Hydrogen fuel cell power stringing drone

Abstract

The application relates to the technical field of power stringing unmanned planes, in particular to a hydrogen fuel cell power stringing unmanned plane, which comprises an unmanned plane body, the unmanned plane body comprises a fuselage, a rack, a propeller and a supporting leg, the rack is arranged on the side surface of the fuselage, the propeller is arranged on the rack, and the supporting leg is arranged below the fuselage; a stringing part, the stringing part comprises a fixing rod and a pay-off part, the fixing rod is fixedly connected with the supporting leg, the fixing rod is provided with a gap section, the pay-off part comprises a supporting frame, a first pay-off roller and a second pay-off roller, the supporting frame is rotationally arranged at the gap section, and the first pay-off roller and the second pay-off roller are rotationally connected with two ends of the supporting frame; when the stringing part is wound by branches and the like, the stringing part can give a certain tension, tries to pull out the wire, and after the tension is exceeded and the wire still cannot be pulled out, the inner rod will be separated from the unmanned plane, so that the unmanned plane is prevented from being damaged.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of power stringing unmanned aerial vehicles, and particularly relates to a hydrogen fuel cell power stringing unmanned aerial vehicle. BACKGROUND

[0002] With the rapid development of power stringing unmanned aerial vehicle technologies at home and abroad, power stringing unmanned aerial vehicles are widely used in various industries. In power facility erection, power stringing unmanned aerial vehicles are also gradually widely used due to their flexibility and low cost. In recent years, the demand is growing, and the market development prospect is good.

[0003] However, because the load capacity of the power stringing unmanned aerial vehicle is limited, when the power stringing unmanned aerial vehicle is used to erect a power cable, the power stringing unmanned aerial vehicle is often entangled with the cable, suddenly bears too much tension, and causes failure or crashes, thereby causing unnecessary economic losses. SUMMARY

[0004] This section aims to summarize some aspects of the embodiments of the application and briefly introduce some preferred embodiments. Some simplifications or omissions may be made in this section and the abstract and title of the specification to avoid obscuring the purpose of this section, the abstract and the title, and such simplifications or omissions cannot be used to limit the scope of the application.

[0005] In view of the following technical problems in the prior art: the prior art cannot effectively avoid the failure or crash of the power stringing unmanned aerial vehicle caused by suddenly bearing too much tension.

[0006] To solve the above technical problems, the application provides the following technical scheme: a hydrogen fuel cell power stringing unmanned aerial vehicle, comprising,

[0007] The unmanned aerial vehicle body comprises a fuselage, a frame, a propeller and a leg, the frame is arranged on the side of the fuselage, the propeller is arranged on the frame, and the leg is arranged below the fuselage.

[0008] The stringing part comprises a fixed rod and a pay-off part, the fixed rod is fixedly connected with the leg, the fixed rod is provided with a notch section, the pay-off part comprises a support frame, a first pay-off roller and a second pay-off roller, the support frame is rotatably arranged at the notch section, and the first pay-off roller and the second pay-off roller are rotatably connected with both ends of the support frame.

[0009] As a preferred technical scheme of the hydrogen fuel cell power stringing unmanned aerial vehicle, the side of the notch section is provided with a first shaft groove, the support frame comprises two symmetrically arranged side plates and a connecting rod connecting the two side plates, the outer side of the side plate is provided with a first embedded shaft, and the first embedded shaft is embedded in the first shaft groove.

[0010] As a preferred technical scheme of the hydrogen fuel cell power stringing unmanned aerial vehicle, the inner side of the side plate is provided with a circular groove, a vertical groove and an arc groove, and the vertical groove is communicated with the circular groove and the arc groove.

[0011] As a preferred technical scheme of the hydrogen fuel cell power stringing unmanned aerial vehicle, the stringing part further comprises a moving rod, the two ends of the moving rod are provided with square rods, and a square groove is further arranged beside the vertical groove; the square rod is embedded in the square groove, and a first spring is arranged in the square groove to connect the square rod.

[0012] As a preferred technical scheme of the hydrogen fuel cell power stringing unmanned aerial vehicle, the first stringing roller comprises an outer tube and an end ring arranged at the end of the outer tube, a first through groove is arranged on the outer tube, a second through groove is arranged on the end ring, and the end ring is embedded in the circular groove.

