CN118083183A - Wing surface folding and unfolding mechanism and flight device - Google Patents

Abstract

The invention relates to the technical field of folding wings of aircrafts, in particular to an airfoil folding and unfolding mechanism and an flying device. The wing surface folding and unfolding mechanism comprises a cabin body, a wing surface group, a hinge seat, a locking piece and an unfolding assembly; the wing surface group comprises a plurality of wing surfaces, the first ends of the wing surfaces are hinged with the hinged seat, and the cabin body is provided with an opening for the wing surfaces to pass through when the wing surfaces are converted from a folding state to an unfolding state; in the folded state, the second ends of the plurality of airfoils gather in the nacelle; in the deployed state, the second ends of the plurality of airfoils are separated and extend out of the nacelle through the opening; the locking piece is inserted into the second end of the wing surface and locks the wing surface group in a folded state, the center of the wing surface group is provided with a cavity extending along the vertical direction, the unfolding assembly is connected with the locking piece and is used for sequentially pushing the locking piece and the wing surface, and the wing surface group is enabled to be converted from the folded state to the unfolded state. Therefore, the folding and unfolding device for the wing surface solves the problems that the folding and unfolding device for the wing surface is complex in structure, large in occupied space and easy to clamp.

Description

Wing surface folding and unfolding mechanism and flight device

Technical Field

The invention relates to the technical field of folding wings of aircrafts, in particular to an airfoil folding and unfolding mechanism and an flying device.

Background

With the development of modern aircrafts, unmanned aircrafts and other small aircrafts have been developed in a long way due to wide application scenes. With the development requirement, the aircraft needs to be reliably contracted into a smaller volume under the condition of no work, and structures such as a flight wing, a control surface and the like for flight control are rapidly unfolded and reliably fixed at a specified position according to instructions after taking off, so that stable and reliable flight is realized.

While this type of aircraft generally has a limited installation space inside, it is necessary, in particular for the aircraft to be launched in a particular manner (e.g. catapulting, launching, etc.), to be able to fit the constraints of the launching device, for example to be able to be folded into a cylindrical, spherical, etc. shape before launching. Meanwhile, the air foil surface inside the air vehicle is contained, so that the space of the internal structure of the air vehicle can be torn, the space is in discretized distribution, and great difficulty is brought to the layout of the internal mechanism.

In the prior art, the folding and unfolding device of the airfoil surface needs to cut the airfoil surface in a large area to make room for installing a locking and unfolding mechanism, and the aerodynamic performance of the airfoil surface is seriously affected. The independent locking and unfolding schemes are difficult to ensure the synchronism of unlocking and unfolding motions, and when the locking state is maintained, the unfolding mechanism starts to work, or the locking state is released, and the unfolding mechanism does not work in time, the mechanism motion is uncoordinated. The scheme that one mechanism simultaneously completes the locking and unfolding functions is difficult to ensure the coordination of the airfoil in the locking and unfolding movement process, so that the space interference is easy to cause, and even the airfoil is blocked in the unfolding process. Meanwhile, the installation process of the mechanism is complex, and the installation reliability is low.

Disclosure of Invention

The invention provides an airfoil folding and unfolding mechanism and a flying device, which aim to solve the problems that an airfoil folding and unfolding device is complex in structure, occupies a large space and is easy to block.

A first aspect provides an airfoil fold and unfold mechanism comprising: the device comprises a cabin body, an airfoil group, a hinge seat, a locking piece and an unfolding assembly; the wing surface group comprises a plurality of wing surfaces, the first ends of the wing surfaces are hinged with the hinged seat so that the wing surface group can be converted from a folding state to an unfolding state, and the cabin body is provided with an opening for the wing surfaces to pass through when the wing surfaces are converted from the folding state to the unfolding state; in the folded state, the second ends of the plurality of airfoils gather in the nacelle; in the deployed state, the second ends of the plurality of airfoils are separated and extend out of the nacelle through the opening; the locking piece is inserted into the second end of the wing surface and locks the wing surface group in a folded state, the center of the wing surface group is provided with a cavity extending along the vertical direction, the unfolding component is connected with the locking piece and is used for sequentially pushing the locking piece and the wing surface, so that the locking piece is separated from the second end of the wing surface and the wing surface group is pushed to be converted from the folded state to the unfolded state.

In some embodiments, the deployment assembly includes a first drive source and first and second pushers connected in sequence with an output of the first drive source; the first driving source can push the first pushing member and the second pushing member to move in the vertical direction.

