Gas cylinder mounting structure of unmanned aerial vehicle and hydrogen energy unmanned aerial vehicle

Abstract

The application discloses a gas cylinder mounting structure of a hydrogen energy unmanned aerial vehicle, and the hydrogen energy unmanned aerial vehicle, wherein the gas cylinder mounting structure comprises a fuselage, a hatch cover, a connecting rod mechanism, a locking and unlocking mechanism and a movable clamp; the fuselage is internally provided with a cabin for accommodating a gas cylinder, the hatch cover can be opened and closed to the cabin, the hatch cover and the movable clamp in the cabin are synchronously linked through the connecting rod mechanism, and the hatch cover and the movable clamp correspond to opening and closing stations and clamping and releasing stations respectively, and the locking and unlocking mechanism is matched to lock the hatch cover. When the hatch cover is closed, the movable clamp synchronously encircles and fixes the gas cylinder; when the hatch cover is opened, the movable clamp synchronously releases the gas cylinder, and the gas cylinder can be directly taken out and placed. According to the scheme, the hatch cover and the clamp are linked and integrated, the rolling and clamping fastening process is omitted, the gas cylinder dismounting and mounting operation is simplified, the maintenance efficiency is improved, the encircling and fixing mode can avoid flight sliding of the gas cylinder, and the mounting stability is improved.

Description

Technical Field

[0001] This invention relates to the field of hydrogen energy storage installation technology for drones, specifically to the gas cylinder installation structure for drones and hydrogen-powered drones. Background Technology

[0002] Hydrogen-powered drones use high-pressure hydrogen cylinders as their power source, offering advantages such as long endurance, rapid refueling, and zero emissions, making them widely applicable in long-endurance operation scenarios. Currently, the hydrogen cylinders used in hydrogen-powered drones mostly employ an aluminum alloy inner liner and a composite material winding structure. The outer wall of the cylinder is smooth and lacks a dedicated fixing interface. Installation and fixing inside the drone are primarily achieved through methods such as strapping and metal clamps, making disassembly and assembly of the hydrogen cylinder inconvenient. Furthermore, the existing installation method has the following drawbacks:

[0003] The insufficient constraint and limiting ability between the rolling strip and the smooth bottle body makes the bottle body prone to axial movement or circumferential slippage when the UAV is in a high-maneuver, high-attitude flight condition, which causes the center of gravity of the whole machine to shift, directly affecting flight stability and flight safety.

[0004] When using metal clamps in conjunction with screws for fastening, on the one hand, the sharp metal edges of the clamps can easily scratch the composite material surface of the tank, causing surface structural defects and weakening the tank's pressure resistance; on the other hand, the force of screw fastening is difficult to control precisely, and excessive fastening force will apply additional compressive load to the high-pressure tank, posing a safety risk of damage to the tank structure. Summary of the Invention

[0005] To address the aforementioned problems and overcome at least one deficiency, this invention proposes a gas cylinder mounting structure for drones and a hydrogen-powered drone.

[0006] The technical solution adopted in this invention is as follows: A gas cylinder mounting structure for a drone includes a fuselage, a canopy, a linkage mechanism, a locking and unlocking mechanism, and a movable clamp. The fuselage is equipped with a cabin for accommodating gas cylinders; The hatch is rotatably mounted on the fuselage and is used to open and close the cabin. The hatch has an opening position and a closing position. The locking and unlocking mechanism is located between the hatch and the fuselage and is used to lock the hatch in the closed position or unlock it. The movable clamp is rotatably mounted inside the engine compartment, and the movable clamp is synchronously linked with the hatch via the linkage mechanism. The movable clamp has a clamping position and a releasing position. When the hatch is in the closed position, the movable clamp is simultaneously in the clamping position, encircling and fixing the gas cylinder inside the engine room; When the hatch is in the open position, the movable clamp is simultaneously in the release position, releasing the constriction on the gas cylinder, allowing the gas cylinder to be removed or loaded into the engine room.

[0007] The hatch cover and movable clamp of this application are linked synchronously through a linkage mechanism. The process of opening and closing the hatch cover can simultaneously complete the surrounding fixation and release of the gas cylinder, eliminating the need for additional operations such as strapping and screw tightening. This greatly simplifies the gas cylinder installation and disassembly process and significantly improves the efficiency of daily maintenance and gas cylinder replacement.

