A hydrogen fuel multi-rotor drone

Abstract

The present invention discloses a hydrogen fuel cell multi-rotor UAV, including a fuselage and a power system. The fuselage is an integrated center disk structure, and the integrated center disk structure includes a battery stack installed on both sides of the center disk. A gas cylinder installation position is formed on the center disk between the battery stacks, and the gas cylinder is placed on the gas cylinder installation position. A flight control component is also installed on the bottom surface of the gas cylinder installation position. The UAV of the present invention designs a new integrated center disk structure, so that the battery stack is located on both sides of the gas cylinder, and the gas cylinder is located at the center of the fuselage body. This structure can greatly reduce the spatial structure of the UAV, increase the rain and dust resistance level of the hydrogen fuel cell, increase the high temperature resistance and low temperature resistance of the hydrogen fuel cell, increase the safety of the hydrogen cylinder and the valve of the hydrogen cylinder, and make the structural layout more reasonable. At the same time, the present invention has a very good air intake system, heat dissipation system, and a better power supply management system to meet the use requirements of the UAV.

Description

Technical Field

[0001] The present invention relates to the field of unmanned aerial vehicles (UAVs), and in particular to a hydrogen fuel multi-rotor UAV. Background Art

[0002] In the current prior art, hydrogen fuel cells and hydrogen cylinders are installed on drones, which rely on hydrogen fuel cells to provide electricity for the drones.

[0003] However, hydrogen fuel requires hydrogen cylinders, which are large and occupy a lot of space inside the drone. The increase in battery stacks and hydrogen cylinders leads to a significant increase in the volume of the drone's internal layout, which in turn increases the overall volume of the entire drone. Therefore, the internal structure layout of the current hydrogen fuel drone is not reasonable.

[0004] Since the stack generates heat during power generation, the stack is generally equipped with a cooling fan. However, the central airflow at the fan position is different from the peripheral airflow, resulting in concentrated airflow at the fan and less airflow at the peripheral position, which in turn leads to uneven oxygen supply to the entire stack, resulting in reduced power generation efficiency of the stack.

[0005] Since current hydrogen fuel UAVs are generally powered by a battery stack, when the power of the battery stack cannot meet the overload operation of the UAV, it often leads to insufficient battery power supply and cannot meet the power supply of the UAV in an emergency. Using only one battery stack to power the UAV often cannot meet the usage needs;

[0006] At present, the design structure of the heat dissipation system of hydrogen fuel UAV is unreasonable. The airflow entering the UAV cannot contact the components well and take away the heat. The entire airflow channel is disordered and the heat dissipation effect is not good.

[0007] At present, the battery stack and fan of hydrogen fuel UAV are fixed by separate fixing methods. During installation, the battery stack is fixed to the UAV host through the bottom of the screws, and the fan is fixed to the UAV host through separate screws. This fixing method is generally only fixed by the bottom, and the number of screws used for fixing is large, and the fixing effect of one-way screws is not good. Summary of the invention

[0008] The technical problem to be solved by the present invention is a hydrogen fuel multi-rotor UAV which adopts a brand-new layout structure and effectively solves many deficiencies in the prior art.

[0009] The present invention is realized by the following technical scheme: a hydrogen fuel multi-rotor UAV, comprising a fuselage main body and a power system, wherein the fuselage main body has an integrated center disk structure, the integrated center disk structure comprises a battery stack arranged on both sides of the center disk, a gas cylinder installation position is formed on the center disk between the battery stacks, the gas cylinder is placed on the gas cylinder installation position, and a flight control component is also arranged on the bottom surface of the gas cylinder installation position;

[0010] A power board is also provided in the main body of the fuselage. The power board is equipped with backup lithium batteries. The backup lithium batteries of the power board are connected in parallel. The power board has an output bus, which is used to power the drone. The gas cylinder is used to provide power generation energy for the battery stack.

[0011] As a preferred technical solution, a middle base support is arranged at the center position of the gas cylinder installation position, a gas cylinder tail support is arranged at the tail end of the gas cylinder installation position, a fixing part at one end of the tail of the gas cylinder is buckled into the gas cylinder tail support, the middle base support is used to support the middle position of the gas cylinder, a Velcro strap is also arranged at the middle position of the gas cylinder, the supporting height of the middle base support is lower than the height of the gas cylinder tail support, and the middle position of the gas cylinder is locked by the Velcro strap.

[0012] As a preferred technical solution, a carbon fiber plate with holes is arranged on the top of the power board, and the carbon fiber plate covers and protects the power board and serves as a heat dissipation device for the power board.

