Hybrid power folding multi-rotor unmanned aerial vehicle

Abstract

According to the hybrid power folding multi-rotor unmanned aerial vehicle based on the hydrogen fuel proton exchange membrane technology, the cruising ability and portability of the unmanned aerial vehicle are improved by optimizing the structural design. The unmanned aerial vehicle body is a hydrogen power system, the vehicle arms can be folded and unfolded through the folding pieces, and the whole vehicle is light and easy to carry. The rectangular pod structure is used for installing a hydrogen fuel pile and a hydrogen cylinder, the pod frame design meets the space requirement, meanwhile, the flow direction of rotor wing airflow is not affected, and the flight stability is improved. The supporting plate adopts a hollow design, and the hydrogen fuel electric pile and the hydrogen cylinder are fixed through the locking holes, so that the weight of the whole machine is reduced, and the heat dissipation performance is enhanced. The cylindrical cushion is arranged at the bottom of the supporting frame, landing impact force is effectively buffered, operation safety of the unmanned aerial vehicle is guaranteed, and the service life is prolonged. The multi-scene task platform is simple in structure and light in weight, can be widely applied to multi-scene tasks, and has high practicability and popularization value.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned plane technical field, concretely relates to a kind of hybrid power folding multi-rotor unmanned plane based on hydrogen energy proton exchange membrane technology BACKGROUND

[0002] In recent years, with the rapid development of unmanned aerial vehicle technology, its application field has gradually expanded from early military reconnaissance to agriculture, logistics, security, surveying and mapping and other industries. This technology expansion benefits from the breakthrough of light composite materials, satellite navigation system, artificial intelligence and flight control technology, especially the rotor unmanned aerial vehicle because of its vertical take-off and landing ability, strong maneuverability and convenient control characteristics, becomes the important branch of current unmanned aerial vehicle market. However, although the rotor unmanned aerial vehicle has made many progress in technology and market application, the performance limitation of its power system still restricts its function play. Although the traditional lithium battery power system has certain technical maturity, due to the physical limit of battery energy density, its endurance is difficult to further improve. At the same time, in order to increase the battery capacity needed to enhance power, often accompanied by greater weight, thus having negative impact on flight performance and energy efficiency ratio. This technical bottleneck directly limits the performance of rotor unmanned aerial vehicle in long time flight, long-range task and high load task.

[0003] In order to break through the limitation of traditional lithium battery technology, new energy power system becomes a research hotspot. Among them, hydrogen fuel power system is gradually introduced into the field of unmanned aerial vehicle because of its high energy density, environmental protection and high efficiency. However, there are still some key technical difficulties in the actual application of existing hydrogen power system. First of all, hydrogen fuel power system needs to carry larger hydrogen storage equipment, which leads to the increase of overall size of unmanned aerial vehicle and the increase of weight, which not only affects the flight efficiency, but also puts forward higher requirements for structural design. Secondly, due to the limited power output capacity of proton exchange membrane technology, the existing hydrogen power unmanned aerial vehicle performs poorly in meeting the demand of rapid response and high maneuverability. In addition, the heat dissipation and shock resistance design of hydrogen power system lacks systematic optimization in existing technology, which further limits its reliability and practicability. Therefore, how to realize the miniaturization and high efficiency of hydrogen power system through structural optimization and technology integration, and effectively improve the endurance time and task adaptability of rotor unmanned aerial vehicle, has become an important problem to be solved in the field of current unmanned aerial vehicle technology. SUMMARY

[0004] The purpose of this part is to summarize some aspects of the embodiments of the utility model and briefly introduce some preferred embodiments. Some simplification or omission may be made in this part and the abstract of the specification and the utility model name to avoid obscuring the purpose of this part, the abstract of the specification and the utility model name, and such simplification or omission cannot be used to limit the scope of the utility model.

[0005] In view of the technical problems in the prior art, the utility model provides a kind of hybrid power folding multi-rotor unmanned aerial vehicle, including unmanned aerial vehicle main body, the lower portion of unmanned aerial vehicle main body is provided with rectangular pod, the bottom of rectangular pod is provided with support plate, hydrogen fuel stack and hydrogen cylinder are installed on support plate, and the bottom of unmanned aerial vehicle main body has support frame.

