Shock-resistant folding hydrogen-powered six-rotor unmanned aerial vehicle made of composite material

Abstract

The invention provides a composite impact-resistant folding hydrogen power six-rotor unmanned aerial vehicle, and relates to the field of unmanned aerial vehicles. The folding type hydrogen power six-rotor unmanned aerial vehicle comprises a central fuselage; the six hydrogen cylinders are controlled by an air pressure valve to supply hydrogen into the central machine body; the six folding arms comprise front machine arms fixed in the circumferential direction of the central machine body and rear machine arms hinged to the front machine arms, when the folding arms are folded, the rear machine arms are folded downwards relative to the front machine arms, and hydrogen cylinders arranged in the rear machine arms can be taken and placed; the rotor wings are rotatably arranged at the tail ends of the rear vehicle arms; and the six landing supporting rods support the tail ends of the rear arms and are used for buffering ground impact during landing. The hydrogen cylinder is arranged in the rear vehicle arm, and the technical problem that a traditional hydrogen cylinder is exposed is solved. The device has the technical effects of effectively protecting the hydrogen cylinder and preventing the hydrogen cylinder from being damaged.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of unmanned aerial vehicles, in particular, to a composite impact-resistant folding hydrogen-powered six-rotor unmanned aerial vehicle. BACKGROUND

[0002] Hydrogen-powered unmanned aerial vehicles are a kind of flight platforms that use hydrogen fuel cells as the main energy source. Due to their high energy utilization efficiency and low emission pollution, they have received widespread attention in recent years. With the continuous maturity of hydrogen energy technology, such unmanned aerial vehicles have gradually been popularized in various application scenarios and shown strong potential for use. Most existing products use a multi-rotor layout, among which the six-rotor configuration is more common in actual use due to its balanced structure, moderate carrying capacity, and good control response.

[0003] Currently, common hydrogen cylinder arrangement methods in hydrogen-powered unmanned aerial vehicles include the upper hanging type and the lower hanging type. The upper hanging type usually installs the hydrogen cylinder above the fuselage, which is beneficial to releasing the space below for installing electronic equipment or task loads; while the lower hanging type sets the hydrogen cylinder at the bottom of the fuselage, which correspondingly leaves the upper space for other system configurations. However, the external hydrogen cylinder leads to an excessively large overall size of the unmanned aerial vehicle, resulting in large wind resistance, difficulty in carrying, and poor risk resistance.

[0004] Regardless of the installation method, the hydrogen cylinder is mostly in a bare state and is fixed on the unmanned aerial vehicle mainly through a strap, buckle, or frame support. However, direct exposure leads to poor impact resistance of the unmanned aerial vehicle.

[0005] Therefore, there is a need for a composite impact-resistant folding hydrogen-powered six-rotor unmanned aerial vehicle to change the installation method of directly exposing the hydrogen cylinder to solve the above technical problems. SUMMARY

[0006] The purpose of the present application is to provide a folding hydrogen-powered six-rotor unmanned aerial vehicle with a built-in hydrogen cylinder, which can solve the above-mentioned technical problems. The specific scheme is as follows:

[0007] According to the specific embodiment of the present application, the present application provides a composite impact-resistant folding hydrogen-powered six-rotor unmanned aerial vehicle, comprising:

[0008] a central fuselage;

[0009] six hydrogen cylinders controlled by a gas pressure valve to supply hydrogen into the central fuselage;

[0010] six folding arms, the folding arms including a front machine arm fixed circumferentially on the central fuselage and a rear machine arm hinged to the front machine arm, when the folding arms are folded, the rear machine arm is folded downward relative to the front machine arm, and the hydrogen cylinder built-in in the rear machine arm can be taken out or hydrogen is added;

[0011] a rotor rotatably arranged at the end of each of the rear arms;

[0012] six landing support rods supporting the ends of the rear arms to cushion the impact of landing.

[0013] further comprising a threaded fitting sleeved at the joint of the front arm and the rear arm;

[0014] when the front arm and the rear arm are docked, the front end of the threaded fitting is threaded outside the end of the front arm, and the rear end of the threaded fitting is sleeved outside the front end of the rear arm to unfold the rear arm relative to the front arm;

[0015] when the threaded fitting is moved to the rear arm to disengage the front arm, the rear arm can be folded downward relative to the front arm.

[0016] further, the upper half of the rear arm is provided with a storage space for storing the hydrogen cylinder, and the storage space further comprises a profile wrapping the hydrogen cylinder, and the profile is made of rough foamed aluminum.

[0017] further, a protective layer is arranged between the profile and the rear arm to absorb impact.

