Fixed wing unfolding and folding mechanism of hovercar and hovercar

Abstract

The invention provides a fixed wing unfolding and folding mechanism of a hovercar and the hovercar, the fixed wing unfolding and folding mechanism comprises a wing body plate, two fixed wings and two unfolding and folding assemblies, each fixed wing is connected with the wing body plate through the corresponding unfolding and folding assembly, the two fixed wings are symmetrically distributed about the YOZ plane, and the two fixed wings are connected with the wing body plate through the corresponding unfolding and folding assembly. The two groups of unfolding and folding assemblies are symmetrically distributed about the YOZ plane; the unfolding and folding assembly is used for driving the fixed wing to be switched between an unfolding state and a folding state, in the unfolding state, the plane where the fixed wing is located is perpendicular to the second direction, in the folding state, the plane where the fixed wing is located is perpendicular to the first direction, and the second direction is parallel to the thickness direction of the wing body plate and perpendicular to the first direction. Through the arrangement, folding operation of the fixed wings can be achieved, the space occupied by the fixed wings is reduced, and the flying car can run on a conventional road and be parked in a universal parking space.

Description

[0001] This application claims the priority of the Chinese patent application with the application number 202510644324.7 and the invention title "Fixed-wing Deployment and Folding Mechanism and Flying Device" filed on May 19, 2025, the entire content of which is incorporated herein by reference. Technical Field

[0002] This application relates to the technical field of flying cars, and particularly to a fixed-wing deployment and folding mechanism of a flying car and a flying car. Background Art

[0003] For a flying car, in order to have the lift required for flight, a fixed wing with a relatively long length is usually provided.

[0004] In the related art, the fixed wing of a flying car usually cannot be folded. When the flying car is not in a flying state, it will occupy a large space near the ground. Compared with traditional aircraft, the difference of a flying car is that it not only requires high flight requirements, but also needs to meet the requirement of being able to drive normally on the ground lane. The existence of the fixed wing makes the flying car need to occupy too much space, thus making it difficult to meet the requirement of road driving. Summary of the Invention

[0005] In view of this, this application provides a fixed-wing deployment and folding mechanism of a flying car and a flying car, which can realize the folding operation of the fixed wing and reduce the space occupied by the fixed wing.

[0006] Specifically, the following technical solutions are included:

[0007] In a first aspect, this application provides a fixed-wing deployment and folding mechanism of a flying car. The fixed-wing deployment and folding mechanism includes a wing body plate, two fixed wings, and two sets of deployment and folding components. Each fixed wing is connected to the wing body plate through the deployment and folding component. The two fixed wings are symmetrically distributed with respect to the YOZ plane, and the two sets of deployment and folding components are symmetrically distributed with respect to the YOZ plane;

[0008] The deployment and folding component is used to drive the fixed wing to switch between the deployed state and the folded state. In the deployed state, the plane where the fixed wing is located is perpendicular to the second direction. In the folded state, the plane where the fixed wing is located is perpendicular to the first direction, where the second direction is parallel to the thickness direction of the wing body plate and perpendicular to the first direction.

[0009] In a possible implementation, the unfolding and folding assembly includes a fixed seat and at least three sequentially hinged connecting rods. The fixed seat is fixed on the wing plate. One end of one of the connecting rods is hinged to the fixed seat and can rotate around a central axis extending along the first direction. One end of another connecting rod is hinged to the fixed seat and can rotate around a central axis extending along the second direction;

[0010] The fixed wing is connected to one of the connecting rods. In the unfolded state, the fixed wing extends along the first direction; in the folded state, the fixed wing extends along the third direction, where the third direction is perpendicular to the first direction and the second direction respectively.

