A cargo hatch device for a cargo drone

Abstract

The present invention discloses a cargo hatch door device for a cargo drone, which includes a cargo hatch door and a hatch door lock mechanism provided on the cargo hatch door. The cargo hatch door includes an upper hatch door and a lower hatch door arranged in an up-and-down split manner. One end of the upper hatch door and the lower hatch door that are away from each other is hinged to the fuselage. When the cargo hatch door is closed, the end of the upper hatch door close to the lower hatch door is located above the lower hatch door, and the hatch door lock mechanism is arranged in the area where the upper hatch door is located. A locking device and a limiting component for opening and closing the lower hatch door are also arranged between the lower hatch door and the fuselage. The cargo hatch door of the drone provided by the present invention includes an upper hatch door and a lower hatch door arranged in an up-and-down split manner, and both the upper hatch door and the lower hatch door are separately designed with a locking device and a limiting mechanism, so that the upper hatch door and the lower hatch door can achieve multiple opening and closing forms, which not only improves the efficiency of loading and unloading goods on the ground by the cargo drone, but also maximizes the cargo loading capacity of the drone.

Description

Technical Field

[0001] The present invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a cargo compartment door device for a cargo unmanned aerial vehicle. Background Art

[0002] With the rapid development of unmanned aerial vehicle technology, large industrial-grade unmanned aerial vehicles have gradually been applied to the logistics and express delivery industries. Different from large civil cargo aircraft, the maximum takeoff weight of industrial-grade cargo unmanned aerial vehicles is relatively small, the space of the fuselage cargo compartment is limited, and the operator cannot enter the cargo compartment to load and unload goods. At the same time, in order to improve the utilization rate of the cargo compartment space and increase the effective load of the unmanned aerial vehicle as much as possible, no heavy cargo boxes or other cargo storage facilities can be arranged in the cargo compartment. However, the hatch structure of the existing industrial-grade cargo unmanned aerial vehicle is still in the traditional single-piece form, which cannot meet the usage requirements of maximizing the cargo compartment loading capacity of the unmanned aerial vehicle and quickly loading and unloading goods, resulting in a low effective load rate of the unmanned aerial vehicle and low work efficiency of cargo loading and unloading, and a long ground idle time. Summary of the Invention

[0003] The purpose of the present invention is to provide a cargo compartment door device for a cargo unmanned aerial vehicle to overcome the defects of the prior art. The structure form of the traditional civil aircraft cargo compartment door is changed, which includes an upper hatch and a lower hatch arranged in an up-and-down opening manner. The upper hatch and the lower hatch are each independently designed with a locking device and a limiting mechanism, so that the upper hatch and the lower hatch can achieve multiple opening and closing forms, which not only meet the usage requirements of maximizing the cargo compartment loading capacity of the unmanned aerial vehicle and quickly loading and unloading goods, improve the effective load and commuting rate of the unmanned aerial vehicle, but also ensure the sealing performance of the cargo compartment of the cargo unmanned aerial vehicle. Moreover, the structure form of the hatch and its locking mechanism is simple, the structural weight is light, the operation is convenient, and functions such as reliable locking and quick opening of the cargo compartment door can be realized.

[0004] The purpose of the present invention is achieved by the following technical solutions:

[0005] A cargo compartment door device for a cargo unmanned aerial vehicle, including a cargo compartment door and a hatch lock mechanism arranged on the cargo compartment door. The cargo compartment door includes an upper hatch and a lower hatch arranged in an up-and-down opening manner. One end of the upper hatch and the lower hatch away from each other is hinged to the fuselage. When the cargo compartment door is closed, one end of the upper hatch close to the lower hatch is located above the lower hatch, and the hatch lock mechanism is arranged in the area where the upper hatch is located. A locking device and a limiting component for opening and closing the lower hatch are further arranged between the lower hatch and the fuselage.

[0006] In one embodiment, the upper hatch and the lower hatch are both of a frame structure composed of a plurality of vertical frames and a plurality of horizontal frames. A corresponding skin is provided on the frame structure, and both the upper hatch and the lower hatch are hinged to the cabin door frame of the fuselage through hinges provided on the horizontal frames. Sealing rubber strips are provided on both the upper hatch and the lower hatch to form a hatch sealing boundary when the cargo hold hatch is closed.

[0007] In one embodiment, the hatch lock mechanism includes a door lock assembly provided in the middle of the upper hatch. Linkage lock pin mechanisms connected to the upper hatch are provided at both ends of the door lock assembly. The linkage lock pin mechanism includes a lock pin bushing provided on the vertical frame and a lock pin limit support provided on the cabin door frame. The linkage lock pin mechanism further includes a linkage and a lock pin provided in the lock pin bushing. The linkage is connected to the lock pin, and the door lock assembly can drive the linkage to reciprocate so that the lock pin can be inserted into the lock pin limit support or disengaged from the lock pin limit support.

[0008] In one embodiment, the door lock assembly includes a handle, a handle rotating shaft, and a handle crank. Both the handle and the handle crank are hinged to the handle rotating shaft through bolts. A button is further provided inside the handle, and a first rotating spring is provided between the handle and the button.