[0018] further, the protective layer adopts a negative Poisson's ratio structure and is annular as a whole, and the cross-sectional shape comprises a first inner wall, a second inner wall and a third inner wall coaxially from inside to outside; an array of inner connecting holes is arranged between the first inner wall and the second inner wall, and an array of outer connecting holes is arranged between the second inner wall and the third inner wall, the inner connecting holes and the outer connecting holes are two connected rhombic holes, and the diagonals of the two rhombic holes are located on the radial direction of the protective layer.

[0019] further, the protective layer has three layers, and the materials used from inside to outside are thermoplastic polyurethane, graphene composite material and T800 carbon fiber reinforced epoxy resin composite material respectively.

[0020] further, the landing support rod comprises:

[0021] a hollow upper cylinder, the inside of the upper cylinder is provided with an upper limit plate and a lower limit plate;

[0022] a lower cylinder, the top end of the lower cylinder is sleeved into the upper cylinder, and the bottom end of the lower cylinder is externally sleeved with a foam sleeve;

[0023] a push rod and a push disc, the bottom end of the push rod is coaxially fixed to the bottom of the lower cylinder, the top end of the push rod is slidingly inserted into the lower limit plate, and the push disc is fixed to the top end of the push rod and slidingly connected with the inner surface of the upper cylinder;

[0024] An air cushion and an upper spring, the air cushion is arranged in the upper spring, and two ends of the upper spring are abutted between a push disc and an upper limiting plate;

[0025] A lower spring, the lower spring is sleeved on the push rod, and two ends of the lower spring are respectively abutted between a bottom surface of a lower limiting plate and a bottom of the lower section cylinder.

[0026] Further, the top end of the landing support rod is hingedly connected with the rear arm at an angle of 90 degrees.

[0027] Two buckles are fixed on the rear arm, one buckle is used for fixing the landing support rod which is stored in a non-working period, and the other buckle is used for fixing the landing support rod which is perpendicular to the rear section arm in a working period.

[0028] Further, a motor is arranged in the tail end of the rear arm, the motor drives the rotation of a rotating disc, and the rotor is detachably connected with the rotating disc.

[0029] Further, the material of the rear section arm is T300 carbon fiber reinforced epoxy resin-based composite material, and the material of the cylinder body of the landing support rod is T300 carbon fiber reinforced epoxy resin-based composite material.

[0030] Compared with the prior art, the above scheme of the embodiment of the present application has at least the following beneficial effects:

[0031] The six hydrogen cylinders are placed in the foldable folding arms, which can better guarantee the safety of the hydrogen cylinders and improve the impact resistance of the unmanned aerial vehicle; the volume of the unmanned aerial vehicle can be reduced, and the unmanned aerial vehicle is more convenient to carry daily; and the influence of damage of a single hydrogen cylinder during flight can be greatly reduced. BRIEF DESCRIPTION OF DRAWINGS

[0032] The drawings incorporated into the specification and forming a part thereof show, in accordance with the embodiments of the present application, and together with the description, serve to explain the principle of the present application. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor. In the drawings:

[0033] Figure 1 A deployment structure schematic diagram of a composite material impact-resistant folding hydrogen-powered six-rotor unmanned aerial vehicle is provided for the embodiment of the present application;

[0034] Figure 2 A folding storage schematic diagram of a composite material impact-resistant folding hydrogen-powered six-rotor unmanned aerial vehicle is provided for the embodiment of the present application;

[0035] Figure 3 An internal structure schematic diagram of a rear arm is provided for the embodiment of the present application;

[0036] Figure 4 A top view of the rear arm structure of an embodiment of the present application is provided;

[0037] Figure 5 A structure diagram of one of the protective layers of an embodiment of the present application is provided;

[0038] Figure 6 An external structure diagram of the protective layer of an embodiment of the present application is provided;

[0039] Figure 7 A position structure diagram of the air pressure valve of an embodiment of the present application is provided;

[0040] Figure 8 A structure diagram of the landing support rod of an embodiment of the present application is provided;

[0041] Figure 9 A structure diagram of the rotating disc of an embodiment of the present application is provided;

[0042] Figure 10 A hinge position structure diagram of the front arm and the rear arm of an embodiment of the present application is provided;

[0043] Figure 11 An assembly structure diagram of the front arm and the rear arm of an embodiment of the present application is provided;

[0044] Figure 12 A structure diagram of the buckle of an embodiment of the present application is provided;

[0045] Figure 13 A structure diagram of the rotor of an embodiment of the present application is provided;

[0046] Figure 14 An internal structure diagram of the double shaft pin sliding connection device of an embodiment of the present application is provided;

[0047] Figure 15 A front side structure diagram of the double shaft pin sliding connection device of an embodiment of the present application is provided;

[0048] Figure 16 A left side structure diagram of the double shaft pin sliding connection device of an embodiment of the present application is provided. DETAILED DESCRIPTION

[0049] In order to make the objects, technical solutions and advantages of the present application clearer, the present application will be further described in detail below with reference to the drawings. Obviously, the described embodiments are only a part of the embodiments of the present application, but not all the embodiments. Based on the embodiments of the present application, all the other embodiments obtained by those skilled in the art without creative work fall into the scope of protection of the present application.

