CN215794404U - Unmanned aerial vehicle - Google Patents

Abstract

The application belongs to the technical field of flight equipment, especially, relates to an unmanned aerial vehicle, and unmanned aerial vehicle includes fuselage and two at least power module, power module symmetric distribution in all sides of fuselage, power module includes fuel bottle subassembly and power component, the one end of fuel bottle subassembly connect in the fuselage, the other end of fuel bottle subassembly connect in power component, and be used for power component provides the fuel. According to the unmanned aerial vehicle, the fuel bottle assembly is used as the horn, the assembly space of the unmanned aerial vehicle is fully utilized, the original space for placing the fuel tank is released, and the unmanned aerial vehicle can carry more functional modules; on the other hand, fuel bottle subassembly and power component equipartition are in all sides of fuselage, simplify unmanned aerial vehicle balance system's the design degree of difficulty, are favorable to unmanned aerial vehicle flight in-process to remain stable.

Description

Unmanned aerial vehicle

Technical Field

This application belongs to the flight equipment field, and more specifically says, relates to an unmanned aerial vehicle.

Background

Unmanned aerial vehicle is an utilize unmanned aerial vehicle of radio remote control equipment and self program control manipulation, and unmanned aerial vehicle generally can divide into fixed wing unmanned aerial vehicle and rotor unmanned aerial vehicle according to its flight mode, and wherein, rotor unmanned aerial vehicle is owing to characteristics such as easy operation, mobility height, and the wide application is in civilian and for military use field, especially in fields such as aerial photograph, agriculture, plant protection, survey and drawing and disaster relief.

At present, unmanned aerial vehicle on the market generally adopts the lithium cell, nevertheless receives the weight of taking off of unmanned aerial vehicle, and unmanned aerial vehicle can't carry on large capacity, bulky lithium cell, and the time of endurance that leads to unmanned aerial vehicle is shorter, the unmanned aerial vehicle's that has restricted to a certain extent practicality. Fuel cell can be as a kind of power generation technology that can directly convert the chemical energy that fuel has into the electric energy, it has the characteristics of high efficiency and environmental protection, some unmanned aerial vehicles that adopt fuel cell have appeared at present, this kind of unmanned aerial vehicle generally adopts the structure of carrying on big fuel jar in the below of fuselage or top, it is great to lead to unmanned aerial vehicle to appear the volume, the big problem of the balanced system design degree of difficulty, and at the flight in-process, along with the continuous consumption of fuel, the unbalanced problem of counter weight appears in the chance of unmanned aerial vehicle, seriously influence unmanned aerial vehicle's use.

SUMMERY OF THE UTILITY MODEL

An object of the embodiment of the application is to provide an unmanned aerial vehicle to solve the unmanned aerial vehicle that exists among the prior art bulky and the technical problem that the counter weight is unbalanced easily appears.

In order to achieve the above purpose, the embodiment of the present application adopts the following technical solutions: the utility model provides an unmanned aerial vehicle, includes fuselage and two at least power module, power module symmetric distribution in week side of fuselage, power module includes fuel bottle subassembly and power component, the one end of fuel bottle subassembly connect in the fuselage, the other end of fuel bottle subassembly connect in power component, and be used for power component provides fuel.

Optionally, the fuel bottle assembly includes a fuel bottle and a fuel bottle holder having an inner cavity, the fuel bottle is disposed in the inner cavity of the fuel bottle holder, one end of the fuel bottle holder is connected to the body, and the other end of the fuel bottle holder is connected to the power assembly.

Optionally, the fuel bottle assembly further comprises a pressure regulating valve connected between the fuel bottle and the power assembly.

Optionally, the fuel bottle comprises an inner container, a connecting pipeline and a fiber layer, the fiber layer is connected to the outer side of the inner container, and the inner container is communicated with the power assembly through the connecting pipeline.

Optionally, the body includes a rack, a control main board and a communication valve, the communication valve is connected to the rack and is used for communicating with each fuel bottle assembly, the control main board is disposed inside the rack, and the control main board is electrically connected to the communication valve and is used for controlling the opening and closing of the communication valve.

