Cabin structure and unmanned aerial vehicle

Abstract

The invention provides a cabin structure and an unmanned aerial vehicle. The cabin structure comprises a machine body, a seat body and a pressing mechanism. The machine body comprises an opening and a cavity, and the opening is communicated with the cavity. The seat body enters the cavity from the opening and is installed in the cavity. The pressing mechanism comprises a fixing base and a pressing piece, the fixing base is fixedly installed in the cavity and located on the outer side of the base body, and the pressing piece is movably connected with the fixing base. Wherein the pressing piece has a first state for pressing the seat body and a second state for releasing the seat body. According to the cabin structure, the size relation between the seat body and the opening is accurately matched, the passing ability of the seat body is guaranteed, meanwhile, the opening area is minimized, and the situation that the structural strength of a machine body is affected due to the too large opening is avoided. The pressing mechanism reduces the dependence on precision machining and positioning and the operation difficulty of limited operation space, meanwhile, the operation efficiency is improved, and the seat body replacement time is shortened.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to a cabin structure and an unmanned aerial vehicle. Background Art

[0002] With the application of drones in many fields such as aerial photography, surveying and mapping, logistics, security, electricity, environmental protection, film and television, scientific research, education and agriculture, improving the operating efficiency of drones has become the current main development direction. In these different fields, drones need to quickly replace payloads such as equipment, batteries or items according to mission requirements. However, due to multiple factors such as the payload seat, the space occupied by the payload in the cabin, and the size of the body opening, the disassembly and assembly space of the payload seat is limited, making it difficult to quickly disassemble and install the payload seat, and the disassembly and assembly efficiency is low. Summary of the invention

[0003] In view of the above problems existing in the prior art, the present invention provides a cabin structure and an unmanned aerial vehicle to improve the technical problem that the payload seat of the existing unmanned aerial vehicle is limited by space and is difficult to quickly disassemble and install.

[0004] In order to achieve the above-mentioned purpose and other related purposes, the first aspect of the present invention provides a cabin structure, which includes a body, a seat and a clamping mechanism. The body includes an opening and a cavity, and the opening is connected to the cavity. The seat enters the cavity from the opening and is installed in the cavity. The clamping mechanism includes a fixed seat and a clamping member, the fixed seat is fixedly installed in the cavity and is located on the outside of the seat, and the clamping member is movably connected to the fixed seat. The clamping member has a first state of clamping the seat and a second state of releasing the seat.

[0005] In an embodiment of the cabin structure of the present invention, the fixing seat is rotatably connected to the pressing member, and the pressing member has a first position rotated to the top of the seat body and a second position rotated to the outside of the seat body.

[0006] In an embodiment of the cabin structure of the present invention, a limiting block is provided on the fixing seat, and when the pressing member rotates to the first position, the limiting block abuts against the pressing member.

[0007] In one embodiment of the cabin structure of the present invention, the pressing member includes a connecting seat, a first connecting rod, a second connecting rod and a third connecting rod, the connecting seat is rotatably connected to the fixing seat, one end of the first connecting rod is rotatably connected to the connecting seat, and the second connecting rod is hinged to the other end of the first connecting rod. The third connecting rod is rotatably connected to an end of the second connecting rod away from the first connecting rod, and is slidably connected to the connecting seat, so as to abut and press the seat body in the first state. In an embodiment of the cabin structure of the present invention, the clamping member further comprises a handle portion, and the handle portion is fixedly connected to the first connecting rod to drive the third connecting rod to clamp or release the seat body.

[0008] In an embodiment of the cabin structure of the present invention, the length dimension of the handle portion is greater than the length dimension of the first connecting rod.

[0009] In one embodiment of the cabin structure of the present invention, the cabin structure further comprises a first limiting structure, the first limiting structure comprises a first protrusion and a first groove, the first protrusion is arranged on one of the fixing seat and the connecting seat, and the first groove is correspondingly arranged on the other of the fixing seat and the connecting seat. In the first state, the first protrusion is inserted into the first groove.

[0010] In one embodiment of the cabin structure of the present invention, the cavity includes a supporting plate, the seat body is disposed on the supporting plate, and a second limiting structure is disposed between the seat body and the supporting plate.