[0013] As a preferred technical scheme of the hydrogen fuel cell power stringing unmanned aerial vehicle, the first stringing roller further comprises an inner rod and a side rod arranged at the end of the inner rod, the inner rod is arranged in the first through groove, the side rod is arranged in the second through groove, and the side rod is arranged in the circular groove; a wire binding groove is arranged on the inner rod.

[0014] As a preferred technical scheme of the hydrogen fuel cell power stringing unmanned aerial vehicle, the inner side of the outer tube is provided with a second spring connected with the side plate.

[0015] As a preferred technical scheme of the hydrogen fuel cell power stringing unmanned aerial vehicle, the second stringing roller comprises a shaft tube and a disc arranged at the two ends of the shaft tube, the shaft tube is sleeved on the connecting rod, and an expanding rod is further connected between the discs.

[0016] As a preferred technical scheme of the hydrogen fuel cell power stringing unmanned aerial vehicle, a transition curved groove is arranged on the disc, a clamping groove is arranged on the low side of the transition curved groove, the clamping groove corresponds to the arc groove, a resisting block is formed on the outer side of the clamping groove, and the resisting block corresponds to the moving rod.

[0017] As a preferred technical scheme of the hydrogen fuel cell power stringing unmanned aerial vehicle, the shaft tube and the connecting rod are connected through a torsional spring, and the torsional spring makes the resisting block contact the moving rod.

[0018] The stringing part of the present application can give a certain tension when the line is wound by branches and the like, in addition to the active control movement of the unmanned aerial vehicle, and try to pull out the line, and when the tension exceeds the tension and the line cannot be pulled out, the inner rod will be separated from the unmanned aerial vehicle, so as to avoid damage to the unmanned aerial vehicle. BRIEF DESCRIPTION OF DRAWINGS

[0019] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiments description will be briefly introduced as follows. 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 also be obtained from these drawings without any creative effort.

[0020] Figure 1 It is a schematic diagram of the overall structure of the present application.

[0021] Figure 2 It is a schematic diagram of the exploded structure of the overhead line part in the present application.

[0022] Figure 3 It is a schematic diagram of the cross-sectional structure of the overhead line part in the present application.

[0023] Figure 4 It is a schematic diagram of the structure of the support frame in the present application.

[0024] Figure 5 It is a schematic diagram of the structure of the first pay-off roller in the present application.

[0025] Figure 6 It is a schematic diagram of the structure of the winding state.

[0026] The drawings are as follows: 100, unmanned aerial vehicle body; 103, propeller; 102, rack; 101, fuselage; 200, overhead line part; 104, support leg; 201, fixed rod; 201a, notch section; 203, support frame; 203c, first embedded shaft; 201b, first shaft groove; 202, pay-off part; 203e, vertical groove; 203g, square groove; 203h, first spring; 204b, end ring; 204, first pay-off roller; 204c, first through groove; 204d, second through groove; 204f, side rod; 203d, circular ring groove; 204e, inner rod; 204g, wire binding groove; 204a, outer tube; 204h, second spring; 203a, side plate; 205, second pay-off roller; 205c, wire expanding rod; 205b, disc; 205d, transition curved groove; 203f, arc groove; 205e, clamping groove; 205f, abutting block; 206, moving rod; 205a, shaft tube; 203b, connecting rod; 300, stay wire; 205g, fixing ring; 205h, sliding ring; 205j, side ring plate; 205k, guide arc groove; 205m, radial surface. DETAILED DESCRIPTION

[0027] In order to make the above-mentioned purposes, 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 below with reference to the drawings.

[0028] In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present application. However, it will be appreciated that the present application can be practiced in a variety of ways beyond the specifics set forth herein, which can be practiced in any number of manners, and that the present application should not be limited to the methods described herein but can be practiced in any number of other ways within the spirit and scope of the present application.

[0029] Second, the "one embodiment" or "an embodiment" referred to herein means a specific feature, structure, or characteristic under discussion. The phrase "in one embodiment" does not necessarily refer to the same embodiment, although it can. The phrase "in one embodiment" is used intermittently throughout this specification to convey one feature, structure, or characteristic of different embodiments.