Optionally, the communication valve includes a valve body and a communication channel opened in the valve body, and the oppositely disposed fuel bottle assemblies are communicated through one of the communication channels, or the fuel bottles are communicated with each other through the communication channel.

Optionally, the rack includes a rack main body and a mounting bracket, each of the fuel bottle assemblies is connected to the mounting bracket, and the mounting bracket is detachably connected to the rack main body.

Optionally, the power assembly comprises a connecting frame, a rotor, a driving motor and a fuel cell, the connecting frame is mounted at the end of the fuel bottle assembly, the driving motor is mounted on the connecting frame, and an output shaft of the driving motor is connected with the rotor and used for driving the rotor to rotate; the feed end of the fuel cell is communicated with the fuel bottle assembly, and the output end of the fuel cell is connected with the driving motor.

Optionally, the power assembly further includes a rotor bracket having an inner cavity, the rotor bracket is mounted on the connecting frame, the rotor is rotatably connected to the rotor bracket, and the driving motor is disposed in the inner cavity of the rotor bracket; the fuel cell set up in the inner chamber of rotor support, perhaps, each group power component the fuel cell set up in the fuselage to connect in parallel or establish ties each other.

Optionally, heat dissipation holes are arranged on the periphery of the rotor wing bracket.

The embodiment of the application provides an unmanned aerial vehicle's beneficial effect lies in: compared with the prior art, the unmanned aerial vehicle that this application embodiment provided utilizes fuel bottle subassembly to provide fuel for power component as the fuel jar, connects fuselage and power component as the horn through utilizing fuel bottle subassembly, for power component provides reliable support, simultaneously, fuel bottle subassembly and power component symmetric distribution are in all sides of fuselage. By the design, on one hand, the fuel bottle assembly can be used as a horn, the assembly space of the unmanned aerial vehicle is fully utilized, the original space for placing the fuel tank is released, and the unmanned aerial vehicle can carry more functional modules; on the other hand, fuel bottle subassembly and power component equipartition are in all sides of fuselage, so along with the consumption of fuel, all sides power module's of fuselage weight reduces simultaneously, and the fuselage still is in balanced state, is favorable to unmanned aerial vehicle flight in-process to remain stable, and in addition, unmanned aerial vehicle flight in-process self-balancing ability is good, need not to design complicated counter weight and balanced system, need not outside counter weight and balanced system even.

Drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed to be used in the embodiments or the prior art descriptions will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without inventive exercise.

Fig. 1 is a schematic perspective view of an unmanned aerial vehicle provided in an embodiment of the present application;

fig. 2 is a top view of an unmanned aerial vehicle provided in an embodiment of the present application;

fig. 3 is a schematic perspective view of a power assembly of the unmanned aerial vehicle provided in the embodiment of the present application;

FIG. 4 is a cross-sectional view of a fuel bottle assembly as used in an embodiment of the present application;

fig. 5 is a partial enlarged view of a portion a in fig. 4.

Wherein, in the figures, the respective reference numerals:

1. a body; 10. a frame; 11. a rack main body; 12. mounting a bracket; 2. a fuel bottle assembly; 20. a fuel bottle; 200. an inner container; 201. a straight tube portion; 202. a sealing head part; 203. a fibrous layer; 204. connecting a pipeline; 205. a seal ring; 206. a sealing groove; 207. sealing the adhesive tape; 21. a fuel bottle holder; 3. a power assembly; 30. a rotor; 31. a rotor support; 32. heat dissipation holes; 33. and a connecting frame.

Detailed Description

In order to make the technical problems, technical solutions and advantageous effects to be solved by the present application clearer, the present application is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present application and are not intended to limit the present application.

It will be understood that when an element is referred to as being "secured to" or "disposed on" another element, it can be directly on the other element or be indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or be indirectly connected to the other element.

It will be understood that the terms "length," "width," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like, as used herein, refer to an orientation or positional relationship indicated in the drawings that is solely for the purpose of facilitating the description and simplifying the 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 application. 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, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present application, "a plurality" means two or more unless specifically limited otherwise.

