CN116141894A

CN116141894A - Aerocar wing folding structure and aerocar

Info

Publication number: CN116141894A
Application number: CN202310268699.9A
Authority: CN
Inventors: 陈恒; 李志虎; 李宏达; 程靖; 秦玉林; 张宁; 严路平; 夏婉莹
Original assignee: Chery Automobile Co Ltd
Current assignee: Chery Automobile Co Ltd
Priority date: 2023-03-15
Filing date: 2023-03-15
Publication date: 2023-05-23

Abstract

The invention discloses a aerocar wing folding structure and an aerocar, wherein the aerocar wing folding structure comprises: the rotary wing is rotatably connected with the fixed wing and is provided with a folding position and an unfolding position; one of the fixed wing and the rotary wing is provided with a first connecting part, the other one of the fixed wing and the rotary wing is provided with a second connecting part, when the rotary wing is positioned at the unfolding position, the first connecting part is fixedly matched with the second connecting part, and when the rotary wing is positioned at the folding position, the first connecting part is separated from the second connecting part. According to the folding structure of the aerocar wing, when the rotary wing is in the unfolding position, the first connecting part and the second connecting part are fixedly matched, so that the connecting strength of the rotary wing and the fixed wing can be enhanced, the structural stability of the rotary wing can be enhanced, the rotary wing can bear bending moment born by the rotary wing during flying, and the aerocar flies in the air in a fixed wing mode.

Description

Aerocar wing folding structure and aerocar

Technical Field

The invention relates to the field of aero-automobiles, in particular to an aero-automobile wing folding structure and an aero-automobile.

Background

In recent years, with the continuous development of innovative technologies such as aerospace control, intelligent transportation, modern communication and the like, the concept of a flying car has been developed, and unlike a common aircraft, the flying car not only needs to have a higher flying requirement, but also needs to meet the requirement of being able to normally run on a ground lane. As a manned aircraft, a aerocar needs longer wings to provide lift required by flight, and meanwhile, in order to meet the requirement of road driving, the aerocar must keep the same external dimension as a traditional car, so that the aerocar needs to be designed into a folded wing, and meanwhile, enough strength can be achieved when the wings are unfolded.

However, when the wing in the related art is unfolded, the wing receives a large bending moment in the flying process, so that the wing can not maintain the form of the fixed wing due to the overlarge bending moment in the flying process.

Disclosure of Invention

The present invention aims to solve at least one of the technical problems existing in the prior art. Therefore, the invention provides the aerocar wing folding structure which can strengthen the connection strength of the rotary wing and the fixed wing when the rotary wing is unfolded.

According to an embodiment of the invention, a folding structure for a wing of a flying car comprises: a fixed wing and a rotating wing, the rotating wing rotatably coupled to the fixed wing, and the rotating wing having a folded position and an unfolded position; one of the fixed wing and the rotary wing is provided with a first connecting part, the other one of the fixed wing and the rotary wing is provided with a second connecting part, when the rotary wing is positioned at the unfolding position, the first connecting part is fixedly matched with the second connecting part, and when the rotary wing is positioned at the folding position, the first connecting part is separated from the second connecting part.

According to the aerocar wing folding structure provided by the embodiment of the invention, the rotary wing is rotatably connected to the fixed wing, the rotary wing is provided with the folding position and the unfolding position, and when the rotary wing is in the unfolding position, the first connecting part and the second connecting part are fixedly matched, so that the connection strength of the rotary wing and the fixed wing can be enhanced, the structural stability of the rotary wing can be enhanced, the rotary wing can bear bending moment born by the rotary wing during flying, and the aerocar flies in the air in a fixed wing mode.

According to some embodiments of the present invention, one of the first and second connection portions is configured as a support bar and the other is configured as a socket slot, the support bar being adapted for a socket fit with the socket slot.

According to the aerocar wing folding structure of some embodiments of the present invention, the support rod is mounted on the fixed wing, the insertion slot is provided on the rotating wing, the fixed wing is provided with a driving member, and when the rotating wing is in the unfolding position, the driving member is used for driving the support rod to move towards a direction approaching or separating from the insertion slot.

According to some embodiments of the invention, the fixed wing is provided with a mounting cavity, and the support rod is slidably mounted in the mounting cavity.

