CN113232869A - Integrated hydrogen energy aircraft power system and electric aircraft - Google Patents
Integrated hydrogen energy aircraft power system and electric aircraft Download PDFInfo
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- CN113232869A CN113232869A CN202110522073.7A CN202110522073A CN113232869A CN 113232869 A CN113232869 A CN 113232869A CN 202110522073 A CN202110522073 A CN 202110522073A CN 113232869 A CN113232869 A CN 113232869A
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- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 title claims abstract description 93
- 239000001257 hydrogen Substances 0.000 title claims abstract description 93
- 229910052739 hydrogen Inorganic materials 0.000 title claims abstract description 93
- 239000000446 fuel Substances 0.000 claims abstract description 51
- 238000006243 chemical reaction Methods 0.000 claims abstract description 29
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 9
- 239000001301 oxygen Substances 0.000 claims abstract description 9
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 9
- 230000002441 reversible effect Effects 0.000 claims abstract description 6
- 238000003860 storage Methods 0.000 claims description 65
- 230000007246 mechanism Effects 0.000 claims description 39
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 37
- 239000011232 storage material Substances 0.000 claims description 34
- 239000002699 waste material Substances 0.000 claims description 28
- 239000007787 solid Substances 0.000 claims description 15
- 230000009471 action Effects 0.000 claims description 6
- 239000000919 ceramic Substances 0.000 claims description 3
- 239000012774 insulation material Substances 0.000 claims description 3
- 229910001220 stainless steel Inorganic materials 0.000 claims description 3
- 239000010935 stainless steel Substances 0.000 claims description 3
- 230000001629 suppression Effects 0.000 claims description 2
- 238000012423 maintenance Methods 0.000 abstract description 6
- 238000004519 manufacturing process Methods 0.000 abstract description 5
- 239000002994 raw material Substances 0.000 abstract description 4
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 3
- 239000002803 fossil fuel Substances 0.000 description 3
- 238000002347 injection Methods 0.000 description 3
- 239000007924 injection Substances 0.000 description 3
- 229910052744 lithium Inorganic materials 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- HBBGRARXTFLTSG-UHFFFAOYSA-N Lithium ion Chemical compound [Li+] HBBGRARXTFLTSG-UHFFFAOYSA-N 0.000 description 2
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000007599 discharging Methods 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 229910001416 lithium ion Inorganic materials 0.000 description 2
- 229910052749 magnesium Inorganic materials 0.000 description 2
- 239000011777 magnesium Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000000843 powder Substances 0.000 description 2
- 239000000376 reactant Substances 0.000 description 2
- 229910015955 MxHy Inorganic materials 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 150000002148 esters Chemical class 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 150000002431 hydrogen Chemical class 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 229910012375 magnesium hydride Inorganic materials 0.000 description 1
- -1 magnesium hydrogen compound Chemical class 0.000 description 1
- 229910052751 metal Chemical class 0.000 description 1
- 239000002184 metal Chemical class 0.000 description 1
- 238000004806 packaging method and process Methods 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 150000003839 salts Chemical class 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
- B60L50/00—Electric propulsion with power supplied within the vehicle
- B60L50/50—Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells
- B60L50/70—Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using power supplied by fuel cells
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/30—Fuel systems for specific fuels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
- B60L2200/00—Type of vehicles
- B60L2200/10—Air crafts
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02T90/40—Application of hydrogen technology to transportation, e.g. using fuel cells
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- Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Sustainable Energy (AREA)
- Aviation & Aerospace Engineering (AREA)
- Power Engineering (AREA)
- Transportation (AREA)
- Mechanical Engineering (AREA)
- Fuel Cell (AREA)
Abstract
The invention provides an integrated hydrogen energy aircraft power system and an electric aircraft, wherein the power system comprises a propeller; the first motor is connected with the propeller; the first fuel cell is connected with the first motor; a hydrogen generator connected to the first fuel cell; wherein, hydrogen generated by the hydrogen generator enters the first fuel cell and reacts with oxygen or oxygen-containing air in the first fuel cell, so as to provide power for the first motor to drive the propeller to rotate and provide thrust or reverse thrust for the aircraft. The power system provided by the invention can provide green pollution-free power for the aircraft, can also provide reaction raw material hydrogen for the fuel cell of the aircraft, and has safe and reliable hydrogen production conditions. The power system is designed as an integrated form, can be integrally replaced as a replaceable unit, does not need online maintenance when power failure occurs, and greatly increases the attendance rate of the airplane.