[0050] It is also to be understood that the terminology "include", "includes" or any other variation thereof is used inclusively and not exclusive, such that a process or device that comprises a list of elements does not include only those elements but can also include other elements not expressly listed or inherent to such process or device. An element proceeded by "comprises a" does not, without more constraints, exclude the presence of additional identical elements in the process or device that includes the recited element.

[0051] The application will be described in greater detail with reference to the accompanying drawings, in which Figures 1-16 Alternative embodiments of the application will be described in detail.

[0052] As Figure 1 shown, according to the specific embodiments of the present application, the present application provides a composite material impact-resistant folding hydrogen power six-rotor unmanned aerial vehicle, comprising: a central fuselage 1, six hydrogen cylinders 6, six foldable and openable folding arms, six rotors 8, and six landing support rods 7.

[0053] In the embodiments of the present application, each hydrogen cylinder 6 is controlled by a gas pressure valve 3 to supply hydrogen into the central fuselage 1. The folding arm comprises a front arm 2 fixed around the circumference of the central fuselage 1 and a rear arm 5 hinged to the front arm 2, the front end of the front arm 2 is fixed to the central fuselage 1, and the rear end of the front arm 2 and the front end of the rear arm 5 are hinged. When the folding arm is folded, the rear arm 5 is folded downward relative to the front arm 2, exposing an opening, and the hydrogen cylinder 6 built in the rear arm 5 can be taken out or placed in. The rotor 8 is rotatably arranged at the end of each rear arm 5. The landing support rod 7 supports the end of the rear arm 5 to buffer the impact of the ground when landing.

[0054] As Figure 1 shown, the six front arms 2 are symmetrically fixed at the six corners of the central fuselage 1, as Figure 10 shown, the rear arm 5 is connected to the front arm 2 by hinging. The rear arm 5 is hollow, and the front end has an opening for easy installation of the hydrogen cylinder. The middle part of the rear arm 5 is provided with a limiting plate, which respectively approaches the upper half of the central fuselage and the rear half of the central fuselage, and the upper half of the rear arm 5 is provided with a storage space for storing hydrogen cylinders. A plurality of hydrogen cylinders 6 are symmetrically distributed in a hexagon along the central fuselage 1, and are respectively placed in the storage space of the rear arm 5, which can be exposed after the folding arm is folded for refueling or removal.

[0055] As Figure 7As shown, the air pressure valve 3 is located in the front arm 2, and the air conveying pipes connected with the air pressure valve 3 on the front and back sides are respectively connected with the hydrogen cylinder 6 located in the rear arm 5 and the hydrogen fuel cell inside the central fuselage 1; the six air pressure valves 3 are distributed in a hexagonal symmetry along the central fuselage 1. A reasonable air pressure value range is set, and the value range set by the six air pressure valves 3 is consistent. The six air pressure valves 3 are controlled by the controller to control the air conveying amount of the hydrogen cylinder 6 in the rear arm 5 to the hydrogen fuel cell inside the central fuselage 1, so that the real-time weight of the six hydrogen cylinders 6 in the corresponding storage position is consistent when the unmanned aerial vehicle is in the working period. In this way, the tilting of the composite impact-resistant folding hydrogen-powered six-rotor unmanned aerial vehicle caused by the center of gravity during the flight process can be avoided.

[0056] The technical scheme provided by the embodiment of the present application can effectively avoid the leakage of the hydrogen cylinder 6, improve the protection level of the hydrogen cylinder, reduce the safety risk caused by single bottle damage, and is suitable for a hydrogen-powered flight platform with high requirements for safety and portability. The hydrogen cylinder is placed in the foldable arm, which can better protect the safety of the hydrogen cylinder and improve the impact resistance of the unmanned aerial vehicle; the volume of the entire unmanned aerial vehicle can be reduced, which is more convenient for daily carrying; and the influence caused by the damage of a single hydrogen cylinder during flight can be greatly reduced.

[0057] The embodiment of the present application also provides a preferred scheme, as shown in Figure 2 、 10 , 12, the present application provides a composite impact-resistant folding hydrogen-powered six-rotor unmanned aerial vehicle, which further comprises a threaded screwing part 4 sleeved at the connection position of the front arm 2 and the rear arm 5.

[0058] In the embodiment of the present application, as shown in Figure 10 , the rear arm 5 is connected to the front arm 2 by hinging, and the hinge position is located at the bottom surface of the side where the two are connected. When the front arm 2 and the rear arm 5 are connected, the front end of the threaded screwing part 4 is threadedly sleeved outside the end of the front arm 2, and the rear end of the threaded screwing part 4 is sleeved outside the front end of the rear arm 5 to unfold the rear arm 5 relative to the front arm 2.