According to the aerocar wing folding structure of some embodiments of the present invention, the driving piece is configured as a driving motor, the driving motor is located in the installation cavity, the supporting rod includes a first sub-rod and a second sub-rod, the first sub-rod is fixedly connected with an output shaft of the driving motor, and the second sub-rod is sleeved outside the first sub-rod. The outer peripheral wall of the first sub-rod is provided with an external thread, the inner peripheral wall of the second sub-rod is provided with an internal thread, and the external thread is in threaded connection with the internal thread.

According to some embodiments of the present invention, the first sub-lever includes a lever body and a connecting portion, the external thread is disposed on an outer peripheral wall of the lever body, and the connecting portion is connected to the lever body and is sleeved on an outer side of an output shaft of the driving motor.

According to the aerocar wing folding structure, a bearing is further arranged in the mounting cavity, and the bearing is sleeved on the outer side of the connecting portion.

According to some embodiments of the present invention, the aerofoil folding structure of the aerocar comprises a fixing frame and a rotating base, wherein the fixing frame is connected with the rotating base, the rotating base is provided with a rotating rod, the rotating rod is rotatably connected with the rotating base, and the rotating rod is connected with the rotating aerofoil.

According to the aerocar wing folding structure of some embodiments of the present invention, the rotating base is provided with a rotating sliding groove, the end part of the rotating wing extends into the rotating sliding groove, the rotating wing is provided with a fixed groove, and the rotating rod is inserted into the fixed groove.

The invention also provides a flying car.

According to an embodiment of the invention, a flying car comprises: the aerocar wing fold structure of any preceding embodiment.

Compared with the prior art, the aerocar has the same advantages as the aerocar wing folding structure, and the description is omitted here.

Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention.

Drawings

The foregoing and/or additional aspects and advantages of the invention will become apparent and may be better understood from the following description of embodiments taken in conjunction with the accompanying drawings in which:

FIG. 1 is a schematic illustration of a wing fold structure of a flying car in accordance with an embodiment of the present invention with a rotating wing in an extended position;

FIG. 2 is a schematic view of the rotating base of FIG. 1;

FIG. 3 is a schematic view of the base of FIG. 1;

FIG. 4 is a schematic view of the copper ring gland of FIG. 1;

FIG. 5 is a schematic view of the fixed wing of FIG. 1;

FIG. 6 is a cross-sectional view of the swivel base of FIG. 1;

FIG. 7 is a cross-sectional view of the support bar of FIG. 1;

FIG. 8 is a schematic view of the rotating wing of the aerocar wing fold structure of FIG. 1 in a folded position;

FIG. 9 is an enlarged schematic view of a portion of the rotary wing of FIG. 8 in a folded position (with the rotating base hidden);

fig. 10 is a schematic view of a flying vehicle according to an embodiment of the present invention.

Reference numerals:

the vehicle 1000 is in a flight with,

the wing-fold structure 100,

the fixed wing 20, the first connection 21, the support bar 22,

a mounting cavity 23, a motor mounting surface 231, a support bar mounting groove 232,

bearing outer ring mounting surface 233, bearing outer ring gland mounting surface 234,

the driving member 25, the first sub-lever 26, the lever body 261, the connecting portion 262, the second sub-lever 27,

bearing 28, bearing outer ring gland 281, bearing inner ring gland 282,

a base 30, a base-swivel base mounting surface 301, a self-lubricating copper ring mounting surface 302,

base-copper ring gland mounting face 303, base-swivel base mounting holes 304,

base-copper ring gland mounting holes 305, self-lubricating copper ring mounting holes 306,

self-lubricating copper ring 32, copper ring gland 33, gland-base mounting face 331,

the rotary slide slot 34, the fixed slot 35, the middle wing section 36,

the swivel base 37, base-to-base mounting surface 371, swivel lever 38,

the rotation wing 40, the second connection 41, the insertion slot 42, the hinge 43,

the transition piece 44, the outer wing piece 45, the rotating plate 46.

Detailed Description

Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are illustrative only and are not to be construed as limiting the invention.

The following disclosure provides many different embodiments, or examples, for implementing different structures of the invention. In order to simplify the present disclosure, components and arrangements of specific examples are described below. They are, of course, merely examples and are not intended to limit the invention. Furthermore, the present invention may repeat reference numerals and/or letters in the various examples. This 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, the present invention provides examples of various specific processes and materials, but one of ordinary skill in the art will recognize the applicability of other processes and/or the use of other materials.