Description
Technical Field
The application relates to the technical field of electric aircrafts, in particular to an integrated hydrogen energy aircraft power system and an electric aircraft.
Background
The current aircraft power system mainly comprises a piston engine and an axial flow engine, the main energy of the engine is to convert the combustion chemical energy of fossil fuel into mechanical energy to output work and propel the aircraft to fly in the air, the combustion emission of the fossil fuel can cause atmospheric pollution and greenhouse effect, and the fossil fuel is non-renewable resource and faces the crisis of energy shortage in the future. There is a need for a clean renewable energy source as a power system for an aircraft.
At present, the research and development work of taking electric power as airplane power drive at home and abroad is underway, and the existing electric airplanes in research adopt a mode of driving a motor by a battery, or adopt a chargeable and dischargeable lithium ion battery as an energy source, or adopt a fuel battery as an electric power source. The lithium ion battery has the problems of short endurance time and long charging and discharging time, the endurance time can only be achieved within 30-90 minutes at present, and the reactant hydrogen of the fuel cell used at present is stored by a high-pressure compressed gas cylinder, the pressure of the gas cylinder is high (about 700 atmospheric pressures), or liquid hydrogen is used (ultra-low temperature storage (about-252.87 ℃)) and has high danger.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides an integrated hydrogen energy aircraft power system and an electric aircraft.
The invention provides an integrated hydrogen energy aircraft power system, which comprises:
a propeller;
the first motor is connected with the propeller;
the first fuel cell is connected with the first motor;
a hydrogen generator connected to the first fuel cell;
wherein the hydrogen generated by the hydrogen generator enters the first fuel cell and reacts with the oxygen or oxygen-containing air in the first fuel cell to provide power for the first motor to drive the propeller to rotate and provide thrust or reverse thrust for the aircraft.
In some embodiments of the invention, the power system further comprises a solid-state hydrogen storage material storage tank and a water storage tank, wherein the solid-state hydrogen storage material storage tank and the water storage tank are respectively connected with the hydrogen generator;
the bottom of the solid hydrogen storage material storage tank body is provided with a second motor, a first screw rod and a first piston mechanism are arranged in the solid hydrogen storage material storage tank body, and the first screw rod is connected with the second motor and the first piston mechanism respectively;
a third motor is arranged at the bottom of the water storage tank body, a second screw rod and a second piston mechanism are arranged in the water storage tank body, and the second screw rod is connected with the third motor and the second piston mechanism respectively;
under the action of the second motor and the third motor, the first piston mechanism and the second piston mechanism respectively reciprocate on the first screw rod and the second screw rod, so that the hydrogen storage materials and water in the solid hydrogen storage material storage tank body and the water storage tank body are filled and discharged.
In some embodiments of the invention, the power system further comprises a reactive waste storage, said reactive waste storage being connected to said hydrogen generator,
the bottom of the reaction waste storage is provided with a fourth motor, a third screw rod and a third piston mechanism are arranged in the reaction waste storage, and the third screw rod is connected with the fourth motor and the third piston mechanism respectively; and under the action of the fourth motor, the third piston mechanism reciprocates on the third screw rod, so that the reaction waste in the reaction waste storage device is filled and discharged.
In some embodiments of the invention, one or more of the second motor, the third motor and the fourth motor are connected to the first fuel cell.
In some embodiments of the invention, the power system further comprises an integrated mounting rack comprising a first fire compartment and a second fire compartment, each comprising a sandwich of ceramic insulation material and stainless steel plate, the first fuel cell and the hydrogen generator being mounted in the first and second fire compartments, respectively;
fire suppression devices are disposed in the first fire compartment and the second fire compartment.
In some embodiments of the invention, the power system further includes a fairing, the first electric machine and the integrated mounting bracket are located inside the fairing, the fairing includes a first aft fairing and a second aft fairing which can be opened towards two sides respectively, and the integrated mounting bracket is provided with a stay bar which is used for supporting and fixing after the first aft fairing and the second aft fairing are opened.