[0013] As a preferred technical solution, an air inlet is provided on the bottom surface of the center disk, a filter is provided at the air inlet, cooling fans are provided on both sides of the fuselage body, and the electric thrusters are provided on one side of the cooling fan. Air is taken in through the air inlet, and the hot air inside the fuselage and the hot air of the battery stack are drawn out to the outside through the cooling fan.

[0014] As a preferred technical solution, the battery stack is installed on a battery stack bracket, and a first screw hole is provided at the bottom of the battery stack bracket, and an adjustment hole is provided on the center plate opposite to the first screw hole. The battery stack bracket is fixed to the fuselage body with a first screw passing through the first screw hole and the adjustment hole. A second screw hole is provided on the outer side of the fuselage body opposite to the cooling fan, and the second screw is locked in the second locking hole to fix the cooling fan and the battery stack bracket.

[0015] As a preferred technical solution, an oxygen balancing device is provided on each of the inner opposite surfaces of the fuel cell stack.

[0016] As a preferred technical solution, the oxygen balancing device includes a fixing frame and a metal wire mesh arranged on the fixing frame, the metal wire mesh is provided with evenly distributed mesh holes, and the fixing frame is fixedly installed on the outside of the battery stack support.

[0017] As a preferred technical solution, the backup power supply module uses at least two lithium batteries, the two lithium batteries are connected in parallel to the power board, a lithium battery holder is provided at the bottom of the lithium battery, and the lithium battery is detachably inserted into the lithium battery holder. When the UAV is operating within the rated power and the backup lithium battery voltage is not fully charged, it can be charged through the battery stack. When the UAV's operating power is greater than the rated power, the backup lithium battery and the battery stack simultaneously power the UAV.

[0018] The beneficial effects of the present invention are as follows: 1. The battery stack of the present invention is arranged on both sides of the hydrogen cylinder to form an integrated central disk structure. This structural layout makes the internal volume of the drone smaller and the structural layout more reasonable. The structure arranged on both sides makes the battery stack have better power generation and better heat dissipation effect;

[0019] Second, an oxygen balancing device is provided at the stack of the present invention, so that the airflow layout at the stack of the present invention is more stable, and the airflow in the center and the surrounding area tends to be balanced, so that the power generation efficiency of the stack is improved;

[0020] 3. The present invention is provided with a backup power lithium battery, so that when the UAV is in use, the backup power can be used to compensate for the power supply to meet various usage requirements of the UAV. At the same time, the battery stack can also supply power to the backup lithium battery while meeting the operation requirements of the UAV;

[0021] Fourth, the air intake of the present invention is at the bottom of the drone fuselage, and fan assemblies are arranged on both sides of the drone fuselage. This method allows air intake at the bottom and air outlet on both sides, which can effectively take away the hot air and the heat on the battery stack. The placement of the hydrogen cylinder will not hinder the circulation of the airflow, making the air intake and outlet of the drone more stable, the airflow is no longer turbulent, and the heat dissipation efficiency is improved;

[0022] 5. The present invention arranges the battery stack and the fan together, so that the battery stack and the fan can be fixed at the same time only by fixing the bottom of the battery stack and the side of the fan. In addition, this method has a better positioning effect and reduces the number of screws used by jointly positioning and locking the bottom and the side. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0024] Figure 1 This is a schematic diagram of the whole machine of the present invention carrying a hydrogen cylinder;

[0025] Figure 2This is a schematic diagram of the structure of the hydrogen cylinder removal of the present invention;

[0026] Figure 3 For the present invention Figure 2 A partial enlarged view of the middle A;

[0027] Figure 4 It is a partial enlarged view of the bottom air intake structure of the present invention;

[0028] Figure 5 It is a structural schematic diagram of the external locking screw of the present invention;

[0029] Figure 6 for Figure 5 A partial enlarged view of point B in the middle;

[0030] Figure 7 This is a schematic diagram of the UAV fuselage of the present invention carrying an oxygen balancing device. DETAILED DESCRIPTION

[0031] All features disclosed in this specification, or steps in all methods or processes disclosed, except mutually exclusive features and / or steps, can be combined in any manner.

[0032] Any feature disclosed in this specification (including any additional claims, abstract and drawings), unless otherwise stated, may be replaced by other equivalent or alternative features with similar purposes. That is, unless otherwise stated, each feature is only an example of a series of equivalent or similar features.

[0033] In the description of the present invention, it is necessary to understand that the terms "one end", "the other end", "outside", "upper", "inside", "horizontal", "coaxial", "center", "end", "length", "outer end" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0034] In addition, in the description of the present invention, “plurality” means at least two, for example, two, three, etc., unless otherwise clearly and specifically defined.