[0030] Third, the present application is described in detail with reference to the accompanying drawings. In the detailed description of the embodiments of the present application, the cross-sectional view of the device structure is partially enlarged without the general proportion for the convenience of explanation, 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 actual production.

[0031] Embodiment 1

[0032] Reference Figures 1-6 The embodiment provides a hydrogen fuel cell power line unmanned aerial vehicle, which comprises an unmanned aerial vehicle body 100, the unmanned aerial vehicle body 100 comprises a fuselage 101, a rack 102, a propeller 103 and a landing leg 104, the rack 102 is arranged on the side of the fuselage 101, the propeller 103 is arranged on the rack 102, and the landing leg 104 is arranged below the fuselage 101; a line mounting part 200, the line mounting part 200 comprises a fixed rod 201 and a pay-off part 202, the fixed rod 201 is fixedly connected with the landing leg 104, the fixed rod 201 is provided with a notch section 201a, the pay-off part 202 comprises a support frame 203, a first pay-off roller 204 and a second pay-off roller 205, the support frame 203 is rotationally arranged at the notch section 201a, and the first pay-off roller 204 and the second pay-off roller 205 are rotationally connected with two ends of the support frame 203 respectively.

[0033] In the present application, a hydrogen energy battery is arranged on the unmanned aerial vehicle as power. It should be noted that the hydrogen fuel cell is not improved in the present application, and the hydrogen fuel cell mentioned herein is a hydrogen fuel cell configured by the present application.

[0034] In the embodiment, the fixed rod 201 is arranged between the landing legs 104, the pull wire 300 is bound at the binding wire groove 204g on the inner rod 204e, the inner rod 204e is embedded with a positioning device, the positioning device adopts the prior art, and the positioning device is used to position the wire end when the wire end of the pull wire 300 falls off.

[0035] The notch section 201a is provided with a first shaft groove 201b on the side, the support frame 203 comprises two symmetrically arranged side plates 203a and a connecting rod 203b connecting the two side plates 203a, and the side plate 203a is provided with a first embedded shaft 203c on the outside, and the first embedded shaft 203c is embedded in the first shaft groove 201b.

[0036] The first pay-off roller 204 is used to relieve the tension on the unmanned aerial vehicle in the case that the pull line 300 is caught by a branch or the like, so as to avoid the sudden tension on the unmanned aerial vehicle and the failure caused by the insufficient reaction, the second pay-off roller 205 is used to provide a tension to the pull rope 300 to try to make the pull rope 300 disengage from the branch, if the pull rope 300 cannot disengage from the branch, the inner rod 204e will limit the rotation of the second pay-off roller 205, and the second pay-off roller 205 rotates under the pulling of the pull line 300, and when the inner rod 204e is disengaged, the unmanned aerial vehicle returns, and the position of the line head is found through the positioning device in the inner rod 204e.

[0037] Further, the rotation amount of the second pay-off roller can be monitored to enable the unmanned aerial vehicle to determine whether the inner rod 204e is disengaged.

[0038] The inner side of the side plate 203a is provided with a circular groove 203d, a vertical groove 203e and an arc groove 203f, and the vertical groove 203e communicates the circular groove 203d and the arc groove 203f.

[0039] The connecting parts of the vertical groove 203e with the circular groove 203d and the arc groove 203f are all roundly transitioned, facilitating the movement and transposition of the inner rod 204e.

[0040] The pay-off device 202 further comprises a moving rod 206, the moving rod 206 is provided with square rods at both ends, and a square groove 203g is further arranged beside the vertical groove 203e; the square rod is embedded in the square groove 203g, and the square groove 203g is provided with a first spring 203h connected with the square rod.

[0041] The square groove 203g is arranged in parallel with the vertical groove 203e, and the square groove 203g is used for limiting and guiding the moving rod 206, and the moving rod 206 is at the lower end of the square groove 203g under the pushing force of the first spring 203h in the initial state.

[0042] The first pay-off roller 204 comprises an outer tube 204a and an end ring 204b arranged at the end of the outer tube 204a, the outer tube 204a is provided with a first through groove 204c, the end ring 204b is provided with a second through groove 204d, and the end ring 204b is embedded in the circular groove 203d.