[0011] In one embodiment of the cabin structure of the present invention, the second limiting structure includes a second protrusion and a second groove, the second protrusion is arranged on one of the seat body and the support plate, the second groove is correspondingly arranged on the other of the seat body and the support plate, and the second protrusion is inserted into the second groove.

[0012] A second aspect of the present invention further provides an unmanned aerial vehicle, comprising a cabin structure as described in any one of the above items.

[0013] The present invention provides a cabin structure and an unmanned aerial vehicle. By accurately matching the size relationship between the seat and the opening, the opening area is minimized while ensuring the passability of the seat, significantly reducing the risk of stress concentration in the fuselage due to an excessively large opening, avoiding the influence of the structural strength of the fuselage itself due to an excessively large opening, and ensuring the overall structural rigidity and aerodynamic integrity of the fuselage. The clamping mechanism adopts a movable connection design, which can complete the fixing or disassembly of the seat without complex positioning, and reduces the dependence on precision machining positioning and the difficulty of operation due to limited operating space. At the same time, the clamping and releasing of the seat by the clamping member can adapt to seat modules of different specifications, realize the rapid disassembly and replacement of different seat modules, improve operating efficiency, and reduce the replacement time of the seat. BRIEF DESCRIPTION OF THE DRAWINGS In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present invention. For ordinary technicians in this field, other embodiments can be obtained based on these drawings without paying creative work.

[0014] Figure 1 This is a structural schematic diagram of a cabin structure in an embodiment of the present invention; Figure 2 It is a structural perspective view of an embodiment of the cabin structure of the present invention; Figure 3 It is a partial structural schematic diagram of the seat body installation state in an embodiment of the cabin body structure of the present invention; Figure 4 It is a top view of the partial structure of the seat body in the installation state in one embodiment of the cabin body structure of the present invention; Figure 5 It is a partial structural schematic diagram of the seat body installation process in an embodiment of the cabin body structure of the present invention; Figure 6 The structure of the clamping mechanism in the first state in one embodiment of the cabin structure of the present invention is schematically shown. Figure 1 ; Figure 7 The structure of the clamping mechanism in the first state in one embodiment of the cabin structure of the present invention is schematically shown. Figure 2 ; Figure 8 The structure of the clamping mechanism in the second state in one embodiment of the cabin structure of the present invention is shown in FIG. Figure 1 ; Fig. 9 The structure of the clamping mechanism in the second state in one embodiment of the cabin structure of the present invention is shown in FIG. Figure 2 ; Fig.10 It is a cross-sectional view of the structure of the clamping mechanism in the second state in one embodiment of the cabin structure of the present invention; Fig.11 It is a top view of the structure in which the clamping mechanism in one embodiment of the cabin structure of the present invention is in the first position; Fig.12 This is a top view of the structure in the second position of the clamping mechanism in one embodiment of the cabin structure of the present invention.

[0015] Component number description: 100, fuselage; 101, opening; 102, cavity; 1021, support plate; 110, fuselage skin; 120, frame; 130, hatch; 200, seat; 300, clamping mechanism; 301, first hinge point; 302, second hinge point; 303, third hinge point; 310, fixed seat; 311, limit block; 312, convex portion; 320, clamping member; 321, connecting seat; 3211, through hole; 3212, notch; 322, first connecting rod; 323, second connecting rod; 324, third connecting rod; 325, handle; 330, rotating shaft; 400, first limiting structure; 410, first protrusion; 420, first groove; 500, second limiting structure; 510, second protrusion; 520, second groove. DETAILED DESCRIPTION

[0016] The following is an explanation of the embodiments of the present invention by specific examples, and those skilled in the art can easily understand other advantages and effects of the present invention from the contents disclosed in this specification. The present invention can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present invention. It should be noted that the features in the following embodiments and the embodiments can be combined with each other without conflict. It should also be understood that the terms used in the embodiments of the present invention are intended to describe specific embodiments, rather than to limit the scope of protection of the present invention. The test methods for which specific conditions are not specified in the following examples are usually carried out under conventional conditions or according to the conditions recommended by the manufacturers.

[0017] When numerical ranges are given in the embodiments, it should be understood that unless otherwise specified in the present invention, both endpoints of each numerical range and any value between the two endpoints can be selected. Unless otherwise defined, all technical and scientific terms used in the present invention are familiar to those skilled in the art and the description of the present invention, and any method, device and material of the prior art similar or equivalent to the method, device and material in the embodiments of the present invention can also be used to implement the present invention.