The invention also provides an electric aircraft comprising:
an airfoil including a second fuel cell; and
in the integrated hydrogen energy aircraft power system, the hydrogen generator is connected with the second fuel cell
In some embodiments of the invention, one or more of the first electric machine, the second electric machine, the third electric machine, and the fourth electric machine is connected to the second fuel cell.
In some embodiments of the invention, the integrated mount is provided with a tab and a shear pin, the wing being connected to the integrated mount by the tab and the shear pin.
In some embodiments of the invention, the water storage tank is connected to a radiator of the first fuel cell and/or the second fuel cell.
The power system provided by the invention can provide green pollution-free power for the aircraft, can also provide reaction raw material hydrogen for the fuel cell of the aircraft, and has safe and reliable hydrogen production conditions. The power system is designed as an integrated form, can be integrally replaced as a replaceable unit, does not need online maintenance when power failure occurs, and greatly increases the attendance rate of the airplane.
Moreover, through combining with the fuel cell on the wing, can improve original electric aircraft duration to 10 hours by 60 ~ 90 minutes, very big increase electric unmanned aerial vehicle's the time of staying empty.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
Fig. 1 is a schematic cross-sectional view of an electric aircraft according to an embodiment of the present invention.
Fig. 2 is a front view schematic diagram of the electric aircraft shown in fig. 1.
Fig. 3 is a schematic view of the electric aircraft shown in fig. 2 in a state where the rear compartment is open.
Detailed Description
The following detailed description of the present invention, taken in conjunction with the accompanying drawings and examples, is provided to enable the invention and its various aspects and advantages to be better understood. However, the specific embodiments and examples described below are for illustrative purposes only and are not limiting of the invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention. Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", may explicitly or implicitly include one or more of the described features. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
In the description of the present invention, it should be noted that unless otherwise explicitly stated or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection, either mechanically, electrically, or in communication with each other; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the present invention, unless otherwise expressly stated or limited, "above" or "below" a first feature means that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact with each other via another feature therebetween. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly above and obliquely above the second feature, or simply meaning that the first feature is at a lesser level than the second feature.
The following disclosure provides many different embodiments or examples for implementing different features of the invention. To simplify the disclosure of the present invention, the components and arrangements of specific examples are described below. Of course, they are merely examples and are not intended to limit the present invention. Furthermore, the present invention may repeat reference numerals and/or letters in the various examples, such repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed. In addition, the present invention provides examples of various specific processes and materials, but one of ordinary skill in the art may recognize applications of other processes and/or uses of other materials.
Fig. 1-3 illustrate an electric aircraft 1000 provided by the present invention, which includes an integrated hydrogen-powered aircraft power system 100 and a wing 200.
The integrated hydrogen-energy aircraft power system 100 includes a propeller 101, a first electric machine 102, a first fuel cell 103, and a hydrogen generator 104. As shown in fig. 1, a propeller 101 is located at one end of the aircraft 1000 (the position of the propeller 101 in fig. 1 is referred to as a front end in this embodiment), a first motor 102 is connected to the propeller 101 and a first fuel cell 103, respectively, and the first fuel cell 103 is also connected to a hydrogen generator 104. Wherein, the hydrogen generated by the hydrogen generator 104 enters the first fuel cell 103 and reacts with the oxygen or oxygen-containing air in the first fuel cell 103, so as to provide power for the first motor 102 to drive the propeller 101 to move and provide thrust or reverse thrust for the aircraft.
