Airborne Equipment, Aircraft and Method for Plugging and Unplugging Airborne Equipment

Abstract

The present invention provides an airborne device, an aircraft, and a method for inserting and removing the airborne device, which relates to the technical field of automatic pod replacement (or battery replacement) of aircraft. The airborne device provided by the present invention is configured to be detachably inserted into the cabin. The airborne device is slidably engaged with the cabin through a coordination mechanism. During the process of inserting and removing the airborne device along the cabin, the coordination mechanism forms a clearance space between the airborne device and the side wall of the cabin. The airborne device provided by the present invention can reduce the frictional resistance and wear during the process of inserting and removing the airborne device relative to the cabin.

Description

Technical Field

[0001] The present invention relates to the technical field of automatic pod (or battery) replacement for aircraft, and particularly to an airborne device, an aircraft, and a method for inserting and removing an airborne device. Background Art

[0002] Airborne devices are usually fixed in the cabin by bolts, which makes it inconvenient to disassemble and assemble the airborne devices. For airborne devices assembled in a direct insertion manner, most of them use an interference fit between the airborne device and the cabin for positioning. During the process of inserting and removing the airborne device, both the airborne device and the cabin are worn, and the frictional resistance is relatively large. This not only makes it inconvenient to disassemble and assemble the airborne device, but also will cause inaccurate positioning of the airborne device in the long run, affecting the assembly stability of the airborne device. Summary of the Invention

[0003] The purpose of the present invention is to provide an airborne device, an aircraft, and a method for inserting and removing an airborne device, so as to reduce the frictional resistance and wear during the insertion and removal of the airborne device relative to the cabin.

[0004] In a first aspect, the airborne device provided by the present invention is configured to be detachably inserted into the cabin; the airborne device is slidably engaged with the cabin through a coordination mechanism; during the process of inserting and removing the airborne device along the cabin, the coordination mechanism forms a clearance space between the airborne device and the side wall of the cabin.

[0005] In an embodiment of the first aspect, the coordination mechanism includes a protrusion, and the protrusion is provided on the outer side wall of the airborne device and / or on the inner side wall of the cabin.

[0006] In an embodiment of the first aspect, the protrusion includes: a first protrusion and a second protrusion; in a cross-section of the airborne device perpendicular to the insertion direction, the first protrusion and the second protrusion are arranged at intervals, and the first protrusion and the second protrusion respectively extend along the insertion direction.

[0007] In an embodiment of the first aspect, the coordination mechanism has a bearing surface; during the process of inserting and removing the airborne device into and from the cabin, the bearing surface bears the airborne device.

[0008] In an embodiment of the first aspect, the coordination mechanism has a guiding surface, and the guiding surface forms an angle with the bearing surface; the guiding surface is configured to guide the airborne device during the process of inserting and removing the airborne device into and from the cabin.

[0009] In an embodiment of the first aspect, the coordination mechanism includes: a slot arranged on one of the airborne equipment and the cabin, and an insert block arranged on the other; the insert block is inserted into the slot to form the avoidance gap between the airborne equipment and the inner wall of the cabin.

[0010] In an embodiment of the first aspect, the slot has an entrance end and a limit end, and during the process of inserting the onboard equipment into the cabin along the insertion direction, the plug is inserted from the entrance end to the limit end; the slot also has a first side wall and a second side wall arranged relative to the first side wall, and the distance between the first side wall and the second side wall gradually decreases from the entrance end to the limit end.

[0011] In an embodiment of the first aspect, the first side wall includes a first curved surface, and the second side wall includes a second curved surface arranged relative to the first curved surface; the second curved surface is located below the first curved surface, and the curvature radius of the second curved surface is greater than the curvature radius of the first curved surface.

[0012] In an embodiment of the first aspect, a first limiting surface is connected to a side of the first curved surface close to the limiting end, a second limiting surface is connected to a side of the second curved surface close to the limiting end, and the first limiting surface is connected to the second limiting surface; from a side close to the entrance end to the limiting end, a distance between the first limiting surface and the second limiting surface gradually decreases.