[0043] Therefore, the outer tube 204a can rotate under the limiting action of the end ring 204b, and the outer tube 204a drives the inner rod 204e to rotate together.

[0044] The first pay-off roller 204 further comprises an inner rod 204e and a side rod 204f arranged at the end of the inner rod 204e, the inner rod 204e is arranged in the first through groove 204c, the side rod 204f is arranged in the second through groove 204d, and the side rod 204f is arranged in the circular ring groove 203d; the inner rod 204e is provided with a wire binding groove 204g.

[0045] The wire end of the pull wire 300 is wound in the wire binding groove 204g, and it should be noted that a storage structure can be arranged in the wire binding groove 204g to store and hide the knot of the wire end, so as to avoid affecting the movement of the inner rod 204e, and the wire binding groove 204g itself is a storage structure, which is arranged according to actual needs.

[0046] The outer tube 204a is used for limiting the inner rod 204e.

[0047] The inner side of the outer tube 204a is provided with a second spring 204h connected with the side plate 203a.

[0048] Specifically, the inner side of the side plate 203a can be provided with a second arc groove with a central angle greater than 180°, the inner side of the outer tube 204a is provided with an extension plate extending into the second arc groove, and the second spring 204h is arranged in the second arc groove and connected with the extension plate, so that the outer tube 204a has an initial position, and when the outer tube 204a rotates, the second spring 204h is compressed, and the arrangement of the second arc groove limits the rotatable angle of the outer tube 204a, and it should be noted that the maximum rotatable angle of the outer tube 204a should be greater than 180°.

[0049] The second pay-off roller 205 comprises a shaft tube 205a and disc 205b arranged at both ends of the shaft tube 205a, the shaft tube 205a is sleeved on the connecting rod 203b, and the discs 205b are further connected with a wire expanding rod 205c.

[0050] The wire expanding rod 205c is fixedly connected with a fixed ring 205g, the fixed ring 205g is slidably connected with a sliding ring 205h, the sliding ring 205h is limited to rotate on the fixed ring 205g, and specifically, an annular groove can be arranged on the fixed ring 205g, and an embedded ring is arranged in the sliding ring 205h, the embedded ring is embedded in the annular groove to limit the sliding ring 205h, and side ring plates 205j are arranged on both sides of the outer side of the sliding ring 205h, and the side ring plates 205j are used for limiting the wire wound on the outer side of the sliding ring 205h.

[0051] The disc 205b is provided with a transition curved groove 205d, the low side of the transition curved groove 205d is provided with a clamping groove 205e corresponding to the arc groove 203f, the outer side of the clamping groove 205e forms a stop block 205f corresponding to the moving rod 206.

[0052] The transition curved groove 205d is used for transition connection from the clamping groove 205e to the stop block 205f.

[0053] The guiding arc groove 205k is arranged at the joint of the clamping groove 205e and the transition curved groove 205d, and corresponds to the vertical groove 203e when the abutting block 205f abuts against the moving rod 206, so that the inner rod 204e can enter the clamping groove 205e from the vertical groove 203e through the guiding arc groove 205k. The guiding arc groove 205k is arranged to control the moving direction of the inner rod 204e, that is, to move counterclockwise after entering the arc groove 203f when being pulled.

[0054] A radial surface 205m is arranged between the clamping groove 205e and the abutting block 205f, which is used to make the inner rod 204e disengage from the disc 205b at last.

[0055] The shaft tube 205a is connected with the connecting rod 203b through a torsional spring, the torsional spring makes the abutting block 205f contact the moving rod 206, that is, the torsional spring is charged when the disc 205b is counterclockwise rotated, and the disc 205b is clockwise rotated nearly a half circle after the moving rod 206 is removed.

[0056] In the initial state, the moving rod 206 is at the lowest end of the square groove 203g under the action of the first spring 203h, and the abutting block 205f abuts against one side of the moving rod 206.

[0057] When the line is entangled by branches and pulled, the unmanned aerial vehicle is not suddenly forced, but has a transition time, and first tries to slowly pull the line, and when it is confirmed that the line cannot be pulled out, the inner rod 204e is disengaged from the unmanned aerial vehicle to avoid damage to the unmanned aerial vehicle.