[0059] The threaded screwing part 4 is moved to the rear arm 5 to be separated from the front arm 2, and the rear arm 5 can be folded downward relative to the front arm 2. The threaded screwing part 4 is annular as a whole, and the front part is threadedly connected outside the front arm 2, and the rear part is slidably sleeved on the rear arm 5.

[0060] The rear arm 5 is outside the front arm 2 and with the front arm 2 as a reference, the rear arm 5 can preferably rotate (60±2) degrees along the hinge connection. The threaded engagement part 4 and the rear arm 5 are coaxially engaged, and the direction of the thread is towards the front arm 2. The rear arm 5 can only be folded after the threaded engagement part 4 disengages from the thread of the front arm 2. When the front end contact surface of the rear arm 5 is in contact with the rear end contact surface of the front arm 2, docking is achieved, and the threaded engagement part 4 can be engaged with the front thread of the front arm 2.

[0061] like Figure 11 As shown, to better position the threaded engagement component 4 axially, a ring of protrusions is provided on the outside of the front arm 2 to prevent the threaded engagement component 4 from advancing. Only after the threaded engagement component 4 successfully engages with the front arm 2 will the front end face of the threaded engagement component 4 abut against the protrusion of the front arm 2. The threaded engagement component 4 is a cylindrical shape with a bottom and a through hole at the bottom for sliding engagement with the rear arm 5.

[0062] A ring of protrusions is provided near the front end of the rear arm 5, dividing the rear arm 5 into two parts with different outer diameters. The outer diameter of the part near the rear end of the rear arm 5 is smaller than that of the part near the front end. This protrusion is located inside a cylinder and slides against the inner wall of the cylinder. After the threaded engagement part 4 is successfully engaged with the front arm 2, the round bottom of the threaded engagement part 4 fits against the protrusion of the rear arm 5, restricting the axial movement of the rear arm 5.

[0063] The present invention also provides a preferred embodiment, wherein the threaded engagement part 4 is preferably a carbon fiber reinforced epoxy resin matrix composite material.

[0064] In this embodiment of the invention, the rear arm 5 is hinged to the front arm 2 to improve the folding performance and portability of the drone. The rear arm 5 has a hollow structure, internally divided into two sections. The front section, closer to the central fuselage, has a larger outer diameter, while the rear section has a smaller outer diameter, thus increasing storage space. A contact plate, or limiting plate, for supporting the hydrogen cylinder 6 is provided at the junction of the two sections. The arm is made of T300 carbon fiber reinforced epoxy resin composite material, and the diameter variation and hollow design work together to reduce structural weight, adapting to the hydrogen cylinder embedding requirements while also achieving the overall lightweight goal. Through holes are provided on the contact plate to allow wires and signal lines to pass through.

[0065] This invention also provides a preferred embodiment, such as... Figure 3 , 4 As shown, the present invention provides a composite material impact-resistant folding hydrogen-powered hexacopter drone, which also includes a profile 10.

[0066] In the embodiment of the present application, the upper half of the rear arm 5 is provided with a storage space for storing the hydrogen cylinder 6, and the storage space further comprises a profile 10 wrapped around the hydrogen cylinder 6, and the profile 10 is made of rough foamed aluminum. The hydrogen cylinder 6 is in abutment with the storage space at both axial ends.

[0067] In the embodiment of the present application, the profile 10 made of rough foamed aluminum is placed in the storage space in the rear arm 5 for storing the hydrogen cylinder 6, and the inner surface is in close contact with the hydrogen cylinder 6, and the outer surface is in close contact with the rear arm. The upper and lower surfaces of the hydrogen cylinder 6 are in close contact with the storage space. The profile 10 has six arc-shaped through holes of equal size, which are uniformly distributed along the circumference. The length of the through hole is along the axial direction of the hydrogen cylinder 6, and the through hole can be used to pass through the electric wire and signal wire. The rear arm 5 is a hollow structure, and the inside is divided into two sections, and the front section is close to the central body with a large outer diameter, and the rear section has a small outer diameter, and a contact plate for supporting the hydrogen cylinder 6 is arranged at the junction of the two sections. The contact plate is also provided with six arc-shaped through holes of equal size for passing through the electric wire and signal wire. The profile is closely attached to the hydrogen cylinder at the hydrogen cylinder placement position, which can stabilize the hydrogen cylinder and avoid violent shaking of the hydrogen cylinder during flight, and also has a certain protection function for the hydrogen cylinder. The six arc-shaped through holes of equal size on the profile can allow the electric wire and signal wire to pass through, avoiding the hydrogen cylinder and the protective layer completely occupying the arm space, which causes the line to be unable to connect the motor and the hydrogen fuel cell. The profile 10 is made of rough foamed aluminum, which can avoid the hydrogen cylinder 6 in the rear arm 5 from shaking violently during flight through friction, and also has a certain protection effect for the hydrogen cylinder 6.