[0006] As a preferred technical scheme of a kind of hybrid power folding multi-rotor unmanned aerial vehicle, the rectangular pod includes upper rod, lower rod and cylindrical vertical connecting piece, the upper rod and the lower rod are arranged in parallel, and the upper rod and the lower rod are connected to the support frame by the cylindrical vertical connecting piece.

[0007] As a preferred technical scheme of a kind of hybrid power folding multi-rotor unmanned aerial vehicle, the upper rod is longer than the unmanned aerial vehicle main body, and the upper rod is connected to the unmanned aerial vehicle main body by the first hoop.

[0008] As a preferred technical scheme of a kind of hybrid power folding multi-rotor unmanned aerial vehicle, locking holes are formed in the support plate, the hydrogen fuel stack and the hydrogen cylinder base are fixedly connected to the support plate through the locking holes, the hydrogen cylinder is embedded on the hydrogen cylinder base, and the support plate is connected to the lower rod by the second hoop.

[0009] As a preferred technical scheme of a kind of hybrid power folding multi-rotor unmanned aerial vehicle, a hollow structure is arranged below the support plate, a rectangular hole is arranged below the hydrogen cylinder base, and a heat dissipation hole is arranged below the hydrogen fuel stack.

[0010] As a preferred technical scheme of a kind of hybrid power folding multi-rotor unmanned aerial vehicle, the unmanned aerial vehicle arm can be connected to the unmanned aerial vehicle main body by the folding piece.

[0011] As a preferred technical scheme of a kind of hybrid power folding multi-rotor unmanned aerial vehicle, cylindrical buffer pads are embedded at both ends of the cylindrical bottom of the support frame.

[0012] Compared with the prior art, the utility model has the following advantages:

[0013] 1. The hydrogen fuel stack and the hydrogen cylinder are placed in the same plane, and there is sufficient space below the support plate to ensure that the hydrogen fuel stack and the hydrogen cylinder are not bumped when landing on uneven ground. The rectangular pod is designed for the hydrogen fuel stack and the hydrogen cylinder placed in the same plane, and the rectangular frame can meet the space requirements without affecting the airflow direction generated by the rotor, thereby simplifying the structure of the unmanned aerial vehicle main body. The arm can be folded by the folding piece, and the entire unmanned aerial vehicle is convenient to carry and light in weight.

[0014] 2, support plate is fixed with hydrogen fuel cell and hydrogen cylinder through locking hole, the hollow structure reduces the whole machine weight, and is favorable to hydrogen fuel cell heat dissipation, hydrogen cylinder base guarantees hydrogen cylinder stability, and in unmanned aerial vehicle movement, rolling drop does not appear, and the cylindrical buffer pad at the bottom of the support frame can greatly reduce the landing impact force, thereby prolonging the service life of the hydrogen power rotor unmanned aerial vehicle. BRIEF DESCRIPTION OF DRAWINGS

[0015] In order to more clearly illustrate the technical scheme of the embodiments of the present application, the following will briefly introduce the drawings needed to be used in the embodiment description, and obviously, the drawings in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can be obtained without creative labor under the premise of not deviating from the connotation of the present application. Among them:

[0016] Fig. 1 It is the main structure diagram of the design;

[0017] Fig. 2 It is the front view of the design;

[0018] Fig. 3 It is the side structure diagram of the design;

[0019] Fig. 4 It is the structure diagram of the support plate in the design;

[0020] Fig. 5 It is the folding structure diagram in the design. In the drawing: 1, unmanned aerial vehicle main body; 2, unmanned aerial vehicle arm; 3, folding piece; 4, rectangular pod; 5, support plate; 6, hydrogen fuel cell; 7, hydrogen cylinder; 8, support frame; 9, upper rod; 10, lower rod; 11, cylindrical vertical connecting piece; 12a, first hoop; 12b, second hoop; 13, locking hole; 14, hydrogen cylinder base; 15, rectangular hole; 16, heat dissipation hole; 17, buffer pad. DETAILED DESCRIPTION

[0021] In order to make the above-mentioned purpose, features and advantages of the present application more obvious and easy to understand, the specific embodiments of the present application will be described in detail in conjunction with the drawings of the specification.