The various features and embodiments described in the embodiments may be combined in any suitable manner, for example, different embodiments may be formed by combining different features/embodiments, and in order to avoid unnecessary repetition, various possible combinations of features/embodiments will not be further described in this application.

Please refer to fig. 1 and fig. 2 together, the embodiment of the present application provides an unmanned aerial vehicle, including fuselage 1 and power module, power module is provided with two sets ofly at least, and the symmetric distribution is in the week side of fuselage 1, power module includes fuel bottle subassembly 2 and power component 3, the one end of fuel bottle subassembly 2 is connected in fuselage 1, the other end of fuel bottle subassembly 2 is connected in power component 3, fuel bottle subassembly 2 can be used for fuel gas such as storage hydrogen, power component 3 can use the gas in fuel bottle subassembly 2 as the fuel, provide power for unmanned aerial vehicle, compare in the unmanned aerial vehicle of lithium cell, the unmanned aerial vehicle of this embodiment can provide stronger duration, and more environmental protection. Unmanned aerial vehicle in this embodiment, the fuel bottle subassembly 2 that utilizes to be used for saving fuel gas is as unmanned aerial vehicle's horn, can make unmanned aerial vehicle under the prerequisite that has enough structural strength, and the limited assembly space of make full use of unmanned aerial vehicle has especially saved the big fuel jar that adopts among the prior art for unmanned aerial vehicle can utilize the space of release, carries on more functional module, effectively improves unmanned aerial vehicle's practicality. Simultaneously, fuel bottle subassembly 2 and the even symmetric distribution of power component 3 are in all sides of fuselage 1, when not occupying 1 space of fuselage as far as possible, need not additionally to increase the counter weight, are favorable to simplifying the design degree of difficulty of unmanned aerial vehicle balanced system, and at the in-process that unmanned aerial vehicle flies, the fuel consumption of each fuel bottle subassembly 2 is unanimous basically, make the power module weight change of 1 all sides of fuselage the same, be favorable to unmanned aerial vehicle at long-time flight in-process remain stable.

As an alternative embodiment of the present embodiment, with reference to fig. 1 and fig. 2, the main body 1 includes a frame 10, a control main board (not shown in the figure) and a communication valve (not shown in the figure), the communication valve is connected to the frame 10, the communication valve is used for communicating with each fuel bottle assembly 2, the control main board is disposed inside the frame 10 and electrically connected to the communication valve, and the control main board can be used for controlling the communication valve to open.

In the concrete application, the communicating valve can be an electromagnetic communicating valve, and the communicating valve can be opened and closed under the control of the control main board, after each fuel bottle assembly 2 is connected to the communicating valve, under the control of the control main board, the communicating valve can communicate between any group of fuel bottle assemblies 2. Such design, when unmanned aerial vehicle the remaining fuel quantity of fuel bottle subassembly 2 in flight process appearance is different (for example different power component 3 of group appear the difference because of the consumption, or fuel leakage problem etc. appears in fuel bottle subassembly 2), the control mainboard can make the remaining more fuel bottle subassembly 2 of fuel through the intercommunication valve, transmit part fuel to the remaining less fuel bottle subassembly 2 of fuel in, be favorable to each power component 3 of unmanned aerial vehicle to keep the same power, maintain the weight of each fuel bottle subassembly 2 simultaneously, be favorable to the balanced stability of unmanned aerial vehicle flight.

Specifically, as one optional implementation manner of the present embodiment, the communication valve includes a valve body and a communication passage opened in the valve body.

Illustratively, as an alternative embodiment of the communication valve of the present embodiment, the oppositely disposed fuel bottle assemblies 2 are communicated through a communication channel, such a design can enable the fuel bottle assemblies 2 located at two sides of the body 1 and distributed oppositely to maintain a communication state (referring to fig. 2, central axes of the oppositely distributed fuel bottle assemblies 2 need to be on the same straight line), so as to enable fuel margins in the communicated fuel bottle assemblies 2 to be consistent. In the specific application, at unmanned aerial vehicle flight in-process, even if the consumption of fuel is different and lead to the condition that difference appears in 2 weights of fuel bottle subassembly, also can utilize the intercommunication valve to realize automatic balance, further improve the stability of unmanned aerial vehicle flight.