[0011] In a possible implementation, the at least three sequentially hinged connecting rods include a front arm rod, a middle arm rod, and a side arm rod;

[0012] The first end of the front arm rod is hinged to the fixed seat and can rotate around a central axis extending along the first direction. The connecting line between the first end and the second end of the front arm rod is inclined to the first direction;

[0013] The first end of the side arm rod is hinged to the fixed seat and can rotate around a central axis extending along the second direction. The connecting line between the first end and the second end of the side arm rod is inclined to the second direction;

[0014] The first end of the middle arm rod is hinged to the second end of the front arm rod, and the second end of the middle arm rod is hinged to the second end of the side arm rod. In the unfolded state, the rotation axis of the first end of the middle arm rod extends along the third direction, and the rotation axis of the second end of the middle arm rod extends along the first direction.

[0015] In a possible implementation, an inclined cut is provided on one side of the fixed wing close to the unfolding and folding assembly, and the middle arm rod is adaptively connected to the inclined cut; in the unfolded state, the extending direction of the middle arm rod is inclined to the first direction and the third direction respectively.

[0016] In a possible implementation, a first hinge seat is provided at one end of the fixed seat, and a second hinge seat is provided at the other end;

[0017] A first front hinge seat is provided at the first end of the front arm rod. The first front hinge seat is hinged to the first hinge seat through a rotating shaft, and the rotating shaft moves synchronously with the first front hinge seat. The rotating shaft is rotatably connected to the first hinge seat. A second front hinge seat is provided at the second end of the front arm rod;

[0018] The first end of the middle arm rod is provided with a first middle hinge seat, the first middle hinge seat is hinged to the second front hinge seat, and the second end of the middle arm rod is provided with a second middle hinge seat;

[0019] The first end of the side arm rod is provided with a first side hinge seat, which is hinged to the second hinge seat. The second end of the side arm rod is provided with a second side hinge seat, which is hinged to the second middle hinge seat.

[0020] In a possible implementation, the fixed-wing unfolding and folding mechanism further includes a driving mechanism installed on the wing body panel, the driving mechanism is drivingly connected to the rotating shaft, and the driving mechanism is used to drive the rotating shaft to rotate.

[0021] In a possible implementation, the driving mechanism includes a driving motor, a gear box, a push rod, and a rocker arm that are sequentially connected in transmission;

[0022] The gear box is hinged to the wing body plate, one end of the push rod facing away from the gear box is hinged to the rocker arm, and the rocker arm is fixedly connected to the rotating shaft.

[0023] In one possible implementation, the driving mechanism includes a telescopic motor, a rack and a gear, the telescopic motor is fixedly connected to the wing body plate, the telescopic rod of the telescopic motor is fixedly connected to the rack, the rack is meshed with the gear, and the gear is coaxially fixedly connected to the rotating shaft.

[0024] In a second aspect, the present application provides a flying car, comprising the fixed-wing unfolding and folding mechanism provided in any embodiment of the first aspect.

[0025] The beneficial effects of the technical solution provided by the embodiments of the present application include at least: by providing an unfolding and folding component, the fixed wings can be switched between an unfolded state and a folded state; when the fixed wings are in the unfolded state, the normal flight of the flying car can be ensured; when the fixed wings are in the folded state, the fixed wings can be folded and stored to both sides of the flying car, greatly reducing the space occupied by the fixed wings of the flying car in the first direction, so that the flying car can be driven on conventional roads and parked in general parking spaces. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0027] Figure 1Schematic structural diagram of the fixed-wing deployment and folding mechanism provided by the embodiments of the present application;

[0028] Figure 2 Schematic structural diagram of the deployment and folding assembly provided by the embodiments of the present application;

[0029] Figure 3 Schematic structural diagram of the fixed wing provided by the embodiments of the present application;

[0030] Figure 4 Schematic structural diagram of the drive mechanism provided by some embodiments of the present application;

[0031] Figure 5 Schematic structural diagram of the drive mechanism provided by other embodiments of the present application.