The integrated hydrogen-energy aircraft power system 100 in the embodiment shown in fig. 1 also includes a feedstock storage comprising a solid-state hydrogen storage material storage tank 105 and a water storage tank 106. The solid hydrogen storage material storage tank 105 in this embodiment is used for storing a solid hydrogen storage material, which is sold under the trade name of POWERPASTE and is a solid paste at room temperature, and the main component of the solid hydrogen storage material storage tank is a magnesium hydrogen compound MxHyThe solid paste is prepared by reacting hydrogen and magnesium at 350 deg.C and five to six times of atmospheric pressure to form magnesium hydride, adding esters and metal salt, and synthesizing. The process is reversible, so that the absorption and release of hydrogen are realized. The solid paste can store hydrogen gas at normal temperature and normal pressure (higher safety compared with high-pressure storage). And the paste can react with water to release hydrogen, and the hydrogen storage mass density of the paste is far higher than that of a high-pressure gaseous hydrogen storage tank of 700 Bar. Compared with the lithium battery, the energy of the hydrogen stored by the lithium battery is 10 times of the energy density of the current lithium battery under the same mass. And the paste can be conveniently collectedThe packaging is carried out by a tank body at normal temperature and normal pressure, so that the transportation and the replacement are convenient, and the safety problem does not exist. It should be noted that other hydrogen storage materials can be used in other embodiments of the present invention, as long as the corresponding functions can be achieved.
A solid-state hydrogen storage material storage tank 105 and a water storage tank 106 are connected to the hydrogen generator 104, respectively. When hydrogen is required to be prepared, the hydrogen storage material in the solid hydrogen storage material storage tank 105 and the water in the water storage tank 106 are added into the hydrogen generator 104 to react, so that the required hydrogen is prepared.
As shown in fig. 1, the bottom of the solid-state hydrogen storage material storage tank 105 and the bottom of the water storage tank 106 (the other end of the solid-state hydrogen storage material storage tank is located opposite to the propeller 101 in this embodiment, and other positions may be provided in other embodiments of the present invention) are respectively provided with a second motor 107 and a third motor 107 (107 in the figure represents the second motor and the third motor at the same time), and the inside of the solid-state hydrogen storage material storage tank 105 and the water storage tank 106 is respectively provided with a first screw rod, a second screw rod 108 (108 in the figure represents the first screw rod and the second screw rod at the same time), and a first piston mechanism and a second piston mechanism 109 (109 in the figure represents the first piston mechanism and the second piston mechanism at the same time). The first screw rod is respectively connected with the second motor and the first piston mechanism, and the second screw rod is respectively connected with the third motor and the second piston mechanism. That is, the solid-state hydrogen storage material storage tank 105 and the water storage tank 106 are respectively provided with a set of motor, screw and piston mechanism.
Under the action of the second motor and the third motor, the first piston mechanism and the second piston mechanism respectively reciprocate on the first screw rod and the second screw rod, so that the hydrogen storage material and the water in the solid hydrogen storage material storage tank 105 and the water storage tank 106 are filled and discharged.
Alternatively, the discharge rate can be tailored to the reaction ratio, thereby improving feedstock utilization and hydrogen production efficiency.
It should be particularly noted that although 107 in the drawing represents the second motor and the third motor, 108 in the drawing represents the first lead screw and the second lead screw, and 109 in the drawing represents the first piston mechanism and the second piston mechanism, the second motor and the third motor are independent of each other, and can be operated independently and simultaneously, and even if operated simultaneously, can be controlled independently. The first screw rod, the second screw rod, the first piston mechanism and the second piston mechanism are similar, and are not described again. In addition, in this embodiment, in order to save space, the second motor, the third motor, the first screw rod, the second screw rod, the first piston mechanism, and the second piston mechanism are designed together, but in other embodiments of the present application, other arrangement modes may be provided.
In the embodiment shown in FIG. 1, power system 100 also includes a reactive waste store 110. The reaction waste storage 110 is connected to the hydrogen generator 104, and stores reaction waste generated when hydrogen is produced.
The bottom of the reaction waste storage 110 is provided with a fourth motor 111, and the reaction waste storage 110 is internally provided with a third screw 112 and a third piston mechanism 113. The third screw 112 is connected to a fourth motor 111 and a third piston mechanism 113, respectively. Under the action of the fourth motor 111, the third piston mechanism 113 reciprocates on the third screw 112, thereby filling and discharging the reaction waste in the reaction waste storage 110. Similarly, the feed rate can be tailored to the proportion of the reaction, thereby allowing sufficient space for the reaction waste. When the reaction waste is slow, it may be discharged into power system 100 through a discharge port.
Alternatively, the second motor, and the fourth motor 111 may be powered from the first fuel cell 103, which may reduce the overall weight of the aircraft 1000. Of course, the second motor, the third motor, and the fourth motor 111 may be separately provided with a battery.