Illustratively, as another alternative embodiment of the communication valve of the present embodiment, the fuel bottle assemblies 2 may communicate with each other through the communication passage of the communication valve. Such design all communicates each other through the intercommunication valve between each fuel bottle subassembly 2, forms a common "fuel cell" for each fuel bottle subassembly 2's weight can keep relatively stable, is favorable to unmanned aerial vehicle's flight stability. In a specific application, the fuel bottle assemblies 2 of the present embodiment may be uniformly distributed on the peripheral side of the body 1 (i.e., the intervals between the fuel bottle assemblies 2 are the same), or may be divided into two regions according to the distance between the fuel bottle assemblies 2, for example, the fuel bottle assembly 2 may be divided into two regions, each region may have the same number of fuel bottle assemblies 2, the interval between the two regions is relatively wide, and the intervals between the fuel bottle assemblies 2 in the regions are relatively narrow. So, can rationally divide the position of fuel bottle subassembly 2 according to unmanned aerial vehicle's practical use (for example according to its function module of carrying on), under the stable prerequisite of guaranteeing unmanned aerial vehicle flight, make unmanned aerial vehicle can more be fit for different application scenarios.

In specific application, the specific number of the fuel bottle assemblies 2 and the power assemblies 3 of the unmanned aerial vehicle can be selected according to actual requirements, and is generally an even number of groups, and preferably, the fuel bottle assemblies 2 and the power assemblies 3 can be respectively provided with two groups, four groups, six groups, eight groups and the like.

Referring to fig. 1, as an alternative embodiment of the present embodiment, the frame 10 includes a frame main body 11 and a mounting bracket 12, the mounting bracket 12 is detachably connected to the frame main body 11, and the fuel bottle assembly 2 can be mounted to the frame 10 through the mounting bracket 12. So, when unmanned aerial vehicle left unused deposit or transport, can lift fuel bottle subassembly 2 off through the installation component, separately deposit or transport with fuselage 1, be favorable to depositing and transporting of unmanned aerial vehicle, prevent that unmanned aerial vehicle from appearing the damage because of rocking in the transportation. In addition, due to the modularized design, on one hand, the fuel bottle assemblies 2 with corresponding quantity can be installed according to the duration, flying height, mileage and the like required by the unmanned aerial vehicle, so that the practicability of the unmanned aerial vehicle is improved; on the other hand, when unmanned aerial vehicle broke down, can directly change the part of damage, and need not to maintain the complete machine, was favorable to unmanned aerial vehicle's maintenance.

For example, as an alternative embodiment of the rack main body 11 and the mounting bracket 12 in the present embodiment, please refer to fig. 1, the mounting bracket 12 may be disposed above the rack main body 11, a mounting position is disposed between the rack main body 11 and the mounting bracket 12, and after the fuel bottle assembly 2 may be placed in the mounting position, the mounting bracket 12 is abutted against the rack main body 11 and is connected to the rack main body 11 through a fastener and/or a buckle, so as to complete the mounting of the fuel bottle assembly 2.

Illustratively, as another alternative embodiment of the rack body 11 and the mounting bracket 12 of the present embodiment, one end of the mounting bracket 12 may be rotatably connected to the rack body 11, and the other end of the mounting bracket 12 may mount the fuel bottle assembly 2 on the rack body 11 by means of a snap and/or fastener. A sealing structure can be arranged between the fuel bottle assembly 2 and the communicating valve, and the sealing structure can be a sealing ring, a sealing thread and the like.