[0032] The reference numerals in the figure are respectively represented as:

[0033] 1: wing body plate; 2: fixed wing; 3: deployment and folding assembly;

[0034] 10: drive mechanism; 10-1: drive motor; 10-2: gearbox; 10-3: push rod; 10-4: rocker arm;

[0035] 10-5: telescopic motor; 10-6: rack; 10-7: gear;

[0036] 20: inclined cut;

[0037] 30: rotating shaft;

[0038] 31: fixed seat; 31-1: first hinge seat; 31-2: second hinge seat;

[0039] 32: front arm rod; 32-1: first front hinge seat; 32-2: second front hinge seat;

[0040] 33: middle arm rod; 33-1: first middle hinge seat; 33-2: second middle hinge seat;

[0041] 34: side arm rod; 34-1: first side hinge seat; 34-2: second side hinge seat;

[0042] 100: first axis; 200: second axis; 300: third axis; 400: fourth axis.

[0043] Through the above-mentioned drawings, specific embodiments of the present application have been shown, and there will be more detailed descriptions hereinafter. These drawings and textual descriptions are not intended to limit the scope of the concept of the present application in any way, but to illustrate the concept of the present application to those skilled in the art by referring to specific embodiments. Detailed implementation manners

[0044] Next, the technical solutions in the embodiments of the present application will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present application without creative efforts shall fall within the protection scope of the present application.

[0045] The orientation terms involved in the embodiments of the present application, such as "upper", "lower", "side", etc., generally take the relative relationship of the orientation shown in the figure as the reference, and these orientation terms are only used to more clearly describe the relationship between the structure and the structure, rather than to describe the absolute orientation. When the product is placed in different postures, the orientation may change. For example, "upper" and "lower" may be interchanged.

[0046] Unless otherwise defined, all technical terms used in the embodiments of the present application have the same meaning as commonly understood by those of ordinary skill in the art. Some technical terms that appear in the embodiments of the present application are described below.

[0047] To make the technical solutions and advantages of the present application clearer, the embodiments of the present application will be further described in detail below in conjunction with the accompanying drawings.

[0048] As Figure 1 shown, the fixed-wing deployment and folding mechanism of the flying car provided in the embodiment of the present application includes a wing body plate 1, two fixed wings 2, and two sets of deployment and folding components 3. Each fixed wing 2 is connected to the wing body plate 1 through a deployment and folding component 3. The two fixed wings 2 are symmetrically distributed about the YOZ plane, and the two sets of deployment and folding components 3 are symmetrically distributed about the YOZ plane.

[0049] The deployment and folding component 3 is used to drive the fixed wing 2 to switch between the deployed state and the folded state. In the deployed state, the plane where the fixed wing 2 is located is perpendicular to the second direction Z. In the folded state, the plane where the fixed wing 2 is located is perpendicular to the first direction X, where the second direction Z is parallel to the thickness direction of the wing body plate 1 and perpendicular to the first direction X.

[0050] Figure 1 A spatial rectangular coordinate system XYZ is established. Exemplarily, the first direction X is the width direction of the fixed-wing deployment and folding mechanism and the flying car, the second direction Z is the height direction of the fixed-wing deployment and folding mechanism and the flying car, the third direction Y is the length direction of the fixed-wing deployment and folding mechanism and the flying car, the first direction X, the second direction Z, and the third direction Y are perpendicular to each other pairwise, and the above YOZ plane is the plane perpendicular to the first direction.

[0051] Exemplarily, the flying car includes a cockpit, and the wing body plate 1 is located on the cockpit. For example, the wing body plate 1 can be a part of the structure of the cockpit or an additional structural member on the cockpit, and is fixedly connected to the cockpit by means such as welding and fastener connection.

[0052] The unfolding and folding assembly 3 realizes the movable connection between the fixed wing 2 and the wing body plate 1. The unfolding and folding assembly 3 can include transmission mechanisms such as a linkage mechanism, a gear mechanism, and a screw mechanism, so as to transmit power to the fixed wing 2.