[0018] It should be noted that the terms such as "upper", "lower", "left", "right", "middle" and "one" etc. used in this specification are only for the convenience of description and are not intended to limit the scope of implementation of the present invention. Changes or adjustments to their relative relationships, without substantially changing the technical content, should also be regarded as the scope of implementation of the present invention.

[0019] In order to improve the technical problem that the load seat of the existing UAV is limited by space and difficult to quickly disassemble and install, the present invention provides a cabin structure and a UAV. The cabin structure can complete the fixing or disassembly of the seat without complicated positioning, and reduces the dependence on precision machining positioning and the difficulty of operation due to limited operating space, improves operating efficiency, and reduces the time for changing the seat.

[0020] See also Figures 1 to 12In a first aspect, the present invention provides a cabin structure, which includes a body 100, a seat 200 and a clamping mechanism 300. The body 100 includes an opening 101 and a cavity 102, the opening 101 is connected to the cavity 102, and the opening 101 is adapted to the seat 200. By accurately matching the size relationship between the seat 200 and the opening 101, the area of ​​the opening 101 is minimized while ensuring the passability of the seat 200, significantly reducing the risk of stress concentration in the body 100 caused by an excessively large opening 101, avoiding the structural strength of the body 100 itself affected by an excessively large opening 101, and ensuring the overall structural rigidity and aerodynamic integrity of the body 100. The opening 101 may be opened at any position on the side, top or bottom of the body 100, as long as the seat 200 can be ensured to smoothly enter the cavity 102. The cavity 102 serves as a load compartment inside the fuselage 100. The cavity 102 is generally a space enclosed by the fuselage skin 110 and the frame 120 of the fuselage 100 for accommodating loads. For example, in one embodiment, the side walls and bottom walls of the cavity 102 are formed by a part of the structure of the existing frame 120, and the top wall of the cavity 102 is formed by a part of the fuselage skin 110. An opening 101 is provided on the fuselage skin 110, and a hatch 130 is detachably installed on the opening 101 of the fuselage skin 110. The hatch 130 covers the opening 101 to ensure the integrity of the fuselage 100 as a whole. However, in other embodiments, the side walls or bottom walls of the cavity 102 may also be formed by combining the fuselage skin 110 and the frame 120 of the existing fuselage structure, but the present invention is not limited thereto.

[0021] The seat 200 is a load-bearing platform. The type of load is not limited. For example, the load is a battery or device that needs to be disassembled and replaced by the drone, or it can be other items carried according to mission requirements. The load is pre-fixed to the seat 200, and the seat 200 and the load enter the cavity 102 from the opening 101 and are installed in the cavity 102. Specifically, in this embodiment, the opening 101 is located at the top of the cavity 102, and the seat 200 is installed from the opening 101 to the bottom of the cavity 102 along the Z-axis direction, and is fixed in the cavity 102 by the clamping mechanism 300, thereby realizing the installation and fixation of the seat 200 in the cavity 102.

[0022] Among them, see Figures 3 to 10The clamping mechanism 300 includes a fixing seat 310 and a clamping member 320. The fixing seat 310 is fixedly installed in the cavity 102 and is located on the outside of the seat body 200. The fixing seat 310 can be installed at the bottom of the cavity 102 or on the inner side of the cavity 102. As long as the fixing seat 310 is firmly connected to the body 100, the fixing seat 310 is fixedly installed in the cavity 102 in any manner, which can be welding, bonding or screw connection, but is not limited thereto. Specifically, in this embodiment, the fixing seat 310 is installed on the side wall of the cavity 102, that is, the fixing seat 310 is connected to the skeleton 120 by screws, and the fixing seat 310 is located on the outside of the seat body 200, so that the installation position of the fixing seat 310 does not interfere with the installation path of the seat body 200 from the opening 101 into the cavity 102. The clamping member 320 is movably connected to the fixing seat 310. The way of active connection between the pressing member 320 and the fixed seat 310 is not limited. The pressing member 320 and the fixed seat 310 can be connected by sliding or rotating, as long as the pressing member 320 can press and fix the seat 200. The pressing member 320 has a first state of pressing the seat 200 and a second state of releasing the seat 200. Specifically, in this embodiment, when the seat 200 is placed at the bottom of the cavity 102, the seat 200 is supported on the skeleton 120, and the pressing member 320 abuts against the upper part of the seat 200, and cooperates with the skeleton 120 to press and fix the seat 200 in the cavity 102, limiting the displacement movement of the seat 200 in any direction. The structural type of the pressing member 320 is not limited, for example, it can be a handle screw, or it can be a connecting rod mechanism using a mechanical dead point. It should be noted that the number of the pressing mechanism 300 can be a single group or multiple groups, as long as the pressing and fixing of the seat 200 can be satisfied. Specifically, in this embodiment, there are two groups of the clamping mechanisms 300 . The two groups of the clamping mechanisms 300 are symmetrically disposed on both sides of the base 200 and are located in the cavity 102 .