A aerocar wing fold structure 100 according to an embodiment of the present invention is described below with reference to fig. 1-10.

As shown in fig. 1-9, a folding structure 100 for a wing of a flying car according to an embodiment of the present invention includes: a fixed wing 20 and a rotating wing 40.

The rotary wing 40 is rotatably coupled to the fixed wing 20, and the rotary wing 40 has a folded position and an unfolded position. Wherein, one of the fixed wing 20 and the rotating wing 40 is provided with a first connecting portion 21, and the other is provided with a second connecting portion 41, when the rotating wing 40 is in the unfolded position, the first connecting portion 21 is fixedly matched with the second connecting portion 41, and when the rotating wing 40 is in the folded position, the first connecting portion 21 is separated from the second connecting portion 41.

Therefore, when the rotary wing 40 is located at the unfolding position, the first connecting portion 21 and the second connecting portion 41 are fixedly matched, so that the connection strength of the rotary wing 40 and the fixed wing 20 can be enhanced, the structural stability of the rotary wing 40 can be enhanced, the rotary wing 40 can bear bending moment received during flying, and the aerocar 1000 can fly in the air in a fixed wing mode.

For example, the fixed wing 20 is fixedly mounted on the aerocar 1000, two rotating wings 40 are provided, the two rotating wings 40 are symmetrically distributed on two sides of the fixed wing 20, and when the rotating wings 40 are located at the unfolding positions, the rotating wings 40 and the fixed wing 20 are unfolded in a straight line, so that the aerocar 1000 can fly in the air to have enough lift force, and in the process that the rotating wings 40 rotate from the unfolding positions to the folding positions, the rotating wings 40 rotate and shrink towards the tail direction of the aerocar 1000 relative to the fixed wing 20, so that when the rotating wings 40 are located at the folding positions, the width of the wing folding structure 100 is approximate to the width of the car body, and the influence on the width dimension of the aerocar 1000 is reduced, so that the aerocar 1000 can run on a regular road surface.

In the related art, when the rotary wing 40 is deployed, the strength of the connection between the rotary wing 40 and the fixed wing 20 is low, so that the rotary wing 40 cannot withstand the bending moment applied during flight, and the aerocar 1000 cannot fly in the fixed wing mode stably.

In the present invention, when the rotary wing 40 is in the extended position, the rotary wing 40 and the fixed wing 20 can be fixedly engaged with each other by the first connection portion 21 and the second connection portion 41, so that the connection strength between the rotary wing 40 and the fixed wing 20 can be enhanced, and the rotary wing 40 of the aerocar 1000 can withstand the bending moment applied to the aerocar when the aerocar is in the extended position and the rotary wing 40 maintains the mode of the fixed wing when the aerocar is in flight.

According to the aerocar wing folding structure 100 of the embodiment of the present invention, the fixed wing 20 is rotatably connected with the rotating wing 40, the rotating wing 40 is provided with a folding position and an unfolding position, and when the rotating wing 40 is in the unfolding position, the first connecting portion 21 and the second connecting portion 41 are fixedly matched, so that the connection strength between the rotating wing 40 and the fixed wing 20 can be enhanced, the structural stability of the rotating wing 40 can be enhanced, the rotating wing 40 can bear bending moment applied to the rotating wing during flying, and the aerocar 1000 flies in the air in a fixed wing mode.

In some embodiments, as shown in fig. 7 and 9, one of the first and second connection portions 21 and 41 is configured as a support bar 22, and the other is configured as a socket groove 42, the support bar 22 being adapted for a socket fit with the socket groove 42.

Therefore, when the rotary wing 40 is unfolded, the supporting rods 22 can be inserted into the inserting grooves 42 to enhance the connection strength between the rotary wing 40 and the fixed wing 20, and the supporting rods 22 are inserted into the inserting grooves 42 so that the supporting rods 22 are not directly visible on the outer side of the wing folding structure 100, thereby being convenient for reducing the influence on the size of the wing folding structure 100 and being beneficial to realizing the miniaturization design of the wing folding structure 100.

