CN214986021U

CN214986021U - Frame and flight equipment

Info

Publication number: CN214986021U
Application number: CN202120546005.XU
Authority: CN
Inventors: 张玉
Original assignee: Fengyi Technology Shenzhen Co ltd
Current assignee: Fengyi Technology Shenzhen Co ltd
Priority date: 2021-03-16
Filing date: 2021-03-16
Publication date: 2021-12-03
Anticipated expiration: 2031-03-16

Abstract

The application discloses a rack and flight equipment, wherein the rack comprises a machine body, a sliding part and wings, a sliding rail extending along the front-back direction is arranged on the machine body, and the sliding part is connected with the sliding rail in a sliding manner; the wing is provided with a hinged end and a free end which are opposite, the hinged end of the wing is provided with a first hinged part which is rotationally connected with the fuselage, the wing is provided with a second hinged part, and the second hinged part is hinged with the sliding part in a sliding manner along the length direction of the sliding rail; the rotation axis of the wing relative to the fuselage and the rotation axis of the wing relative to the sliding piece extend along the vertical direction of the fuselage; the sliding part is used for sliding back and forth relative to the fuselage to push the wings to rotate relative to the fuselage between a folding position and an unfolding position, and the distance between the free ends of the wings and the fuselage in the unfolding position is larger than the distance between the free ends of the wings and the fuselage in the folding position. The wing can be folded or unfolded by enabling the sliding piece to slide relative to the fuselage in a reciprocating mode, and the wing folding device is more convenient to use outdoors.

Description

Frame and flight equipment

Technical Field

The application relates to the technical field of flight equipment, in particular to a rack and flight equipment.

Background

Along with the rapid development of commodity circulation trade, the fixed wing unmanned aerial vehicle that hangs down has combined the VTOL lift process place to occupy fewly, and the efficient advantage of fixed wing is also more and more common in the use of transportation, transports the express delivery through the fixed wing unmanned aerial vehicle that hangs down, can improve the conveying efficiency of express delivery, reduces the cost of labor.

In order to conveniently accommodate the drooping fixed-wing unmanned aerial vehicle, the fuselage and the wings of the fixed-wing unmanned aerial vehicle are generally arranged into detachable structures, and when the drooping fixed-wing unmanned aerial vehicle needs to be accommodated, the fuselage and the wings are detached so as to be accommodated.

However, the disassembly and assembly of the fuselage and the wings of the vertical fixed wing unmanned aerial vehicle require tools, which leads to complicated disassembly and assembly and inconvenient outdoor use.

SUMMERY OF THE UTILITY MODEL

The embodiment of the application provides a frame and flight equipment, aims at solving the problem that the fuselage and the wing of the existing flight equipment are complex to disassemble and assemble and are inconvenient for outdoor use.

The embodiment of the present application provides a frame, the frame includes:

the device comprises a machine body, wherein a sliding rail extending along the front-back direction is arranged on the machine body;

the sliding piece is connected with the sliding rail in a sliding manner;

the wing is provided with a hinged end and a free end which are opposite, the hinged end of the wing is provided with a first hinged part, the first hinged part is rotatably connected with the fuselage, and the wing extends along the vertical direction of the fuselage relative to the rotation axis of the fuselage; the wing is provided with a second hinge part, the second hinge part is hinged with the sliding part in a sliding manner along the length direction of the sliding rail, and the wing extends along the vertical direction of the fuselage relative to the rotating axis of the sliding part;

the sliding piece is used for sliding in a reciprocating mode relative to the fuselage to push the wings to rotate relative to the fuselage between a folding position and an unfolding position, and the distance between the free end and the fuselage when the wings are in the unfolding position is larger than the distance between the free end and the fuselage when the wings are in the folding position.

Optionally, a hinge rod is arranged on the wing to form the second hinge part, and the hinge rod extends along the up-down direction of the fuselage;

the slider includes the connecting portion that extend along its sliding direction, be provided with the confession on the connecting portion the inserted sliding tray of articulated arm, the extending direction of sliding tray with the length direction of slide rail is the contained angle, the width of sliding tray is more than or equal to the diameter of articulated arm.