[0013] In an embodiment of the first aspect, the insert block includes: a guide portion and an extension portion connected to the guide portion; the guide portion has a first end face and a second end face; from an end connected to the extension portion to an end away from the extension portion, the distance between the first end face and the second end face gradually decreases.

[0014] In an implementation manner of the first aspect, at least one of the airborne equipment and the cabin is provided with an alignment portion; when the airborne equipment is inserted into the cabin, the airborne equipment and the cabin cooperate through the alignment portion, and eliminate the margin of movement of the airborne equipment relative to the cabin in any direction having an angle with the insertion direction.

[0015] In an implementation of the first aspect, the airborne equipment is provided with an alignment portion adapted to the opening of the cabin; when the airborne equipment is inserted into the cabin, the alignment portion closes the gap between the airborne equipment and the opening of the cabin.

[0016] In a second aspect, the present invention provides an aircraft, wherein the aircraft is provided with the cabin compatible with the airborne equipment provided in the first aspect.

[0017] In a third aspect, the present invention provides a method for inserting and removing an airborne device. The method for inserting and removing an airborne device includes: disposing a coordination mechanism on the inner side wall of the airborne device or the cabin; the coordination mechanism forms a clearance space between the airborne device and the inner side wall of the cabin; inserting and removing the airborne device along the inner side wall of the cabin.

[0018] The embodiments of the present invention bring the following beneficial effects: The airborne device is configured to be detachably inserted into the cabin. The airborne device is slidably engaged with the cabin through the coordination mechanism. During the process of inserting and removing the airborne device along the cabin, the coordination mechanism guides and positions the airborne device, and forms a clearance space between the airborne device and the side wall of the cabin, thereby reducing the wear between the airborne device and the cabin, and reducing the frictional resistance during the process of inserting and removing the airborne device.

[0019] In order to make the above objects, features, and advantages of the present invention more obvious and understandable, the following specifically enumerates preferred embodiments and, in conjunction with the accompanying drawings, makes a detailed description as follows. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the related art, the following will briefly introduce the drawings required for use in the description of the specific embodiments or the related art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0021] Figure 1 Schematic diagram of the first airborne device and the cabin provided by the embodiment of the present invention;

[0022] Figure 2 Schematic diagram of the first airborne device provided by the embodiment of the present invention;

[0023] Figure 3 Cross-sectional view of the first airborne device and the cabin provided by the embodiment of the present invention;

[0024] Figure 4 Schematic diagram of the second airborne device and the insertion block provided by the embodiment of the present invention;

[0025] Figure 5 Schematic diagram of the second airborne device provided by the embodiment of the present invention;

[0026] Figure 6 Schematic diagram of the third airborne device and the insertion block provided by the embodiment of the present invention.

[0027] Icons: 001 - airborne equipment; 101 - avoidance space; 002` - cabin; 011 - protrusion; 111 - first protrusion; 112 - second protrusion; 012 - alignment part; 013 - bearing surface; 014 - guiding surface; 015 - slot; 1501 - limiting end; 1502 - entrance end; 151 - first side wall; 1511 - first curved surface; 1512 - first limiting surface; 152 - second side wall; 1521 - second curved surface; 1522 - second limiting surface; 016 - insertion block; 161 - guiding part; 1611 - first end face; 1612 - second end face; 162 - extension part. Detailed implementation manners

[0028] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0029] In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", 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 cannot be understood as a limitation of the present invention. In addition, the terms "first", "second", and "third" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance. Physical quantities in the formulas, unless otherwise specifically marked, should be understood as the basic quantities of the basic units of the International System of Units, or derived quantities derived from the basic quantities through mathematical operations such as multiplication, division, differentiation, or integration.