[0068] The embodiment of the present application further provides a preferred scheme, in order to more stably protect the hydrogen cylinder, avoid damage, and improve the impact resistance of the unmanned aerial vehicle, such as Figures 3-6 As shown, a protective layer 9 is arranged between the profile 10 and the rear arm 5 to absorb impact. The protective layer 9 is placed in the storage space in the rear arm 5 for storing the hydrogen cylinder, and is filled between the shell of the rear arm 5 and the profile.

[0069] In the embodiment of the present application, the protective layer 9 adopts a negative Poisson's ratio structure and is annular as a whole, and the cross-sectional shape comprises a first inner wall 9.1, a second inner wall 9.2 and a third inner wall 9.3 coaxially from inside to outside; a circle of inner connecting holes is arranged between the first inner wall 9.1 and the second inner wall 9.2, and a circle of outer connecting holes is arranged between the second inner wall 9.2 and the third inner wall 9.3, the inner connecting hole and the outer connecting hole are two connected rhombic holes, and the diagonals of the two rhombic holes are located on the radial direction of the protective layer 9. The cross-sectional shape is axially stretched to obtain the annular protective layer 9. The two opposite vertices of the outer connecting hole are located on the second inner wall 9.2 and the third inner wall 9.3, and the two opposite vertices of the inner connecting hole are located on the second inner wall 9.2 and the first inner wall 9.1, and the inner and outer positions of the inner connecting hole and the outer connecting hole correspond. The adjacent inner connecting holes are spaced apart, and the adjacent outer connecting holes are spaced apart. The space between the spacing is dumbbell-shaped.

[0070] That is, the single cell of the protective layer 9 is dumbbell-shaped with arc-shaped upper and lower bottom edges, a plurality of cells are connected and uniformly distributed in the circumferential direction, and the single cell includes a common bottom edge of the inner and outer two circles. The structure of the protective layer 9 is a negative Poisson's ratio structure, and the single cell is a hollow double-taper axisymmetric honeycomb shape with circular arc-shaped upper and lower bottom edges. During compression of the protective layer 9, the internal microstructure will simultaneously undergo axial compression and transverse contraction, causing the cells to rapidly fold and interlock, forming a densified deformation state. This synergistic response mechanism can achieve uniform dispersion of stress in a shorter deformation path, effectively inhibiting the formation of shear bands. At the same time, the structure undergoes multi-stage energy dissipation during deformation, having strong impact absorption capacity; the locking action between nodes and the strain hardening of the ligament region further improve the overall compression stiffness and stability, enabling the structure to exhibit good impact resistance under dynamic impact conditions.

[0071] In the embodiment of the present application, in order to improve the protection ability of the protective layer 9, the protective layer 9 adopts a three-layer structure, and the materials from inside to outside are thermoplastic polyurethane, graphene composite material and T800 carbon fiber reinforced epoxy resin-based composite material. That is, there are three quantities of protective layers 9, and adjacent protective layers can be pasted together. That is, the material of each layer of the protective layer from inside to outside is thermoplastic polyurethane, graphene composite material and T800 carbon fiber reinforced epoxy resin-based composite material.

[0072] The embodiment of the present application also provides a preferred scheme, the outer layer of the T800 carbon fiber reinforced epoxy resin-based composite material is attached to the wall surface of the rear arm 5, the inner layer of the thermoplastic polyurethane is attached to the profile 10, and the graphene-based composite material is filled between the outer layer of the protective layer and the inner layer of the protective layer. The hydrogen cylinder 6 can be placed in the corresponding storage space and the upper half of the rear arm 5, the bottom of the cylinder touches the limiting plate, and the lower half of the rear arm 5 and the motor placement are through.

[0073] In the embodiment of the present application, the three-layer protective layer realizes a three-layer negative Poisson's ratio structure and is completely filled between the profile and the arm, thereby effectively protecting the hydrogen cylinder, avoiding damage to the hydrogen cylinder and improving the impact resistance of the unmanned aerial vehicle. The three-layer structure is fixed, and each layer adopts the cross-sectional shape described above. The application of the composite material enables the composite material impact-resistant folding hydrogen-powered six-rotor unmanned aerial vehicle to be lightweight, and the corresponding structure design can effectively protect the hydrogen cylinder, thereby improving the safety performance of the composite material impact-resistant folding hydrogen-powered six-rotor unmanned aerial vehicle.