[0053] Optionally, the unfolding and folding assembly 3 can generate motion under the drive of a driving device such as a motor, and then drive the fixed wing 2 to move, so that the fixed wing 2 can be switched between the unfolded state and the folded state; or, optionally, the unfolding and folding assembly 3 can generate motion under manual operation, and then drive the fixed wing 2 to move, so that the fixed wing 2 can be switched between the unfolded state and the folded state.

[0054] As Figure 1 shown, in the unfolded state of the fixed wing 2, the fixed wing 2 is parallel to the XOY plane and extends along the first direction X. At this time, the fixed wing 2 can provide lift for the flying car to support the flying car to fly in the air.

[0055] In the folded state of the fixed wing 2, the fixed wing 2 is parallel to the YOZ plane, and the fixed wing 2 can extend along the second direction Z or the third direction Y. At this time, the fixed wing 2 can be folded and stored on both sides of the wing body plate 1, reducing the space occupied in the first direction X.

[0056] The fixed wing unfolding and folding mechanism provided by the embodiment of the present application enables the fixed wing 2 to be switched between the unfolded state and the folded state by setting the unfolding and folding assembly 3; when the fixed wing 2 is in the unfolded state, it can ensure the normal flight of the flying car; when the fixed wing 2 is in the folded state, the fixed wing 2 can be folded and stored on both sides of the flying car, greatly reducing the space occupied by the fixed wing 2 of the flying car in the first direction X, so that the flying car can drive on a conventional road and park in a general parking space.

[0057] In some embodiments, the unfolding and folding assembly 3 includes a fixed seat 31 and at least three sequentially hinged connecting rods. The fixed seat 31 is fixed on the wing body plate 1. One end of one of the connecting rods is hinged to the fixed seat 31 and can rotate around a central axis extending along the first direction X, and one end of the other of the connecting rods is hinged to the fixed seat 31 and can rotate around a central axis extending along the second direction Z.

[0058] The fixed wing 2 is connected to a connecting rod. In the unfolded state, the fixed wing 2 extends along the first direction X; in the folded state, the fixed wing 2 extends along the third direction Y.

[0059] As Figure 1As shown, the top of the wing body plate 1 has two fixing seats 31, and the fixing seats 31 and the fixed wings 2 correspond one by one. Among them, the wing body plate 1 and the fixing seats 31 can be integrally formed, or they can be two independent structures, and are fixedly connected together by means such as welding and fastener connection.

[0060] In this embodiment, the unfolding and folding assembly 3 is a spatial link mechanism. In the unfolding and folding assembly 3, one end of one link is hinged to the fixing seat 31 and can rotate around the first axis 100, and the first axis 100 extends along the first direction X; one end of the other link is hinged to the fixing seat 31 and can rotate around the second axis 200, and the second axis 200 extends along the second direction Z; and the other links are connected between these two links to achieve power transmission.

[0061] With the cooperation of multiple links, the fixed wing 2 realizes a composite movement of rotating around the first axis 100 and the second axis 200. During the process of the fixed wing 2 changing from the unfolded state to the folded state, the fixed wing 2 changes from extending along the first direction X to extending along the third direction Y, reducing the space occupied in the second direction Z and making full use of the dimensions and space in the length direction of the wing body plate 1 and the flying car.

[0062] Optionally, the second axis 200 and the first axis 100 are located in the same plane (XOZ plane), or the second axis 200 and the first axis 100 can be skew lines.

[0063] In some embodiments, at least three sequentially hinged links include a front arm rod 32, a middle arm rod 33, and a side arm rod 34.

[0064] The first end of the front arm rod 32 is hinged to the fixing seat 31 and can rotate around the central axis extending along the first direction X, and the connecting line between the first end and the second end of the front arm rod 32 is inclined to the first direction X.

[0065] The first end of the side arm rod 34 is hinged to the fixing seat 31 and can rotate around the central axis extending along the second direction Z, and the connecting line between the first end and the second end of the side arm rod 34 is inclined to the second direction Z.