[0030] In the description of the present invention, it should be noted that unless otherwise clearly specified and limited, the terms "installation", "connection", and "connection" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the internal communication of two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0031] Embodiment 1

[0032] Such as Figure 1 And Figure 4As shown in the figure, the airborne device provided by the embodiment of the present invention is configured to be detachably inserted into the cabin 002`. The airborne device 001 is slidably engaged with the cabin 002` through a coordination mechanism. During the process of inserting and removing the airborne device 001 along the cabin 002`, the coordination mechanism forms a clearance space 101 between the airborne device 001 and the side wall of the cabin 002`. Among them, the airborne device 001 includes a battery or a pod. By forming the clearance space 101 between the airborne device 001 and the cabin 002`, the friction area between the airborne device 001 and the cabin 002` can be reduced, thereby reducing the wear and frictional resistance during the insertion and removal process.

[0033] In some embodiments, the coordination mechanism may adopt a slide rail, and the slide rail is arranged on the airborne device 001 or the cabin 002`. During the process of inserting and removing the airborne device 001, the airborne device 001 and the cabin 002` are engaged through the slide rail, and the slide rail supports and guides the airborne device 001, so as to form a clearance space 101 between the airborne device 001 and the side wall of the cabin 002`.

[0034] It should be noted that the airborne device 001 can be arranged outside the cabin 002`. The coordination mechanism adopts a slide rail and extends along the outer side wall of the cabin 002`. By matching the airborne device 001 with the slide rail, a clearance space 101 can be formed between the airborne device 001 and the cabin 002`. In contrast, inserting the airborne device 001 into the cabin 002` can avoid the wind resistance generated by the exposure of the airborne device 001 and can prevent the airborne device 001 from being eroded by natural environments such as rain.

[0035] In this embodiment, the coordination mechanism includes a convex portion 011. The convex portion 011 is arranged on the outer side wall of the airborne device 001, and / or the convex portion 011 is arranged on the inner side wall of the cabin 002`. Among them, the convex portion 011 can be arranged on the outer side wall of the airborne device 001. When the airborne device 001 is inserted into the cabin 002`, the convex portion 011 can support the airborne device 001 and form a clearance space 101 between the airborne device 001 and the cabin 002`. Similarly, the convex portion 011 can also be arranged on the inner side wall of the cabin 002`, or convex portions 011 are respectively arranged on the airborne device 001 and the cabin 002`. The convex portion 011 located between the airborne device 001 and the cabin 002` has a supporting effect and can form a clearance space 101 between the airborne device 001 and the cabin 002`.

[0036] Furthermore, the convex portion 011 is arranged on the battery housing or the pod housing. The side wall of the battery housing or the pod housing bulges outward to form the convex portion 011. In this way, the convex portion 011 can be formed by means such as stamping or bending, and the convex portion 011 is integrally formed with the housing, which is beneficial to improving the structural stability.

[0037] Such asFigure 1 and Figure 2 As shown, the protrusion 011 includes: a first protrusion 111 and a second protrusion 112; on a cross section of the airborne device 001 perpendicular to the insertion direction, the first protrusion 111 and the second protrusion 112 are arranged at intervals, and the first protrusion 111 and the second protrusion 112 extend along the insertion direction respectively. The airborne device 001 is supported by the first protrusion 111 and the second protrusion 112 respectively, so that the airborne device 001 can slide smoothly along the cabin 002'.

[0038] In some embodiments, the cross-sectional shape of the cabin 002' approaches a rectangle, and the first protrusion 111 and the second protrusion 112 are arranged at two diagonal positions in a one-to-one correspondence, and extend along the edges of the cabin 002' respectively. The first protrusion 111 and the second protrusion 112 jointly support the airborne device 001, thereby preventing the airborne device 001 from being deflected in the cabin 002'. The first protrusion 111 and the second protrusion 112 jointly support the airborne device 001, thereby reducing the contact area between the airborne device 001 and the inner wall of the cabin 002', and forming a space avoidance gap 101 between the airborne device 001 and the cabin 002'.

[0039] In this embodiment, the first protrusion 111 and the second protrusion 112 are respectively arranged at the bottom of the airborne device 001. When the airborne device 001 is plugged in and out of the cabin 002', the first protrusion 111 and the second protrusion 112 are respectively abutted against the lower end surface of the inner cavity of the cabin 002', and the first protrusion 111 and the second protrusion 112 can jointly support the airborne device 001. Under the action of gravity, a space gap 101 can be formed between the top of the airborne device 001 and the top surface of the inner cavity of the cabin 002'.