For example, when the first connecting portion 21 is configured as the support bar 22, the second connecting portion 41 is configured as the insertion groove 42, and vice versa, in this embodiment, the first connecting portion 21 is configured as the support bar 22, the second connecting portion 41 is configured as the insertion groove 42, and the support bar 22 is engaged with the insertion groove 42.

For example, the first connection portion 21 may be disposed on the fixed wing 20, and the second connection portion 41 may be disposed on the rotating wing 40, and vice versa, in this embodiment, the first connection portion 21 is disposed on the fixed wing 20, and the second connection portion 41 is disposed on the rotating wing 40, so that the support rod 22 is disposed on the fixed wing 20, the inserting slot 42 is disposed on the rotating wing 40, and when the rotating wing 40 is in the extended position, the support rod 22 may be inserted into the inserting slot 42 to enhance the connection strength between the rotating wing 40 and the fixed wing 20, so that the rotating wing 40 can bear the bending moment suffered by the flying.

In some embodiments, as shown in fig. 7 and 9, the support bar 22 is mounted on the fixed wing 20, the insertion slot 42 is provided on the rotating wing 40, the fixed wing 20 is provided with a driving member 25, and the driving member 25 is used to drive the support bar 22 to move toward or away from the insertion slot 42 when the rotating wing 40 is in the deployed position.

Therefore, by arranging the driving piece 25, the movement of the supporting rod 22 does not need to be controlled manually when the supporting rod 22 is in plug-in fit with the plug-in groove 42, so that the automation degree of the wing folding structure 100 is improved.

For example, when the rotary wing 40 is in the extended position, the driving member 25 can drive the support bar 22 to move toward the insertion slot 42 so that the support bar 22 can extend into the insertion slot 42, or when the rotary wing 40 is moved from the extended position to the folded position, the driving member 25 drives the support bar 22 to move away from the insertion slot 42 so that the support bar 22 is separated from the insertion slot 42, thereby enabling the rotary wing 40 to rotate on the fixed wing 20.

In this way, the movement of the support bar 22 can be driven by the driving member 25, so as to achieve an improvement in the automation degree of the wing-folding structure 100.

In some embodiments, as shown in fig. 2 and 7, the fixed wing 20 is provided with a mounting cavity 23, and the support bar 22 is slidably mounted within the mounting cavity 23.

Therefore, the support rods 22 are not directly visible on the outer side of the fixed wing 20, so that the influence on the size of the fixed wing 20 is reduced, and the miniaturization design of the fixed wing 20 is realized.

Meanwhile, when the rotary wing 40 is located at the unfolding position, the supporting rods 22 can slide from the mounting cavity 23 towards the inserting grooves 42, so that the end parts of the supporting rods 22 can extend into the inserting grooves 42, and therefore the connection strength between the rotary wing 40 and the fixed wing 20 can be enhanced, and when the rotary wing 40 needs to move from the unfolding position to the folding position, the end parts of the supporting rods 22 move from the inserting grooves 42 into the mounting cavity 23, and therefore the rotary wing 40 is not limited in movement.

It should be noted that, when the rotary wing 40 is located at the unfolding position, the opening of the installation cavity 23 is opposite to the opening of the inserting groove 42, and meanwhile, the inner wall of the installation cavity 23 can play a role in guiding and limiting the movement of the support rod 22, so as to ensure that the support rod 22 can directly move into the inserting groove 42.

In some embodiments, as shown in fig. 6, the driving member 25 is configured as a driving motor, the driving motor is located on a motor mounting surface 231 in the mounting cavity 23, and the supporting rod 22 includes a first sub-rod 26 and a second sub-rod 27, the first sub-rod 26 is fixedly connected with an output shaft of the driving motor, and the second sub-rod 27 is sleeved outside the first sub-rod 26. Wherein, the outer periphery wall of the first sub-rod 26 is provided with external threads, and the inner periphery wall of the second sub-rod 27 is provided with internal threads, and the external threads are in threaded connection with the internal threads.

Thus, the rotation of the first sub-lever 26 can drive the second sub-lever 27 to move in the axial direction of the first sub-lever 26 when the driving member 25 drives the first sub-lever 26 to rotate.