In some embodiments, the first pusher member is in the shape of a long rod, a first end of the first pusher member is coupled to the locking member, and a second end of the first pusher member is coupled to the second pusher member.

In some embodiments, the airfoil is provided with a first pushing surface towards the position of the second pushing member; the second pushing piece is provided with a second pushing surface towards the position of the airfoil, and the first driving source can push the second pushing piece and drive the second pushing surface to be connected with the first pushing surface so as to push the airfoil group to be switched from the folded state to the unfolded state.

In some embodiments, the second end of the airfoil is provided with a locking slot, and the locking member has a plurality of locking pawls that mate with the locking slot, the locking pawls being disposed in a one-to-one correspondence with the airfoil.

In some embodiments, in the folded state, the first pushing surface and the second pushing surface have a first separation distance therebetween in a vertical direction; in the folded state, the length of the part of the locking claw, which is matched with the locking groove, is smaller than or equal to the first interval distance.

In some embodiments, the airfoil is provided with a unfilled corner disposed toward the cavity, the unfilled corners of the plurality of airfoils enclosing a receiving cavity in a lower portion of the cavity, and the second pusher is disposed within the receiving cavity.

In some embodiments, the airfoil folding and unfolding mechanism further comprises a positioning assembly, wherein the positioning assembly comprises a plurality of positioning assemblies and is arranged in one-to-one correspondence with the airfoils, the positioning assembly is arranged on the hinging seat, and the positioning assembly is used for positioning the airfoil groups in an unfolding state.

In some embodiments, the positioning assembly comprises a second driving source and a positioning piece, one end of the second driving source is fixedly connected to the hinge seat, the second end of the second driving source can move away from the hinge seat, and the positioning piece is connected to the second end of the second driving source; when the wing surface group is switched from the folded state to the unfolded state, the second driving source can push the positioning piece to move in the direction away from the hinge seat and is abutted against the upper side surface of the wing surface in the unfolded state.

In some embodiments, the second drive source is a spring in a compressed state.

In some embodiments, the airfoil is provided with a first limiting boss, and the positioning piece is abutted against the front surface of the first limiting boss when the airfoil group is in the folded state, and is abutted against the side surface of the first limiting boss when the airfoil group is in the unfolded state.

In some embodiments, the hinge mount includes a limit slot within which the airfoil can slide; the limiting groove comprises a first limiting surface extending along the horizontal direction, and when the airfoil group is in the unfolding state, the lower side surface of the airfoil is attached to the first limiting surface.

In some embodiments, the lower side of the airfoil is further provided with a second limiting boss, and when the airfoil group is in the unfolded state, the second limiting boss is abutted with a second limiting surface of the limiting groove, and the second limiting surface is perpendicular to the first limiting surface.

In some embodiments, the first end of the airfoil is provided with a hinge portion by which the airfoil is hinged with the hinge seat.

The second aspect of the invention also provides a flying device comprising the airfoil folding and unfolding mechanism of any of the embodiments described above.

In order to solve the problems that the folding and unfolding device of the wing surfaces is complex in structure, large in occupied space and easy to clamp, in a folding state, only a single locking piece is used for simultaneously locking a plurality of wing surfaces, so that the space is effectively saved, when the wing surfaces are required to be unfolded, the locking piece is pushed by the unfolding component on one hand so that the locking piece is separated from the wing surfaces, the movement restriction on the wing surfaces is relieved, and on the other hand, after the movement restriction on the wing surfaces is relieved, the wing surfaces of the wing surface group are pushed by the unfolding component to stretch out of the cabin body through the opening of the cabin body, and therefore the conversion from the folding state to the unfolding state of the wing surface group is completed. The movable restriction on the wing surface is relieved only by the unfolding assembly, and the wing surface is pushed to unfold, so that the arrangement of parts is effectively reduced, the structure is simplified, the equipment weight is reduced, the occupied internal space of the cabin is saved, the occupation of the wing surface space is reduced, and the stability of aerodynamic performance can be ensured by the more complete wing surface shape. In addition, the locking piece and the wing surface are sequentially pushed by the unfolding assembly, so that the problems of slow unfolding speed or unfolding failure caused by interference between unlocking action and wing surface unfolding action are effectively prevented.