[0074] The embodiment of the present application provides a preferred scheme, as shown in Figure 8 A composite material impact-resistant folding hydrogen-powered six-rotor unmanned aerial vehicle, the landing support rod 7 includes a hollow upper segment cylinder, a lower segment cylinder, a push rod, a push disc, an air cushion 73, an upper spring 72 and a lower spring 71.

[0075] The upper and middle positions of the interior of the upper section cylinder are provided with upper and lower limit plates. The top end of the lower section cylinder is sleeved into the upper section cylinder and is below the lower limit plate, and the bottom end of the lower section cylinder is externally sleeved with a foam sleeve. The bottom end of the push rod is coaxially fixed to the bottom of the lower section cylinder, the top end of the push rod is slidably inserted into the lower limit plate, and the push disc is fixed to the top end of the push rod and slidably connected with the inner surface of the upper section cylinder. The upper spring 72 is internally provided with an air cushion 73, and the two ends of the upper spring 72 abut between the push disc and the upper limit plate. The lower spring 71 is sleeved outside the push rod, and the two ends of the lower spring 71 abut between the bottom surface of the lower limit plate and the bottom of the lower section cylinder.

[0076] In the embodiment of the present application, the lower spring 71 realizes elastic connection between the lower section cylinder and the lower limit plate, the top end of the landing support rod 7 is fixed to the end of the rear arm 5, the rear end, and is preferably mounted to the bottom of the motor seat built in the end of the rear arm 5, and the motor seat is internally provided with a motor for driving the rotor to rotate. The landing support rod 7 is of a two-section structure, the diameter of the upper section cylinder is larger than that of the lower section cylinder, and the upper end of the lower section cylinder is sleeved into the upper section cylinder. The lower section cylinder is a hollow cylinder with a top removed, and the bottom is sleeved with a foam sleeve. The upper section cylinder is a hollow structure, and is internally provided with upper and lower limit plates. The lower spring 71 is sleeved outside the periphery of the longitudinally arranged push rod. The push disc is movable between the upper and lower limit plates, and the diameter of the push disc is larger than that of the push rod. The upper spring 72 has an air cushion in the middle, the push rod penetrates the lower limit plate from the interior of the upper section cylinder and is fixedly connected to the lower section cylinder, and the push rod and the cylinder body form a sliding fit through the push disc. The push rod and the upper section cylinder are relatively movable in the axial direction. The structure enhances the buffering performance of the support rod, is beneficial to reducing the impact of landing to the unmanned aerial vehicle body, and further protects the hydrogen cylinder. The push disc is above the lower limit plate of the upper section cylinder and is used for preventing the lower section cylinder from falling off. The push disc is connected with the upper limit plate through the upper spring 72. When the unmanned aerial vehicle lands, the lower section cylinder of the landing support rod 7 with the foam sleeve contacts the ground, causing the push rod to push upward and the lower spring 71 to contract at the same time. Then, the upper spring 72 is extruded by the push disc and contracts at the same time, and the air cushion 73 is extruded and finally buffered.

[0077] As shown in Figure 11 , a composite material impact-resistant folding hydrogen-powered six-rotor unmanned aerial vehicle, the top end of the landing support rod 7 is hingedly connected with the rear arm 5 at an angle of 90°; the landing support rod 7 can be vertical or horizontal. Two buckles are fixed on the rear arm 5, one buckle is used for fixing the landing support rod 7 which is stored during the non-working period, and the other buckle is used for fixing the landing support rod 7 which is perpendicular to the rear arm 5 during the working period.

[0078] In the embodiment of the present application, from Figure 1 , Figure 2 , Figure 11It can be seen that the landing support rod 7 can be fixed on two buckles respectively, one of which is provided with an open ring with an opening size smaller than the diameter of the landing support rod 7 and has a certain elasticity to tightly wrap the landing support rod, and the horizontal landing support rod 7 can be clamped into the ring from the opening. The ring is used to fix the vertical landing support rod 7 during the working period.

[0079] The other buckle is used to fix the landing support rod 7 stored during the non-working period, and the other buckle can also be an open ring in shape, and the vertical landing support rod 7 enters the buckle from the opening. The landing support rod 7 can be rotated by 90 degrees along the rotating shaft fixed on the rear arm 5, and the corresponding position of the rear arm 5 has a groove with a suitable shape to fit the landing support rod 7 clamped by the other buckle to achieve the purpose of stable storage.

[0080] The technical scheme provided by the embodiment of the application can flexibly change the shape of the composite impact-resistant folding hydrogen-powered six-rotor unmanned aerial vehicle, which not only ensures stable connection between parts during the working period, but also can be stored in a smaller box during the non-working period, facilitating daily carrying.