Optionally, a cavity is formed in the fuselage, a through hole is formed in a position, corresponding to the wing, of a side wall of the cavity, the wing penetrates through the through hole to extend out of the fuselage when in the unfolded position, and the wing is accommodated in the cavity when in the folded position.

Optionally, the sliding member includes a baffle connected to the connecting portion, the baffle closes the through hole when the sliding member pushes the wing to rotate to the folded position, and the baffle opens the through hole when the sliding member pushes the wing to rotate to the unfolded position.

Optionally, the baffle is located in the cavity, connecting portion are the platelike setting, connecting portion are located the baffle deviates from one side of lateral wall, the face of connecting portion with the upper and lower direction of fuselage is the contained angle, the sliding tray set up in on the face of connecting portion.

Optionally, the connecting portion is connected to the lower edge of the baffle, and the sliding groove is formed in the plate surface on the upper side of the connecting portion; alternatively, the first and second electrodes may be,

the connecting part is connected to the edge of the upper side of the baffle, and the sliding groove is formed in the plate surface of the lower side of the connecting part.

Optionally, in a direction from the rear end to the front end of the body, a distance between the sliding groove and the baffle gradually decreases.

Optionally, a guide groove is formed in the connecting portion, the guide groove extends along the sliding direction of the sliding member, the width of the guide groove is greater than or equal to the diameter of the hinge rod, and the guide groove is located at one end of the sliding groove along the direction from the rear end to the front end of the body and is communicated with the sliding groove.

Optionally, the hinge rod extends downwards from the wing and is inserted into the sliding groove, and the second hinge part is positioned on the upper side of the wing; alternatively, the hinge rod extends upward from the wing and is inserted into the sliding groove, and the second hinge part is located at the lower side of the wing.

The embodiment of this application still provides a flight equipment, flight equipment includes:

a power system;

the power system is arranged on the wing and/or the fuselage of the frame and is used for providing flight power for the frame.

The frame that this application embodiment provided is connected through the articulated end that makes the wing rotates with the fuselage through first articulated portion, and set up the slider on the fuselage, the second articulated portion that makes slider and wing slides with the slider along the length direction of slide rail and articulates, through making the relative fuselage reciprocating sliding of slider, can make the relative fuselage of wing rotate between folding position and expansion position, in order to realize folding and the expansion of wing, need not in addition to use the instrument with wing and fuselage to disassemble and assemble, it is more convenient to use in the open air.

Drawings

The technical solution and other advantages of the present application will become apparent from the detailed description of the embodiments of the present application with reference to the accompanying drawings.

FIG. 1 is a schematic, partial, structural view of an embodiment of a airframe provided with an embodiment of the present application with wings in a folded position;

FIG. 2 is a top view of the frame of FIG. 1;

FIG. 3 is a partial schematic structural view of an embodiment of a airframe provided by an embodiment of the present application with wings in a deployed position;

fig. 4 is a top view of the frame of fig. 3.

A frame 100; a body 110; a through-hole 111; a wing 120; a hinged end 121; a free end 122; a first hinge 123; a second hinge 124; a slide member 130; a connecting portion 131; a slide groove 1311; a guide groove 1312; a baffle 132; a handle 1321.

Detailed Description

The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. It is to be understood that the embodiments described are only a few embodiments of the present application and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

In the description of the present application, it is to be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the present application and for simplicity in description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed in a particular orientation, and be operated in a particular manner, and are not to be construed as limiting the present application. Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", may explicitly or implicitly include one or more of the described features. In the description of the present application, "a plurality" means two or more unless specifically limited otherwise.

In the description of the present application, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; may be mechanically connected, may be electrically connected or may be in communication with each other; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.

In this application, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may comprise direct contact of the first and second features, or may comprise contact of the first and second features not directly but through another feature in between. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.