[0023] In the cabin structure and drone of the present invention, the clamping mechanism 300 adopts a movable connection design, which can complete the fixing or disassembly of the seat body 200 without complex positioning, and reduces the dependence on precision machining positioning. At the same time, after the seat body 200 enters the cavity 102 from the opening 101, the difficulty of operation and locking is reduced under the premise of limited operating space. The clamping member 320 quickly realizes the clamping and release of the seat body 200, realizes the rapid disassembly and replacement of different seat body modules, improves the operating efficiency, and reduces the replacement time of the seat body 200.

[0024] See also Figure 3 , Figure 4 , Figure 5 , Fig.11 and Fig.12, in order to smoothly place the seat body 200 supporting the load from the opening 101 into the cavity 102, and reduce the difficulty of the operation during the installation of the seat body 200. In an embodiment of the cabin structure of the present invention, the fixed seat 310 is rotatably connected with the pressing member 320, and the pressing member 320 has a first position that rotates to the top of the seat body 200 and a second position that rotates to the outside of the seat body 200, so as to avoid the seat body 200 on the installation path. Specifically, the pressing member 320 is rotatably connected with the fixed seat 310 through the rotating shaft 330, and the axial direction of the rotating shaft 330 is consistent with the installation direction of the seat body 200, that is, the pressing member 320 can rotate around the Z axis. When the seat body 200 is to be installed in the cavity 102, the pressing member 320 rotates to the second position. When the pressing member 320 is in the second position, the pressing member 320 does not interfere with the installation path of the seat body 200, and the seat body 200 can be smoothly placed in the bottom of the cavity 102 without deliberately avoiding the pressing member 320. When the seat body 200 is located at the bottom of the cavity 102, the pressing member 320 rotates to the top of the seat body 200, that is, the pressing member 320 can press and fix the side of the seat body 200 along the Z axis. On the contrary, when the seat body 200 needs to be disassembled, the pressing member 320 is in the second state, releasing the pressing and fixing of the seat body 200, and at the same time, the pressing member 320 rotates to the second position, so that the pressing member 320 is located outside the seat body 200 and no longer interferes with the disassembly path of the seat body 200. Through the above structural design, the disassembly efficiency of the seat body 200 in a limited operating space is further improved, and precise positioning is not required, which reduces the disassembly time.

[0025] See also Figure 3 and Fig.11 In one embodiment of the cabin structure of the present invention, in order to further improve the accuracy of the rotation of the pressing member 320 and prevent the pressing member 320 from rotating excessively beyond the pressing and fixing position of the pressing member 320 on the seat body 200, a limit block 311 is further provided on the fixing seat 310. The limit block 311 limits the maximum rotation position of the rotation movement of the pressing member 320. The limit block 311 cooperates with the fixing seat 310 to limit the reciprocating rotation movement of the pressing member 320 between the first position and the second position. Specifically, in this embodiment, when the pressing member 320 rotates to the first position, the limit block 311 abuts against the pressing member 320 to limit the further rotation of the pressing member 320 relative to the fixing seat 310. The limit block 311 provides a clear stop position, simplifies the operation process, enables the pressing member 320 to be quickly positioned to a better pressing position, and improves the operation efficiency.