In the embodiment shown in FIG. 1, the power system 100 further includes an integrated mount 114. The integrated mounting bracket 114 includes a first fire compartment 114a and a second fire compartment 114 b. The first fire compartment 114a and the second fire compartment 114b are formed of a sandwich of ceramic insulation material and stainless steel plates, and the first fuel cell 103 and the hydrogen generator 104 are installed in the first fire compartment 114a and the second fire compartment 114b, respectively. When hydrogen gas leaks, the range of fire caused can be prevented from being expanded.
In the embodiment shown in fig. 1, the integrated mounting bracket 114 further includes a third fire compartment 114c and a fourth fire compartment 114 d. The solid-state hydrogen storage material storage tank 105 and the water storage tank 106 are placed in the third flameproof compartment 114c, and the reaction waste storage 110 is placed in the fourth flameproof compartment 114 d.
Alternatively, fire extinguishing means may be arranged in the respective cabin. Optionally, the fire extinguishing device is a powder fire extinguisher, and when a fire is detected, the system can automatically detect and automatically spray the powder fire extinguishing agent to prevent the fire from spreading.
As shown in fig. 1, the first motor 102 is mounted to the integrated mounting bracket 114 in this embodiment.
As shown in fig. 1, the power system 100 also includes a fairing 115 that encases all of the power system components except the propeller 101, i.e., the first motor 102 and the integrated mounting bracket 114 are located inside the fairing 115.
In the present embodiment, as shown in fig. 3, the cowl 115 includes a first cowl 115a and a second cowl 115b that can be opened to both sides, respectively. The integrated mounting frame 114 is provided with a stay bar 114e, and when the first and second aft cowls 115a and 115b are opened, the stay bar 114e is fixed by the stay bar supports at both sides. Optionally, the bottoms of the first aft fairing 115a and the second aft fairing 115b are provided with a lock catch.
When the power system 100 needs maintenance, the first and second aft cowls 115a and 115b are opened towards both sides and supported and fixed by the stay 114e, so that periodic maintenance and inspection of system components are facilitated. After maintenance is finished, the stay bar 114e is put down and is locked by the lock catches at the bottoms of the first cabin tail fairing 115a and the second cabin tail fairing 115 b.
The wing 200 comprises a second fuel cell 201. In the present invention, the second fuel cell 201 is connected to the hydrogen generator 104 of the power system 100, so that the hydrogen in the hydrogen generator 104 can enter the second fuel cell 201 to provide power for the wing 200.
Optionally, one or more of the first, second, third and fourth electric machines 102, 111 are connected to the second fuel cell 201 so that the second fuel cell 201 can supply power to the first fuel cell 103 when it is dead.
Alternatively, in the present invention, the water storage tank 10 is connected to a radiator of the first fuel cell 103 and/or the second fuel cell 201. The water in the water storage tank body can be used for water-cooling heat dissipation of the fuel cell.
As shown in fig. 2, in the present embodiment, the integrated mounting bracket 114 of the power system 100 is provided with a tab 114f and a shear pin 114g, and the wing 200 is connected to the integrated mounting bracket 114 through the tab 114f and the shear pin 114g, so as to connect the power system 100 and the wing 200.
The tabs 114f are used to carry the normal and side loads of the powertrain as a whole, and the shear pins 114g are used to carry the heading loads of the nacelle as a whole, while the shear pins 114g are the primary structural members for transmitting the thrust of the powertrain to the aircraft. The tabs 114f and shear pins 114g on the top of the powertrain act together to withstand the torque of the powertrain and the gyroscopic moments generated by the pitch and yaw of the aircraft.
The power system 100 of the present invention is in the form of a pod that is replaceable as a whole.
In this embodiment, as shown in fig. 2, hydrogen storage material and water injection ports are provided above both sides of the cowling 115, and a discharge port for reaction waste is provided below the cowling 115.
When the hydrogen storage material POWERPASTE is used, the generated reaction waste can be recycled for continuous use, water and electric energy are generated by reaction, the water can be directly discharged, and the electric energy is supplied to a motor for use. When the hydrogen storage material and water are exhausted, reaction raw materials can be injected in time through the hydrogen storage material and the water injection port, reactants are discharged through the reaction waste discharge port and are transported to a corresponding manufacturing plant, and the reaction waste continuously stores hydrogen through reverse reaction.