[0040] like Figure 1 and Figure 3 As shown, the first protrusion 111 and the second protrusion 112 are arranged one-to-one at the two edges of the bottom of the airborne device 001. The bottom surface of the first protrusion 111 and the bottom surface of the second protrusion 112 are respectively abutted against the lower end surface of the inner cavity of the cabin 002', and the first protrusion 111 and the second protrusion 112 both play a bearing role for the airborne device 001; the side surface of the first protrusion 111 and the side surface of the second protrusion 112 are respectively abutted against the two side walls of the cabin 002', and the side surface of the first protrusion 111 and the side surface of the second protrusion 112 both play a guiding role during the plugging and unplugging process of the airborne device 001, and can generate a space-avoiding gap 101 on both sides of the airborne device 001.

[0041] Furthermore, the coordination mechanism has a bearing surface 013 ; when the airborne device 001 is plugged in or out of the cabin 002 ′, the bearing surface 013 bears the airborne device 001 .

[0042] In some embodiments, the coordination mechanism may adopt the protrusion 011, or the coordination mechanism adopts a groove provided at the bottom of the airborne device 001. The groove extends along the insertion direction and is adapted to a protrusion connected to the bottom surface of the inner cavity of the cabin 002`. During the insertion and extraction of the airborne device 001, the bottom surface of the protrusion 011 can serve as the bearing surface 013, and the end surface where the groove abuts against the top surface of the protrusion can also serve as the bearing surface 013.

[0043] In this embodiment, the first protrusion 111 and the second protrusion 112 are respectively provided at the bottom of the airborne device 001, and both the first protrusion 111 and the second protrusion 112 are provided with the bearing surface 013. The first protrusion 111 and the second protrusion 112 respectively abut against the bottom surface of the inner cavity of the cabin 002` through the bearing surface 013, and a clearance space 101 is formed between the top surface of the airborne device 001 and the top surface of the inner cavity of the cabin 002` under the action of gravity.

[0044] Furthermore, the coordination mechanism has a guiding surface 014, and the guiding surface 014 has an angle with the bearing surface 013; the guiding surface 014 is configured to align the airborne device 001 during the insertion and extraction of the airborne device 001 into and out of the cabin 002`. Taking the coordination mechanism including a groove provided at the bottom of the airborne device 001 as an example, a protrusion connected to the bottom surface of the inner cavity of the cabin 002` is inserted into the groove, and the side wall of the groove can serve as the guiding surface 014 to prevent the airborne device 001 from deflecting left and right relative to the cabin 002`, so that clearance spaces 101 are respectively formed on both sides of the airborne device 001.

[0045] In this embodiment, the first protrusion 111 is provided at one edge of the bottom of the airborne device 001, and the second protrusion 112 is provided at the other edge of the bottom of the airborne device 001. A guiding surface 014 is provided on the side of the first protrusion 111 facing away from the second protrusion 112, and a guiding surface 014 is provided on the side of the second protrusion 112 facing away from the first protrusion 111. By respectively abutting against the left and right side walls of the cabin 002` through the two guiding surfaces 014, clearance spaces 101 can be respectively formed on both sides of the airborne device 001, and the airborne device 001 can be prevented from shifting left and right relative to the cabin 002`.

[0046] Embodiment Two

[0047] As Figure 4 shown, as a supplementary solution to Embodiment One, the coordination mechanism includes: a slot 015 provided on one of the airborne device 001 and the cabin 002`, and a plug 016 provided on the other; the plug 016 is inserted into the slot 015, and a clearance space 101 is formed between the airborne device 001 and the inner side wall of the cabin 002`.

[0048] In some embodiments, a slot 015 is provided on the inner sidewall of the cabin 002`. The airborne device 001 is provided with a plug block 016 adapted to the slot 015. When the airborne device 001 is inserted into the cabin 002`, the plug block 016 is inserted into the slot 015. The slot 015 guides the plug block 016, thereby guiding the airborne device 001 and forming a clearance space 101 between the airborne device 001 and the inner sidewall of the cabin 002`.