[0009] In one embodiment, a handle box provided on the skin is further included. The door lock assembly is installed on the handle box. A limit hole is provided on the handle box, and a limit rod is installed therein. A paper clip hook capable of hooking the limit rod is further provided on the button.

[0010] In one embodiment, the handle and the handle rotating shaft are respectively located on both sides inside the handle box. A second rotating spring is further connected between the handle and the handle rotating shaft, and the second rotating spring is used to automatically pop out the handle after the handle is unlocked.

[0011] In one embodiment, the hatch lock mechanism is further provided with a mid - stroke locking mechanism, which includes a mid - stroke spring link hinged to the horizontal frame and a mid - stroke spring sleeve hinged to the handle crank. The mid - stroke spring sleeve is installed on the mid - stroke spring link, and a compression spring that abuts against both of them is arranged on the mid - stroke spring sleeve and the mid - stroke spring link.

[0012] In one embodiment, the upper hatch is further provided with a hatch strut mechanism, which has a strut base and a fixed clamp fixed on the horizontal frame of the upper hatch. The hatch strut mechanism further includes a support rod and a strut base. One end of the support rod is connected to the strut base through a connecting ring, and the other end is provided with a positioning pin and can be connected to the fixed clamp through the positioning pin.

[0013] In one embodiment, two maintenance access covers are further provided on the upper hatch, which are respectively located on both sides of the door lock assembly, and the positions of the maintenance access covers correspond to the connection positions of the pull rod and the lock pin, for emergency unlocking and maintenance observation when the cabin door lock mechanism fails.

[0014] In one embodiment, the lower hatch limiting assembly includes a first limiting mechanism and a second limiting mechanism located on both sides of the lower hatch. Both the first limiting mechanism and the second limiting mechanism include a first connecting rod and a second connecting rod. The first connecting rod is connected to the fuselage through a first support, and the second connecting rod is connected to the lower hatch through a second support. The first connecting rod and the second connecting rod are hinged to each other by bolts to form a four-bar linkage mechanism. A limiting convex head is also designed on the first connecting rod, and a spring plunger pin is installed on the second connecting rod in the first limiting mechanism or the second limiting mechanism for locking the lower hatch limiting mechanism.

[0015] In one embodiment, the sealing method of the cargo hold door device provided by the present invention is as follows;

[0016] When the cargo hold door is completely closed, the rubber strips at the edges of the upper hatch and the lower hatch are pressed against the fuselage cabin door frame to form a complete sealing line, ensuring the waterproof sealing of the entire hatch. At the same time, one end of the upper hatch close to the lower hatch is located above the lower hatch, and the horizontal frame of the upper hatch with a sealing rubber strip can press the edge strip of the horizontal frame of the lower hatch, thereby ensuring the waterproof sealing effect of the mating edge of the upper hatch and the lower hatch.

[0017] In one embodiment, according to the usage requirements of loading and unloading goods of the unmanned aerial vehicle, the design and usage method of the cargo hold door provided by the present invention is as follows;

[0018] When loading goods, the upper hatch can be opened and the lower hatch can be closed. At this time, the entire fuselage cargo hold can form a semi-open space, similar to a cargo net or an open cargo box, and the goods can be loaded quickly without using a heavy cargo box, improving the effective load of the unmanned aerial vehicle, which has important economic value; when unloading goods, both the upper and lower hatches can be opened, and the goods can be quickly unloaded to the transfer vehicle; thus greatly reducing the working time of ground cargo loading and unloading and improving the effective utilization rate of the aircraft.

[0019] The beneficial effects of the present invention are as follows:

[0020] (1) Different from the single-piece integral structure form of the traditional cargo hold door, the fuselage cargo hold door of the cargo-carrying unmanned aerial vehicle is designed into two parts: an upper hatch and a lower hatch that open in opposite directions. Compared with the prior art, this structural form is unique to this application;

[0021] (2) The upper hatch and the lower hatch are each separately designed with a locking device and a limiting mechanism, enabling the upper and lower hatches to achieve multiple opening and closing configurations. This not only improves the efficiency of loading and unloading goods on the ground but also ensures the sealing performance of the cargo drone.

[0022] (3) The cargo hatch door device provided by the present invention can select the opening and closing states of the upper hatch and the lower hatch according to the actual needs of loading and unloading goods on the ground, so as to improve the efficiency of the drone during ground loading and unloading of goods and maximize the cargo loading capacity of the drone.

[0023] (4) When closing the hatch, the rubber strips at the edges of the upper and lower hatches are pressed tightly against the fuselage hatch door frame, forming a complete sealing line, ensuring the waterproof sealing between the entire hatch and the fuselage cargo hatch opening frame. At the same time, the cross-frame with the sealing rubber strip on the upper hatch presses against the edge strip of the cross-frame of the lower hatch, effectively realizing the sealing and waterproof function between the upper and lower hatches.