Referring to the bold arrows and the description in fig. 1 and fig. 2, in use, firstly, the hydrogen storage material and water are injected into the solid hydrogen storage material storage tank 105 and the water storage tank 106 through the injection ports, and the hydrogen storage material and the water are respectively sent into the hydrogen generator 104 through the second motor, the first lead screw, the first piston mechanism, the third motor, the second lead screw and the second piston mechanism to react to generate hydrogen according to a set speed, and the hydrogen is sent into the first fuel cell 103 and the second fuel cell 201 to react with the oxygen therein to generate electric energy and water, so as to respectively supply power to the first motor 102 and the wing 200 (also can be the second motor, the third motor and the fourth motor 111). The waste discharged from the hydrogen generator 104 enters the reactive waste storage 110, receives the reactive waste through the fourth motor 111, the third screw 112 and the third piston mechanism 113 at a set speed, and is discharged through a discharge port when full.
The power system provided by the invention can provide green pollution-free power for the aircraft, can also provide reaction raw material hydrogen for the fuel cell of the aircraft, and has safe and reliable hydrogen production conditions. The power system is designed as an integrated form, can be integrally replaced as a replaceable unit, does not need online maintenance when power failure occurs, and greatly increases the attendance rate of the airplane.
Moreover, through combining with the fuel cell on the wing, can improve original electric aircraft duration to 10 hours by 60 ~ 90 minutes, very big increase electric unmanned aerial vehicle's the time of staying empty.
It should be understood that the above examples are only for clearly illustrating the present invention and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications of the invention may be made without departing from the scope of the invention.
Claims (10)
1. An integrated hydrogen-energy aircraft power system, comprising:
a propeller;
the first motor is connected with the propeller;
the first fuel cell is connected with the first motor;
a hydrogen generator connected to the first fuel cell;
wherein the hydrogen generated by the hydrogen generator enters the first fuel cell and reacts with the oxygen or oxygen-containing air in the first fuel cell to provide power for the first motor to drive the propeller to rotate and provide thrust or reverse thrust for the aircraft.
2. The power system of claim 1, further comprising a solid-state hydrogen storage material storage tank and a water storage tank, the solid-state hydrogen storage material storage tank and the water storage tank being connected to the hydrogen generator, respectively;
the bottom of the solid hydrogen storage material storage tank body is provided with a second motor, a first screw rod and a first piston mechanism are arranged in the solid hydrogen storage material storage tank body, and the first screw rod is connected with the second motor and the first piston mechanism respectively;
a third motor is arranged at the bottom of the water storage tank body, a second screw rod and a second piston mechanism are arranged in the water storage tank body, and the second screw rod is connected with the third motor and the second piston mechanism respectively;
under the action of the second motor and the third motor, the first piston mechanism and the second piston mechanism respectively reciprocate on the first screw rod and the second screw rod, so that the hydrogen storage materials and water in the solid hydrogen storage material storage tank body and the water storage tank body are filled and discharged.
3. The power system of claim 2, further comprising a reactive waste storage reservoir coupled to the hydrogen generator,
the bottom of the reaction waste storage is provided with a fourth motor, a third screw rod and a third piston mechanism are arranged in the reaction waste storage, and the third screw rod is connected with the fourth motor and the third piston mechanism respectively; and under the action of the fourth motor, the third piston mechanism reciprocates on the third screw rod, so that the reaction waste in the reaction waste storage device is filled and discharged.
4. The power system of claim 3, wherein one or more of the second, third, and fourth electric machines are coupled to the first fuel cell.
5. The power system of claim 1, further comprising an integrated mounting bracket comprising a first fire compartment and a second fire compartment, each comprising a sandwich of ceramic insulation material and stainless steel plate, the first fuel cell and the hydrogen generator being mounted in the first and second fire compartments, respectively;
fire suppression devices are disposed in the first fire compartment and the second fire compartment.
6. The power system of claim 5, further comprising a fairing, the first electric machine and the integrated mounting bracket being positioned inside the fairing, the fairing including a first aft fairing and a second aft fairing that can be opened to either side, respectively, the integrated mounting bracket being provided with a brace that is supported and secured by the brace when the first aft fairing and the second aft fairing are opened.