[0049] In this embodiment, to make the outer shape of the airborne device 001 relatively smooth, the slot 015 is provided on the airborne device 001. In addition, the airborne device 001 is provided with a plurality of slots 015, and the plurality of slots 015 are spaced apart on a plane perpendicular to the insertion direction. A plurality of plug blocks 016 are provided on the inner sidewall of the cabin 002`. The plurality of slots 015 can be correspondingly engaged with the plurality of plug blocks 016, thereby avoiding skew of the airborne device 001 during the insertion and extraction process. By inserting the plug block 016 into the slot 015, a guiding effect can be exerted on the airborne device 001, and thus a clearance space 101 is formed between the airborne device 001 and the inner sidewall of the cabin 002`, which can reduce the friction area between the airborne device 001 and the cabin 002` and reduce the frictional resistance of inserting and extracting the airborne device 001.

[0050] As Figure 4 and Figure 5 shown, the slot 015 has an inlet end 1502 and a limiting end 1501. During the process of inserting the airborne device 001 into the cabin 002` along the insertion direction, the plug block 016 is inserted from the inlet end 1502 into the limiting end 1501. The slot 015 also has a first sidewall 151 and a second sidewall 152 provided opposite to the first sidewall 151. From the inlet end 1502 to the limiting end 1501, the distance between the first sidewall 151 and the second sidewall 152 gradually decreases. The distance between the first sidewall 151 and the second sidewall 152 is larger at the inlet end 1502 to facilitate the insertion of the plug block 016 between the first sidewall 151 and the second sidewall 152. As the plug block 016 is inserted from the inlet end 1502 into the limiting end 1501, the distance between the first sidewall 151 and the second sidewall 152 gradually decreases, thereby guiding the plug block 016 and positioning the airborne device 001 at a corresponding position in the cabin 002`.

[0051] Further, the first side wall 151 includes a first curved surface 1511, and the second side wall 152 includes a second curved surface 1521 disposed opposite to the first curved surface 1511; the second curved surface 1521 is located below the first curved surface 1511, and the radius of curvature of the second curved surface 1521 is greater than that of the first curved surface 1511. When the insertion block 016 is inserted between the first curved surface 1511 and the second curved surface 1521, the insertion block 016 abuts against the first curved surface 1511 or the second curved surface 1521, thereby guiding the insertion block 016. The radius of curvature of the first curved surface 1511 is smaller, and from the side close to the entrance end 1502 to the side close to the limit end 1501, the first curved surface 1511 inclines towards the inner side of the slot 015 to a greater extent. When the insertion block 016 abuts against the first curved surface 1511, the first curved surface 1511 can exert a guiding effect on the insertion block 016, thereby correcting the insertion path of the insertion block 016. The radius of curvature of the second curved surface 1521 is larger, and from the side close to the entrance end 1502 to the side close to the limit end 1501, the second curved surface 1521 inclines towards the inner side of the slot 015 to a smaller extent. When the insertion block 016 abuts against the second curved surface 1521, the second curved surface 1521 has a bearing and guiding effect on the insertion block 016, and the inclination amplitude of the second curved surface 1521 slows down, which is beneficial to reducing the resistance of inserting the insertion block 016. In other words, during the insertion process of the airborne device 001, considering that the airborne device 001 sags under the action of gravity, the slot 015 provided on the airborne device 001 is deflected downward relative to the insertion block 016, and the insertion block 016 slides along the first curved surface 1511, and the first curved surface 1511 with a smaller radius of curvature exerts a guiding effect on the insertion block 016. When the insertion block 016 approaches the limit end 1501, the insertion block 016 is clamped between the first curved surface 1511 and the second curved surface 1521, realizing the calibration of the insertion block 016, and further enabling the accurate positioning of the airborne device 001 relative to the cabin 002`, and the insertion resistance is small.