[0081] The rotating disc 11 is rotatable, and the rotating disc 11 is driven to rotate by the motor in the rear arm 5, and the rotor can be fixed on the rotating disc 11 and rotate integrally with the rotating disc 11. This technical scheme is not conducive to carrying the unmanned aerial vehicle, and the rotor and the rotating disc 11 can be detachably connected through bolts and nuts, but the following embodiments are preferred to realize detachable connection:

[0082] The embodiment of the application provides a preferred scheme, and the application also provides an embodiment connected with the first embodiment, as shown in Figure 9 A composite impact-resistant folding hydrogen-powered six-rotor unmanned aerial vehicle, a motor is arranged in the rear end of the rear arm 5, the motor drives the rotating disc to rotate, and the rotor 8 is detachably connected with the rotating disc. The rotating disc is connected with the motor in the rear arm 5.

[0083] The rotor 8 is connected with and detachable from the rotating disc at the motor of the rear arm 5, and the connection structure is a double-shaft pin sliding connection device. The rotor can be detached during the non-working period, improving the portability of the unmanned aerial vehicle. The rotor 8 is detachably fixed on the rotating disc 11 of the rear arm 5 through the double-shaft pin sliding connection device.

[0084] The rotor rotates with the rotary disc 11, but the rotor is detachably connected to the rotary disc 11. The rotary disc 11 is provided with a double shaft pin sliding connection device for detachably connecting the rotor 8, and the rotor 8 can be individually stored. The double shaft pin sliding connection device comprises a hollow rectangular fixed block 111 fixed on the top surface of the rotary disc 11, two push rods 112, two convex rods 113 and a spring. The length direction of the push rod is along the left-right direction, and a convex rod is vertically fixed in the middle of each push rod, and the push rod and the convex rod form a T shape as a whole. The two push rods are oppositely arranged and elastically connected by the spring between the two push rods, and the two convex rods are located outside the two push rods. The spring is located in the inside of the rectangular fixed block 111, and a circular through hole is formed in the front-rear direction of the rectangular fixed block 111, and the two convex rods slide out of the inside of the rectangular fixed block 111. By pressing the two convex rods, the spring is compressed, and the relative distance between the two push rods can be changed. Long circular through holes are formed in the left-right direction of the rectangular fixed block, and one push rod is arranged at the two ends of each through hole, and the two ends of the push rod are arranged to pass through the through hole and protrude. The middle part of the bottom surface of the rotor 8 is a rectangular plate, and four L-shaped plates are fixed below the rectangular plate, and the four L-shaped plates are oppositely arranged in front of each other, and form a right-angled hook shape below the rotor 8.

[0085] The left-right direction outside of the end of each push rod outside the rectangular fixed block 111 is hooked by the L-shaped plate, the top surface of the rectangular fixed block 111 is attached to the rectangular plate, and the rectangular fixed block 111 limits the downward movement of the rotor; the left-right spacing of the four L-shaped plates is equal to the left-right width of the rectangular fixed block 111, and the rectangular fixed block 111 limits the left-right movement of the L-shaped plate; the outside of the end of each push rod outside the rectangular fixed block 111 is hooked by the L-shaped plate, and the four L-shaped plates are limited in the front-rear direction by the push rod. Pressing the two convex rods in the front-rear direction of the double shaft pin sliding connection device can control the distance between the left and right push rods to be smaller, and the L-shaped plate is separated from the hook. The minimum spacing of the L-shaped plate in the front-rear direction is greater than the diameter of the two push rods, so that the push rod can be separated from the L-shaped plate, and at the same time the convex rod is retracted into the inside of the rectangular fixed block 111, and the rectangular plate moves upward to separate from the rectangular fixed block 111.

[0086] The application provides a preferred scheme, the material of the rear arm 5 is T300 carbon fiber reinforced epoxy resin based composite material, and the barrel body material of the landing support rod 7 is T300 carbon fiber reinforced epoxy resin based composite material. The application of the composite material makes the composite material impact-resistant folding hydrogen-powered six-rotor unmanned aerial vehicle lightweight, and the corresponding structure design can effectively protect the hydrogen cylinder, so that the safety performance of the composite material impact-resistant folding hydrogen-powered six-rotor unmanned aerial vehicle is improved.

[0087] It should be noted that the various embodiments described in the specification are intended to be illustrative only and are not in any way limiting. Although the present application has been described in considerable detail, various modifications and changes can be made to the present application by one skilled in the art and it is understood that the application is not limited by the embodiments described herein. Accordingly, the specification and figures are to be regarded in an illustrative manner and contributions to the art are to be measured only in terms of the patentability of the claims and their equivalents.

[0088] The above embodiments are only used to illustrate the technical solutions of the present application, but not limit the present application. Although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that the technical solutions recorded in the foregoing embodiments can be modified, or some technical features can be replaced by equivalent features. The modification or replacement does not make the essence of the corresponding technical solution deviate from the spirit and scope of the technical solutions of the embodiments of the present application.