7. An electric flying machine, comprising:
an airfoil including a second fuel cell; and
the integrated hydrogen-energy aircraft power system of any of claims 1-6, wherein said hydrogen generator is coupled to said second fuel cell.
8. The electric aircraft of claim 7, wherein one or more of the first electric machine, the second electric machine, the third electric machine, and the fourth electric machine is coupled to the second fuel cell.
9. The electric flying machine of claim 7, wherein the integrated mount is provided with tabs and shear pins, the wing being connected to the integrated mount by the tabs and the shear pins.
10. The electric aircraft of claim 7, wherein the water storage tank is connected to a radiator of the first fuel cell and/or the second fuel cell.
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| CN202110522073.7A CN113232869A (en) | 2021-05-13 | 2021-05-13 | Integrated hydrogen energy aircraft power system and electric aircraft |
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| CN202110522073.7A CN113232869A (en) | 2021-05-13 | 2021-05-13 | Integrated hydrogen energy aircraft power system and electric aircraft |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3129435A1 (en) * | 2021-11-25 | 2023-05-26 | Safran Nacelles | Aircraft assembly equipped with at least one hydrogen-powered thrust reverser actuation system. |
| GB2620438A (en) * | 2022-07-08 | 2024-01-10 | Gkn Aerospace Services Ltd | Apparatus |
| WO2024089670A1 (en) * | 2022-10-28 | 2024-05-02 | H3 Dynamics Holdings Pte. Ltd. | Frame device for a propulsion unit of a flight device |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030230671A1 (en) * | 2000-08-24 | 2003-12-18 | Dunn James P. | Fuel cell powered electric aircraft |
| US20040118969A1 (en) * | 2000-04-03 | 2004-06-24 | Maccready Paul B. | Hydrogen powered aircraft |
| CN107925101A (en) * | 2015-07-06 | 2018-04-17 | 深圳市大疆创新科技有限公司 | System and method for unmanned vehicle fuel cell |
| CN109159892A (en) * | 2018-10-22 | 2019-01-08 | 苏州神龙航空科技有限公司 | A kind of clean energy resource is the aerofoil profile aircraft of power |
| CN110963052A (en) * | 2018-09-30 | 2020-04-07 | 中国航发商用航空发动机有限责任公司 | Distributed propulsion system, aircraft and propulsion method |
| CN112582641A (en) * | 2019-09-27 | 2021-03-30 | 空中客车简化股份公司 | System for a fuel cell for an aircraft and aircraft |
-
2021
- 2021-05-13 CN CN202110522073.7A patent/CN113232869A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040118969A1 (en) * | 2000-04-03 | 2004-06-24 | Maccready Paul B. | Hydrogen powered aircraft |
| US20030230671A1 (en) * | 2000-08-24 | 2003-12-18 | Dunn James P. | Fuel cell powered electric aircraft |
| CN107925101A (en) * | 2015-07-06 | 2018-04-17 | 深圳市大疆创新科技有限公司 | System and method for unmanned vehicle fuel cell |
| CN110963052A (en) * | 2018-09-30 | 2020-04-07 | 中国航发商用航空发动机有限责任公司 | Distributed propulsion system, aircraft and propulsion method |
| CN109159892A (en) * | 2018-10-22 | 2019-01-08 | 苏州神龙航空科技有限公司 | A kind of clean energy resource is the aerofoil profile aircraft of power |
| CN112582641A (en) * | 2019-09-27 | 2021-03-30 | 空中客车简化股份公司 | System for a fuel cell for an aircraft and aircraft |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3129435A1 (en) * | 2021-11-25 | 2023-05-26 | Safran Nacelles | Aircraft assembly equipped with at least one hydrogen-powered thrust reverser actuation system. |
| GB2620438A (en) * | 2022-07-08 | 2024-01-10 | Gkn Aerospace Services Ltd | Apparatus |
| WO2024089670A1 (en) * | 2022-10-28 | 2024-05-02 | H3 Dynamics Holdings Pte. Ltd. | Frame device for a propulsion unit of a flight device |
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