Drawings

FIG. 1 is a schematic view of a folded state of an airfoil fold-and-unfold mechanism according to the present application;

FIG. 2 is a schematic illustration of an airfoil according to the present application;

FIG. 3 is a schematic view of a deployment assembly and positioning member according to the present application;

FIG. 4 is an enlarged partial block diagram of the deployment assembly of the present application in an unactuated state;

FIG. 5 is a schematic view of the connection of an airfoil to a positioning member according to the present application;

FIG. 6 is a schematic view of a first configuration of an airfoil fold and unfold mechanism according to the application during deployment;

FIG. 7 is a schematic view of a second configuration of an airfoil fold and unfold mechanism according to the application during deployment;

FIG. 8 is a schematic view of a third configuration of an airfoil fold and unfold mechanism according to the application during deployment;

FIG. 9 is a schematic view of an airfoil fold and unfold mechanism according to the present application in an unfolded state.

Reference numerals: 10-airfoil, 11-hinge, 12-first limit boss, 13-second limit boss, 14-locking slot, 15-unfilled corner, 151-first thrust surface, 20-locking piece, 21-locking pawl, 30-hinge seat, 31-limit slot, 311-first limit surface, 40-deployment assembly, 41-first drive source, 411-output, 42-first thrust piece, 43-second thrust piece, 431-second thrust surface, 50-positioning assembly, 51-second drive source, 52-positioning piece, 60-cabin, 61-opening.

Detailed Description

The disclosure will now be discussed with reference to several exemplary embodiments. It should be understood that these embodiments are discussed only to enable those of ordinary skill in the art to better understand and thus practice the present disclosure, and are not meant to imply any limitation on the scope of the present disclosure.

As used herein, the term "comprising" and variants thereof are to be interpreted as meaning "including but not limited to" open-ended terms. The term "based on" is to be interpreted as "based at least in part on". The terms "one embodiment" and "an embodiment" are to be interpreted as "at least one embodiment. The term "another embodiment" is to be interpreted as "at least one other embodiment". The terms "upper", "lower", "left", "right", "front", "rear", "top", "bottom", "inner", "outer", "vertical", "horizontal", "transverse", "longitudinal", etc. refer to an orientation or positional relationship based on that shown in the drawings. These terms are only used to better describe the present application and its embodiments and are not intended to limit the scope of the indicated devices, elements or components to the particular orientations or to configure and operate in the particular orientations. Also, some of the terms described above may be used to indicate other meanings in addition to orientation or positional relationships, for example, the term "upper" may also be used to indicate some sort of attachment or connection in some cases. The specific meaning of these terms in the present application will be understood by those of ordinary skill in the art according to the specific circumstances. Furthermore, the terms "mounted," "configured," "provided," "connected," and "connected" are to be construed broadly. For example, it may be a fixed connection, a removable connection, or a unitary construction; may be a mechanical connection, or an electrical connection; may be directly connected, or indirectly connected through intervening media, or may be in internal communication between two devices, elements, or components. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art according to the specific circumstances. Furthermore, the terms "first," "second," and the like, are used primarily to distinguish between different devices, elements, or components (the particular species and configurations may be the same or different), and are not used to indicate or imply the relative importance and number of devices, elements, or components indicated. Unless otherwise indicated, the meaning of "a plurality" is two or more.

The embodiment discloses an airfoil folding and unfolding mechanism, as shown in fig. 1 to 5, may include:

The nacelle 60, the airfoil group, the hinge mount 30, the lock 20, and the deployment assembly 40; the airfoil group comprises a plurality of airfoils 10, a first end of the airfoils 10 is hinged with a hinge seat 30 so that the airfoil group can be converted from a folded state to an unfolded state, and the cabin 60 is provided with an opening 61 for the airfoils 10 to pass through when the airfoils are converted from the folded state to the unfolded state; in the folded state, the second ends of the plurality of airfoils 10 are gathered within the nacelle 60; in the deployed state, the second ends of the plurality of airfoils 10 are separated and extend out of the nacelle 60 through the opening 61; the locking piece 20 is inserted into the second end of the airfoil 10 and locks the airfoil group in a folded state, the center of the airfoil group is provided with a cavity extending along the vertical direction, the unfolding assembly 40 is connected with the locking piece 20, and the unfolding assembly 40 is used for sequentially pushing the locking piece 20 and the airfoil 10 so as to separate the locking piece 20 from the second end of the airfoil 10 and push the airfoil group to switch from the folded state to the unfolded state.