[0008] This application integrates the functions of the movable clamp, hatch opening and closing, and locking, eliminating the need to design a large number of dedicated limiting structures on the inner wall of the fuselage, reducing the weight of redundant structures, and adapting to the lightweight design requirements of UAVs.

[0009] In practical use, the hatch is rotatably mounted on the fuselage via a hinge assembly. The hinge assembly includes a fixed hinge, a rotating hinge, and a hinge shaft connecting the fixed hinge and the rotating hinge. The fixed hinge and the rotating hinge are respectively fixed to the fuselage and the hatch.

[0010] The gas cylinders mentioned in this application are used to store fuel, particularly green fuels such as hydrogen.

[0011] In one embodiment of the present invention, the body has an mounting plate and a support plate, the mounting plate has a limiting port that cooperates with the gas cylinder, and the support plate is located below the mounting plate and directly opposite the limiting port.

[0012] The limiting port of the mounting plate forms a radial constraint on the gas cylinder, while the support plate below forms an axial support on the bottom of the gas cylinder. The displacement of the gas cylinder is restricted from two dimensions. Combined with the movable clamp, the stability of the gas cylinder installation can be further enhanced, eliminating the risk of movement during flight.

[0013] In one embodiment of the present invention, a clamp mounting base is further included, the clamp mounting base being detachably mounted on the mounting plate, and the movable clamp being rotatably mounted on the clamp mounting base.

[0014] The movable clamp is a detachable structure, allowing for the replacement of different sizes of movable clamps to accommodate gas cylinders of varying volumes. This significantly improves the compatibility of the installation structure with gas cylinders of multiple sizes, resolving the shortcomings of existing drones that struggle to be compatible with gas cylinders of different volumes.

[0015] In one embodiment of the present invention, one side of the movable clamp is a working surface and the other side is a non-working surface. The non-working surface of the movable clamp has a limiting boss. When the movable clamp is in the release position, the limiting boss abuts against the mounting plate.

[0016] When the hatch is opened to its maximum angle (opening position), the limiting boss abuts against the mounting plate, limiting the maximum rotation angle of the movable clamp.

[0017] In one embodiment of the present invention, the working surface of the movable clamp has a flexible layer.

[0018] The flexible layer on the working surface allows the clamp to make flexible contact with the gas cylinder, which not only avoids the rigid structure from scratching the surface of the composite material tank and protects the integrity of the gas cylinder's pressure-resistant structure, but also increases the contact friction, further suppressing cylinder slippage and improving clamping stability.

[0019] The flexible layer can buffer vibration and impact during flight, disperse local clamping pressure, and reduce the risk of high-pressure tank being damaged by compression.

[0020] In one embodiment of the present invention, the linkage mechanism includes: The zigzag connecting rod has a first rocker arm, a drive shaft, and a second rocker arm. The zigzag connecting rod is rotatably mounted on the mounting plate via the drive shaft. The first connecting rod has one end hinged to the movable clamp and the other end hinged to the first rocker arm; The second link is hinged at one end to the second rocker arm and at the other end to the hatch.

[0021] The linkage mechanism of this application can smoothly and accurately convert the opening and closing rotation of the hatch into the rotation of the movable clamp. The transmission path is clear, the movement of the hatch and the clamp is highly synchronized, and the operation is smooth without jamming.

[0022] The zigzag connecting rod achieves motion reversal through the drive shaft, which can convert the rotation of the canopy side into the radial clamping action of the clamp inside the cabin. The structure is compact and adaptable to the narrow installation space inside the fuselage, with high space utilization.

[0023] In practical applications, preferably, the first connecting rod is hinged to the movable clamp via a pin, and can be quickly and easily disassembled and installed.

[0024] In one embodiment of the present invention, the linkage mechanism further includes a fixing seat fixed on the mounting plate, the fixing seat having a shaft hole; Of the first rocker arm and the second rocker arm, one has a mounting hole and the other has the drive shaft fixed thereon. The first rocker arm and the second rocker arm are located on opposite sides of the shaft hole, and one end of the drive shaft passes through the shaft hole and is inserted into the mounting hole and fixed thereon.