[0066] The first end of the middle arm rod 33 is hinged to the second end of the front arm rod 32, and the second end of the middle arm rod 33 is hinged to the second end of the side arm rod 34.

[0067] In the unfolded state, the rotation axis of the first end of the middle arm rod 33 extends along the third direction Y, and the rotation axis of the second end of the middle arm rod 33 extends along the first direction X.

[0068] As Figure 2As shown, the forearm rod 32, the middle arm rod 33, and the side arm rod 34 are sequentially hinged. The forearm rod 32 is hinged to the fixed seat 31 at its first end to achieve its rotation around the first axis 100. The side arm rod 34 is hinged to the fixed seat 31 at its first end to achieve its rotation around the second axis 200. The two ends of the middle arm rod 33 are respectively hinged to the second end of the forearm rod 32 and the second end of the side arm rod 34, so as to transmit power between the forearm rod 32 and the side arm rod 34.

[0069] Among them, the first end of the middle arm rod 33 rotates around the third axis 300 with the second end of the forearm rod 32, and the second end of the middle arm rod 33 rotates around the fourth axis 400 with the second end of the side arm rod 34.

[0070] Exemplarily, the first axis 100, the second axis 200, the third axis 300, and the fourth axis 400 respectively extend along different radii of the same sphere.

[0071] For example Figure 2 As shown, the first axis 100 can extend along the radius of the corresponding sphere in the positive X-axis direction, and the second axis 200 can extend along the radius of the corresponding sphere in the negative Z-axis direction.

[0072] At the same time, the third axis 300 can move in the YOZ plane, and the fourth axis 400 can move in the XOY plane. When the fixed wing 2 is in the deployed state, the third axis 300 can extend along the radius of the corresponding sphere in the positive Y-axis direction, and the fourth axis 400 can extend along the radius of the corresponding sphere in the negative X-axis direction.

[0073] In the case where the fixed wing 2 is in the deployed state, when the forearm rod 32 rotates around the first axis 100 along Figure 2 the rotation direction A shown in Figure 2 it can drive the side arm rod 34 to rotate around the second axis 200 along

[0074] the rotation direction B shown in Figure 2 Thereby, the fixed wing 2 can be switched from the deployed state to the folded state. Figure 2 In the case where the fixed wing 2 is in the folded state, when the forearm rod 32 rotates around the first axis 100 along the direction opposite to

[0075] the rotation direction A in

[0076] Exemplarily, in the deployed state, the middle arm rod 33 is located in the XOY plane and is inclined to the first direction X and the third direction Y respectively.

[0077] As Figure 3 shown, the inclined cut 20 is an inclined plane located on one side of the fixed wing 2. The inclined cut 20 is used to adapt to the inclination angle of the middle arm rod 33. While realizing the connection between the fixed wing 2 and the deployment and folding assembly 3, the connection area between the fixed wing 2 and the middle arm rod 33 is increased, the connection strength between the fixed wing 2 and the middle arm rod 33 is improved, and interference between the fixed wing 2 and the front arm rod 32 and the side arm rod 34 is avoided. Optionally, the fixed wing 2 can be connected to the middle arm rod 33 by welding, fastener connection or other means.

[0078] In some embodiments, as Figure 2 shown, one end of the fixed seat 31 is provided with a first hinge seat 31-1, and the other end is provided with a second hinge seat 31-2.

[0079] The first end of the front arm rod 32 is provided with a first front hinge seat 32-1. The first front hinge seat 32-1 is hinged to the first hinge seat 31-1 through a rotating shaft 30. And the rotating shaft 30 moves synchronously with the first front hinge seat 32-1. The rotating shaft 30 is rotatably connected to the first hinge seat 31-1. The second end of the front arm rod 32 is provided with a second front hinge seat 32-2.

[0080] The first end of the middle arm rod 33 is provided with a first middle hinge seat 33-1. The first middle hinge seat 33-1 is hinged to the second front hinge seat 32-2. The second end of the middle arm rod 33 is provided with a second middle hinge seat 33-2.