Therefore, when the rotary wing 40 is located at the unfolding position, the driving motor drives the first sub-rod 26 to rotate and then drives the second sub-rod 27 to move along the axial direction of the first sub-rod 26, so that the end part of the first sub-rod 26 extends into the inserting groove 42, and the connection strength between the rotary wing 40 and the fixed wing 20 can be enhanced, and when the rotary wing 40 moves from the unfolding position to the folding position, the driving motor drives the first sub-rod 26 to rotate and then controls the second sub-rod 27 to leave from the inserting groove 42, so that the rotary wing 40 can be folded.

Alternatively, when the first sub-rod 26 is fixedly connected to the output shaft of the driving motor, the connection manner may have various forms, for example, when the first sub-rod 26 is connected to the output shaft of the driving motor, it may be directly plugged onto the output shaft, or when the first sub-rod 26 is connected to the output shaft of the driving motor, it is fixed together through a threaded connection, preferably, in this embodiment, the first sub-rod 26 is directly plugged onto the output shaft of the driving motor.

Alternatively, after the first sub-rod 26 is screwed with the second sub-rod 27, the screw direction of the first sub-rod 26 and the second sub-rod 27 is not limited, for example, when the first sub-rod 26 rotates clockwise to drive the second sub-rod 27 to approach the socket 42, the first sub-rod 26 rotates counterclockwise to drive the second sub-rod 27 to move away from the socket 42, or when the first sub-rod 26 rotates clockwise to drive the second sub-rod 27 to move away from the socket 42, the first sub-rod 26 rotates counterclockwise to drive the second sub-rod 27 to move toward the direction approaching the socket 42.

In some embodiments, as shown in fig. 7, the first sub-rod 26 includes a rod body 261 and a connecting portion 262, the external thread is disposed on an outer peripheral wall of the rod body 261, and the connecting portion 262 is connected with the rod body 261 and sleeved on an outer side of an output shaft of the driving motor.

In other words, the outer peripheral wall of the rod body 261 of the first sub-rod 26 is provided with an external thread matching with an internal thread on the inner peripheral wall of the second sub-rod 27, so that the first sub-rod 26 can drive the second sub-rod 27 to move towards a direction approaching or separating from the inserting slot 42, the connecting portion 262 of the first sub-rod 26 is sleeved outside the output shaft of the driving motor, and the connecting portion 262 is connected with the rod body 261, so that the driving motor can drive the second sub-rod 27 by driving the first sub-rod 26.

Therefore, in the present embodiment, the first sub-rod 26 is sleeved on the output shaft of the driving motor, so that the first sub-rod 26 is more convenient when connected with the output shaft of the driving motor, and the first sub-rod 26 is coaxial with the output shaft of the driving motor after the installation is completed, so that the power of the driving motor can be better transmitted to the first sub-rod 26.

In some embodiments, as shown in fig. 7, a bearing 28 is further disposed in the mounting cavity 23, and the bearing 28 is sleeved outside the connecting portion 262.

It will be appreciated that the bearing 28 in the mounting cavity 23 is disposed around the outer side of the connecting portion 262, and the bearing 28 can better fix the first sub-rod 26 to the driving motor.

Optionally, a support rod mounting groove 232, a bearing outer ring mounting surface 233 and a bearing outer ring gland mounting surface 234 are provided in the mounting cavity 23 of the fixed wing 20, the support rod 22 is firstly mounted in the support rod mounting groove 232, then the bearing 28 is placed on the bearing outer ring mounting surface 233, at this time, the connecting portion 262 of the first sub-rod 26 is clamped in the bearing 28, a bearing outer ring gland 281 and a bearing inner ring gland 282 are provided on one side of the bearing 28, which is close to the driving motor, the bearing outer ring gland 281 is mounted on the bearing outer ring gland mounting surface 234 in a threaded connection manner, and the bearing inner ring gland 282 is sleeved on the connecting portion 262 of the first sub-rod 26, so that the bearing 28 can limit the connecting portion 262 of the first sub-rod 26, and the first sub-rod 26 can be better connected to the output shaft of the driving motor.

In some embodiments, as shown in fig. 1-5, the fixed wing 20 includes a fixed mount and a rotating base 37, the fixed mount is connected to the rotating base 37, the rotating base 37 is provided with a rotating lever 38, the rotating lever 38 is rotatably connected to the rotating base 37, and the rotating lever 38 is connected to the rotating wing 40.