[0025] The fixed base provides stable rotational support for the drive shaft, improves the overall operating rigidity of the bend connecting rod, avoids radial wobble during transmission, ensures stable transmission torque, and improves the linkage accuracy between the hatch and the clamp. The rocker arm and drive shaft adopt a separate plug-in assembly form, which simplifies the processing technology, facilitates assembly, and allows for easy production assembly and individual component replacement, thereby reducing manufacturing costs.

[0026] In one embodiment of the present invention, the fuselage has reinforcing frames at both ends of the cabin; The hatch equipped with a locking and unlocking mechanism has a strip-shaped through-hole; The locking and unlocking mechanism includes: A multi-functional connecting seat is fixed to the inside of the hatch and has a sliding groove; the second connecting rod is hinged to the multi-functional connecting seat. An unlocking paddle is slidably mounted in the slide groove, and the unlocking paddle has an operating part that extends outward through a strip-shaped through-hole; The locking seat, fixed to the reinforcing frame, has a lock hole; The latch seat is fixed to the inside of the hatch cover; The pin is slidably installed in the pin holder, and the end of the pin extending out of the pin holder has a guide slope. A spring, located inside the pin holder, engages with the pin to give it a tendency to move outward. The guide tube is located between the pin socket and the multi-functional connector. A control cable is threaded through the guide tube, with one end connected to the unlocking lever and the other end connected to the pin. During the hatch closing process, the guide ramp of the latch automatically retracts under the pressure of the fuselage. When the hatch is closed in place, the latch extends into the lock hole under the action of the spring to complete the automatic locking. When the pin is inserted into the lock hole and is in the locked state, pressing the operating part can drive the unlocking lever to slide. The unlocking lever drives the pin to move into the pin seat through the control cable, and the pin disengages from the lock hole, thus completing the unlocking.

[0027] The canopy employs a flexible transmission unlocking structure consisting of an unlocking lever, control cable, and pin. Unlocking is quick and easy, requiring only the movement of the operating part on the outside of the canopy. The pin, in conjunction with a guide ramp and a return spring, automatically retracts and locks when the canopy is closed, eliminating the need for manual locking and significantly improving canopy opening and closing efficiency. A guide tube guides and protects the control cable, ensuring smooth cable transmission, preventing cable wear and jamming, and enhancing the long-term reliability of the unlocking mechanism. The locking seat is mounted on a reinforced frame, increasing the structural strength of the locking area, ensuring a secure and reliable lock that is less prone to loosening due to vibration during flight. The multi-functional connector integrates both linkage hinge and unlocking slide functions, offering high integration, simplifying the internal structural layout of the canopy, and reducing the number of parts.

[0028] In one embodiment of the present invention, one hatch is provided on the left and one on the right, the two hatches being a first hatch and a second hatch, and the locking and unlocking mechanism is provided between the second hatch and the fuselage; The outer end of the first hatch away from its own axis of rotation has a splicing edge. When the cabin is closed, the first hatch closes before the second hatch. When the second hatch closes, it presses against the splicing edge of the first hatch. When the second hatch is locked by the locking and unlocking mechanism, the first hatch is locked synchronously. Each hatch is provided with at least two sets of linkage mechanisms arranged at intervals along the front and rear directions. The locking and unlocking mechanisms are provided with two sets, one in front and one in back. The locking seat of one set of locking and unlocking mechanisms is fixed to the reinforcing frame on the front side of the fuselage, and the locking seat of the other set of locking and unlocking mechanisms is fixed to the reinforcing frame on the rear side of the fuselage.

[0029] The dual-hatched structure, opening from both sides, provides a wide operating range for the engine compartment, offering ample space for loading and unloading gas cylinders and significantly improving the ease of installation and replacement of large-sized cylinders. The locking and unlocking mechanism is only located on the second hatch; by pressing the edge of the first hatch together when closed, both hatches lock simultaneously. This eliminates the need for separate locking and unlocking mechanisms on each side, simplifying the structural design, reducing the number of parts, and contributing to lower structural weight and manufacturing costs.

[0030] Each hatch is equipped with two sets of linkage mechanisms and locking mechanisms at the front and rear, which makes the force on the hatch opening and closing more balanced, the clamping force of the movable clamp on the gas cylinder more evenly distributed, the locking synchronization of the front and rear ends is good, and the overall structural stability and locking reliability are significantly improved.

[0031] This application also discloses a hydrogen-powered drone, including the gas cylinder mounting structure of the drone described above.