[0052] Further, a first limiting surface 1512 is connected to one side of the first curved surface 1511 close to the limit end 1501, and a second limiting surface 1522 is connected to one side of the second curved surface 1521 close to the limit end 1501, and the first limiting surface 1512 is in contact with the second limiting surface 1522; from the side close to the entrance end 1502 to the limit end 1501, the distance between the first limiting surface 1512 and the second limiting surface 1522 gradually decreases. In the state where the airborne device 001 is inserted completely, the insertion block 016 is jointly limited by the first limiting surface 1512 and the second limiting surface 1522 in the insertion direction, and the insertion block 016 is clamped between the first limiting surface 1512 and the second limiting surface 1522, thereby ensuring the accurate positioning of the airborne device 001 relative to the cabin 002`. In addition, in the state where the airborne device 001 is inserted completely, a buckle can be used to lock the airborne device 001, thereby preventing the airborne device 001 from disengaging from the cabin 002`.

[0053] Further, the insertion block 016 includes a guiding portion 161 and an extension portion 162 connecting the guiding portion 161; the guiding portion 161 has a first end face 1611 and a second end face 1612; from one end of the connecting extension portion 162 to the end away from the extension portion 162, the distance between the first end face 1611 and the second end face 1612 gradually decreases. Wherein, the first end face 1611 and the second end face 1612 can form a pointed portion for guiding during the process of inserting the insertion block 016 into the insertion slot 015. In the state where the airborne device 001 is completely inserted, the first end face 1611 abuts against the second limiting surface 1522, the second end face 1612 abuts against the first limiting surface 1512, and the extension portion 162 is clamped between the first curved surface 1511 and the second curved surface 1521. The included angle between the first end face 1611 and the second end face 1612 is equal to the included angle between the first limiting surface 1512 and the second limiting surface 1522, and the guiding portion 161 contacts the side wall surface of the insertion slot 015, thereby ensuring the stable positioning of the airborne device 001.

[0054] As Figure 1 , Figure 2 and Figure 4 shown, at least one of the airborne device 001 and the cabin 002` is provided with a positioning portion 012; in the state where the airborne device 001 is inserted into the cabin 002`, the airborne device 001 and the cabin 002` are cooperated through the positioning portion 012, and the movement margin of the airborne device 001 relative to the cabin 002` in any direction having an included angle with the insertion direction is eliminated.

[0055] In some embodiments, the positioning portion 012 is arranged at the end of the insertion direction of the airborne device 001. In the state where the airborne device 001 is completely inserted into the cabin 002`, the positioning portion 012 cooperates with the inner side wall of the cabin 002`, thereby preventing the airborne device 001 from shaking in any direction having an included angle with the insertion direction relative to the cabin 002`. In addition, the positioning portion 012 can also be arranged at one end of the cabin 002` away from the hatch. Only when the airborne device 001 is completely inserted into the cabin 002`, the outer side wall of the airborne device 001 cooperates with the positioning portion 012, thereby ensuring the alignment of the airborne device 001 relative to the cabin 002`.

[0056] Further, the airborne device 001 is provided with a positioning portion 012 adapted to the opening of the cabin 002`; in the state where the airborne device 001 is inserted into the cabin 002`, the positioning portion 012 closes the gap between the airborne device 001 and the opening of the cabin 002`.

[0057] In this embodiment, the alignment part 012 is arranged on the airborne device 001. When the airborne device 001 is fully inserted into the cabin 002`, the alignment part 012 cooperates with the hatch, which can not only prevent the airborne device 001 from shaking in the cabin 002`, but also shield the clearance gap 101 between the airborne device 001 and the cabin 002`, thus preventing external dust from entering the cabin 002`. During the insertion process of the airborne device 001, the alignment part 012 does not rub against the cabin 002`, so the frictional resistance during the insertion process of the airborne device 001 can be reduced.

[0058] As Figure 4 and Figure 5 shown, the bottom of the airborne device 001 is set as a curved surface so that the airborne device 001 forms a streamlined shape when assembled on the aircraft to reduce wind resistance. As Figure 1 and Figure 6 shown, in another embodiment, the airborne device 001 can be set to any shape adapted to the cabin 002`.