[0026] See also Figures 6 to 10In one embodiment of the cabin structure of the present invention, the pressing member 320 includes a connecting seat 321, a first connecting rod 322, a second connecting rod 323 and a third connecting rod 324. In the Z-axis direction, the connecting seat 321 is rotatably connected to the fixed seat 310 through the rotating shaft 330, and the connecting seat 321 rotates around the Z-axis direction. The side of the connecting seat 321 away from the fixed seat 310 is hingedly connected to the first connecting rod 322. In addition, along the installation direction of the seat body 200, the lower end of the first connecting rod 322 is hingedly connected to the upper end of the second connecting rod 323, and the lower end of the second connecting rod 323 is hingedly connected to the upper end of the third connecting rod 324. In the Z-axis direction, a through hole 3211 adapted to the third connecting rod 324 is provided on the connecting seat 321, and the third connecting rod 324 passes through the through hole 3211. Under the driving action of the first connecting rod 322 and the second connecting rod 323, the third connecting rod 324 slides relative to the connecting seat 321 along the Z-axis direction. In the first state, the third connecting rod 324 abuts against and presses the seat body 200 , and in the second state, the third connecting rod 324 does not contact the seat body 200 .

[0027] See also Figure 7 and Figure 8 In one embodiment of the cabin structure of the present invention, the pressing member 320 further includes a handle portion 325, which is fixedly connected to the first connecting rod 322 to drive the third connecting rod 324 to press or release the seat body 200. Specifically, the handle portion 325 is an operating rod for manually operating the rotation of the first connecting rod 322. When the handle portion 325 is manually operated to pull up, the first connecting rod 322 rotates upward around the connecting seat 321, thereby driving the hinged second connecting rod 323 and the third connecting rod 324 to move upward, and the bottom of the third connecting rod 324 releases the pressing of the seat body 200, so that the pressing member 320 is in the second state. Conversely, along the Z-axis direction, the handle portion 325 is pressed downward, the first connecting rod 322 rotates downward around the connecting seat 321, thereby driving the hinged second connecting rod 323 and the third connecting rod 324 to move downward, and the bottom of the third connecting rod 324 abuts and presses the seat body 200, so that the pressing member 320 is in the first state. The first connecting rod 322 is controlled to rotate by manually operating the handle 325. The clamping member 320 is easy to use. It can be locked by simply rotating and pressing, and unlocked by lifting and rotating. The rotation of the clamping member 320 has a limit structure, which further simplifies the operation process. It does not require precise positioning and can quickly achieve the clamping and fixing of the seat body 200.

[0028] See also Figures 6 to 10The hinge point between the connecting seat 321 and the first connecting rod 322 is the first hinge point 301, the hinge point between the first connecting rod 322 and the second connecting rod 323 is the second hinge point 302, and the hinge point between the second connecting rod 323 and the third connecting rod 324 is the third hinge point 303. When the first connecting rod 322, the second connecting rod 323 and the third connecting rod 324 are collinear along the Z axis, the second hinge point 302 is at a dead point, and the lower end of the third connecting rod 324 abuts against the seat body 200, and the seat body 200 is pressed and fixed in the Z axis by the pressing member 320.

[0029] See also Figure 3 and Fig.10 In one embodiment of the cabin structure of the present invention, in order to ensure that the pressing member 320 uses the mechanical dead point to press and fix the seat body 200 along the Z-axis direction, and prevent the seat body 200 from shaking in the horizontal direction to destroy the pressing effect of the pressing member 320, in one embodiment of the cabin structure of the present invention, the cavity 102 includes a support plate 1021, and the seat body 200 is arranged on the support plate 1021. A second limiting structure 500 is arranged between the seat body 200 and the support plate 1021. The second limiting structure 500 limits the horizontal shaking of the seat body 200 in the cavity 102, so that the seat body 200 has only the degree of freedom along the installation direction. And the degree of freedom of the seat body 200 along the installation direction is controlled by the pressing member 320. The support plate 1021 may be a part of the existing UAV skeleton 120 structure, or a part of the fuselage skin 110 structure, which is not limited here. Specifically, in this embodiment, the support plate 1021 serves as the bottom wall of the cavity 102 and is a part of the existing UAV skeleton 120 structure. The type of the second limiting structure 500 is not limited, for example, it may be a stopper structure, a pin positioning structure, etc.