The following disclosure provides many different embodiments or examples for implementing different features of the application. In order to simplify the disclosure of the present application, specific example components and arrangements are described below. Of course, they are merely examples and are not intended to limit the present application. Moreover, the present application may repeat reference numerals and/or letters in the various examples, such repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed. In addition, examples of various specific processes and materials are provided herein, but one of ordinary skill in the art may recognize applications of other processes and/or use of other materials.

The embodiment of the application provides a frame and flight equipment. The following are detailed below.

Firstly, the embodiment of the application provides a rack, which comprises a machine body, a sliding part and wings, wherein the machine body is provided with a sliding rail extending along the front-back direction; the sliding piece is connected with the sliding rail in a sliding manner; the wing is provided with a hinged end and a free end which are opposite, the hinged end of the wing is provided with a first hinged part, the first hinged part is rotatably connected with the fuselage, and the wing extends along the vertical direction of the fuselage relative to the rotation axis of the fuselage; the wing is provided with a second hinge part, the second hinge part is hinged with the sliding part in a sliding way along the length direction of the sliding rail, and the wing extends along the up-down direction of the fuselage relative to the rotating axis of the sliding part; the sliding part is used for sliding back and forth relative to the fuselage to push the wings to rotate relative to the fuselage between a folding position and an unfolding position, and the distance between the free ends of the wings and the fuselage in the unfolding position is larger than the distance between the free ends of the wings and the fuselage in the folding position.

Fig. 1 is a partial schematic structural diagram of an embodiment of a rack according to an embodiment of the present disclosure. As shown in fig. 1, the airframe 100 includes a fuselage 110 and wings 120, the wings 120 are disposed on both sides of the fuselage 110 (only the wing 120 on the left side of the fuselage 110 is shown in fig. 1), and when the airframe 100 is used in a flight device (not shown), a power system (not shown) of the flight device is disposed on the wings 120 of the airframe 100 to provide flight power for the airframe 100. Alternatively, the power system of the flight device may be disposed on the fuselage 110 for providing horizontal flight power to the airframe 100, and the wings 120 for providing lift to the airframe 100.

Of course, the power system may be disposed on both the fuselage 110 and the wing 120. Specific examples thereof include: the flying apparatus is a vertical-lift fixed-wing drone, such that the power system includes a plurality of rotary-wing engines disposed on the fuselage 110 and the two wings 120, wherein the rotational axis of one part of the rotary-wing engines extends in the up-down direction to provide the lifting power to the airframe 100, and the rotational axis of the other part of the rotary-wing engines extends in the front-rear direction to provide the horizontal flight power to the airframe 100. The power system may also be a jet engine or other engine capable of providing power.

As shown in fig. 1, the wing 120 of the airframe 100 has an opposite hinged end 121 and a free end 122, the hinged end 121 of the wing 120 is provided with a first hinge 123, the first hinge 123 is rotatably connected with the fuselage 110, and the wing 120 extends along the up-down direction of the fuselage 110 relative to the rotation axis of the fuselage 110. The rotation axis of the wing 120 relative to the fuselage 110 may be parallel to the vertical direction of the fuselage 110, or may form a certain angle with the vertical direction of the fuselage 110.

Thus, the wing 120 may be rotated relative to the fuselage 110 by rotating the wing 120 between a folded position (shown in fig. 1 and 2) and an unfolded position (shown in fig. 3 and 4), wherein the distance between the free end 122 of the wing 120 and the fuselage 110 in the unfolded position is greater than the distance between the free end 122 of the wing 120 and the fuselage 110 in the folded position. When the flying equipment needs to be used, the wings 120 are rotated to the unfolding position relative to the fuselage 110, and when the flying equipment needs to be stored, the wings 120 are rotated to the folding position relative to the fuselage 110, so that the size of the rack 100 is reduced, and the operation is very convenient.