[0059] Embodiment III

[0060] As Figure 1 shown, the aircraft provided by the embodiment of the present invention is provided with a cabin 002` adapted to the airborne device 001 provided by the above embodiment. The aircraft can be a rotary-wing UAV or a fixed-wing UAV. The aircraft is provided with a cabin 002`, and the airborne device 001 adopts a pod or a battery. By inserting and removing the airborne device 001, the disassembly and assembly of the pod or the battery can be realized. By forming a clearance gap 101 between the airborne device 001 and the cabin 002`, the wear and frictional resistance during the insertion and removal process can be reduced.

[0061] Embodiment IV

[0062] The method for inserting and removing the airborne device 001 provided by the embodiment of the present invention includes: arranging a coordination mechanism on the inner side wall of the airborne device 001 or the cabin 002`; the coordination mechanism forms a clearance gap 101 between the airborne device 001 and the inner side wall of the cabin 002`; inserting and removing the airborne device 001 along the inner side wall of the cabin 002`. Among them, the coordination mechanism is arranged on the side wall of the airborne device 001, or the coordination mechanism is arranged on the inner side wall of the cabin 002`. For the structure and function of the coordination mechanism, reference can be made to the above embodiment. By forming a clearance gap 101 between the airborne device 001 and the inner side wall of the cabin 002`, the wear and frictional resistance during the insertion and removal process of the airborne device 001 can be reduced.

[0063] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements on some or all of the technical features; and these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the various embodiments of the present invention.

Claims

1. An airborne device, characterized in that, The airborne device (001) is configured to be detachably inserted into the cabin (002`); The airborne device (001) is slidably engaged with the cabin (002`) through a coordination mechanism; During the process of inserting and removing the airborne device (001) along the cabin (002`), the coordination mechanism forms a clearance space (101) between the airborne device (001) and the side wall of the cabin (002`); The airborne device (001) includes a battery or a pod; The coordination mechanism includes a protrusion (011), and the protrusion (011) is disposed on the outer side wall of the airborne device (001), and / or, the protrusion (011) is disposed on the inner side wall of the cabin (002`).

2. The airborne device according to claim 1, wherein The protrusion (011) includes: a first protrusion (111) and a second protrusion (112); In a cross-section of the airborne device (001) perpendicular to the insertion direction, the first protrusion (111) and the second protrusion (112) are spaced apart, and the first protrusion (111) and the second protrusion (112) respectively extend along the insertion direction.

3. The airborne device according to claim 1, wherein The coordination mechanism has a bearing surface (013); During the process of inserting and removing the airborne device (001) into and out of the cabin (002`), the bearing surface (013) bears the airborne device (001).

4. The airborne device according to claim 3, characterized in that, The coordination mechanism has a guiding surface (014), and the guiding surface (014) has an included angle with the bearing surface (013); The guiding surface (014) is configured to align the airborne device (001) during the process of inserting and removing the airborne device (001) into and out of the cabin (002`).

5. The airborne device according to any one of claims 1-4, characterized in that, At least one of the airborne device (001) and the cabin (002`) is provided with a positioning portion (012); In a state where the airborne device (001) is inserted into the cabin (002`), the airborne device (001) and the cabin (002`) are engaged through the positioning portion (012), and the movement margin of the airborne device (001) relative to the cabin (002`) in any direction having an included angle with the insertion direction is eliminated.

6. The airborne device according to any one of claims 1-4, characterized in that, The airborne device (001) is provided with a positioning portion (012) adapted to the opening of the cabin (002`); In a state where the airborne device (001) is inserted into the cabin (002`), the positioning portion (012) closes the gap between the airborne device (001) and the opening of the cabin (002`).

7. An aircraft, characterized in that, The aircraft is provided with the cabin (002`) adapted to the airborne device (001) according to any one of claims 1-6.