In the folded state, only a single locking piece 20 is used for locking a plurality of airfoils 10 at the same time, so that the space is effectively saved, when the aircraft takes off in a power propulsion, ejection, launching and other modes, and when the airfoils 10 need to be unfolded, the unfolding assembly 40 is used for pushing the locking piece 20 on one hand so as to separate the locking piece from the airfoils 10, thereby removing the movement restriction on the airfoils 10, and on the other hand, after removing the movement restriction on the airfoils 10, the unfolding assembly 40 is used for pushing the airfoils 10 of the airfoil group to extend out of the cabin 60 through the opening 61 of the cabin 60, thereby completing the conversion from the folded state to the unfolded state. Namely, the movement restriction on the airfoil surface 10 is relieved only by using the unfolding assembly 40, and the airfoil surface 10 is pushed to unfold, so that the arrangement of parts is effectively reduced, the structure is simplified, the equipment weight is reduced, the occupied internal space of the cabin 60 is saved, the occupation of the space of the airfoil surface 10 is reduced, and the design flexibility of the airfoil surface 10 is improved to obtain better flight control effect. In addition, compared with the scheme of adopting inertial kinetic energy to destroy the structure so as to finish unlocking action, the application adopts an actively triggered mechanical structure, has better stability, and can meet the requirement of long-term storage of ammunition when the aircraft is ammunition, guided missile and the like and has better stability in triggering.

It should be noted that, as shown in fig. 2, the airfoil 10 is similar to a flat plate structure, and its cross section may have a shape satisfying aerodynamics, after being unfolded, the airfoil 10 may be capable of cutting the airflow, and may be capable of achieving the purpose of adjusting the state of the flying device in which it is located, such as the flying attitude by adjusting parameters such as angle and rotation of the airfoil 10. One end of the airfoil 10 is connected to the hinge seat 30 and is disposed in the cabin 60 by the hinge seat 30, and in order to control the unfolded airfoil 10, the hinge seat 30 may be a part of a rudder shaft, so that the action of the airfoil 10 is controlled by controlling the action of the rudder shaft. The first end of the airfoil 10 is hinged to the hinge seat 30 in a variety of manners, such as hinges, etc., and for simplicity the device may simply be connected to the hinge seat 30 by passing a pin through the airfoil 10 in the thickness direction, thereby enabling the airfoil 10 to rotate about the hinge seat 30. In addition, since the locking member 20 and the airfoil 10 are sequentially pushed only by the deployment assembly 40, the problem of slow deployment speed or failure of deployment due to interference between the unlocking action and the deployment action of the airfoil 10 is effectively prevented.

In the folded state, the second ends of the plurality of airfoils 10 of the airfoil group gather in the cavity located at the center of the airfoil group, at this time, the plurality of airfoils 10 are arranged along the radial direction of the nacelle 60, but because the airfoils 10 are thinner, other components can be arranged between the airfoils 10 arranged adjacently, and under the premise of not influencing the actions of the airfoils 10, the space in the nacelle 60 can be fully utilized, and the space utilization rate is improved. Since the plurality of airfoils 10 are closer to one side of the cavity in the folded state, the locking member 20 may be detachably coupled to the plurality of airfoils 10 at the same time, thereby maintaining the airfoil group in the folded state, and for facilitating the installation of the locking member 20, the locking member 20 may be installed in the cavity or in an extended space of the cavity, as shown in fig. 5, at a position close to the second end of the airfoils 10, and detachably coupled to the second end of the airfoils 10.

When transitioning from the folded to the unfolded state, the unfolding assembly 40 pushes the locking member 20 away from the airfoil 10 and then pushes the airfoil 10 to rotate about the hinge, thereby transitioning it to the unfolded state. Specifically, the deployment assembly 40 may transition to the deployed state by impinging upon the airfoil 10 upon contact therewith. By the crash, forces are transmitted to the airfoil 10, causing the airfoil 10 to fully expand using inertia after having an initial velocity. At the same time, the airfoil 10 can be fully deployed by utilizing the flying inertia of the flying device in which the airfoil is positioned. Because a simple pin connection can be adopted between the airfoil 10 and the hinge seat 30, under the condition of sufficient lubrication (under the condition of small friction force at the hinge joint), the airfoil 10 can be pushed to be unfolded with small acting force. In addition, bearings or the like may be provided to further reduce friction at the hinge between the airfoil 10 and the hinge seat 30. The components of the unfolding assembly 40 for pushing can occupy only the middle cavity position when the plurality of airfoils 10 are folded, the occupied space is small, and the number of components can be reduced because the components for pushing the airfoils 10 to unfold can be eliminated, so that the occupied space in the cabin 60 is reduced as much as possible.