[0035] Terms such as "upper", "above", "lower", and "below" used in the present invention to indicate spatial relative positions are for the purpose of convenience to describe the relationship of one unit or feature relative to another unit or feature as shown in the accompanying drawings. Terms of spatial relative position may be intended to include different orientations of the device in use or operation in addition to the orientation shown in the drawings. For example, if the device in the figure is turned over, the units described as being "below" or "beneath" other units or features will be located "above" the other units or features. Therefore, the exemplary term "below" can encompass both above and below orientations. The device may be otherwise oriented (rotated 90 degrees or in other orientations) and the spatially relative descriptive terms used herein interpreted accordingly.

[0036] In the present invention, unless otherwise clearly specified and limited, the terms "disposed", "socketed", "connected", "through", "plugged" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral one; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0037] like Figure 1 and Figure 2 As shown, a hydrogen fuel multi-rotor drone of the present invention comprises a fuselage body 1 and a power system 5. The fuselage body 1 has an integrated center disk structure, and the integrated center disk structure comprises a battery stack 14 arranged on both sides of the center disk. A gas cylinder installation position is formed on the center disk between the battery stacks 14, and a gas cylinder 18 is placed on the gas cylinder installation position. A flight control component is also arranged on the bottom surface of the gas cylinder 18 installation position;

[0038] Among them, a power board is also provided in the fuselage body 1, through which the UAV is powered. The power board uses a backup lithium battery to compensate for the power supply of the power board. The power board has an output bus, through which the UAV is powered. The gas cylinder 18 is used to provide power generation energy for the battery stack.

[0039] like Figure 3 As shown, a middle base support 11 is provided at the center of the gas cylinder installation position, a gas cylinder tail support 5 is provided at the tail end of the gas cylinder installation position, a fixing piece 6 at one end of the tail of the gas cylinder is buckled into the gas cylinder tail support 5, the middle base support 11 is used to support the middle position of the gas cylinder 18, a Velcro strap 9 is also provided at the middle position of the gas cylinder 18, the supporting height of the middle base support 11 is lower than the height of the gas cylinder tail support 5, and the middle position of the gas cylinder is locked by the Velcro strap 9. This fixing method can more stably fix the hydrogen cylinder inside the drone, making the drone more stable during flight and reducing shaking.

[0040] Among them, a carbon fiber plate 4 with holes is set on the top of the power board, which covers and protects the power board and serves as a heat dissipation for the power board. The power board is located at the bottom of the carbon fiber plate, so it is not shown in the figure.

[0041] like Figure 4 As shown, an air inlet is provided on the bottom surface of the center disk, a filter 13 is provided at the air inlet, cooling fans 3 are provided on both sides of the fuselage body, and the electric thrusters 14 are arranged on one side of the cooling fan 3. Air is taken in through the air inlet, and the hot air inside the fuselage and the hot air of the battery stack 14 are extracted to the outside through the cooling fan 3.

[0042] like Figure 5 and Figure 6 As shown, the battery stack 14 is installed on the battery stack bracket 18. The bottom of the battery stack bracket 18 is provided with a first screw hole 17, and an adjustment hole 16 is provided on the center plate opposite to the first screw hole 17. The battery stack bracket is fixed to the fuselage main body 1 by a first screw passing through the first screw hole and the adjustment hole. A second screw hole is provided on the outer side of the fuselage main body 1 opposite to the cooling fan. The second screw is locked in the second locking hole to fix the cooling fan and the battery stack bracket. The bottom of the battery stack bracket is locked by the first screw, and the outer side is locked by the second screw 15. In this way, the battery stack bracket can be fixed, and the fan can be fixed. At the same time, the fixing position of the battery stack bracket is increased, and the bottom and side fixation are achieved at the same time. The fixing method is diverse and the fixing effect is better.

[0043] Among them, Figure 7 As shown, an oxygen balancing device 2 is provided on the opposite inner sides of the fuel cell stack 14. The oxygen balancing device 2 includes a fixing frame and a metal wire mesh arranged on the fixing frame. The metal wire mesh is provided with evenly distributed mesh holes. The fixing frame is fixedly installed on the outside of the fuel cell stack bracket. Through the oxygen balancing device, the airflow at the fan can evenly pass through the metal wire mesh when passing through the balancing device, so that the air intake is more balanced, thereby ensuring the power generation of the fuel cell stack.

[0044] Among them, the backup lithium battery uses two lithium batteries 7, and the two lithium batteries 7 are connected in parallel to the power board. A lithium battery holder 8 is set at the bottom of the lithium battery. The lithium battery 7 is detachably buckled into the lithium battery holder 8. When the drone is running within the rated power, if the backup lithium battery is not fully charged, it can be charged through the battery stack. When the power used by the drone is greater than the rated power, the backup lithium battery and the battery stack simultaneously power the power board. For example, within the rated power range, the present invention is powered by the battery stack. When it exceeds 2.6 kWh, the backup power module compensates for the power supply. When the power of the drone does not exceed the rated power, the battery stack can be used to charge the backup lithium battery, thereby realizing this hybrid power supply method.