The specific angle of the wing 120 rotating relative to the fuselage 110 from the folded position (shown in fig. 1 and 2) to the unfolded position (shown in fig. 3 and 4) can be determined according to the actual situation. In some embodiments, the length direction of the wing 120 may be parallel to the front-back direction of the fuselage 110 when the wing 120 is in the unfolded position, and the length direction of the wing 120 may be perpendicular to the front-back direction of the fuselage 110 when the wing 120 is in the folded position, that is, the rotation angle of the wing 120 relative to the fuselage 110 from the folded position (shown in fig. 1 and 2) to the unfolded position (shown in fig. 3 and 4) is 90 °. Of course, the rotation angle of the wing 120 from the folded position (shown in fig. 1 and 2) to the unfolded position (shown in fig. 3 and 4) with respect to the fuselage 110 may also be 80 °, 110 °, and so on, and is not limited herein.

As shown in fig. 1 and 2, the frame 100 may further include a slider 130, the slider 130 is slidably connected to the fuselage 110, and the slider 130 is connected to the wing 120, so that the wing 120 is pushed to rotate back and forth between the folded position and the unfolded position by sliding the slider 130 to and fro relative to the fuselage 110.

Alternatively, a slide rail (not shown) extending in the front-rear direction is provided on the body 110, and the slider 130 is slidably coupled to the slide rail. Thereby, the slider 130 can slide back and forth in the front-rear direction with respect to the body 110. Wherein, the slide rail extends along fore-and-aft direction: the slide rail may be parallel to the front-back direction of the body 110, or the length direction of the slide rail may form a certain angle with the front-back direction of the body 110.

The wing 120 is provided with a second hinge 124, the second hinge 124 is slidably hinged with the slider 130 along the length direction of the slide rail, and the wing 120 extends along the up-down direction of the fuselage 110 relative to the rotation axis of the slider 130. The rotation axis of the wing 120 relative to the slider 130 may be parallel to the vertical direction of the fuselage 110, or may form a certain angle with the vertical direction of the fuselage 110.

Therefore, the rotation axis of the wing 120 relative to the slider 130 is parallel to or at an angle with respect to the rotation axis of the wing 120 relative to the fuselage 110, and when the slider 130 slides along the slide rail to and fro relative to the fuselage 110, the wing 120 can be pushed to rotate between the folded position and the unfolded position relative to the fuselage 110.

The second hinge portion 124 of the wing 120 and the slider 130 are slidably hinged along the length direction of the slide rail, which means that the second hinge portion 124 of the wing 120 and the slider 130 can rotate relative to the slider 130 while sliding along the length direction of the slide rail. When the slider 130 slides, the second hinge portion 124 of the wing 120 can slide relative to the slider 130 and rotate relative to the slider 130.

According to the frame 100 provided by the embodiment of the application, the hinge end 121 of the wing 120 is rotatably connected with the fuselage 110 through the first hinge part 123, the slider 130 is arranged on the fuselage 110, the slider 130 and the second hinge part 124 of the wing 120 are slidably hinged with the slider 130, and the slider 130 is reciprocally slid relative to the fuselage 110, so that the wing 120 can be rotated between the folding position and the unfolding position relative to the fuselage 110, the folding and unfolding of the wing 120 can be realized, the wing 120 and the fuselage 110 do not need to be disassembled and assembled by using additional tools, and the use is more convenient outdoors.

Alternatively, as shown in fig. 1, 2 and 3, a hinge rod may be provided on the wing 120 to form the second hinge 124, the hinge rod extending in the up-down direction of the fuselage 110; correspondingly, the sliding member 130 includes a connecting portion 131 extending along the sliding direction thereof, a sliding groove 1311 for inserting the hinge rod is disposed on the connecting portion 131, the extending direction of the sliding groove 1311 forms an angle with the length direction of the slide rail, and the width of the sliding groove 1311 is greater than or equal to the diameter of the hinge rod.

When the sliding member 130 slides along the length direction of the sliding rail, the side wall of the sliding groove 1311 can apply a force to the hinge rod, which has a component in the width direction of the body 110 (the direction parallel to the left-right direction in fig. 1) to push the wing 120 to rotate relative to the body 110. Therefore, the wing 120 can be pushed to rotate between the unfolding position and the folding position relative to the body 110 by controlling the sliding piece 130 to slide back and forth along the length direction of the sliding rail.