It should be noted that, the airfoil folding and unfolding mechanism in the above scheme may be applied to various aircrafts, unmanned aerial vehicles, missiles, and the like having flying or air-stagnation capability, specifically, the cabin 60 may be a part of an aircraft or a shell of a projectile body, and be provided with an opening 61 for passing through during unfolding of the airfoil 10, and the width of the opening 61 may be set to be slightly larger than the thickness dimension of the airfoil 10, so as to prevent blocking of the unfolding of the airfoil 10. In the folded condition, sufficient clearance should be provided between the tip of the nacelle 60 and the second end of the airfoil 10 to prevent a blockage of the airfoil 10 during deployment of the airfoil 10, thereby resulting in a deployment failure.

As a specific embodiment, as shown in fig. 3 and 4,

The deployment assembly 40 includes a first driving source 41 and a first pusher 42 and a second pusher 43 sequentially connected to an output 411 of the first driving source 41; the first driving source 41 is capable of pushing the first pushing member 42 and the second pushing member 43 to move in the vertical direction.

The first driving source 41 may be an electric device, a pneumatic device, or a device accumulating elastic potential energy, etc., but since it is generally required for an aircraft such as an unmanned aerial vehicle, an ammunition to be rapidly unfolded after leaving the launching device, there is a high requirement for the corresponding speed and the action speed, and it is limited by the volume and the load requirement of the aircraft such as the unmanned aerial vehicle, the ammunition, etc., it is required to have as small volume and weight as possible, and thus, it is preferable that the first driving source 41 may be a promoter. The ejector can adopt an initiating explosive device as a power source, and drives the extensible ejector pin arranged in the ejector to extend rapidly after the initiating explosive device is ignited.

The first pushing member 42 and the second pushing member 43 may be integrally provided, or may be separately provided and fixedly connected as a whole. In order to reduce the parts, the connection can be performed in a plugging manner, for example, the first pushing member 42 is provided with a groove, the second pushing member 43 is provided with a connection portion matched with the groove, and the first pushing member 42 and the second pushing member 43 are directly connected in an interference fit manner, so that the use of the parts is reduced, and the installation steps are simplified. By pushing the first pushing member 42 and the second pushing member 43 by the first driving source 41 to move in the vertical direction, the locking member 20 and the airfoil 10 can be further pushed, respectively, to separate the locking member 20 from the airfoil 10 and to push the airfoil 10 to be unfolded.

Specifically, as shown in fig. 1 and 3, the first pushing member 42 has a long rod shape, a first end of the first pushing member 42 is connected to the locking member 20, and a second end of the first pushing member 42 is connected to the second pushing member 43.

The first pushing member 42 in the form of a long rod is capable of penetrating the cavity portion of the airfoil group to be connected with the locking member 20 with reduced volume occupation, and in particular, the first pushing member 42 may be provided to have a cross-sectional area as small as possible to reduce occupation of the space in the nacelle 60 as much as possible and influence on the shape of the airfoil 10 while ensuring structural strength of the first pushing member 42.

In addition, the airfoil 10 is provided with a first thrust surface 151 towards the position of the second thrust piece 43; the second pushing member 43 is provided with a second pushing surface 431 facing the airfoil 10, and the first driving source 41 can push the second pushing member 43 and drive the second pushing surface 431 to meet the first pushing surface 151 so as to push the airfoil group to switch from the folded state to the unfolded state.

The second pushing member 43 may be configured as a disk, a disc, or the like, and may be disposed at a lower side of the first pushing member 42, and a top surface of the second pushing member 43 is a second pushing surface 431, which may be in contact with a lower side surface of the first end of the airfoil 10 under the driving of the first driving source 41, and a lower side surface of the airfoil 10 may be a first pushing surface 151, so as to transmit the driving force of the first driving source 41 to the airfoil 10. Specifically, the first pushing surface 151 and the second pushing surface 431 may be disposed opposite to each other, and only need to be able to contact with each other under the pushing of the first driving source 41.

The locking member 20 may be connected to the airfoil 10 by plugging, as shown in fig. 5, and as a specific embodiment, the second end of the airfoil 10 is provided with a locking slot 14, and the locking member 20 has a plurality of locking claws 21 matching with the locking slot 14, where the locking claws 21 are disposed in a one-to-one correspondence with the airfoil 10.

The airfoil group is locked in the folded condition by mating the locking pawl 21 with the locking slot 14. Specifically, the locking groove 14 may be provided to extend in the vertical direction, and accordingly, the locking claw 21 of the locking piece 20 is also provided to extend in the vertical direction, and since the driving direction of the first driving source 41 is the vertical direction, the unlocking direction of the locking piece 20 is provided to coincide with the driving direction of the first driving source 41, enabling the locking claw 21 to be smoothly disengaged from the locking groove 14. Further, the second end of the airfoil 10 may be provided with a recess, and the locking groove 14 may be provided at the bottom of the recess, so that the top surface of the locking member 20 may be flush with the end surface of the second end of the airfoil 10 when the locking member 20 is mounted to the locking groove 14 in the folded state, thereby further reducing the volume of the unfolding assembly 40. In addition, since the overall volume of the locking member 20 can be made smaller, particularly in terms of the height dimension, the depth of the recess can also be made smaller, which can improve the space utilization without significantly affecting the overall structure of the airfoil 10 and without excessively affecting the aerodynamic performance thereof.