[0030] See also Figure 5In one embodiment of the cabin structure of the present invention, the second limiting structure 500 adopts a pin limiting structure. The second limiting structure 500 includes a second protrusion 510 and a second groove 520. The second protrusion 510 is arranged on one of the seat body 200 and the supporting plate 1021, and the second groove 520 is correspondingly arranged on the other of the seat body 200 and the supporting plate 1021. The second protrusion 510 is inserted into the second groove 520. Specifically, in this embodiment, the second protrusion 510 is located on the supporting plate 1021, and the second groove 520 is opened on the seat body 200. The second protrusion 510 and the second groove 520 are plugged and positioned, so that the seat body 200 has only a degree of freedom along the installation direction in the non-locking state, which can ensure the accuracy of the pressing member 320 being pressed against the seat body 200 after rotating to the first position. At the same time, it is ensured that the pressing member 320 uses the mechanical dead point to self-lock and fix the seat body 200 to avoid locking failure. Furthermore, in order to ensure that the second groove 520 on the seat body 200 is smoothly inserted into the second protrusion 510, the insertion end of the second protrusion 510 is provided with a chamfer to reduce the difficulty of docking the second groove 520 with the second protrusion 510, so that the seat body 200 can be quickly inserted and positioned.

[0031] See also Fig.10 In one embodiment of the cabin structure of the present invention, the length of the handle portion 325 is greater than the length of the first connecting rod 322. Specifically, in this embodiment, the handle portion 325 and the first connecting rod 322 are an integral structure, and the handle portion 325 is located on the rod body of the first connecting rod 322 away from the connecting seat 321. Since the rotation of the first connecting rod 322 is controlled by manually operating the handle portion 325 to press or lift up, and then the third connecting rod 324 is controlled to press or release the seat body 200, the operating length of the handle portion 325 is greater than the length of the line between the two hinge points (the first hinge point 301 and the second hinge point 302) of the first connecting rod 322. By using the principle of a labor-saving lever, the difficulty of operating the handle portion 325 can be effectively reduced, achieving the effect of labor-saving and rapid disassembly and assembly of the seat body 200. The pressing member 320 does not require the use of operating tools or accurate positioning of the connection position, thereby improving the disassembly and assembly efficiency of the seat body 200 and meeting the use requirements of rapid tool-free disassembly and assembly.

[0032] See also Figure 6 and Fig.10In order to further enhance the pressing and fixing effect of the pressing member 320 on the seat body 200 by using the mechanical dead point, in one embodiment of the cabin structure of the present invention, the cabin structure further includes a first limiting structure 400, and the first limiting structure 400 includes a first protrusion 410 and a first groove 420. The first protrusion 410 is arranged on one of the fixing seat 310 and the connecting seat 321, and the first groove 420 is correspondingly arranged on the other of the fixing seat 310 and the connecting seat 321. When the pressing member 320 is in the first state, the first protrusion 410 is inserted into the first groove 420. Specifically, in this embodiment, a notch 3212 is provided on the connecting seat 321, and a convex portion 312 is provided on the fixing seat 310, and the convex portion 312 is inserted into the notch 3212. Along the Z-axis direction, the convex part 312 is connected to the connecting seat 321 through the rotating shaft 330, and the installation spacing of the notch 3212 is greater than the installation spacing of the convex part 312, so that the connecting seat 321 can slide relative to the fixed seat 310 along the axial direction of the rotating shaft 330. A first groove 420 is provided at the lower part of the convex part 312, and a first protrusion 410 is provided at the lower part of the notch 3212 corresponding to the position of the first groove 420. When the pressing member 320 is in the first state, the first protrusion 410 is inserted into the first groove 420, so as to prevent the pressing member 320 from rotating under external force in the pressing state and thus escaping from the seat body 200, and ensure that the pressing member 320 is always in a pressing state with respect to the seat body 200 in the first state.

[0033] See also Figure 6 and Figure 8 In order to further ensure the self-locking effect of the mechanical dead point of the clamping piece 320 on the seat body 200, in one embodiment of the cabin structure of the present invention, during the process of pressing the handle portion 325 downward, the second hinge point 302 passes the dead point position, and at the same time, the connecting seat 321 moves axially upward relative to the fixed seat 310, the lower end of the protrusion 312 abuts against the lower end of the groove 3212, the hinge between the first connecting rod 322 and the second connecting rod 323 abuts against the connecting seat 321, and the lower end of the third connecting rod 324 abuts against the seat body 200, and the clamping piece 320 is in the first state, that is, the clamping piece 320 is in the self-locking state, limiting the displacement movement of the seat body 200 along the Z axis.