As shown in fig. 2 and 4, the sliding groove 1311 may be inclined from left to right in the direction from the front end to the rear end of the fuselage 110, so that when the slider 130 slides along the direction from the front end to the rear end of the fuselage 110, the wing 120 is pushed to rotate to the right relative to the fuselage 110 until the wing 120 rotates to the folded position, and when the slider 130 slides along the direction from the rear end to the front end of the fuselage 110, the wing 120 is pushed to rotate to the left relative to the fuselage 110 until the wing 120 rotates to the unfolded position.

Or, the sliding groove 1311 may be inclined from left to right in the direction from the rear end to the front end of the fuselage 110, so that when the slider 130 slides along the direction from the front end to the rear end of the fuselage 110, the wing 120 is pushed to rotate left relative to the fuselage 110 until the wing 120 rotates to the unfolded position, and when the slider 130 slides along the direction from the rear end to the front end of the fuselage 110, the wing 120 is pushed to rotate right relative to the fuselage 110 until the wing 120 rotates to the folded position.

In other embodiments, a guide rail may be disposed on the slider 130, the extending direction of the guide rail forms an angle with the sliding direction of the slider 130, a slider is slidably connected on the guide rail, the slider is hinged with the second hinge portion 124 of the wing 120, wherein the second hinge portion 124 of the wing 120 extends along the up-down direction of the fuselage 110 relative to the rotation axis of the slider, and the sliding hinge connection of the second hinge portion 124 of the wing 120 and the slider 130 can also be realized.

The specific extending direction of the guide rail can refer to the extending direction of the sliding groove 1311, and is not described herein again.

As shown in fig. 1 and 3, the fuselage 110 has a cavity therein, a through hole 111 is formed in a sidewall of the cavity corresponding to the wing 120, the wing 120 passes through the through hole 111 and extends outside the fuselage 110 when in the extended position, and the wing 120 is accommodated in the cavity when in the folded position. Therefore, when the airframe 100 is stored, the wings 120 are stored in the storage cavities of the airframe 110, so that the wings 120 can be well protected, and the wings 120 can be prevented from being damaged due to collision in the moving or transporting process of the airframe 100.

Wherein, the sliding member 130 may further include a baffle 132 connected to the connecting portion 131, and when the sliding member 130 pushes the wing 120 to rotate to the extended position, the baffle 132 of the sliding member 130 opens the through hole 111, so that the wing 120 can extend out of the fuselage 110 through the through hole 111; when the slider 130 pushes the wing 120 to rotate to the folded position, the baffle 132 of the slider 130 closes the through hole 111 to prevent water, dust, etc. outside the fuselage 110 from entering the fuselage 110.

Wherein, can make baffle 132 be located the cavity, connecting portion 131 is the platelike setting, and connecting portion 131 is located the one side that baffle 132 deviates from the lateral wall, and the face of connecting portion 131 is the contained angle with the upper and lower direction of fuselage 110, and sliding tray 1311 sets up on the face of connecting portion 131. By forming the connection portion 131 in a plate-like structure, the structural strength of the connection portion 131 in the width direction (direction parallel to the left and right) of the fuselage 110 can be increased, and the sliding groove 1311 of the connection portion 131 can more stably push the wing 120 to rotate relative to the fuselage 110.

Of course, the connecting portion 131 may have a rod-like structure or another structure, and the sliding groove 1311 may be provided in the connecting portion 131.

In other embodiments, the baffle 132 may be located outside the body 110, the connecting portion 131 is located in the cavity, and the connecting portion 131 passes through the through hole 111 to connect with the baffle 132, and the connecting structure 111 may slide in the through hole 111 along the length direction of the slide rail, so that the baffle 132 of the sliding member 130 can open or close the through hole 111.

Alternatively, as shown in fig. 1 and 3, the connection portion 131 may be connected to the lower edge of the shutter 132, and the slide groove 1311 may be formed on the upper plate surface of the connection portion 131. This can reduce the width of the baffle 132 in the height direction of the body 110, and the width of the baffle 132 can be set to cover the through-hole 111.