[0024] (5) The locking mechanisms of the upper and lower hatches are simple in operation, light in structural weight, and high in reliability, enabling reliable locking and rapid opening of the cargo hatch door. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] The present invention will be described in more detail below based on embodiments and with reference to the drawings. Among them:

[0026] Figure 1 shows a schematic structural diagram of the hatch of the present invention when it is completely closed;

[0027] Figure 2 shows a schematic structural diagram of the present invention when the lower hatch is closed and the upper hatch is open;

[0028] Figure 3 shows a schematic structural diagram of the hatch of the present invention when it is completely open;

[0029] Figure 4 shows a schematic diagram of the complete sealing line formed by the rubber strips of the upper hatch and the lower hatch of the present invention;

[0030] Figure 5 shows a schematic structural diagram of the upper hatch and the hatch door locking mechanism of the present invention;

[0031] Figure 6 shows a schematic structural diagram of the door lock assembly of the present invention;

[0032] Figure 7 shows an exploded view of the schematic structural diagram of the door lock assembly of the present invention;

[0033] Figure 8 shows a schematic structural diagram of the door lock assembly of the present invention when it is locked;

[0034] Figure 9 Shows the structural schematic diagram of the door lock assembly of the present invention when unlocking;

[0035] Figure 10 Shows the structural schematic diagram of the lower hatch and the limit component of the present invention;

[0036] Figure 11 Shows Figure 10 The partial enlarged schematic diagram at position C in

[0037] In the drawings, the same components are denoted by the same reference numerals.

[0038] Reference numerals:

[0039] 100 - upper hatch, 200 - lower hatch, 300 - door lock assembly, 400 - limit component, 500 - hatch strut mechanism, 1 - first vertical frame, 2 - second vertical frame, 3 - third vertical frame, 4 - fourth vertical frame, 5 - first horizontal frame, 6 - second horizontal frame, 7 - third horizontal frame, 8 - upper hatch skin, 9 - upper hatch rubber strip, 10 - first metal hinge, 11 - fuselage cabin door frame, 12 - first maintenance access cover, 13 - second maintenance access cover, 14 - button, 15 - handle, 16 - handle rotating shaft, 17 - handle crank, 18 - handle box, 19 - first pull rod, 20 - second pull rod, 21 - first lock pin, 22 - second lock pin, 23 - pressure plate, 24 - first bolt, 25 - first rotating spring, 26 - limit rod, 27 - limit hole, 28 - split pin, 29 - bushing, 30 - second bolt, 31 - second rotating spring, 32 - unlocking limit support, 33 - locking limit support, 34 - first lock pin bushing, 35 - second lock pin bushing, 36 - front limit support of lock pin, 37 - rear limit support of lock pin, 38 - compression spring, 39 - over-center spring connecting rod, 40 - over-center spring sleeve, 41 - strut base, 42 - strut, 43 - fixed clamp, 44 - fixed support, 45 - positioning pin, 46 - fifth vertical frame, 47 - sixth vertical frame, 48 - seventh vertical frame, 49 - eighth vertical frame, 50 - fourth horizontal frame, 51 - fifth horizontal frame, 52 - lower hatch skin, 53 - lower hatch rubber strip, 54 - second metal hinge, 55 - first button spring pin, 56 - second button spring pin, 57 - front lock hole support of lower hatch, 58 - rear lock hole support, 59 - first connecting rod, 60 - second connecting rod, 61 - first support, 62 - second support, 63 - spring plunger pin. Detailed implementation manner

[0040] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "upper", "lower", "bottom", "top", "front", "rear", "inner", "outer", "left", "right", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention.

[0041] The present invention will be further described below in conjunction with the drawings.

[0042] The present invention provides a cargo hatch door device for a cargo drone, including a cargo hatch door and a hatch door lock mechanism provided on the cargo hatch door. The cargo hatch door includes an upper hatch door 100 and a lower hatch door 200 arranged in an up-and-down split opening manner. One end of the upper hatch door 100 and the lower hatch door 200 away from each other is hinged to the fuselage. One end of the upper hatch door 100 close to the lower hatch door 200 is located above the lower hatch door 200, and the hatch door lock mechanism is arranged in the area where the upper hatch door 100 is located. A locking device and a limiting component 400 for opening and closing the lower hatch door 200 are also arranged between the lower hatch door and the fuselage;

[0043] In the present invention, the fuselage cargo hatch door is divided into two parts, an upper hatch door 100 and a lower hatch door 200. In order not to occupy the loading space of the cargo hold, the hatch door adopts an outward-opening form;

[0044] It should be noted that the cargo hatch door is divided into an upper hatch door 100 and a lower hatch door 200 arranged in an up-and-down split opening manner. Both the upper hatch door 100 and the lower hatch door 200 have individually designed locking devices and limiting mechanisms, so that the upper hatch door and the lower hatch door can achieve various opening and closing forms. When the cargo hatch door is completely closed, one end of the upper hatch door 100 close to the lower hatch door 200 is located above the lower hatch door 200, and one end of the upper hatch door 100 can press the lower hatch door 200, and the hatch door lock mechanism is located on the upper hatch door 100, that is, the hatch door lock mechanism can lock both the upper hatch door 100 and the lower hatch door 200 at the same time, which can further ensure the safety of the cargo drone.