[0032] The beneficial effects of this invention are as follows: The hatch and movable clamp are synchronously linked through a linkage mechanism, allowing the gas cylinder to be simultaneously secured and released during the opening and closing of the hatch. This eliminates the need for additional operations such as strapping and tightening screws, significantly simplifying the gas cylinder installation and disassembly process and greatly improving the efficiency of daily maintenance and gas cylinder replacement. This invention integrates the movable clamp, hatch opening / closing, and locking functions, eliminating the need for numerous dedicated limiting structures on the inner wall of the fuselage, reducing redundant structural weight, and adapting to the lightweight design requirements of UAVs. Attached Figure Description

[0033] Figure 1 This is a schematic diagram of a hydrogen-powered drone with its hatch closed. Figure 2 yes Figure 1 Enlarged view of point A in the middle; Figure 3 This is a schematic diagram of a hydrogen-powered drone with its hatch in the open position. Figure 4 This is a schematic diagram of a hydrogen-powered drone with its hatch in the open position and equipped with gas cylinders. Figure 5This is a partial schematic diagram showing the hatch in the closed position and the movable clamps simultaneously in the tightened position; Figure 6 yes Figure 5 Enlarged view of point B in the middle; Figure 7 This is a cross-sectional view of the hydrogen-powered drone with the hatch in the open position. Figure 8 This is a cross-sectional view of the hydrogen-powered drone with the hatch in the closed position. Figure 9 yes Figure 7 Enlarged view of point C in the middle; Figure 10 yes Figure 8 Enlarged view of point D in the middle; Figure 11 It is a sectional view of the mounting plate, clamp mounting base, and fixing base; Figure 12 This is a partial cross-sectional view of the locking and unlocking mechanism when the pin extends into the keyhole; Figure 13 This is a cross-sectional schematic diagram of the control cable and unlocking lever; Figure 14 This is a diagram of the multi-functional connector and the unlocking lever.

[0034] The labels for the attached figures are as follows: 1. Fuselage; 11. Cabin; 12. Reinforcing frame; 13. Mounting plate; 131. Limiting port; 14. Support plate; 2a. First hatch cover; 21a. Splicing edge; 2b. Second hatch cover; 21b. Strip-shaped through-hole; 3. Linkage mechanism; 31. Bending link; 311. First rocker arm; 312. Drive shaft; 313. Second rocker arm; 3131. Mounting hole; 32. First link; 33. Second link; 34. Fixing seat; 341. Shaft hole; 4. Locking and unlocking mechanism ; 41. Multifunctional connecting seat; 411. Slide groove; 42. Unlocking lever; 421. Operating part; 43. Locking seat; 431. Lock hole; 44. Pin seat; 45. Pin; 451. Guide slope; 46. Spring; 47. Guide tube; 48. Control cable; 5. Movable clamp; 51. Working surface; 52. Non-working surface; 521. Limiting boss; 6. Clamp mounting seat; 7. Gas cylinder; 8. Hinge assembly; 81. Fixed hinge; 82. Rotating hinge; 83. Hinge shaft. Detailed Implementation

[0035] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. The components of the embodiments of this application described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0036] In the description of this application, it should be noted that the terms "inner" and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product is in use. They are used only for the convenience of describing this application and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application. Furthermore, the terms "first," "second," etc., are used only to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0037] In the description of this application, it should also be noted that, unless otherwise expressly specified and limited, the terms "setup" and "connection" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0038] The present invention will now be described in detail with reference to the accompanying drawings.

[0039] like Figure 1 , Figure 3 and Figure 4 As shown, this application discloses a hydrogen-powered drone, including a gas cylinder 7 mounting structure for the drone. The term "hydrogen-powered drone" in this application is general and not limited to hydrogen energy; other green fuels are also acceptable.