The hinge rod on the wing 120 can be extended downward from the wing 120 and inserted into the sliding slot 1311, and correspondingly, the second hinge 124 on the wing 120 is located on the upper side of the wing 120, so as to avoid the connection portion 131 of the slider 130 interfering with the second hinge 124 in the process that the slider 130 pushes the wing 120 to rotate.

Of course, the connecting portion 131 may be connected to the upper edge of the flap 132, the sliding groove 1311 may be opened on the lower side of the connecting portion 131, and the hinge rod may be inserted into the sliding groove 1311 by extending upward from the wing 120, so that the width of the flap 132 in the height direction of the fuselage 110 may be reduced.

Wherein, the hinge rod on the wing 120 can be extended upwards from the wing 120 and inserted into the sliding slot 1311, and correspondingly, the second hinge part 124 on the wing 120 is located at the lower side of the wing 120, so as to avoid the connection part 131 of the slider 130 interfering with the second hinge part 124 in the process that the slider 130 pushes the wing 120 to rotate.

It should be noted that the sliding groove 1311 may extend through the connection portion 131, or may not extend through the connection portion 131, and only after the hinge rod is inserted into the sliding groove 1311, the side wall of the sliding groove 1311 can push the wing 120 to rotate relative to the fuselage 110.

Alternatively, as shown in fig. 2 and 4, the distance between the sliding groove 1311 and the baffle 132 may be gradually reduced in the direction from the rear end to the front end of the body 110. Thus, the wing 120 can be rotated to the right to the folded position with respect to the fuselage 110 by controlling the slider 130 to slide in the front-to-rear direction of the fuselage 110 to apply a rightward thrust to the hinge lever through the side wall of the sliding groove 1311; the wing 120 is rotated to the left to the deployed position relative to the fuselage 110 by controlling the slider 130 to slide in the direction from the rear end to the front end of the fuselage 110 to apply a leftward thrust to the hinge rod through the side wall of the sliding slot 1311.

Optionally, as shown in fig. 2 and 4, a guide groove 1312 is further formed on the connection portion 131, the guide groove 1312 extends along the sliding direction of the slider 130, the width of the guide groove 1312 is greater than or equal to the diameter of the hinge rod, and the guide groove 1312 is located at one end of the sliding groove 1311 along the direction from the rear end to the front end of the body 110 and is communicated with the sliding groove 1311.

Since the guide groove 1312 extends along the sliding direction of the slider 130, when the wing 120 is in the folded position and the hinge rod on the wing 120 is located in the guide groove 1312, even if the slider 130 slides relative to the fuselage 110, the wing 120 is not pushed to rotate by the side wall of the guide groove 1312, and the wing 120 can be kept in the folded position, so that the wing 120 can be prevented from being rotated from the folded position to the unfolded position to collide with the baffle 132 of the slider 130 prematurely.

It can be understood that the length of the wing 120 is generally longer, and thus the length of the through hole 111 on the sidewall of the fuselage 110 in the length direction of the slide rail is also longer, and the baffle 132 of the slider 130 needs to slide a longer distance from the position where the through hole 111 is closed to the position where the through hole 111 is opened.

By forming the guide groove 1312 on the connecting portion 131, in the process that the slider 130 slides along the front end to the rear end of the fuselage 110, the baffle 132 can open a part of the through hole 111 first, and the hinge rod on the wing 120 is located in the guide groove 1312, so that the wing 120 is kept in the folded position, and when the sliding distance of the slider 130 is the same as the length of the guide groove 1312, the hinge rod on the wing 120 enters the slide groove 1311, so that the wing 120 rotates from the folded position to the unfolded position without colliding with the baffle 132 of the slider 130.