[0081] The first end of the side arm rod 34 is provided with a first side hinge seat 34-1. The first side hinge seat 34-1 is hinged to the second hinge seat 31-2. The second end of the side arm rod 34 is provided with a second side hinge seat 34-2. The second side hinge seat 34-2 is hinged to the second middle hinge seat 33-2.

[0082] Exemplarily, the rotating shaft 30 is connected to the first front hinge seat 32-1 by a key to realize the synchronous movement of the rotating shaft 30 and the first front hinge seat 32-1; the rotating shaft 30 is connected to the first hinge seat 31-1 by a bearing to realize the hinged connection between the rotating shaft 30 and the first hinge seat 31-1. The rotating shaft 30 can rotate around the first axis 100, thereby driving the first front hinge seat 32-1 to rotate, and further causing the front arm rod 32 to rotate around the first axis 100.

[0083] Wherein, the rotating shaft 30 is connected to two deployment and folding assemblies 3 at the same time, that is, the rotating shaft 30 moves synchronously with the first front hinge seats 32-1 in two deployment and folding assemblies 3 respectively, and the rotating shaft 30 is hinged to the first hinge seats 31-1 of two deployment and folding assemblies 3 respectively, so that the rotating shaft 30 drives the front arm rods 32 in two deployment and folding assemblies 3 to move at the same time.

[0084] In some embodiments, the fixed-wing deployment and folding mechanism further includes a driving mechanism 10 mounted on the wing body plate 1. The driving mechanism 10 is drivingly connected to the rotating shaft 30 and is used to drive the rotating shaft 30 to rotate.

[0085] The driving mechanism 10 is mounted on the wing body plate 1 and is used to drive the rotating shaft 30 to rotate. The rotating shaft 30 transmits power to the front arm rod 32, the middle arm rod 33, and the side arm rod 34 in sequence, so that the fixed wing 2 is switched between the deployed state and the folded state.

[0086] In this embodiment, by providing the driving mechanism 10, the automation degree of the fixed-wing deployment and folding mechanism is improved.

[0087] In an alternative embodiment, as Figure 4 shown, the driving mechanism 10 includes a driving motor 10-1, a gearbox 10-2, a push rod 10-3, and a rocker arm 10-4 that are sequentially drivingly connected. The gearbox 10-2 is hinged to the wing body plate 1. One end of the push rod 10-3 facing away from the gearbox 10-2 is hinged to the rocker arm 10-4, and the rocker arm 10-4 is fixedly connected to the rotating shaft 30.

[0088] In this embodiment, the driving mechanism 10 is an electric push rod 10-3, which can convert the rotational motion of the driving motor 10-1 into the linear motion of the push rod 10-3.

[0089] Specifically, the driving motor 10-1 serves as a power source, and deceleration is achieved through the gearbox 10-2. The decelerated rotational motion is transmitted to the screw-nut pair, converting the rotational motion into the linear motion of the screw. Since the screw is rigidly connected to the push rod 10-3, the push rod 10-3 realizes telescopic motion under the drive of the screw, and the telescopic motion of the push rod 10-3 drives the swing arm to move, causing the swing arm to drive the rotating shaft 30 to rotate around the first axis 100.

[0090] In another alternative embodiment, as Figure 5 shown, the driving mechanism 10 includes a telescopic motor 10-5, a rack 10-6, and a gear 10-7. The telescopic motor 10-5 is fixedly connected to the wing body plate 1. The telescopic rod of the telescopic motor 10-5 is fixedly connected to the rack 10-6. The rack 10-6 meshes with the gear 10-7, and the gear 10-7 is coaxially and fixedly connected to the rotating shaft 30.