In order to prevent the expansion assembly 40 from interfering with the two actions of unlocking the airfoil 10 and pushing the airfoil 10 open, in particular, in the folded state, the first pushing surface 151 and the second pushing surface 431 have a first separation distance in the vertical direction; in the folded state, the length of the portion of the locking claw 21 that mates with the locking groove 14 is equal to or less than the first separation distance.

The first separation distance is a distance between the first pushing surface 151 and the second pushing surface 431 in the vertical direction (also the driving direction of the first driving source 41), and is not a distance between the two surfaces. By making the length of the portion where the locking claw 21 engages with the locking groove 14 equal to or smaller than the first spacing distance, it is sufficiently ensured that the second pushing member 43 comes into contact with the airfoil 10 to push it out at the same time as or after completion of the unlocking operation of the locking member 20.

To further reduce the volume of the deployment mechanism, the deployment assembly 40 is prevented from interfering with the two actions of unlocking the airfoil 10 and pushing the airfoil 10 open, in some embodiments, as shown in FIGS. 2 and 4, the airfoil 10 is provided with a unfilled corner 15 disposed toward the cavity, the unfilled corners 15 of the plurality of airfoils 10 enclosing a receiving cavity in a lower portion of the cavity, and a second pusher 43 disposed in the receiving cavity.

Specifically, the volume of the accommodating chamber is sufficient to accommodate the second pushing member 43, and since the second pushing member 43 needs to push the portion of the airfoil 10 located at the lower side or facing the cavity, so as to be unfolded, but pushing the portion of the airfoil 10 facing the cavity is not easy to achieve for the second pushing member 43 moving in the vertical direction, so that, as a preferable option, pushing the airfoil 10 to be unfolded by pushing the downwardly disposed face of the airfoil 10 is selected. However, when the airfoil group is in a folded state, the airfoil 10 is directly pushed to move upwards, the force application direction is perpendicular to the movement trend direction of the unfolding action, and if the lower side surface which is horizontally arranged is directly pushed, interference with the hinge position can occur, so that the airfoil 10 cannot be unfolded and blocked. The provided unfilled corner 15 structure makes the first pushing surface 151 and the second pushing surface 431 both be inclined planes having a certain included angle with the horizontal direction, so that the force application direction of the airfoil 10 can be changed, and at this time, a certain included angle is formed between the force application direction and the movement trend direction of the unfolding action, so that the airfoil 10 can be pushed open smoothly, and the unfolding action can be performed. Meanwhile, the accommodating cavity can accommodate the second pushing member 43, so that the length of the unfolding assembly 40 is reduced, and the size of the unfolding assembly 40 is reduced.

In order to fix the airfoil 10 in the unfolded state after being unfolded, the airfoil folding and unfolding mechanism is prevented from being refolded under the action of air flow and the like to influence aerodynamic performance, as shown in fig. 1, the airfoil folding and unfolding mechanism further comprises a positioning assembly 50, wherein the positioning assembly 50 comprises a plurality of positioning assemblies and is arranged in one-to-one correspondence with the airfoils 10, the positioning assembly 50 is arranged on the hinging seat 30, and the positioning assembly 50 is used for positioning the airfoil group in the unfolded state.

The positioning assembly 50 may have various embodiments, such as magnetic attraction or mechanical locking, but for stability, it is preferable to use a mechanical structure to lock the positioning assembly due to the large airflow force received by the airfoil 10 during the re-flight. Specifically, the locking device can be locked by adopting a pin joint mode, an abutting mode and the like. For example, a telescoping pin may be used that extends through a mating through hole in airfoil 10 when airfoil 10 is fully extended to mate with a pivot pin at the hinge to complete the locking of airfoil 10.

As a preferred embodiment, specifically, as shown in fig. 1 and fig. 6 to 9, the positioning assembly 50 includes a second driving source 51 and a positioning member 52, one end of the second driving source 51 is fixedly connected to the hinge base 30, the second end of the second driving source 51 can move away from the hinge base 30, and the positioning member 52 is connected to the second end of the second driving source 51; when the airfoil group is switched from the folded state to the unfolded state, the second driving source 51 can push the positioning piece 52 to move away from the hinge seat 30 and abut against the upper side surface of the airfoil 10 in the unfolded state.