[0045] In one embodiment, both the upper hatch door 100 and the lower hatch door 200 are frame structures composed of a plurality of vertical frames and a plurality of horizontal frames. Corresponding skins are provided on the frame structures. Both the upper hatch door 100 and the lower hatch door 200 are hinged to the cabin door frame of the fuselage through hinges provided on the horizontal frames. At the same time, in order to meet the high sealing requirements of the cargo hold of the cargo drone, sealing rubber strips are provided on the edges of the upper hatch door 100 and the lower hatch door 200. When the hatch door is closed, the sealing rubber strips between the upper and lower hatch doors and the cabin door frame of the fuselage, and between the upper hatch door and the lower hatch door are pressed tightly to form a hatch door sealing boundary;

[0046] Specifically, as Figure 1 、Figure 2 and Figure 5 As shown in Figure 5 , the upper hatch 100 is a frame structure composed of a first vertical frame 1, a second vertical frame 2, a third vertical frame 3, a fourth vertical frame 4, a first horizontal frame 5, a second horizontal frame 6, and a third horizontal frame 7. An upper hatch skin 8 with corresponding dimensions is also provided on the frame structure. The upper hatch 100 is hinged to the fuselage hatch door frame 11 through a first metal hinge 10 installed on the first horizontal frame 1. When opening and closing the hatch, the upper hatch 100 rotates around the first metal hinge 10. An upper hatch rubber strip 9 is pasted along the four peripheral edges of the upper hatch skin 8 for waterproof sealing of the upper hatch 100 in the closed state;

[0047] Furthermore, as Figure 10 shown in Figure 10 , the lower hatch 200 is a frame structure composed of a fifth vertical frame 46, a sixth vertical frame 47, a seventh vertical frame 48, an eighth vertical frame 49, a fourth horizontal frame 50, and a fifth horizontal frame 51. A lower hatch skin 52 is provided thereon; the lower hatch 200 is hinged to the fuselage hatch door frame 11 through a second metal hinge 54 installed on the fifth horizontal frame 51. When opening and closing the hatch, the lower hatch 200 rotates around the axis of the second metal hinge 54. Rubber strips 53 are pasted along the edges of the skin 52 of the fifth vertical frame 46, the fifth horizontal frame 51, and the eighth vertical frame 49 for waterproof sealing of the lower hatch 200;

[0048] It should be noted that as Figure 4 shown in Figure 4 , after the upper hatch 100 and the lower hatch 200 are both closed, after the upper hatch rubber strip 9, the lower hatch rubber strip 53 and the fuselage hatch door frame 11 are cooperatively pressed, a complete hatch seal boundary can be formed to achieve the waterproof sealing effect of the entire fuselage hatch. At the same time, the third horizontal frame 7 of the upper hatch 100 with a sealing rubber strip pressed against the flange of the fourth horizontal frame 50 of the lower hatch 200, thereby achieving the waterproof sealing purpose of the mating edge of the upper hatch 100 and the lower hatch 200 when the hatch is closed.

[0049] In one embodiment, the hatch lock mechanism includes a door lock assembly 300 provided in the middle of the upper hatch 100. Linkage lock pin mechanisms connected to the upper hatch 100 are provided at both ends of the door lock assembly 300. The linkage lock pin mechanism includes a lock pin bushing provided on the vertical frame and a lock pin limit support provided on the fuselage hatch door frame 11. The linkage lock pin mechanism further includes a linkage and a lock pin provided in the lock pin bushing. The linkage is connected to the lock pin. The door lock structure can drive the linkage to reciprocate for the lock pin to be inserted into or disengaged from the lock pin limit support;

[0050] Specifically, as Figure 5As shown, a set of left - right linkage pull - rod lock pin mechanism is provided at the bottom of the upper hatch 100. This mechanism includes a first pull - rod 19, a second pull - rod 20, a first lock pin 21, a second lock pin 22, a first lock - pin bushing 34, a second lock - pin bushing 35, a front limit support 36 for the lock pin, and a rear limit support 37 for the lock pin.

[0051] It should be noted that both the first connecting rod 19 and the second connecting rod 20 are hinged to the first lock pin 21, the second lock pin 22, and the handle crank 17 by bolts. The first lock - pin bushing 34 and the second lock - pin bushing 35 are respectively installed on the first vertical frame 1 and the fourth vertical frame 4 of the upper hatch 100. The front limit support 36 for the lock pin and the rear limit support 37 for the lock pin are installed on the fuselage hatch frame 11. Driven by the first connecting rod 19, the first lock pin 21 can move linearly along the axis of the first lock - pin bushing 34, so that the first lock pin 21 can be inserted into or disengaged from the front limit support 36 for the lock pin. Driven by the second connecting rod 20, the second lock pin 22 can move linearly along the axis of the second lock - pin bushing 35, so that the second lock pin 22 can be inserted into or disengaged from the rear limit support 37 for the lock pin, thus realizing the unlocking or locking operation of the upper hatch 100.

[0052] In one embodiment, the door lock assembly 300 includes a handle 15, a handle rotating shaft 16, and a handle crank 17. Both the handle 15 and the handle crank 17 are hinged to the handle rotating shaft 16 by bolts. A button 14 is also provided inside the handle 15, and a first rotating spring 25 is provided between the handle 15 and the button 14.

[0053] It should be noted that the first rotating spring 25 provided can restore the installation contact state between the button 14 and the handle 15.