[0045] The beneficial effects of the present invention are as follows: 1. The battery stack of the present invention is arranged on both sides of the hydrogen cylinder to form an integrated central disk structure. This structural layout makes the internal volume of the drone smaller and the structural layout more reasonable. The structure arranged on both sides makes the battery stack have better power generation and better heat dissipation effect;

[0046] Second, an oxygen balancing device is provided at the stack of the present invention, so that the airflow layout at the stack of the present invention is more stable, and the airflow in the center and the surrounding area tends to be balanced, so that the power generation efficiency of the stack is improved;

[0047] 3. The present invention is provided with a backup lithium battery, so that when the drone is in use, the backup lithium battery can be used to compensate for power supply to meet various usage requirements of the drone. At the same time, the battery stack can supply power to the backup lithium battery while meeting the operation of the drone;

[0048] Fourth, the air intake of the present invention is at the bottom of the drone fuselage, and fan assemblies are arranged on both sides of the drone fuselage. This method allows air intake at the bottom and air outlet on both sides, which can effectively take away the hot air and the heat on the battery stack. The placement of the hydrogen cylinder will not hinder the circulation of the airflow, making the air intake and outlet of the drone more stable, the airflow is no longer turbulent, and the heat dissipation efficiency is improved;

[0049] 5. The present invention arranges the battery stack and the fan together, so that the battery stack and the fan can be fixed at the same time only by fixing the bottom of the battery stack and the side of the fan. In addition, this method has a better positioning effect and reduces the number of screws used by jointly positioning and locking the bottom and the side.

[0050] The above is only a specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that are not conceived through creative work should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope defined in the claims.

Claims

1. A hydrogen fuel multi-rotor drone, characterized in that: It includes a fuselage and a power system. The fuselage body has an integrated center disk structure. The integrated center disk structure includes a battery stack arranged on both sides of the center disk. A gas cylinder installation position is formed on the center disk between the battery stacks. The gas cylinder is placed on the gas cylinder installation position. A flight control component is also arranged on the bottom surface of the gas cylinder installation position. The fuselage body is also provided with a power board. The power board is also configured with a backup power module. The fuel cell supplies power to the power board. The backup power module is used to compensate the power supply to the power board. The power board has an output bus. The output bus is used to supply power to the drone. The gas cylinder is used to provide a hydrogen source for the battery stack to generate electricity. A middle bottom bracket is arranged at the center of the gas cylinder installation position, a gas cylinder tail bracket is arranged at the tail end of the gas cylinder installation position, a fixing piece at one end of the tail of the gas cylinder is buckled into the gas cylinder tail bracket, the middle bottom bracket is used to support the middle position of the gas cylinder, a Velcro strap is also arranged at the middle position of the gas cylinder, the support height of the middle bottom bracket is lower than the height of the gas cylinder tail bracket, and the middle position of the gas cylinder is locked by the Velcro strap; A carbon fiber plate with holes is arranged on the top of the power board, and the carbon fiber plate covers and protects the power board and serves as a heat dissipation device for the power board; The bottom surface of the central disk is provided with an air inlet, a filter is provided at the air inlet, cooling fans are provided on both sides of the fuselage body, and the electric thrusters are provided on one side of the cooling fan, air is taken in through the air inlet, and the hot air inside the fuselage and the hot air of the battery stack are extracted to the outside through the cooling fan; The battery stack is installed on the battery stack bracket, the bottom of the battery stack bracket is provided with a first screw hole, an adjustment hole is provided on the center plate facing the first screw hole, the battery stack bracket is fixed to the fuselage main body by a first screw passing through the first screw hole and the adjustment hole, a second screw hole is provided at a position on the outer side of the fuselage main body facing the cooling fan, and a second screw is locked in the second locking hole to fix the cooling fan and the battery stack bracket; An oxygen balancing device is provided on opposite inner surfaces of the stack; The oxygen balancing device comprises a fixing frame and a metal wire mesh arranged on the fixing frame, the metal wire mesh is provided with evenly distributed mesh holes, and the fixing frame is fixedly mounted on the outside of the battery stack support; The backup power supply module uses at least two lithium batteries, which are connected in series to a power board. A lithium battery holder is provided at the bottom of the lithium battery, and the lithium battery is detachably inserted into the lithium battery holder. When the UAV is operating within the rated power and the backup lithium battery voltage is not fully charged, it is charged through the battery stack. When the power used by the UAV is greater than the rated power, the backup lithium battery and the battery stack simultaneously power the UAV.

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