Specifically, the fixed frame is connected to the rotating base 37, a base 30 is disposed in the rotating base 37, a self-lubricating copper ring 32 is mounted on the base 30, one end of a rotating rod 38 disposed in the rotating base 37 is connected to the rotating wing 40, the other end is connected to a hinge 43 of the fixed frame, and the rotating rod 38 can drive the rotating wing 40 to move on the fixed wing 20, so that the rotating wing 40 has a folded position and an unfolded position.

Thus, the fixed frame is connected with the rotating base 37 so that the rotating base 37 can provide a mounting point for the rotating wing 40, and the rotating wing 40 is driven to move by the rotating rod 38 after the rotating wing 40 is mounted on the rotating base 37.

It should be noted that, in this embodiment, the fixing frame may be configured as the middle wing section 36.

For example, the fixed wing 20 includes a middle wing section 36 and a rotating base 37, where the middle wing section 36 includes a spar, a longitudinal wall, a stringer, a rib, and the like, the structure of which is similar to that of a conventional wing in the related art, the section of the rotating base 37 is an airfoil structure, the rotating base 37 is provided with a mounting cavity 23 and a base-base mounting surface 371, the rotating wing 40 is rotatably disposed on the rotating base 37 of the fixed wing 20, and the rotating wing 40 includes a hinge 43, a rotating rod 38, a rotating plate 46, a transition connection section 44, and an outer wing section 45, where the structure of the outer wing section 45 is the same as that of the middle wing section 36.

The two ends of the middle wing section 36 are respectively provided with a rotating base 37, a base 30 is installed in the rotating base 37, a self-lubricating copper ring 32 is sleeved on the base 30, two rotating wings 40 are symmetrically arranged at two ends of the fixed wing 20, one end of a hinge 43 is installed on the middle wing section 36 of the fixed wing 20, the other end of the hinge 43 is connected with a rotating rod 38, the hinge 43 and the rotating rod 38 can be in a pin connection mode, the rotating plate 46 is in a flat plate structure with one end being arc-shaped, one end, close to the arc-shaped side edge, of the rotating plate 46 is provided with a self-lubricating copper ring mounting hole 306, the rotating plate 46 is sleeved on the self-lubricating copper ring 32 through the self-lubricating copper ring mounting hole 306, the rotating plate 46 is connected with one end, far away from the hinge 43, of the rotating plate 46, of the rotating plate 38 is not connected with the rotating rod 38, and one end, of the rotating plate 46 is clamped in the transition connecting section 44.

The transition connection section 44 of the rotary wing 40 is connected with the outer wing section 45 and is clamped with the rotating plate 46, the transition connection section 44 connects the outer wing section 45 to the rotating plate 46 of the rotary wing 40, so when the rotary wing 40 moves from the unfolding position to the folding position, the rotating rod 38 stretches to drive the rotating plate 46 to rotate 90 degrees around the self-lubricating copper ring 32 towards the tail direction, and accordingly the outer wing section 45 can rotate 90 degrees along with the rotating plate 46 towards the tail direction, and the folding function of the rotary wing 40 is achieved.

Further, the angle by which the wing 40 rotates toward the tail of the vehicle when the wing 40 moves from the folded position to the unfolded position is not limited, for example, the wing 40 can rotate 45 ° toward the tail of the vehicle, or the wing 40 rotates 120 ° toward the tail of the vehicle, and the rotation of 90 ° in the above embodiment is only one embodiment, when the wing 40 moves from the folded position to the folded position, the rotating rod 38 is retracted to move the wing 40 toward the head of the vehicle, and when the wing 40 is folded, the wing 40 rotates by the same degree.

Therefore, the two rotating wings 40 are symmetrically disposed at two ends of the fixed wing 20, after the fixed wing 20 is mounted on the aerocar 1000, the rotating wing 40 can provide enough lift force for the aerocar 1000 together with the fixed wing 20 when being located at the unfolding position, and when the rotating wing 40 is folded, the width of the folded wing structure 100 in the width direction of the aerocar 1000 is smaller than or equal to the width of the aerocar 1000 in the width direction of the aerocar 1000, so that the folded wing structure 100 does not affect other vehicles when the aerocar 1000 is running on the road.

