the flight propeller module until the low-altitude aircraft enters a flight state; According to the flight attitude of the low-altitude aircraft, the output power of the fuel cell module is dynamically adjusted, and according to the adjusted hydrogen demand of the fuel cell module, the hydrogen release rate, hydrogen release pressure and hydrogen release temperature of the solid-state hydrogen pool module are dynamically adjusted; In response to the low-altitude aircraft entering a parking state, the fuel cell module is controlled to enter a cooling and continuous discharge state in sequence until the fuel cell module is shut down, and then the solid-state hydrogen pool module is controlled to enter a stop hydrogen release state until the solid-state hydrogen pool module is shut down.

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