Specifically, as one of them optional implementation mode of this embodiment, fuselage 1 can also include stand-by power supply, stand-by power supply can set up in the inside of frame 10, stand-by power supply's size and capacity can be less relatively, avoid taking too much space, stand-by power supply can be in fuel bottle subassembly 2 fuel consumption complete back (or when fuel bottle subassembly 2 breaks down), as emergency power supply for unmanned aerial vehicle provides the electric energy, prevent that unmanned aerial vehicle from leading to falling because of losing the electricity, improve unmanned aerial vehicle's security. For example, the standby power supply can be a lithium battery or a super capacitor, and can provide temporary power supply for the unmanned aerial vehicle.

Referring to fig. 3, as an alternative embodiment of the present embodiment, the power assembly 3 includes a connecting frame 33, a rotor 30, a driving motor (not shown), and a fuel cell (not shown), the connecting frame 33 is installed at an end of the fuel bottle assembly 2, the driving motor is installed at the connecting frame 33, the rotor 30 is connected to an output shaft of the driving motor, the driving motor can be used to drive the rotor 30 to rotate, a feed end of the fuel cell is communicated with the fuel bottle assembly 2, and an output end of the fuel cell is connected to the driving motor.

In the specific application, fuel cell can be for breathing in formula fuel cell, and fuel bottle subassembly 2 can be connected in fuel cell's positive pole, and fuel cell's negative pole can contact with the air, and through the reaction of anodal fuel (for example hydrogen) and the oxygen of negative pole, convert chemical energy into the electric energy and for the driving motor power supply, and need not to carry on the oxygen container on unmanned aerial vehicle, reduce unmanned aerial vehicle's volume.

Illustratively, as one of the optional embodiments of this embodiment, the fuel cell may be a flexible cell, the fuel cell may be designed to be a cylindrical structure, the anode of the fuel cell may be located inside, and the cathode of the fuel cell may be located outside, so that on one hand, fuel leakage may be reduced, and the utilization rate of the fuel may be improved, and on the other hand, the contact area between the cathode and the air may be increased, and the efficiency of the fuel cell may be improved.

As an alternative embodiment of the present embodiment, the power assembly 3 further includes a rotor bracket 31, the rotor bracket 31 has an inner cavity, the rotor bracket 31 is connected to the end of the fuel bottle assembly 2, and the driving motor is disposed in the inner cavity of the rotor bracket 31.

Exemplarily, as one of the optional implementation modes of this embodiment, fuel cell can set up in rotor support 31's inner chamber, so, place fuel cell and driving motor together in rotor support 31's inner chamber, be favorable to improving unmanned aerial vehicle's integrated level, reduce unmanned aerial vehicle's volume, simultaneously, fuel cell can rotate produced air current with the help of rotor 30, increase fuel cell's oxygen supply, also be favorable to fuel cell's heat dissipation.

Specifically, as one of alternative embodiments of the present embodiment, the rotor bracket 31 may be located below the rotor 30, and the circumferential side of the rotor bracket 31 is provided with heat radiation holes 32. In specific application, when the rotor 30 rotates, a large amount of airflow can be generated downwards, and the airflow can circulate inside the rotor bracket 31 through the heat dissipation holes 32, so that the fuel cell has sufficient oxygen supply, the temperature of the fuel cell and the temperature of the driving motor during operation can be reduced, and the power assembly 3 is prevented from being failed due to heat concentration.

Illustratively, as an alternative embodiment of the present embodiment, the fuel cells of each group of power assemblies 3 may also be disposed in the airframe 1, and the fuel cells may be connected in parallel or in series. Such design can be after each group power component 3's fuel cell produces the electric energy, and the unified driving motor that supplies with makes each group driving motor's power can keep relatively stable, is favorable to unmanned aerial vehicle's flight stability.

Referring to fig. 4 and 5 together, as an alternative embodiment of the present embodiment, the fuel bottle assembly 2 includes a fuel bottle 20 and a fuel bottle holder 21, the fuel bottle holder 21 has an inner cavity, and the fuel bottle 20 is disposed in the inner cavity of the fuel bottle holder 21. The fuel bottle support 21 can wrap the fuel bottle 20 to improve the structural strength of the fuel bottle assembly 2 when the fuel bottle assembly is used as a horn, and meanwhile, the fuel bottle support can also play a role in protecting the fuel bottle 20 to a certain extent.