Optionally, the base 30 of the fixed wing 20 is a disc structure with a boss, on which a base-rotating base mounting surface 301, a self-lubricating copper ring mounting surface 302, a base-copper ring gland mounting surface 303, a base-rotating base fixing hole 304 and a base-copper ring gland fixing hole 305 are provided, the rotating base 37 is further provided with the base 30, the base 30 and the rotating base 37 are connected together by screws, wherein the self-lubricating copper ring 32 is in a hollow circular ring structure, the self-lubricating copper ring 32 is sleeved on the boss of the base 30, the inner ring of the self-lubricating copper ring 32 is in contact with the self-lubricating copper ring mounting surface 32, and the copper ring gland 33 is connected with the base 30 and abuts against the boss, so that the self-lubricating copper ring 32 is clamped between the base 30 and the copper ring gland 33.

For example, the copper ring gland 33 is constructed in a disc-shaped structure, on which a gland-base mounting surface 331 is provided, and the gland-base mounting surface 331 can be mounted on the rotating base 37 by means of screw connection, so that the self-lubricating copper ring 32 can be restrained.

Further, when the base 30 is connected to the rotating base 37, the screw passes through the base-rotating base fixing hole 304, so that the base 30 and the rotating base 37 are fixedly connected, the copper ring gland 33 is mounted on the base-copper ring gland mounting surface 303, the screw passes through the base-copper ring gland fixing hole 305, so that the copper ring gland 33 is fixed on the base 30, meanwhile, one end of the rotating rod 38 is connected to the rotating wing 40, the other end is connected to the fixed wing 20, and when the rotating rod 38 stretches and contracts, the rotating plate 46 can be driven to rotate around the self-lubricating copper ring 32, so that the rotating wing 40 is driven to rotate by the rotating plate 46.

In some embodiments, as shown in fig. 2, the rotating base 37 is provided with a rotating sliding groove 34, an end of the rotating wing 40 extends into the rotating sliding groove 34, the rotating wing 40 is provided with a fixed groove 35, and the rotating rod 38 is inserted into the fixed groove 35.

It will be appreciated that the rotating base 37 is provided with the rotary sliding groove 34, the end portion of the rotating wing 40 can extend into the rotary sliding groove 34, so that when the rotating wing 40 is driven to rotate by the rotating rod 38, no obstruction exists on the moving path of the rotating wing 40, meanwhile, the fixed groove 35 provided on the rotating wing 40 can be configured as a rectangular opening, the rotating rod 38 is inserted into the fixed groove 35 so that the fixed wing 20 is connected with the rotating wing 40, the other end of the rotating rod 38 is connected to the fixed wing 20, and when the rotating rod 38 stretches, the fixed groove 35 has enough space for the rotating rod 38 to move, and meanwhile, the rotating rod 38 is inserted into the fixed groove 35 so that the rotating rod 38 is positioned in the fixed wing 20 and can be connected with the rotating plate 46 of the rotating wing 40, thus the influence on the size of the fixed wing 20 is reduced, and the miniaturized design of the fixed wing 20 is facilitated.

Specifically, when the fixed wing 20 is mounted on the top of the aerocar 1000, the rotary sliding groove 34 is provided with an opening in the direction of the tail, and when the rotary wing 40 moves from the unfolded position to the folded position, the rotary wing 40 rotates 90 ° toward the tail around the self-lubricating copper ring 32, and the rotary wing 40 can be clamped in the opening of the rotary sliding groove 34, so that the width of the folded wing structure 100 of the rotary wing 40 in the width direction of the aerocar 1000 is substantially consistent with the width of the aerocar 1000, and other vehicles cannot be affected when the aerocar 1000 normally runs on a lane.

The invention also provides the aerocar 1000.

As shown in fig. 10, a flying car 1000 according to an embodiment of the present invention includes: the aerocar wing fold structure 100 of any of the above embodiments.

According to the aerocar 1000 of the embodiment of the present invention, in the aerocar wing folding structure 100 mounted thereon, the rotating wing 40 is rotatably connected to the fixed wing 20, the rotating wing 40 is provided with a folding position and an unfolding position, and when the rotating wing 40 is in the unfolding position, the first connecting portion 21 and the second connecting portion 41 are fixedly matched, so that the connection strength between the rotating wing 40 and the fixed wing 20 can be enhanced, and the structural stability of the rotating wing 40 can be enhanced, so that the rotating wing 40 can bear bending moment applied to the rotating wing during flying, and the aerocar 1000 flies in the air in a fixed wing mode.