[0040] like Figures 1-14 As shown, the gas cylinder 7 mounting structure of the UAV includes a fuselage 1, a first hatch 2a, a second hatch 2b, a linkage mechanism 3, a locking and unlocking mechanism 4, and a movable clamp 5; See Figure 3 and Figure 4 The fuselage 1 is equipped with a cabin 11, which is used to accommodate gas cylinders 7; See Figure 1 and Figure 4 The first hatch 2a and the second hatch 2b are both rotatably mounted on the fuselage 1 and used to open and close the cabin 11. The hatches have an opening position and a closing position. See Figure 3 and Figure 4 The locking and unlocking mechanism 4 is located between the second hatch 2b and the fuselage 1, and is used to lock the second hatch 2b in the closed position or unlock it. See Figure 3 , Figure 4 and Figure 5The movable clamp 5 is rotatably installed inside the engine compartment 11, and the movable clamp 5 is synchronously linked with the hatch cover through the linkage mechanism 3. The movable clamp 5 has a clamping position and a releasing position. See Figure 1 , Figure 8 and Figure 10 When the hatch is in the closed position, the movable clamp 5 is simultaneously in the clamping position, encircling and fixing the gas cylinder 7 inside the engine room 11. See Figure 4 , Figure 7 and Figure 9 When the hatch is in the open position, the movable clamp 5 is simultaneously in the release position, releasing the restraint on the gas cylinder 7, so that the gas cylinder 7 can be taken out or put into the engine room 11.

[0041] The hatch cover and the movable clamp 5 of this application are linked synchronously through the linkage mechanism 3. The process of opening and closing the hatch cover can simultaneously complete the circumferential fixation and release of the gas cylinder 7, eliminating the need for additional operations such as strapping and screw tightening. This greatly simplifies the installation and disassembly process of the gas cylinder 7 and significantly improves the efficiency of daily maintenance and gas cylinder 7 replacement.

[0042] This application integrates the functions of the movable clamp 5, hatch opening and closing, and locking, eliminating the need to design a large number of dedicated limiting structures on the inner wall of the fuselage 1, reducing the weight of redundant structures, and adapting to the lightweight design requirements of UAVs.

[0043] In actual use, the hatch is rotatably mounted on the fuselage 1 via the hinge assembly 8. The hinge assembly 8 includes a fixed hinge 81, a rotating hinge 82, and a hinge shaft 83 connecting the fixed hinge 81 and the rotating hinge 82. The fixed hinge 81 and the rotating hinge 82 are respectively fixed on the fuselage 1 and the hatch.

[0044] The gas cylinder 7 mentioned in this application is used to install fuel, particularly green fuels such as hydrogen.

[0045] In practical applications, the locking and unlocking mechanism 4 can also be simultaneously located between the first hatch 2a and the fuselage 1.

[0046] like Figure 3 and Figure 5 In one embodiment, the body 1 has a mounting plate 13 and a support plate 14. The mounting plate 13 has a limiting port 131 that cooperates with the gas cylinder 7. The support plate 14 is located below the mounting plate 13 and directly opposite the limiting port 131.

[0047] The limiting port 131 of the mounting plate 13 forms a radial constraint on the gas cylinder 7, and the lower support plate 14 forms an axial support on the bottom of the gas cylinder 7. The displacement of the gas cylinder 7 is restricted from two dimensions. Combined with the movable clamp 5, the stability of the gas cylinder 7 installation can be further enhanced, and the risk of movement during flight can be eliminated.

[0048] like Figure 11 In one embodiment, the device further includes a clamp mounting base 6, which is detachably mounted on the mounting plate 13, and the movable clamp 5 is rotatably mounted on the clamp mounting base 6.

[0049] The movable clamp 5 is a detachable structure, and different specifications of movable clamp 5 can be replaced to adapt to gas cylinders 7 of different volumes. This significantly improves the adaptability of the installation structure to gas cylinders 7 of multiple sizes and solves the defect of existing drones being unable to be compatible with gas cylinders 7 of different volumes.

[0050] like Figure 6 and Figure 11 As shown, in one embodiment, one side of the movable clamp 5 is a working surface 51 and the other side is a non-working surface 52. The non-working surface 52 of the movable clamp 5 has a limiting boss 521. When the movable clamp 5 is in the release position, the limiting boss 521 abuts against the mounting plate 13.

[0051] When the hatch is opened to its maximum angle (opening position), the limiting boss 521 abuts against the mounting plate 13, limiting the maximum rotation angle of the movable clamp 5.

[0052] In one embodiment, the working surface 51 of the movable clamp 5 has a flexible layer.