Alternatively, as shown in fig. 1 and 2, the second hinge 124 is located at the hinge end 121 of the wing 120, and when the wing 120 is in the folded position, the second hinge 124 is located at a side of the first hinge 123 close to the side wall, so that the second hinge 124 is more stably engaged with the guide groove 1312 and the sliding groove 1311, and when the slider 130 slides back and forth along the length direction of the sliding rail, the wing 120 can be more smoothly pushed to rotate between the unfolded position and the folded position relative to the fuselage 110.

Optionally, as shown in fig. 1 to 4, a handle 1321 is further provided on the baffle 132, and the handle 1321 passes through the through hole 111 and protrudes out of the outer surface of the body 110. Therefore, the operator can conveniently control the sliding of the slider 130 through the handle 1321, and further control the wing 120 to rotate between the unfolding position and the folding position.

The embodiment of the present application further provides a flight device, which includes a rack, and the rack structure refers to the above embodiments, and since the rack employs all technical solutions of all embodiments of the above rack, the rack at least has all beneficial effects brought by the technical solutions of the above embodiments, and details are not repeated herein.

The flight equipment (not shown) includes a power system (not shown) disposed on the wing 120 and/or the fuselage 110 of the airframe 100 for providing flight power to the airframe.

It should be noted that the flight device in the embodiment of the present application may be any flight device including the above-mentioned airframe, such as an unmanned aerial vehicle, a helicopter, and the like, and is not limited herein.

In the foregoing embodiments, the descriptions of the respective embodiments have respective emphasis, and for parts that are not described in detail in a certain embodiment, reference may be made to related descriptions of other embodiments.

The above detailed description is made on a rack and a flight device provided by the embodiment of the present application, and a specific example is applied in the detailed description to explain the principle and the implementation of the present application, and the description of the above embodiment is only used to help understand the technical scheme and the core idea of the present application; those of ordinary skill in the art will understand that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications or substitutions do not depart from the spirit and scope of the present disclosure as defined by the appended claims.

Claims

1. A rack, the rack comprising:

the sliding piece is connected with the sliding rail in a sliding manner;

2. The airframe as recited in claim 1, wherein a hinge rod is provided on said wing to form said second hinge, said hinge rod extending in an up-down direction of said fuselage;

3. The airframe as recited in claim 2, wherein a cavity is provided in said fuselage, a through hole is provided in a side wall of said cavity at a position corresponding to said wing, said wing extends outside said fuselage through said through hole when in said deployed position, and said wing is received in said cavity when in said collapsed position.

4. The airframe as recited in claim 3, wherein said slider includes a flap connected to said connecting portion, said flap closing said through hole when said slider pushes said wing to rotate to said folded position, said flap opening said through hole when said slider pushes said wing to rotate to said unfolded position.

5. The frame according to claim 4, wherein the baffle is located in the cavity, the connecting portion is in a plate shape, the connecting portion is located on a side of the baffle facing away from the side wall, a plate surface of the connecting portion forms an included angle with the vertical direction of the machine body, and the sliding groove is formed in the plate surface of the connecting portion.

6. The frame according to claim 5, wherein the connecting part is connected to the lower edge of the baffle plate, and the sliding groove is formed in the plate surface on the upper side of the connecting part; alternatively, the first and second electrodes may be,

7. The airframe as recited in claim 6, wherein a distance between said slide channel and said barrier decreases in a direction from a rear end to a front end of said airframe.

8. The frame according to claim 7, wherein the connecting portion has a guide groove formed therein, the guide groove extending in the sliding direction of the sliding member, the guide groove having a width greater than or equal to the diameter of the hinge rod, the guide groove being located at an end of the sliding groove in the direction from the rear end to the front end of the body and communicating with the sliding groove.

9. The airframe as recited in claim 6, wherein said hinge rod extends downwardly from said wing and is inserted into said slide channel, said second hinge being located on an upper side of said wing; alternatively, the hinge rod extends upward from the wing and is inserted into the sliding groove, and the second hinge part is located at the lower side of the wing.

10. A flying apparatus, characterized in that the flying apparatus comprises:

a power system;

and a frame as claimed in any one of claims 1 to 9, wherein the power system is provided on the wing and/or fuselage of the frame for providing flight power to the frame.