[0091] In this embodiment, the telescopic rod of the telescopic motor 10-5 serves as a power source, driving the rack 10-6 to move along the axial direction of the telescopic rod, and then driving the gear 10-7 meshing with the rack 10-6 to rotate, so that the rotating shaft 30 rotates around the first axis 100 under the drive of the gear 10-7.

[0092] The present application also provides an aerial vehicle, which includes the fixed-wing deployment and folding mechanism provided in any of the above embodiments.

[0093] The aerial vehicle further includes a cockpit, and the wing plate 1 of the fixed-wing deployment and folding mechanism is located on the cockpit. For example, the wing plate 1 can be a part of the structure of the cockpit or an additional structural member on the cockpit, and is fixedly connected to the cockpit by means of welding, fasteners, etc.

[0094] In the aerial vehicle provided by the embodiments of the present application, the fixed wing 2 can be switched between the deployed state and the folded state; when the fixed wing 2 is in the deployed state, it can ensure the normal flight of the aerial vehicle; when the fixed wing 2 is in the folded state, the fixed wing 2 can be folded and stored on both sides of the aerial vehicle, greatly reducing the space occupied by the fixed wing 2 of the aerial vehicle in the first direction X. When the aerial vehicle is an aerial vehicle, the aerial vehicle can drive on a conventional road and park in a general parking space.

[0095] In the present application, the terms "first" and "second" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance. The term "plurality" means two or more, unless otherwise clearly defined.

[0096] Those skilled in the art will readily think of other embodiments of the present application after considering the specification and practicing the present application disclosed herein. The present application is intended to cover any variations, uses, or adaptations of the present application, and these variations, uses, or adaptations follow the general principles of the present application and include common general knowledge or conventional technical means in the technical field not disclosed in the present application. The specification and embodiments are only regarded as exemplary.

[0097] The terms "comprising" and "including" indicate the presence of the described features, wholes, steps, operations, elements, and / or components, but do not exclude the presence or addition of one or more other features, wholes, steps, operations, elements, components, and / or their combinations.

[0098] In the present application, unless otherwise clearly specified and defined, terms such as "installed", "connected", "connected", "fixed", etc. should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be directly connected or indirectly connected through an intermediate medium, and can be the internal communication of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances.

[0099] It should be understood that the present application is not limited to the exact structures described above and shown in the drawings, and various modifications and changes can be made without departing from its scope. The scope of the present application is only limited by the appended claims.

Claims

1. A fixed-wing deployment and folding mechanism for a flying car, characterized in that The fixed-wing deployment and folding mechanism includes a wing body plate (1), two fixed wings (2), and two sets of deployment and folding components (3). Each fixed wing (2) is connected to the wing body plate (1) through the deployment and folding component (3). The two fixed wings (2) are symmetrically distributed with respect to the YOZ plane, and the two sets of deployment and folding components (3) are symmetrically distributed with respect to the YOZ plane. The deployment and folding component (3) is used to drive the fixed wing (2) to switch between the deployed state and the folded state. In the deployed state, the plane where the fixed wing (2) is located is perpendicular to the second direction (Z). In the folded state, the plane where the fixed wing (2) is located is perpendicular to the first direction (X). Wherein, the second direction (Z) is parallel to the thickness direction of the wing body plate (1) and perpendicular to the first direction (X).

2. The fixed-wing deployment and folding mechanism according to claim 1, characterized in that, The deployment and folding component (3) includes a fixed seat (31) and at least three successively hinged connecting rods. The fixed seat (31) is fixed on the wing body plate (1). One end of one of the connecting rods is hinged to the fixed seat (31) and can rotate around a central axis extending along the first direction (X). One end of another connecting rod is hinged to the fixed seat (31) and can rotate around a central axis extending along the second direction (Z). The fixed wing (2) is connected to one of the connecting rods. In the deployed state, the fixed wing (2) extends along the first direction (X). In the folded state, the fixed wing (2) extends along the third direction (Y). Wherein, the third direction (Y) is perpendicular to the first direction (X) and the second direction (Z) respectively.