[0053] The flexible layer of the working surface 51 allows the clamp to form a flexible contact with the gas cylinder 7, which not only avoids the rigid structure from scratching the surface of the composite material tank and protects the integrity of the pressure-resistant structure of the gas cylinder 7, but also increases the contact friction, further suppresses the slippage of the cylinder and improves the clamping stability.

[0054] The flexible layer can buffer vibration and impact during flight, disperse local clamping pressure, and reduce the risk of high-pressure tank being damaged by compression.

[0055] like Figures 6-10 As shown in the figure, in one embodiment, the linkage mechanism 3 includes: The zigzag connecting rod 31 has a first rocker arm 311, a drive shaft 312 and a second rocker arm 313. The zigzag connecting rod 31 is rotatably mounted on the mounting plate 13 via the drive shaft 312. The first connecting rod 32 is hinged at one end to the movable clamp 5 and at the other end to the first rocker arm 311; The second link 33 is hinged at one end to the second rocker arm 313 and at the other end to the hatch.

[0056] The linkage mechanism 3 of this application can smoothly and accurately convert the opening and closing rotation of the hatch into the rotation of the movable clamp 5. The transmission path is clear, the movement of the hatch and the clamp is highly synchronized, and the operation is smooth without jamming.

[0057] The zigzag connecting rod 31 achieves motion reversal through the transmission shaft 312, which can convert the rotation of the canopy side into the radial clamping action of the clamp inside the cabin 11. The structure is compact and adaptable to the narrow installation space inside the fuselage 1, with high space utilization.

[0058] In practical applications, preferably, the first connecting rod 32 is hinged to the movable clamp 5 via a pin, and can be quickly and easily disassembled and installed.

[0059] like Figure 6 and Figure 11 As shown, in one embodiment, the linkage mechanism 3 further includes a fixing seat 34 fixed on the mounting plate 13, and the fixing seat 34 has a shaft hole 341. In the first rocker arm 311 and the second rocker arm 313, one has a mounting hole 3131 and the other has a drive shaft 312 fixed thereon. The first rocker arm 311 and the second rocker arm 313 are located on both sides of the shaft hole 341, and one end of the drive shaft 312 passes through the shaft hole 341 and is inserted into the mounting hole 3131 and fixed thereon.

[0060] The fixed base 34 provides stable rotational support for the drive shaft 312, improves the overall operating rigidity of the bend connecting rod 31, avoids radial wobble during transmission, ensures stable transmission of torque, and improves the linkage accuracy between the hatch and the clamp. The rocker arm and the drive shaft 312 adopt a separate plug-in fixed assembly form, which is simple to process, convenient to assemble, facilitates production assembly and individual replacement of parts, and reduces manufacturing costs.

[0061] like Figure 3 , Figure 4 , Figure 12 , Figure 13 and Figure 14 As shown, in one embodiment, the fuselage 1 has reinforcing frames 12 at both ends of the cabin 11; The hatch equipped with the locking and unlocking mechanism 4 has a strip-shaped through-hole 21b; Locking / unlocking mechanism 4 includes: The multi-functional connecting seat 41 is fixed to the inside of the hatch and has a sliding groove 411. The second connecting rod 33 is hinged to the multi-functional connecting seat 41. Unlocking paddle 42 is slidably mounted in slide groove 411. Unlocking paddle 42 has an operating part 421 that extends outward through strip-shaped through-hole 21b. Locking seat 43, fixed to reinforcing frame 12, has locking hole 431; The latch seat 44 is fixed to the inside of the hatch cover; The pin 45 is slidably installed in the pin seat 44, and the end of the pin 45 extending out of the pin seat 44 has a guide slope 451. Spring 46 is disposed in the pin seat 44 and is used to cooperate with pin 45 to give pin 45 a tendency to move outward. Guide tube 47 is located between pin seat 44 and multi-functional connector 41; A control cable 48 is threaded through a guide tube 47. One end of the control cable 48 is connected to an unlocking lever 42, and the other end is connected to a pin 45. During the hatch closing process, the guide slope 451 of the latch 45 is automatically retracted by the pressure of the fuselage 1. When the hatch is closed in place, the latch 45 extends into the lock hole 431 under the action of the spring 46 to complete the automatic locking. When the pin 45 is inserted into the lock hole 431 and is in the locked state, pressing the operating part 421 can drive the unlocking lever 42 to slide. The unlocking lever 42 drives the pin 45 to move into the pin seat 44 through the control cable 48, and the pin 45 disengages from the lock hole 431, thus completing the unlocking.