[0054] Furthermore, a locking component for locking the handle 15 is also provided. It includes two loop hooks provided on the button 14. When the upper hatch 100 is closed, the loop hooks hook the limit rod 26 on the handle box 18, thus locking the handle 15. When the button 14 is pressed, the loop hooks are separated from the limit rod 26, completing the unlocking of the handle 15.

[0055] In one embodiment, as Figure 6 and Figure 7 shown, the door lock assembly 300 is arranged between the second cross - frame 2 and the third cross - frame 3 of the upper hatch 100. A handle box 18 is also provided on the upper hatch skin 8. The handle box 18 is connected to the upper hatch skin 8 and the pressing plate 23 by rivets. The handle box 18 serves as the installation support for the door lock assembly 300.

[0056] In one embodiment, as Figure 6 and Figure 7As shown, the limit rod 26 is installed in the limit hole 27 on the handle box 18. The two ends of the limit rod 26 are limited by split pins 28. The handle rotating shaft 16 is installed on the handle box 18 through a bushing 29. The handle rotating shaft 16 can rotate around the axis of the installation hole of the handle box 18. The handle 15 and the handle crank 17 are hinged to the handle rotating shaft 16 through a second bolt 30. The handle 15 and the handle crank 17 are separately installed on both sides of the handle box 18. A second rotating spring 31 is arranged between the handle 15 and the handle rotating shaft 16 to automatically eject the handle 15 after the handle 15 is unlocked;

[0057] In one embodiment, as Figure 7 shown, the handle crank 17 can rotate with the handle rotating shaft 16, and the rotation range of the handle crank 17 is limited by an unlocking limit support 32 and a locking limit support 33 installed on the handle box 18.

[0058] In one embodiment, as Figure 5 、 Figure 8 and Figure 9 shown, the cabin door lock mechanism further includes a handle crank over-center locking mechanism, which consists of a compression spring 38, an over-center spring connecting rod 39 and an over-center spring sleeve 40; the lug at the upper end of the over-center spring connecting rod 39 is hinged to point A on the second cross frame 6 of the upper cabin door 100 through a bolt, and the lower end of the over-center spring sleeve 40 is hinged to point B on the handle crank 17 through a bolt. The over-center spring connecting rod 39 is sleeved in the over-center spring sleeve 40. After installing the compression spring 38, as the handle crank 17 rotates around a fixed axis, the compression spring 38 is compressed or relaxed, so that the handle crank over-center locking mechanism makes a piston-like telescopic movement; when the handle crank 17 is rotated to lock the upper cabin door 100 so that the straight line AB passes above the axis of the handle crank rotating shaft, the handle crank over-center locking mechanism is driven by the compression spring 38 to keep the cabin door in a locked state. When the handle crank 17 is rotated to unlock the cabin door so that the straight line AB passes below the axis of the handle crank rotating shaft, the handle crank over-center locking mechanism is driven by the compression spring 38 to keep the cabin door in an unlocked state.

[0059] In one embodiment, the cargo hold door device further includes a support assembly for supporting the upper cabin door 100 and keeping it in an open posture after the upper cabin door 100 is opened;

[0060] It should be noted that the support assembly may include a support rod, which supports the upper cabin door when it is opened. When the upper cabin door is closed, the support rod moves to be flush with the upper cabin door 100 and is then received in the upper cabin door 100. During the movement of the support rod, it can be manual or can adopt methods such as hydraulic or pneumatic, so that during the process of opening the upper cabin door 100, the support rod can automatically open the upper cabin door 100 and keep it in an open posture;

[0061] Specifically, as Figure 3As shown, the support component is the hatch strut mechanism 500, which consists of a strut base 41, a strut 42, a fixed clamp 43, and a strut fixed support 44; the strut base 41 and the fixed clamp 43 are fixed to the third cross-frame 7 of the upper hatch 100, and both ends of the strut 42 are respectively designed with a connecting ring and a bayonet pin 45. The strut 42 is hinged to the strut base 41 through the connecting ring; the strut fixed support 44 is installed on the fuselage hatch frame 11;

[0062] It should be further noted that when the upper hatch 100 is closed, the bayonet pin 45 is stuck on the fixed clamp 43 to prevent the strut 42 from shaking in the cargo hold during flight; when the upper hatch 100 is opened, the strut 42 is removed from the fixed clamp 43 and stuck on the strut fixed support 44. At this time, the strut 42, the upper hatch 100, and the fuselage hatch frame 11 form a self-stabilizing triangle, thus maintaining the stability of the open state of the upper hatch 100, facilitating operations such as cargo loading and unloading, and at the same time resisting the ground gust load acting on the hatch.