However, since the expansion operation of the airfoil 10 is relatively quick, the second drive source 51 is preferably configured to be quickly operated. The positioning member 52 may be a sphere, plate, or cylinder that can abut the upper side of the airfoil 10 in the deployed state and limit its rotation about the hinge. By abutting the upper side of the airfoil 10 in the extended state, movement thereof to the folded state is restricted. Additionally, the positioning assembly 50 may move in synchronization with the deployment assembly 40 as the airfoil 10 deploys such that the positioning member 52 is always in abutment against the airfoil 10, the positioning assembly 50 locking the airfoil 10 in the deployed position while the airfoil 10 is deployed. While the positioning assembly 50 is moving, it also pushes the airfoil 10 in the deployment direction, facilitating rapid deployment of the airfoil 10.

Specifically, the second drive source 51 is a spring in a compressed state.

As a specific embodiment, as shown in fig. 2, the airfoil 10 is provided with a first limiting boss 12, when the airfoil group is in a folded state, the positioning element 52 abuts against the front surface of the first limiting boss 12, and when the airfoil group is in an unfolded state, the positioning element 52 abuts against the side surface of the first limiting boss 12.

The arrangement of the limiting boss ensures that the positioning piece 52 can always keep in contact with the airfoil 10 when the airfoil 10 is in a folded state, and can continuously support the airfoil 10 against the positioning piece 52 when the airfoil 10 is unfolded, so that the airfoil 10 is prevented from shaking.

As a specific embodiment, the hinge base 30 as shown in FIG. 1 includes a limiting slot 31, and the airfoil 10 is capable of sliding within the limiting slot 31; the limiting groove 31 comprises a first limiting surface 311 extending along the horizontal direction, and when the airfoil group is in the unfolded state, the lower side surface of the airfoil 10 is attached to the first limiting surface 311.

The limiting groove 31 can prevent the airfoil 10 from shaking during the unfolding process, and can continuously provide supporting force for the airfoil 10 after the airfoil 10 is unfolded. When the airfoil 10 is unfolded, a part of its side, i.e. the lower side located below at this time, can be attached to the first limiting surface 311, so as to limit the continued rotation of the airfoil 10, and enable it to stay in a proper unfolded position. By adjusting the angle of the first limiting surface 311, an adjustment of the position of the airfoil 10 in the extended state can also be achieved.

In order to further enhance the limitation of the airfoil 10 in the unfolded state, as shown in fig. 1 and 2, a second limiting boss 13 is further disposed on the lower side surface of the airfoil 10, and when the airfoil group is in the unfolded state, the second limiting boss 13 abuts against the second limiting surface of the limiting slot 31, and the second limiting surface is perpendicular to the first limiting surface 311.

The second limiting surface may be an outward surface of the limiting groove 31, and the second limiting boss 13 protrudes with respect to a side surface of the airfoil 10, so that the second limiting surface abuts against the second limiting boss 13 in the unfolded state, and the limiting effect on the airfoil 10 is enhanced.

As a specific embodiment, as shown in FIG. 2, the first end of the airfoil 10 is provided with a hinge portion 11, and the airfoil 10 is hinged to a hinge seat 30 by the hinge portion 11.

To further illustrate the operation of the deployment assembly 40, a preferred embodiment of the present application is illustrated in fig. 1 and 6-9:

the airfoil fold-and-unfold mechanism shown in FIG. 1 is the airfoil stack in a folded condition wherein the locking member 20 engages the airfoil 10 and locks the airfoil stack in the folded condition.

When the aeroplane device needs to spread the airfoil 10, as shown in fig. 6, the driving end of the first driving source 41 extends to drive the first pushing member 42 and the second pushing member 43 to move upwards and push the locking member 20 to separate from the airfoil 10, and meanwhile, the positioning member 52 in the positioning assembly 50 is driven by the second driving source 51 to maintain an abutting state with the side surface of the airfoil 10 and generate small-angle rotation.

The airfoil 10 continues to expand, as shown in FIG. 7, the drive end of the first drive source 41 continues to extend such that the second pusher member 43 collides with the unfilled corner 15 portion of the airfoil 10, i.e., the first pusher surface 151 and the second pusher surface 431 collide, and the first pusher member 42 transmits force to the airfoil 10 to cause rapid expansion thereof.