[0062] The canopy employs a flexible transmission unlocking structure consisting of an unlocking paddle 42, a control cable 48, and a pin 45. Unlocking is quick and easy, requiring only the movement of the operating part 421 on the outside of the canopy. The pin 45, in conjunction with the guide ramp 451 and the return spring 46, automatically retracts and locks when the canopy is closed, eliminating the need for manual locking and significantly improving canopy opening and closing efficiency. The guide tube 47 guides and protects the control cable 48, ensuring smooth cable transmission, preventing cable wear and jamming, and enhancing the long-term reliability of the unlocking mechanism. The locking seat 43, mounted on the reinforcing frame 12, improves the structural strength of the locking part, ensuring a secure and reliable lock that is less prone to loosening due to vibration during flight. The multi-functional connecting seat 41 integrates both the linkage hinge and the unlocking slide 411 functions, achieving high integration, simplifying the internal structural layout of the canopy, and reducing the number of parts.

[0063] like Figure 1 and Figure 4 As shown, in one embodiment, one hatch is provided on the left and one on the right, the two hatches are the first hatch 2a and the second hatch 2b, and the locking and unlocking mechanism 4 is provided between the second hatch 2b and the fuselage 1; See Figure 3 and 4 The outer end of the first hatch 2a away from its own rotation axis has a splicing edge 21a. When the cabin 11 is closed, the first hatch 2a closes before the second hatch 2b. When the second hatch 2b closes, it presses against the splicing edge 21a of the first hatch 2a. When the second hatch 2b is locked by the locking and unlocking mechanism 4, the first hatch 2a is locked synchronously. Each hatch is provided with at least two sets of linkage mechanisms 3 arranged at intervals along the front and rear directions. The locking and unlocking mechanisms 4 are provided with two sets, one in front and one in back. The locking seat 43 of one set of locking and unlocking mechanisms 4 is fixed to the reinforcing frame 12 on the front side of the fuselage 1, and the locking seat 43 of the other set of locking and unlocking mechanisms 4 is fixed to the reinforcing frame 12 on the rear side of the fuselage 1.

[0064] The design employs a dual-cover structure that opens from the left and right, providing a large opening range for the engine compartment 11 and ample operating space for loading and unloading gas cylinders 7, significantly improving the ease of installation and replacement of large-sized gas cylinders 7. The locking and unlocking mechanism 4 is only configured on the second cover 2b, achieving simultaneous locking of both covers by pressing against the splicing edge 21a of the first cover 2a when closed. This eliminates the need for separate locking and unlocking mechanisms 4 on each side of the covers, simplifying the structural design, reducing the number of parts, and contributing to lower structural weight and manufacturing costs.

[0065] Each hatch is equipped with two sets of linkage mechanisms 3 and locking mechanisms, which makes the force on the hatch opening and closing more balanced, the clamping force of the movable clamp 5 on the gas cylinder 7 more even, the locking synchronization of the front and rear ends is good, and the overall structural stability and locking reliability are significantly improved.

[0066] The above description is merely a preferred embodiment of the present invention and does not limit the scope of patent protection of the present invention. Any equivalent structural transformations made based on the description and drawings of the present invention, whether directly or indirectly applied to other related technical fields, are similarly included within the scope of protection of the present invention.

Claims

1. A gas cylinder mounting structure for a drone, characterized in that, This includes the fuselage, canopy, linkage mechanism, locking and unlocking mechanism, and movable clamps; The fuselage is equipped with a cabin for accommodating gas cylinders; The hatch is rotatably mounted on the fuselage and is used to open and close the cabin. The hatch has an opening position and a closing position. The locking and unlocking mechanism is located between the hatch and the fuselage and is used to lock the hatch in the closed position or unlock it. The movable clamp is rotatably mounted inside the engine compartment, and the movable clamp is synchronously linked with the hatch via the linkage mechanism. The movable clamp has a clamping position and a releasing position. When the hatch is in the closed position, the movable clamp is simultaneously in the clamping position, encircling and fixing the gas cylinder inside the engine room; When the hatch is in the open position, the movable clamp is simultaneously in the release position, releasing the constriction on the gas cylinder, allowing the gas cylinder to be removed or loaded into the engine room.