8. An airborne device plugging and unplugging method, characterized in that, The method for inserting and removing the airborne device is applied to the aircraft according to claim 7, and the method for inserting and removing the airborne device includes: Disposing a coordination mechanism on the inner side wall of the airborne device (001) or the cabin (002`); The coordination mechanism forms a clearance space (101) between the airborne device (001) and the inner side wall of the cabin (002`); Inserting and removing the airborne device (001) along the inner side wall of the cabin (002`).

9. An airborne device, characterized in that The onboard equipment (001) is configured to be detachably inserted into the cabin (002'); The onboard equipment (001) is slidably matched with the cabin (002') via a matching mechanism; During the process of inserting and removing the airborne equipment (001) along the cabin (002'), the matching mechanism forms a space-avoiding gap (101) between the airborne equipment (001) and the side wall of the cabin (002'); The onboard equipment (001) includes a battery or a pod; The matching mechanism comprises: a slot (015) arranged on one of the onboard equipment (001) and the cabin (002'), and an insert block (016) arranged on the other; The insert block (016) is inserted into the slot (015) and forms the avoidance gap (101) between the onboard equipment (001) and the inner wall of the cabin (002').

10. The airborne device according to claim 9, characterized in that, The slot (015) has an entrance end (1502) and a limit end (1501), and when the airborne device (001) is inserted into the cabin (002') along the insertion direction, the insert block (016) is inserted from the entrance end (1502) into the limit end (1501); The slot (015) further comprises a first side wall (151) and a second side wall (152) arranged relative to the first side wall (151), and the distance between the first side wall (151) and the second side wall (152) gradually decreases from the inlet end (1502) to the limit end (1501).

11. The airborne device according to claim 10, characterized in that, The first side wall (151) comprises a first curved surface (1511), and the second side wall (152) comprises a second curved surface (1521) arranged relative to the first curved surface (1511); The second curved surface (1521) is located below the first curved surface (1511), and the radius of curvature of the second curved surface (1521) is greater than the radius of curvature of the first curved surface (1511).

12. The airborne device according to claim 11, characterized in that, A side of the first curved surface (1511) close to the limiting end (1501) is connected to a first limiting surface (1512), a side of the second curved surface (1521) close to the limiting end (1501) is connected to a second limiting surface (1522), and the first limiting surface (1512) and the second limiting surface (1522) are connected; From the side close to the inlet end (1502) to the limiting end (1501), the distance between the first limiting surface (1512) and the second limiting surface (1522) gradually decreases.

13. The airborne device according to claim 9, characterized in that, The insert block (016) comprises: a guide portion (161) and an extension portion (162) connected to the guide portion (161); The guide portion (161) has a first end surface (1611) and a second end surface (1612); From an end connected to the extension portion (162) to an end away from the extension portion (162), the distance between the first end surface (1611) and the second end surface (1612) gradually decreases.

14. The airborne device according to any one of claims 9-13, characterized in that, At least one of the onboard equipment (001) and the cabin (002') is provided with a positioning portion (012); In a state where the airborne device (001) is inserted into the cabin (002`), the airborne device (001) cooperates with the cabin (002`) through the alignment portion (012), and the movement margin of the airborne device (001) relative to the cabin (002`) in any direction having an angle with the insertion direction is eliminated.

15. The airborne device according to any one of claims 9-13, characterized in that, The airborne device (001) is provided with an alignment portion (012) adapted to the opening of the cabin (002`); In a state where the airborne device (001) is inserted into the cabin (002`), the alignment portion (012) closes the gap between the airborne device (001) and the opening of the cabin (002`).

16. An aircraft, characterized in that, The aircraft is provided with the cabin (002`) adapted to the airborne device (001) according to any one of claims 9-15.

17. An airborne device plugging and unplugging method, characterized in that, The method for inserting and removing the airborne device is applied to the aircraft according to claim 16, and the method for inserting and removing the airborne device includes: A coordination mechanism is arranged on the inner side wall of the airborne device (001) or the cabin (002`); The coordination mechanism forms a clearance space (101) between the airborne device (001) and the inner side wall of the cabin (002`); The airborne device (001) is inserted and removed along the inner side wall of the cabin (002`).

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