[0063] In one embodiment, a locking device is provided between the lower hatch 200 and the fuselage for locking or unlocking the lower hatch 200;

[0064] Specifically, as Figure 10 and Figure 11 shown, the locking device of the lower hatch 200 includes a first button spring bolt 55 arranged at the upper left corner of the lower hatch 200 and a second button spring bolt 56 arranged at the upper right corner of the lower hatch 200. The first button spring bolt 55 cooperates with the front lock hole support 57 of the lower hatch installed on the fuselage hatch frame 11, and the second button spring bolt 56 cooperates with the rear lock hole support 58 of the lower hatch installed on the fuselage hatch frame 11, thereby realizing the locking or unlocking operation of the lower hatch 200;

[0065] In one embodiment, the limit component of the lower hatch 200 can keep the lower hatch 200 at a required angle and support it after the lower hatch 200 is opened; the limit component is arranged between the fifth cross-frame 51 of the lower hatch 200 and the fuselage hatch frame 11, and the limit component includes two sets of limit mechanisms for restricting the opening angle of the lower hatch 200 and locking the opening position of the lower hatch 200;

[0066] Specifically, as Figure 10 and Figure 11As shown in the figure, the second limiting mechanism is a four-bar linkage mechanism composed of a first connecting rod 59, a second connecting rod 60, a first support 61, and a second support 62. A limiting convex head is designed on the first connecting rod 59, and a spring plunger pin 63 is installed on the second connecting rod 60. During the process of opening the lower hatch 200, the pin shaft of the spring plunger pin 63 abuts against the flange of the second connecting rod 60 and moves along its surface. When the limiting convex head of the first connecting rod 59 contacts and abuts against the second connecting rod 60, and at the same time the pin shaft of the spring plunger pin 63 is inserted into the pin hole of the second connecting rod 60, the lower hatch limiting mechanism is locked, and the hatch is opened in place and locked, which can prevent the lower hatch 200 from swinging arbitrarily under the action of external force and causing safety accidents;

[0067] It should be noted that except for not including the spring plunger pin 63, the first limiting mechanism and the second limiting mechanism have the same composition. Under the combined action of the two sets of limiting mechanisms, it can ensure the stable posture of the lower hatch 200 after being opened and locked, and the symmetric loading of the opening limiting mechanism, prevent the limiting mechanism from jamming due to load deformation, and improve the reliability of the lower hatch 200 limiting.

[0068] In one embodiment, the process of opening the upper hatch is as follows:

[0069] Manually press the button 14 on the handle 15 of the upper hatch 100, so that the spring hook of the button 14 is separated from the limiting rod 26 on the handle box 18, and the unlocking of the handle 15 is completed. At this time, the first torsion spring 25 forces the handle 15 to pop out automatically. After the handle 15 pops out, manually rotate the handle 15 in the clockwise direction. Driven by the handle rotating shaft 16, the handle crank 17 rotates clockwise following the handle 15, and then transmits the unlocking driving force to the left and right linkage rod lock pin mechanisms of the upper hatch 100. The handle crank 17 drives the first connecting rod 19 and the second connecting rod 20 to move, thereby driving the first lock pin 21 and the second lock pin 22 to retract along the axes of the first lock pin bushing 34 and the second lock pin bushing 35 respectively. When the handle crank 16 rotates until the axis AB of the over-center locking mechanism is located below the axis of the handle rotating shaft 16, the over-center locking mechanism automatically drives the handle crank 17 to rotate to the position in contact with the unlocking limit support 32 and lock. At this time, the limit support 1 completely disengages from the lock pin front limit support 36 and retracts into the upper hatch 100, and at the same time the second lock pin 22 also completely disengages from the lock pin rear limit support 37 and retracts into the upper hatch 100. Thus, the unlocking operation of the upper hatch 100 is completed;

[0070] After the upper hatch 100 is unlocked, apply a driving force through the handle 15 to make the upper hatch 100 perform an upward opening movement around its first metal hinge 10 axis. After the upper hatch 100 is opened to an appropriate position, manually remove the support rod 42 from the fixed clamp 43, and push the upper hatch 100 to continue to open upward through the support rod 42. After the limit pin shaft of the support rod 42 slides into the fixed support 44, the upper hatch 100 is fully opened and supported.

[0071] In one embodiment, the process of opening the lower hatch is as follows:

[0072] After the upper hatch 100 is opened in place and supported, manually press the quick-release buttons of the first button spring bolt 55 and the second button spring bolt 56 of the lower hatch 200 one by one. At this time, the stainless steel locking tongues of the first button spring bolt 55 and the second button spring bolt 56 retract from the front lock hole support 57 and the rear lock hole support 58 of the lower hatch into the interior of the lower hatch 200 respectively, so that the lower hatch 200 is unlocked; under the action of the operator's thrust and the self-weight of the lower hatch 200, the lower hatch 200 performs a downward opening movement around its second metal hinge 54. At the same time, its front limit mechanism and rear limit mechanism follow and unfold. When the limit convex head of the first connecting rod 59 contacts and abuts against the second connecting rod 60, and the pin shaft of the spring plunger pin 63 of the rear limit mechanism is inserted into the pin hole of the second connecting rod 60, the limit mechanism locks, and the lower hatch 200 is opened in place and locked accordingly.

[0073] In one embodiment, the process of closing the lower hatch is as follows:

[0074] The operator manually holds the edge of the fourth cross frame 50 of the lower hatch 200 and manually pulls out the spring plunger pin 63 on the fifth cross frame 51 of the lower hatch 200 to unlock the opening limit mechanism of the lower hatch 200. Then manually drive the lower hatch 200 to perform an upward closing movement around its second metal hinge 54 axis. After the sealing edge of the lower hatch 200 with the lower hatch rubber strip 53 is well fitted with the edge of the fuselage cabin door frame 11, manually push the bolts of the first button spring bolt 55 and the second button spring bolt 56 on the fourth cross frame 50 to insert into the limit holes of the limit front support and the limit rear support of the lower hatch 200, and the closing and locking operation of the lower hatch 200 can be completed.