In a specific application, the fuel bottle holder 21 may be made of a light and high-strength metal material such as an aluminum alloy, or may be made of a polymer or modified polymer material, or may be made of a material such as carbon fiber. The fuel bottle holder 21 may be integrally formed and wrapped around the fuel bottle 20, or the fuel bottle holder 21 may be divided into an upper half and a lower half, which are engaged with each other to wrap the fuel bottle 20.

Specifically, as one of them optional implementation mode of this embodiment, can be used for walking the line between fuel bottle 20 and the fuel bottle support 21 to clearance between the two can be filled with the buffering bubble cotton, and on the one hand, the buffering bubble cotton can prevent that fuel bottle 20 from rocking in fuel bottle support 21's inner chamber, improves unmanned aerial vehicle's stability, and on the other hand, the buffering bubble cotton can reduce the influence of external impact to fuel bottle 20, improves fuel bottle 20's security performance.

Specifically, as an alternative embodiment of the present embodiment, please refer to fig. 4 and 5, the fuel bottle 20 includes an inner container 200, a connecting pipe 204 and a fiber layer 203, the fiber layer 203 is connected to the outside of the inner container 200, and the connecting pipe 204 is connected to the end of the inner container 200. The fuel can be stored in the inner cavity of the inner container 200, the fiber layer 203 can improve the strength of the inner container 200, so that the inner container 200 can store the fuel with higher pressure, two groups of connecting pipelines 204 can be arranged and respectively connected to two ends of the inner container 200, one group of connecting pipelines 204 can be connected with the fuel cell, and the other group of connecting pipelines 204 can be connected with the communicating valve.

In the specific application, according to unmanned aerial vehicle's practical use and design size, can rationally select the fuel bottle 20 of different sizes, generally speaking, the external diameter of fuel bottle 20 can be less than 200mm, and length can be less than 400 mm.

Illustratively, as one optional implementation manner of this embodiment, the inner container 200 may be a resin inner container 200, the fiber layer 203 may be a carbon fiber layer 203, the inner container 200 may have a substantially cylindrical structure, and may be divided into a straight cylinder portion 201 and end enclosure portions 202 at two ends, and the straight cylinder portion 201 and the end enclosure portions 202 may be connected by a sealing structure, for example, a sealing ring 205, a sealing groove 206, a sealing tape 207, a sealing thread, and the like. The sealing head part 202 and the straight cylinder part 201 of the inner container 200 can generate break-away force which is separated from each other under the action of high-pressure fuel, and the fiber layer 203 wrapped outside the inner container 200 can tightly bind the two parts, so that under the internal pressure and the external constraint, a self-tightening effect can be generated between the sealing head part 202 and the straight cylinder part 201, and a good sealing effect can be kept between the sealing head part 202 and the straight cylinder part 201.

Specifically, as an optional implementation manner of this embodiment, the fuel bottle assembly 2 further includes a pressure regulating valve, which can be disposed in the inner cavity of the rotor bracket 31, and the pressure regulating valve is connected to the fuel bottle 20 and the power assembly 3, and can regulate the pressure when the fuel in the fuel bottle 20 is discharged, so that the fuel flows to the fuel cell at a proper pressure and flow rate, and further regulate the output current and voltage of the fuel cell, thereby improving the utilization rate of the fuel.

The embodiment of the application provides an unmanned aerial vehicle's beneficial effect lies in: compared with the prior art, the unmanned aerial vehicle that this application embodiment provided utilizes fuel bottle subassembly 2 to provide fuel for power component 3 as the fuel jar, connects fuselage 1 and power component 3 as the horn through utilizing fuel bottle subassembly 2, for power component 3 provides reliable support, simultaneously, fuel bottle subassembly 2 and power component 3 symmetric distribution are in the week side of fuselage 1. By the design, on one hand, the fuel bottle assembly 2 can be used as a horn, the assembly space of the unmanned aerial vehicle is fully utilized, the original space for placing the fuel tank is released, and the unmanned aerial vehicle can carry more functional modules; on the other hand, fuel bottle subassembly 2 and power component 3 equipartition are in all sides of fuselage 1, so along with the consumption of fuel, all sides power module's of fuselage 1 weight reduces simultaneously, and fuselage 1 still is in balanced state, is favorable to unmanned aerial vehicle flight in-process to remain stable, and in addition, unmanned aerial vehicle flight in-process self-balancing ability is good, need not to design complicated counter weight and balanced system, need not outside counter weight and balanced system even.