3. The fixed-wing deployment and folding mechanism according to claim 2, characterized in that, The at least three successively hinged connecting rods include a forearm rod (32), a middle arm rod (33), and a side arm rod (34). The first end of the forearm rod (32) is hinged to the fixed seat (31) and can rotate around a central axis extending along the first direction (X). The connecting line between the first end and the second end of the forearm rod (32) is inclined to the first direction (X). The first end of the side arm rod (34) is hinged to the fixed seat (31) and can rotate around a central axis extending along the second direction (Z). The connecting line between the first end and the second end of the side arm rod (34) is inclined to the second direction (Z). The first end of the middle arm rod (33) is hinged to the second end of the forearm rod (32), and the second end of the middle arm rod (33) is hinged to the second end of the side arm rod (34). In the deployed state, the rotation axis of the first end of the middle arm rod (33) extends along the third direction (Y), and the rotation axis of the second end of the middle arm rod (33) extends along the first direction (X).

4. The fixed-wing deployment and folding mechanism according to claim 3, characterized in that, An inclined notch (20) is provided on the side of the fixed wing (2) close to the deployment and folding component (3). The middle arm rod (33) is adaptively connected to the inclined notch (20). In the deployed state, the extending direction of the middle arm rod (33) is inclined to the first direction (X) and the third direction (Y) respectively.

5. The fixed-wing deployment and folding mechanism according to claim 3, characterized in that, One end of the fixed seat (31) is provided with a first hinge seat (31-1), and the other end is provided with a second hinge seat (31-2); The first end of the forearm rod (32) is provided with a first front hinge seat (32-1), and the first front hinge seat (32-1) is hinged to the first hinge seat (31-1) through a rotating shaft (30). The rotating shaft (30) moves synchronously with the first front hinge seat (32-1). The rotating shaft (30) is rotatably connected to the first hinge seat (31-1). The second end of the forearm rod (32) is provided with a second front hinge seat (32-2); The first end of the middle arm rod (33) is provided with a first middle hinge seat (33-1), and the first middle hinge seat (33-1) is hinged to the second front hinge seat (32-2). The second end of the middle arm rod (33) is provided with a second middle hinge seat (33-2); The first end of the side arm rod (34) is provided with a first side hinge seat (34-1), and the first side hinge seat (34-1) is hinged to the second hinge seat (31-2). The second end of the side arm rod (34) is provided with a second side hinge seat (34-2), and the second side hinge seat (34-2) is hinged to the second middle hinge seat (33-2).

6. The fixed-wing deployment and folding mechanism according to claim 5, characterized in that The fixed-wing unfolding and folding mechanism further includes a driving mechanism (10) installed on the wing body plate (1). The driving mechanism (10) is drivingly connected to the rotating shaft (30), and the driving mechanism (10) is used to drive the rotating shaft (30) to rotate.

7. The fixed-wing deployment and folding mechanism according to claim 6, characterized in that The driving mechanism (10) includes a driving motor (10-1), a gearbox (10-2), a push rod (10-3) and a rocker arm (10-4) that are sequentially drivingly connected; The gearbox (10-2) is hinged to the wing body plate (1). One end of the push rod (10-3) facing away from the gearbox (10-2) is hinged to the rocker arm (10-4), and the rocker arm (10-4) is fixedly connected to the rotating shaft (30).

8. The fixed-wing deployment and folding mechanism according to claim 6, characterized in that, The driving mechanism (10) includes a telescopic motor (10-5), a rack (10-6) and a gear (10-7). The telescopic motor (10-5) is fixedly connected to the wing body plate (1). The telescopic rod of the telescopic motor (10-5) is fixedly connected to the rack (10-6). The rack (10-6) meshes with the gear (10-7), and the gear (10-7) is coaxially and fixedly connected to the rotating shaft (30).

9. A flying car, characterized in that, The flying car includes the fixed-wing unfolding and folding mechanism according to any one of claims 1 to 8.

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