Claims

1. A composite impact-resistant foldable hydrogen-powered hexa-copter drone, characterized in that, It comprises: a central body (1); six hydrogen cylinders (6) controlled by air pressure valves (3) to supply hydrogen into the central body (1); six folding arms, which comprise front arms (2) fixed circumferentially on the central body (1) and rear arms (5) hinged to the front arms (2), the rear arms (5) being folded downward relative to the front arms (2) when the folding arms are folded, and the hydrogen cylinders (6) being taken out or filled with hydrogen inside the rear arms (5); rotors (8) rotatably arranged at the ends of each of the rear arms (5); six landing support rods (7) supporting the ends of the rear arms (5) to buffer the impact of landing on the ground.

2. The composite impact-resistant foldable hydrogen-powered hexa-copter UAV of claim 1, wherein, It also comprises a threaded screwing piece (4) sleeved at the joint of the front arms (2) and the rear arms (5); when the front arms (2) and the rear arms (5) are connected, the front end of the threaded screwing piece (4) is threadedly sleeved outside the end of the front arm (2), and the rear end of the threaded screwing piece (4) is sleeved outside the front end of the rear arm (5) to unfold the rear arm (5) relative to the front arm (2); when the threaded screwing piece (4) is moved to the rear arm (5) to be separated from the front arm (2), the rear arm (5) can be folded downward relative to the front arm (2).

3. The composite impact-resistant foldable hydrogen-powered hexa-copter drone of claim 1, wherein, The upper half of the rear arm (5) is provided with a storage space for storing the hydrogen cylinders (6), and the storage space further comprises a profile (10) wrapping the hydrogen cylinders (6), and the material of the profile (10) is rough foamed aluminum.

4. The composite impact-resistant foldable hydrogen-powered hexa-copter drone of claim 3, wherein, A protective layer (9) is arranged between the profile (10) and the rear arm (5) to absorb impact.

5. The composite impact-resistant foldable hydrogen-powered hexa-copter drone of claim 4, wherein, The protective layer (9) adopts a negative Poisson's ratio structure and is annular as a whole, and the cross-sectional shape comprises coaxial first, second and third inner walls from inside to outside; a circle of inner connecting holes is arranged between the first and second inner walls, and a circle of outer connecting holes is arranged between the second and third inner walls, the inner and outer connecting holes are two connected rhombic holes, and the diagonals of the two rhombic holes are on the radial direction of the protective layer (9).

6. The composite impact-resistant foldable hydrogen-powered hexa-copter drone of claim 4, wherein, The protective layer (9) has three, and the materials adopted from inside to outside are thermoplastic polyurethane, graphene composite material and carbon fiber reinforced epoxy resin-based composite material respectively.

7. The composite impact-resistant foldable hydrogen-powered hexa-copter UAV of claim 1, wherein, The landing support rod (7) comprises: a hollow upper section cylinder, the inside of which is provided with upper and lower limit plates; a lower section cylinder, the top end of which is sleeved into the upper section cylinder, and the bottom end of which is externally sleeved with a foam sleeve; a push rod and a push disc, the bottom end of the push rod being coaxially fixed on the bottom of the lower section cylinder, the top end of the push rod slidingly extending into the lower limit plate, and the push disc being fixed on the top end of the push rod and slidingly connected with the inner surface of the upper section cylinder; an air cushion (73) and an upper spring (72), the air cushion (73) being arranged in the upper spring (72), and the two ends of the upper spring (72) abutting between the push disc and the upper limit plate; A lower spring (71) is sleeved outside the push rod, and two ends of the lower spring (71) are respectively abutted between the bottom surface of the lower limiting plate and the cylinder bottom of the lower section cylinder.

8. The composite impact-resistant foldable hydrogen-powered hexa-copter drone of claim 7, wherein, The top end of the landing support rod (7) is hingedly connected with the rear machine arm (5) at an angle of 90°. Two buckles are fixed on the rear machine arm (5), one buckle is used for fixing the landing support rod (7) which is stored in the non-working period, and the other buckle is used for fixing the landing support rod (7) which is perpendicular to the rear machine arm (5) in the working period.

9. The composite impact-resistant foldable hydrogen-powered hexa-copter UAV of claim 1, wherein, A motor is arranged in the tail end of the rear machine arm (5), the motor drives the rotation of a rotary disc, and the rotary wing (8) is detachably connected with the rotary disc.

10. The composite impact-resistant foldable hydrogen-powered hexa-copter UAV of claim 1, wherein, The material of the rear machine arm (5) is carbon fiber reinforced epoxy resin based composite material, and the material of the cylinder body of the landing support rod (7) is carbon fiber reinforced epoxy resin based composite material.

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