[0034] The second aspect of the present invention further provides a drone, which includes the cabin structure described in any of the above embodiments. It should be noted that the drone of the present invention also includes conventional structures and conventional functional modules of existing drones such as a tail, a gimbal, a communication module, a control module, and a power module, which will not be described one by one here.

[0035] In the cabin structure and the UAV of the present invention, by accurately matching the size relationship between the seat and the opening, the opening area is minimized while ensuring the passability of the seat, significantly reducing the risk of stress concentration in the fuselage due to an excessively large opening, avoiding the influence of an excessively large opening on the structural strength of the fuselage itself, and ensuring the rigidity and aerodynamic integrity of the overall structure of the fuselage. The clamping mechanism adopts a movable connection design, which can complete the fixing or disassembly of the seat without complex positioning, and reduces the dependence on precision machining positioning and the difficulty of operation due to limited operating space. At the same time, the clamping and release of the seat by the clamping member can adapt to seat modules of different specifications, realize the rapid disassembly and replacement of different seat modules, improve operating efficiency, and reduce the replacement time of the seat. This improves the technical problem that the load seat of the existing UAV is limited by space and difficult to quickly realize disassembly and installation. Therefore, the present invention effectively overcomes some practical problems in the prior art and has high utilization value and use significance.

[0036] The above embodiments are merely illustrative of the principles and effects of the present invention, and are not intended to limit the present invention. Anyone familiar with the art may modify or alter the above embodiments without departing from the spirit and scope of the present invention. Therefore, all equivalent modifications or alterations made by a person of ordinary skill in the art without departing from the spirit and technical concept disclosed by the present invention shall still be covered by the claims of the present invention.

Claims

1. A cabin structure, characterized in that: include: A body, the body comprising an opening and a cavity, the opening being in communication with the cavity; A seat body, the seat body enters into the cavity from the opening and is installed in the cavity; A clamping mechanism, the clamping mechanism comprising a fixing seat and a clamping piece, the fixing seat is fixedly installed in the cavity and is located outside the seat body; the clamping piece is movably connected to the fixing seat; The pressing member has a first state of pressing the seat body and a second state of releasing the seat body.

2. The cabin structure according to claim 1, characterized in that: The fixing seat is rotatably connected to the pressing member, and the pressing member has a first position where it is rotated to the top of the seat body and a second position where it is rotated to the outside of the seat body.

3. The cabin structure according to claim 2, characterized in that: A limiting block is arranged on the fixing seat, and when the pressing member rotates to the first position, the limiting block abuts against the pressing member.

4. The cabin structure according to claim 1, characterized in that: The clamping member includes a connecting seat, a first connecting rod, a second connecting rod and a third connecting rod. The connecting seat is rotatably connected to the fixed seat, one end of the first connecting rod is rotatably connected to the connecting seat, and the second connecting rod is hinged to the other end of the first connecting rod; the third connecting rod is rotatably connected to one end of the second connecting rod away from the first connecting rod, and is slidably connected to the connecting seat to abut and clamp the seat body in the first state.

5. The cabin structure according to claim 4, characterized in that: The pressing member further comprises a handle portion, and the handle portion is fixedly connected to the first connecting rod to drive the third connecting rod to press or release the seat body.

6. The cabin structure according to claim 5, characterized in that: The length dimension of the handle portion is greater than the length dimension of the first connecting rod.

7. The cabin structure according to claim 4, characterized in that: The cabin structure also includes a first limiting structure, which includes a first protrusion and a first groove. The first protrusion is arranged on one of the fixing seat and the connecting seat, and the first groove is correspondingly arranged on the other of the fixing seat and the connecting seat. In the first state, the first protrusion is inserted into the first groove.

8. The cabin structure according to claim 1 or 4, characterized in that: The cavity comprises a supporting plate, and the seat body is arranged on the supporting plate; a second limiting structure is arranged between the seat body and the supporting plate.

9. The cabin structure according to claim 8, characterized in that: The second limiting structure includes a second protrusion and a second groove, the second protrusion is arranged on one of the base body and the supporting plate, the second groove is correspondingly arranged on the other of the base body and the supporting plate, and the second protrusion is inserted into the second groove.

10. A drone, characterized in that: The cabin structure comprises the cabin structure as described in any one of claims 1 to 9.

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