The above description is only exemplary of the present application and should not be taken as limiting the present application, as any modification, equivalent replacement, or improvement made within the spirit and principle of the present application should be included in the protection scope of the present application.

Claims (10)

1. The utility model provides an unmanned aerial vehicle, its characterized in that includes fuselage (1) and two at least power module, power module symmetric distribution in all sides of fuselage (1), power module includes fuel bottle subassembly (2) and power component (3), the one end of fuel bottle subassembly (2) connect in fuselage (1), the other end of fuel bottle subassembly (2) connect in power component (3), and be used for power component (3) provide fuel.

2. An unmanned aerial vehicle according to claim 1, wherein the fuel bottle assembly (2) comprises a fuel bottle (20) and a fuel bottle holder (21) having an inner cavity, the fuel bottle (20) being disposed in the inner cavity of the fuel bottle holder (21), one end of the fuel bottle holder (21) being connected to the fuselage (1), the other end of the fuel bottle holder (21) being connected to the power assembly (3).

3. The unmanned aerial vehicle of claim 2, wherein the fuel bottle assembly (2) further comprises a pressure regulating valve connected between the fuel bottle (20) and the power assembly (3).

4. The unmanned aerial vehicle of claim 2, wherein the fuel bottle (20) comprises an inner container (200), a connecting pipeline (204) and a fiber layer (203), the fiber layer (203) is connected to the outer side of the inner container (200), and the inner container (200) is communicated with the power assembly (3) through the connecting pipeline (204).

5. The unmanned aerial vehicle of claim 1, wherein the fuselage (1) comprises a frame (10), a control main board and a communication valve, the communication valve is connected with the frame (10) and is used for communicating each fuel bottle assembly (2), the control main board is arranged inside the frame (10), and the control main board is electrically connected with the communication valve and is used for controlling the opening and closing of the communication valve.

6. An unmanned aerial vehicle according to claim 5, wherein the communication valve comprises a valve body and a communication passage opened in the valve body, and the oppositely arranged fuel bottle assemblies (2) are communicated through one of the communication passages, or the fuel bottles (20) are communicated with each other through the communication passage.

7. The unmanned aerial vehicle of claim 5, wherein the chassis (10) comprises a chassis body (11) and a mounting bracket (12), each fuel bottle assembly (2) being connected to the mounting bracket (12), the mounting bracket (12) being detachably connected to the chassis body (11).

8. The unmanned aerial vehicle of any one of claims 1 to 7, wherein the power assembly (3) comprises a connecting frame (33), a rotor (30), a drive motor and a fuel cell, the connecting frame (33) is mounted at an end of the fuel bottle assembly (2), the drive motor is mounted at the connecting frame (33), an output shaft of the drive motor is connected with the rotor (30) and is used for driving the rotor (30) to rotate; the feed end of the fuel cell is communicated with the fuel bottle assembly (2), and the output end of the fuel cell is connected with the driving motor.

9. The drone according to claim 8, wherein the power assembly (3) further comprises a rotor bracket (31) having an inner cavity, the rotor bracket (31) being mounted on the connecting bracket (33), the rotor (30) being rotatably connected to the rotor bracket (31), the drive motor being disposed in the inner cavity of the rotor bracket (31); the fuel cell set up in the inner chamber of rotor support (31), perhaps, each group power component (3) the fuel cell set up in fuselage (1) to connect in parallel or establish ties each other.

10. The drone according to claim 9, characterised in that the circumferential side of the rotor bracket (31) is provided with heat dissipation holes (32).

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