[0058] Further, referring to Figure 6 In the present application, the winding method is that the line head is fixed on the inner rod 204e, the inner rod 204e is wound between the abutting block 205f and the moving rod 206, the end of the inner rod 204e passes through the arc groove 203f, the line 300 is wound around the slip ring 205h for one turn and then drives the line 300 to be wound between the abutting block 205f and the moving rod 206 again, the inner rod 204e is moved to the first through groove 204c through the arc groove 203f and the vertical groove 203e, and then the outer tube 204a is rotated under the action of the second spring 204h, and the inner rod 204e is rotated to the top position.

[0059] At this time, after one end of the line 300 is pulled, there is a friction force between the line 300 and the slip ring 205h, the slip ring 205h will be driven to rotate, and the size of the slip ring 205h is greater than the size of the outer tube 204a, so at this time the pulling force tends to pull the inner rod 204e and drive the outer tube 204a to rotate, and the inner rod 204e enters the vertical groove, which is the first buffer setting after the line is hung, so that the unmanned aerial vehicle is not suddenly pulled.

[0060] The inner rod 204e continues to be pulled. After entering the arc groove from the vertical groove, the inner rod 204e will press the moving rod 206 upward. The disc 205b rotates clockwise without obstruction under the action of the torsion spring. During the clockwise rotation, the inner rod 204e and the pull line will have a rightward pulling force. With the drone's power remaining unchanged, this is used to try to pull the pull line off the attached object. If it can be pulled off, the torsion spring will drive the inner rod 204e to rotate, and it will not fall off and can continue to work. If the pull line cannot be pulled off, the pulling force will counteract the clockwise rotational force of the torsion spring. That is, the disc will not rotate. Instead, the pulling force will continuously increase during the drone's movement, causing the disc 205b to overcome the torsion spring and continue to rotate counterclockwise. After one rotation, the inner rod 204e will detach from the radial surface 205m.

[0061] Since the inner rod 204e needs to be disengaged by rotating the disk counterclockwise from its natural state for about one and a half turns (the exact number depends on the initial position of the disk) and then returning to its original position against the moving rod, the movement of the disk can be monitored to determine whether the inner rod, i.e. the thread end, has disengaged.

[0062] The process of pulling the string to rotate the disc 205b counterclockwise one revolution is the second buffering process of this application.

[0063] It should be noted that the moving rod 206 is initially located near the arc groove, which hinders the movement of the inner rod 204e. When the inner rod 204e moves downward, it presses the moving rod 206 upward. Specifically, when the inner rod 204e moves in the arc groove 203f, it presses the moving rod 206 upward.

[0064] It should be noted that, due to the limited weight of the 300mm pull cord, the influence of the pull cord's weight is ignored in the description. In actual applications, the weight of the pull cord is roughly calculated based on the actual pull cord material and span length, and then the spring constant is selected accordingly. The torsion spring and the second spring are calculated separately. The spring constant of the second spring does not need to be particularly large, because its design is intended to facilitate detachment for cushioning purposes.

[0065] This application does not cause the wire to detach immediately after being subjected to force, but rather buffers the tension and attempts to pull it out before causing the inner rod to detach.

[0066] It should be understood that numerous specific implementation decisions can be made during the development of any practical implementation, such as in any engineering or design project. Such development efforts may be complex and time-consuming, but for those skilled in the art who benefit from this disclosure, the development effort will be a routine work of design, manufacturing, and production without requiring much experimentation.

[0067] It should be noted that the above examples are only used to illustrate the technical solutions of the present application but not limit the present application. Although the present application is described in detail with reference to the preferred embodiments, those skilled in the art should understand that the technical solutions of the present application can be modified or equivalently replaced, without departing from the spirit and scope of the technical solutions of the present application, which should be covered in the scope of the claims of the present application.