In the description of the present invention, it should 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", "axial", "radial", "circumferential", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present invention.

Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present invention, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.

In the present invention, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; the device can be mechanically connected, electrically connected and communicated; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.

In the present invention, unless expressly stated or limited otherwise, a first feature "up" or "down" a second feature may be the first and second features in direct contact, or the first and second features in indirect contact via an intervening medium. Moreover, a first feature being "above," "over" and "on" a second feature may be a first feature being directly above or obliquely above the second feature, or simply indicating that the first feature is level higher than the second feature. The first feature being "under", "below" and "beneath" the second feature may be the first feature being directly under or obliquely below the second feature, or simply indicating that the first feature is less level than the second feature.

In the description of the present specification, a description referring to terms "one embodiment," "some embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.

While embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that: many changes, modifications, substitutions and variations may be made to the embodiments without departing from the spirit and principles of the invention, the scope of which is defined by the claims and their equivalents.

Claims

1. A folding structure (100) for a wing of a flying vehicle, comprising:

a fixed wing (20) and a rotating wing (40), the rotating wing (40) being rotatably connected to the fixed wing (20), and the rotating wing (40) having a folded position and an unfolded position;

wherein one of the fixed wing (20) and the rotating wing (40) is provided with a first connecting portion (21), and the other is provided with a second connecting portion (41), when the rotating wing (40) is located at the unfolding position, the first connecting portion (21) is fixedly matched with the second connecting portion (41), and when the rotating wing (40) is located at the folding position, the first connecting portion (21) is separated from the second connecting portion (41).

2. The aerocar wing fold structure (100) according to claim 1, wherein one of the first connection portion (21) and the second connection portion (41) is configured as a support bar (22) and the other is configured as a socket groove (42), the support bar (22) being adapted for a socket fit with the socket groove (42).

3. The folding structure (100) of a wing of a flying car according to claim 2, characterized in that the supporting bar (22) is mounted on the fixed wing (20), the insertion slot (42) is provided on the rotating wing (40), the fixed wing (20) is provided with a driving member (25), and the driving member (25) is used for driving the supporting bar (22) to move towards a direction approaching or away from the insertion slot (42) when the rotating wing (40) is in the unfolded position.

4. A folding structure (100) for a wing of a flying car according to claim 3, characterized in that the fixed wing (20) is provided with a mounting cavity (23), the support bar (22) being slidably mounted in the mounting cavity (23).

5. A folding structure (100) for a wing of a flying vehicle according to claim 3, characterized in that the driving element (25) is configured as a driving motor, which is located in the mounting cavity (23), and the supporting bar (22) comprises a first sub-bar (26) and a second sub-bar (27), the first sub-bar (26) being fixedly connected to the output shaft of the driving motor, the second sub-bar (27) being sheathed outside the first sub-bar (26);

the outer peripheral wall of the first sub rod (26) is provided with external threads, the inner peripheral wall of the second sub rod (27) is provided with internal threads, and the external threads are in threaded connection with the internal threads.

6. The aerocar wing folding structure (100) according to claim 5, wherein the first sub-lever (26) comprises a lever body portion (261) and a connecting portion (262), the external thread is provided on the outer peripheral wall of the lever body portion (261), and the connecting portion (262) is connected with the lever body portion (261) and is sleeved on the outer side of the output shaft of the driving motor.

7. The aerocar wing folding structure (100) according to claim 6, wherein a bearing (28) is further provided in the mounting cavity (23), and the bearing (28) is sleeved outside the connecting portion (262).

8. The aerocar wing folding structure (100) according to any of claims 1 to 7, wherein the fixed wing (20) comprises a fixed frame and a rotating base (37), the fixed frame being connected to the rotating base (37), the rotating base (37) being provided with a rotating lever (38), the rotating lever (38) being rotatably connected to the rotating base (37), and the rotating lever (38) being connected to the rotating wing (40).

9. The aerocar wing folding structure (100) according to claim 8, wherein the rotating base (37) is provided with a rotating sliding groove (34), the end of the rotating wing (40) extends into the rotating sliding groove (34), the rotating wing (40) is provided with a fixed groove (35), and the rotating rod (38) is inserted into the fixed groove (35).

10. A flying vehicle (1000), comprising: the flying car wing folding structure (100) of any one of claims 1-9.