[0022] In the following description, many specific details are set forth in order to provide a thorough understanding of the present application, but the present application can also be implemented in other ways different from those described herein, and those skilled in the art can make similar generalizations without deviating from the connotation of the present application, therefore the present application is not limited by the specific embodiments disclosed below.

[0023] Secondly, the "one embodiment" or "embodiments" referred to herein are intended to encompass a particular implementation of the present application, which can include a particular feature, structure, or characteristic. However, such a particular implementation can not be the only implementation to encompass the "one embodiment" or "embodiments". Other implementations of the present application can include the same feature, structure, or characteristic, or omit the same feature, structure, or characteristic.

[0024] Thirdly, the present application is described in detail in combination with the schematic diagram. In the detailed description of the embodiments of the present application, the sectional view of the device structure is partially enlarged without the general proportion for the convenience of description, and the schematic diagram is only an example, which should not limit the scope of protection of the present application. In addition, the three-dimensional spatial dimensions of length, width and depth should be included in the actual manufacture.

[0025] Referring to Figs. 1 to 5 As shown in the figure, a hybrid folding multi-rotor unmanned aerial vehicle based on hydrogen fuel proton exchange membrane technology includes an unmanned aerial vehicle body 1, which is a hydrogen-powered unmanned aerial vehicle. The unmanned aerial vehicle arm 2 has a folding part 3. The lower part of the unmanned aerial vehicle body 1 is provided with a rectangular pod 4. The bottom of the rectangular pod 4 is installed with a support plate 5, which serves as the installation basis of the unmanned aerial vehicle power system and has good bearing capacity and stability. Above the support plate 5, a hydrogen fuel stack 6 is installed, which is the core power component of the unmanned aerial vehicle and is responsible for converting hydrogen fuel into electrical energy to drive the unmanned aerial vehicle to fly. In addition, a hydrogen cylinder 7 is fixedly installed on the support plate 5, which provides continuous fuel supply for the hydrogen fuel stack 6, thereby ensuring that the unmanned aerial vehicle can operate stably for a long time. In order to further enhance the safety and stability of the unmanned aerial vehicle, a support frame 8 is designed at the bottom of the unmanned aerial vehicle body 1. The support frame 8 not only provides buffer protection for the unmanned aerial vehicle during landing, but also improves the strength and stability of the overall structure.

[0026] In this embodiment, the rectangular pod 4 includes an upper rod 9, a lower rod 10, and a cylindrical vertical connecting piece 11. The upper rod 9 and the lower rod 10 are arranged in parallel, and the upper rod 9 and the lower rod 10 are connected to the support frame 8 through the cylindrical vertical connecting piece 11. The upper rod 9 is longer than the unmanned aerial vehicle body 1, and the upper rod 9 is connected to the unmanned aerial vehicle body 1 through a first hoop 12a. The rectangular frame meets the space requirements for placing the hydrogen fuel stack 6 and the hydrogen cylinder 7, does not affect the airflow direction generated by the rotor, and simplifies the structure of the unmanned aerial vehicle.

[0027] In the embodiment, the locking hole 13 is arranged on the support plate 5, the hydrogen fuel cell stack 6 is fixedly connected with the support plate 5 through the locking hole 13, the hydrogen cylinder base 14 is fixedly connected with the support plate 5 through the locking hole 13, the hydrogen cylinder 7 is embedded and placed in the hydrogen cylinder base 14, the support plate 5 is connected with the rectangular pod lower rod 10 through the second hoop 12b, the locking hole 13 fixes the hydrogen fuel cell stack 6, and the hydrogen cylinder base 14 ensures that the hydrogen cylinder 7 is stable, so that the hydrogen fuel cell stack 6 cannot roll off during the movement of the unmanned aerial vehicle.

[0028] In the embodiment, the hollow structure is arranged below the support plate 5, the rectangular hole 15 is arranged below the hydrogen cylinder base 14, and the semicircular and rectangular combined heat dissipation hole 16 is arranged below the hydrogen fuel cell stack 6.