Claims

1. A hydrogen fuel cell electric power stringing drone, characterized by: The utility model relates to a kind of unmanned aerial vehicle and its line winding device, including, Unmanned aerial vehicle body (100), the unmanned aerial vehicle body (100) includes fuselage (101), rack (102), propeller (103) and support leg (104), the rack (102) is set to fuselage (101) side, the propeller (103) is set on the rack (102), the support leg (104) is set below fuselage (101); Cable member (200), the cable member (200) includes fixed rod (201) and pay-off device (202), the fixed rod (201) is fixedly connected with support leg (104), and the fixed rod (201) is provided with gap section (201a), and the pay-off device (202) includes support frame (203), first pay-off roller (204) and second pay-off roller (205), the support frame (203) is rotationally arranged at gap section (201a), and the first pay-off roller (204) and the second pay-off roller (205) are rotationally connected with both ends of the support frame (203) respectively; First pay-off roller (204) includes outer tube (204a) and inner rod (204e), and the support frame (203) includes two symmetrically arranged side plates (203a), and the inner side of side plate (203a) is provided with vertical groove (203e) and arc groove (203f), the pay-off device (202) further includes moving rod (206), the second pay-off roller (205) is provided with abutment (205f) and slip ring (205h), the outer tube (204a) is provided with first through groove (204c), and the inner side of the outer tube (204a) is provided with second spring (204h) and is connected with the side plate (203a); Winding mode is that wire head is fixed on inner rod (204e), inner rod (204e) is wound between abutment (205f) and moving rod (206), inner rod (204e) end portion passes through arc groove (203f), and pull wire (300) is wound around slip ring (205h) after one round, and then pull wire (300) is wound around abutment (205f) and moving rod (206) again, inner rod (204e) moves to first through groove (204c) through arc groove (203f) and vertical groove (203e), then outer tube (204a) rotates under the action of second spring (204h), and inner rod (204e) is rotated to top position.

2. The hydrogen fuel cell electric power line stringing drone of claim 1, wherein: Gap section (201a) side is provided with first shaft groove (201b), and the support frame (203) includes two symmetrically arranged side plates (203a) and connecting rod (203b) connecting two side plates (203a), and the outer side of side plate (203a) is provided with first embedded shaft (203c), and the first embedded shaft (203c) is embedded in the first shaft groove (201b).

3. The hydrogen fuel cell electric power line stringing drone of claim 2, wherein: The inner side of side plate (203a) is further provided with circular groove (203d), and the vertical groove (203e) is communicated with the circular groove (203d) and arc groove (203f).

4. The hydrogen fuel cell electric power line stringing drone of claim 3, wherein: The movable rod (206) has square rods at both ends, and a square groove (203g) is provided next to the vertical groove (203e); the square rods are embedded in the square groove (203g), and a first spring (203h) is provided in the square groove (203g) to connect the square rods.

5. The hydrogen fuel cell electric power line stringing drone of claim 4, wherein: The first wire feeding roller (204) also includes an end ring (204b) disposed at the end of the outer tube (204a), the end ring (204b) being provided with a second through groove (204d), and the end ring (204b) being embedded in the annular groove (203d).

6. The hydrogen fuel cell electric power line stringing drone of claim 5, wherein: The first wire feeding roller (204) further includes a side rod (204f) disposed at the end of the inner rod (204e). The inner rod (204e) is disposed in the first through groove (204c), the side rod (204f) is disposed in the second through groove (204d), and the side rod (204f) is disposed in the annular groove (203d). A wire binding groove (204g) is provided on the inner rod (204e).

7. The hydrogen fuel cell electric power line stringing drone of claim 6, wherein: The second wire feeding roller (205) includes a shaft tube (205a) and discs (205b) disposed at both ends of the shaft tube (205a). The shaft tube (205a) is sleeved on the connecting rod (203b), and a wire expanding rod (205c) is connected between the discs (205b).

8. The hydrogen fuel cell electric power line stringing drone of claim 7, wherein: The disc (205b) is provided with a transition groove (205d), and a slot (205e) is provided on the lower side of the transition groove (205d). The slot (205e) corresponds to the arc groove (203f), and a stop block (205f) is formed on the outer side of the slot (205e). The stop block (205f) corresponds to the moving rod (206).

9. The hydrogen fuel cell electric power line stringing drone of claim 8, wherein: The shaft tube (205a) and the connecting rod (203b) are connected by a torsion spring, which causes the abutment block (205f) to contact the moving rod (206).

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