[0075] In one embodiment, the process of closing the upper hatch is as follows:

[0076] After the lower hatch 200 is closed, the operator manually removes the support rod 42 from the support rod fixed support 44, and drives the upper hatch 100 to make a downward turning and closing movement around the first metal hinge 10 through the support rod 42. After the upper hatch 100 moves to a suitable position, the positioning pin 45 of the support rod 42 is pressed into the fixed clamp 43, so as to fix the upper hatch support rod mechanism. Then, manually lift the edge of the third cross frame 7 and the handle 15 of the upper hatch 100, and continue to close the upper hatch 100. After the sealing edge of the upper hatch rubber strip 9 on the upper hatch 100 is closed with the edge of the fuselage cabin door frame 11 and the edge strip of the fourth cross frame 50 of the lower hatch, apply force to press the upper hatch 100, so as to compact the sealing boundary rubber strip of the entire hatch;

[0077] Thereafter, manually rotate the handle 15 counterclockwise, and drive the handle crank 17 to rotate counterclockwise, and then drive the first connecting rod 19 and the second connecting rod 20 to move, so as to drive the first locking pin 21 and the second locking pin 22 to extend out of the upper hatch 100 along the axes of the first locking pin bushing 34 and the second locking pin bushing 35. When the axis AB of the over-center locking mechanism rotates to be above the axis of the handle rotating shaft when the handle crank 17 rotates, the over-center locking mechanism automatically drives the handle crank to rotate to the contact position with the unlocking limit support and locks. At this time, the locking pin 1 is completely inserted into the front limit support of the locking pin, and the locking pin 2 is completely inserted into the rear limit support of the locking pin. Thus, the upper hatch completes the locking operation; Finally, manually press the handle 15 into the handle box 18. At the same time, force the spring hook of the button to hook the limit rod 26 on the handle box 18 to complete the locking of the handle 15. Thus, the entire fuselage cargo hold hatch is completely closed and successfully locked.

[0078] In one embodiment, when the cabin door lock mechanism fails and cannot work, the first maintenance cover 12 and the second maintenance cover 13 of the upper hatch can be opened, the connecting bolts of the first pull rod 19 of the pull rod lock pin mechanism and the first locking pin 21, and the second pull rod 20 and the second locking pin 22 are removed, and then the first locking pin 21 and the second locking pin 22 are manually pulled out from the front limit support 36 of the locking pin and the rear limit support 37 of the locking pin respectively and retracted into the upper hatch 100 for emergency unlocking, that is, the first maintenance cover 12 and the second maintenance cover 13 provided can achieve emergency unlocking, and at the same time, the first maintenance cover 12 and the second maintenance cover 13 can also maintain and observe the door lock assembly.

[0079] In one embodiment, an upper hatch rubber strip 9 is pasted along the four peripheral edges of the upper hatch skin 8 for waterproof sealing of the upper hatch 100 in the closed state. At the same time, a rubber strip 53 is pasted along the edges of the skin 52 of the lower hatch along the fifth vertical frame 46, the fifth horizontal frame 51, and the eighth vertical frame 49 for waterproof sealing of the lower hatch 200. When the upper hatch 100 and the lower hatch 200 are closed together, after the upper hatch rubber strip 9, the lower hatch rubber strip 53 and the fuselage cabin door frame 11 are pressed together, a complete cabin door sealing boundary can be formed to achieve the waterproof sealing effect of the entire fuselage cabin door. At the same time, the third horizontal frame 7 with a sealing rubber strip pasted on the upper hatch 100 presses the flange of the fourth horizontal frame 50 of the lower hatch 200, thereby achieving the waterproof sealing purpose of the mating edge of the upper hatch 100 and the lower hatch 200 when the cabin door is closed.

[0080] In order to meet the use requirements of maximizing the cargo loading capacity of the UAV and quickly loading and unloading goods, and to improve the effective load and commuting rate of the UAV, the UAV cargo cabin door provided by the present invention changes the structural form of the traditional civil aircraft cargo cabin door, including two parts: an upper hatch 100 and a lower hatch 200, and locking devices and limit components are respectively designed, so that the upper hatch 100 and the lower hatch 200 can achieve various opening and closing forms;

[0081] In one embodiment, according to the use requirements of loading and unloading goods, the present invention also provides a method for using a cargo cabin door, which is specifically as follows:

[0082] When loading goods, the upper hatch 100 can be opened and supported, and the lower hatch 200 is in the closed state. At this time, the entire fuselage cargo cabin forms a semi-open space, similar to a cargo net or an open cargo box. The operator can quickly deliver the packaged scattered goods into the cargo cabin without the occurrence of cargo spillage. When unloading goods, the upper hatch 100 and the lower hatch 200 are opened simultaneously, and the goods can be quickly unloaded from the cabin door and slide into the cargo transfer vehicle.