2. The gas cylinder mounting structure for the UAV as described in claim 1, characterized in that, The machine body has a mounting plate and a support plate. The mounting plate has a limiting port that cooperates with the gas cylinder. The support plate is located below the mounting plate and directly opposite the limiting port.

3. The gas cylinder mounting structure for the UAV as described in claim 2, characterized in that, It also includes a clamp mounting base, which is detachably mounted on the mounting plate, and the movable clamp is rotatably mounted on the clamp mounting base.

4. The gas cylinder mounting structure for the UAV as described in claim 3, characterized in that, One side of the movable clamp is a working surface, and the other side is a non-working surface. The non-working surface of the movable clamp has a limiting boss. When the movable clamp is in the release position, the limiting boss abuts against the mounting plate.

5. The gas cylinder mounting structure for the UAV as described in claim 4, characterized in that, The working surface of the movable clamp has a flexible layer.

6. The gas cylinder mounting structure for the UAV as described in claim 3, characterized in that, The linkage mechanism includes: The zigzag connecting rod has a first rocker arm, a drive shaft, and a second rocker arm. The zigzag connecting rod is rotatably mounted on the mounting plate via the drive shaft. The first connecting rod has one end hinged to the movable clamp and the other end hinged to the first rocker arm; The second link is hinged at one end to the second rocker arm and at the other end to the hatch.

7. The gas cylinder mounting structure for the UAV as described in claim 6, characterized in that, The linkage mechanism also includes a mounting base fixed to the mounting plate, and the mounting base has a shaft hole; Of the first rocker arm and the second rocker arm, one has a mounting hole and the other has the drive shaft fixed thereon. The first rocker arm and the second rocker arm are located on opposite sides of the shaft hole, and one end of the drive shaft passes through the shaft hole and is inserted into the mounting hole and fixed thereon.

8. The gas cylinder mounting structure for a drone as described in claim 6, characterized in that, The fuselage has reinforcing frames at both ends of the cabin; The hatch equipped with a locking and unlocking mechanism has a strip-shaped through-hole; The locking and unlocking mechanism includes: A multi-functional connecting seat is fixed to the inside of the hatch and has a sliding groove; the second connecting rod is hinged to the multi-functional connecting seat. An unlocking paddle is slidably mounted in the slide groove, and the unlocking paddle has an operating part that extends outward through a strip-shaped through-hole; The locking seat, fixed to the reinforcing frame, has a lock hole; The latch seat is fixed to the inside of the hatch cover; The pin is slidably installed in the pin holder, and the end of the pin extending out of the pin holder has a guide slope. A spring, located inside the pin holder, engages with the pin to give it a tendency to move outward. The guide tube is located between the pin socket and the multi-functional connector. A control cable is threaded through the guide tube, with one end connected to the unlocking lever and the other end connected to the pin. During the hatch closing process, the guide ramp of the latch automatically retracts under the pressure of the fuselage. When the hatch is closed in place, the latch extends into the lock hole under the action of the spring to complete the automatic locking. When the pin is inserted into the lock hole and is in the locked state, pressing the operating part can drive the unlocking lever to slide. The unlocking lever drives the pin to move into the pin seat through the control cable, and the pin disengages from the lock hole, thus completing the unlocking.

9. The gas cylinder mounting structure for a drone as described in claim 8, characterized in that, One hatch is provided on each side, and the two hatches are respectively the first hatch and the second hatch. The locking and unlocking mechanism is located between the second hatch and the fuselage. The outer end of the first hatch away from its own axis of rotation has a splicing edge. When the cabin is closed, the first hatch closes before the second hatch. When the second hatch closes, it presses against the splicing edge of the first hatch. When the second hatch is locked by the locking and unlocking mechanism, the first hatch is locked synchronously. Each hatch is provided with at least two sets of linkage mechanisms arranged at intervals along the front and rear directions. The locking and unlocking mechanisms are provided with two sets, one in front and one in back. The locking seat of one set of locking and unlocking mechanisms is fixed to the reinforcing frame on the front side of the fuselage, and the locking seat of the other set of locking and unlocking mechanisms is fixed to the reinforcing frame on the rear side of the fuselage.

10. A hydrogen-powered drone, characterized in that, The gas cylinder mounting structure for the UAV as described in any one of claims 1 to 9.

Images