[0029] In the embodiment, the unmanned aerial vehicle arm 2 can be unfolded and folded through the folding piece 3, the cylindrical buffer pad 17 is embedded in the bottom of the support frame 8, the unmanned aerial vehicle is small in overall area, convenient to carry, light in weight after the unmanned aerial vehicle arm 2 is folded through the folding piece 3, and the cylindrical buffer pad 13 at the bottom of the support frame 8 can greatly reduce the landing impact force, thereby prolonging the service life of the hydrogen-powered rotor unmanned aerial vehicle.

[0030] Working principle: the hydrogen fuel cell stack 6 and the hydrogen cylinder 7 are placed in the same plane, sufficient space is left below the support plate 8, so that the hydrogen fuel cell stack 6 and the hydrogen cylinder 7 cannot be bumped when landing on the uneven ground, the frame of the rectangular pod 4 can meet the space requirement, the airflow generated by the rotor is not affected, thereby simplifying the structure of the unmanned aerial vehicle main body 1, the unmanned aerial vehicle arm 2 can be folded through the folding piece 3, the unmanned aerial vehicle is convenient to carry and light in weight. The support plate 8 is fixedly connected with the hydrogen fuel cell stack 6 and the hydrogen cylinder 7 through the locking hole 13, the hollow structure reduces the overall weight of the unmanned aerial vehicle, and is beneficial to heat dissipation of the hydrogen fuel cell stack 6, the hydrogen cylinder base 14 ensures that the hydrogen cylinder 7 is stable, so that the hydrogen fuel cell stack 6 cannot roll off during the movement of the unmanned aerial vehicle, and the cylindrical buffer pad 17 at the bottom of the support frame 8 can greatly reduce the landing impact force, thereby prolonging the service life of the hydrogen-powered rotor unmanned aerial vehicle.

[0031] The embodiment is only used to illustrate the technical scheme of the utility model and is not limited, although the utility model is described in detail with reference to the preferred embodiment, it should be understood by those skilled in the art that the technical scheme of the utility model can be modified or replaced equivalently without departing from the spirit and scope of the technical scheme of the utility model, and all should be covered in the claim range of the utility model.

Claims

1. A hybrid folding multi-copter drone, characterized by: The unmanned aerial vehicle body (1) is provided with a rectangular pod (4) at the lower part, the bottom of the rectangular pod (4) is provided with a support plate (5), the support plate (5) is installed with a hydrogen fuel stack (6) and a hydrogen cylinder (7), and the bottom of the unmanned aerial vehicle body (1) is provided with a support frame (8).

2. The hybrid folding multi-copter drone of claim 1, wherein: The rectangular pod (4) comprises an upper rod (9), a lower rod (10) and a cylindrical vertical connecting piece (11), the upper rod (9) and the lower rod (10) are arranged in parallel, and the upper rod (9) and the lower rod (10) are connected to the support frame (8) through the cylindrical vertical connecting piece (11).

3. The hybrid folding multi-copter drone of claim 2, wherein: The upper rod (9) is longer than the unmanned aerial vehicle body (1), and the upper rod (9) is connected to the unmanned aerial vehicle body (1) through a first hoop (12a).

4. The hybrid folding multi-copter drone of claim 3, wherein: Locking holes (13) are formed in the support plate (5), the hydrogen fuel stack (6) and a hydrogen cylinder base (14) are fixedly connected to the support plate (5) through the locking holes (13), the hydrogen cylinder (7) is embedded on the hydrogen cylinder base (14), and the support plate (5) is connected to the lower rod (10) through a second hoop (12b).

5. The hybrid folding multi-copter drone of claim 4, wherein: The support plate (5) is provided with a hollow structure below, the hydrogen cylinder base (14) is provided with a rectangular hole (15) below, and the hydrogen fuel stack (6) is provided with a heat dissipation hole (16) below.

6. The hybrid folding multi-copter drone of claim 1, wherein: The unmanned aerial vehicle arm (2) can be connected to the unmanned aerial vehicle body (1) through a folding piece (3).

7. The hybrid folding multi-copter drone of claim 1, wherein: The bottom of the support frame (8) is embedded with a cylindrical buffer pad (17) at both ends of the cylinder.

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