[0083] Through the above flexible method of using the cabin door when loading and unloading goods, there is no need to arrange heavy cargo boxes or other cargo storage facilities in the UAV cargo cabin, which significantly improves the effective load of the UAV and has important economic value; when loading goods, there is no need for the operator to enter the cargo hold to stack the goods, saving a large amount of time for regular placement and fixation of the goods. At the same time, fast unloading operations can also be achieved when unloading goods, greatly reducing the working time of ground cargo loading and unloading and improving the effective utilization rate of the aircraft. Therefore, the cargo cabin door device provided by the present invention can select the opening and closing states of the upper hatch and the lower hatch according to the actual needs of ground cargo loading and unloading, so as to improve the efficiency of the UAV when loading and unloading goods on the ground, and at the same time maximize the cargo loading capacity of the UAV cargo cabin.

[0084] Although the present invention has been described herein with reference to particular embodiments, it should be understood that these embodiments are merely examples of the principles and applications of the present invention. Accordingly, it should be understood that numerous modifications may be made to the exemplary embodiments, and other arrangements may be devised, without departing from the spirit and scope of the present invention as defined by the appended claims. It should be understood that the different dependent claims and the features described herein may be combined in ways different from those described in the original claims. It should also be understood that the features described in connection with separate embodiments may be used in other described embodiments.

Claims

1. A cargo hold door device for a freight drone, characterized in that, It includes a cargo hold door and a cabin door lock mechanism arranged on the cargo hold door. The cargo hold door includes an upper cabin door and a lower cabin door arranged in an up-and-down split type. One end of the upper cabin door and the lower cabin door away from each other is hinged to the fuselage. When the cargo hold door is closed, one end of the upper cabin door close to the lower cabin door is located above the lower cabin door, and the cabin door lock mechanism is arranged in the area where the upper cabin door is located. A locking device and a limiting component for opening and closing the lower cabin door are also arranged between the lower cabin door and the fuselage. Both the upper cabin door and the lower cabin door are of a frame structure composed of a plurality of vertical frames and a plurality of horizontal frames. Corresponding skins are arranged on the frame structure. Both the upper cabin door and the lower cabin door are hinged to the cabin door frame of the fuselage through hinges arranged on the horizontal frames. Sealing rubber strips are arranged on both the upper cabin door and the lower cabin door to form a cabin door sealing boundary when the cargo hold door is closed. The cabin door lock mechanism includes a door lock component arranged in the middle of the upper cabin door. Linkage lock pin mechanisms connected to the upper cabin door are arranged at both ends of the door lock component. The linkage lock pin mechanism includes a lock pin bushing arranged on the vertical frame and a lock pin limit support arranged on the cabin door frame. The linkage lock pin mechanism also includes a linkage and a lock pin arranged in the lock pin bushing. The linkage is connected to the lock pin. The door lock component can drive the linkage to move reciprocally to insert the lock pin into the lock pin limit support or withdraw the lock pin from the lock pin limit support. The door lock component includes a handle, a handle rotating shaft, and a handle crank. Both the handle and the handle crank are hinged to the handle rotating shaft through bolts. A button is also arranged inside the handle. A first rotating spring is arranged between the handle and the button. The cabin door lock mechanism is also provided with a mid-position locking mechanism, which includes a mid-position spring linkage hinged to the horizontal frame and a mid-position spring sleeve hinged to the handle crank. The mid-position spring sleeve is installed on the mid-position spring linkage, and a compression spring that abuts against both of them is arranged on the mid-position spring sleeve and the mid-position spring linkage. A cabin door strut mechanism is also included, which has a strut base and a fixed clamp fixed on the horizontal frame of the upper cabin door. The cabin door strut mechanism also includes a support rod and a strut base. One end of the support rod is connected to the strut base through a connecting ring, and the other end is provided with a positioning pin and can be connected to the fixed clamp through the positioning pin.

2. The cargo compartment door device of a freight drone according to claim 1, characterized in that, It also includes a handle box arranged on the skin. The door lock component is installed on the handle box. The handle box is provided with a limiting hole, and a limiting rod is installed inside it. A paper clip hook that can hook the limiting rod is also arranged on the button.

3. The cargo hold door device of a freight drone according to claim 2, characterized in that, The handle and the handle rotating shaft are respectively located on both sides inside the handle box. A second rotating spring is also connected between the handle and the handle rotating shaft. The second rotating spring is used to automatically pop out the handle after the handle is unlocked.

4. The cargo compartment door device of a freight drone according to claim 1, wherein, Two maintenance covers are also opened on the upper cabin door, respectively located on both sides of the door lock component, and the positions of the maintenance covers correspond to the connection positions of the pull rod and the lock pin.

5. A cargo hold door device of a freight drone according to any one of claims 1 to 4, characterized in that, The limiting component of the lower hatch includes a first limiting mechanism and a second limiting mechanism located on both sides of the lower hatch. Both the first limiting mechanism and the second limiting mechanism include a first connecting rod and a second connecting rod. The first connecting rod is connected to the fuselage through a first support, and the second connecting rod is connected to the lower hatch through a second support. The first connecting rod and the second connecting rod are hinged to each other by bolts to form a four-bar linkage mechanism. A limiting convex head is also designed on the first connecting rod. A spring plunger pin is installed on the second connecting rod in the first limiting mechanism or the second limiting mechanism for locking the lower hatch limiting mechanism.

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