Under the impact force and the pushing force of the positioning assembly 50, as shown in fig. 8, the airfoil 10 continues to be unfolded, and finally as shown in fig. 9, the airfoil 10 reaches a fully unfolded state, the lower side surface of the airfoil 10 is attached to the first limiting surface 311 of the limiting slot 31, at this time, the positioning assembly 50 is fully extended, and the positioning member 52 abuts against the upper side surface of the airfoil 10 and locks the same, so that the airfoil 10 can be kept in the unfolded state.

The second aspect of the invention also provides a flying device comprising the airfoil folding and unfolding mechanism of any of the embodiments described above. The flight device has the same advantages as the folding and unfolding device of the airfoil 10 and is not described in detail herein.

In some embodiments, the airfoil fold-and-unfold mechanism may also be used in a flying device such as an ammunition, a missile, or the like.

It will be understood by those of ordinary skill in the art that the foregoing embodiments are specific examples of implementing the disclosure, and that various changes in form and details may be made therein without departing from the scope of the disclosure.

Claims (11)

1. An airfoil folding and unfolding mechanism, characterized in that the airfoil folding and unfolding mechanism comprises:

the device comprises a cabin (60), an airfoil group, a hinge seat (30), a locking piece (20) and a unfolding assembly (40);

The airfoil group comprises a plurality of airfoils (10), a first end of the airfoils (10) is hinged with the hinge seat (30) so that the airfoil group can be converted from a folded state to an unfolded state, and the cabin (60) is provided with an opening (61) for the airfoils (10) to pass through when the airfoils are converted from the folded state to the unfolded state;

In the folded state, second ends of the plurality of airfoils (10) are gathered within the nacelle (60);

in the deployed state, a second end of a plurality of said airfoils (10) is separated and protrudes out of said nacelle (60) through said opening (61);

The locking piece (20) is inserted into the second end of the airfoil (10) and locks the airfoil group in the folded state;

The center of the airfoil group is provided with a cavity extending along the vertical direction, the unfolding assembly (40) is connected with the locking piece (20), and the unfolding assembly (40) is used for sequentially pushing the locking piece (20) and the airfoil (10) so as to separate the locking piece (20) from the second end of the airfoil (10) and push the airfoil group to be converted from the folded state to the unfolded state;

The unfolding assembly (40) comprises a first driving source (41) and a first pushing piece (42) and a second pushing piece (43) which are fixedly connected with an output end (411) of the first driving source (41), the first pushing piece (42) is in a long rod shape, the top end of the first pushing piece (42) is connected with the locking piece (20), and the bottom end of the first pushing piece (42) is connected with the second pushing piece (43);

the first driving source (41) is capable of pushing the first pushing member (42) and the second pushing member (43) to move in a vertical direction;

The second end of the airfoil surface (10) is provided with a locking groove (14), the locking piece (20) is provided with a plurality of locking claws (21) matched with the locking groove (14), and the locking claws (21) are arranged in one-to-one correspondence with the airfoil surface (10);

the airfoil (10) is provided with unfilled corners (15) towards the cavity, a plurality of unfilled corners (15) of the airfoil (10) enclose to form a containing cavity positioned at the lower part of the cavity, and the second pushing piece (43) is arranged in the containing cavity.

2. An airfoil fold-and-unfold mechanism according to claim 1,

-The airfoil (10) is provided with a first thrust surface (151) towards the position of the second thrust member (43);

The second pushing piece (43) is provided with a second pushing surface (431) at a position facing the airfoil (10), and the first driving source (41) can push the second pushing piece (43) and drive the second pushing surface (431) to be connected with the first pushing surface (151) so as to push the airfoil group to be converted from the folded state to the unfolded state.

3. An airfoil fold-and-unfold mechanism according to claim 2,

In the folded state, a first separation distance in a vertical direction is provided between the first pushing surface (151) and the second pushing surface (431);

in the folded state, the length of the portion of the locking claw (21) which is matched with the locking groove (14) is smaller than or equal to the first interval distance.

4. An airfoil fold-and-unfold mechanism according to claim 1,

The folding and unfolding mechanism of the wing surface (10) further comprises a positioning assembly (50), wherein the positioning assembly (50) comprises a plurality of wing surfaces (10) and is arranged in one-to-one correspondence with the wing surfaces, the positioning assembly (50) is arranged on the hinge seat (30), and the positioning assembly (50) is used for positioning the wing surface groups in the unfolding state.

5. An airfoil fold-and-unfold mechanism according to claim 4,

The positioning assembly (50) comprises a second driving source (51) and a positioning piece (52), one end of the second driving source (51) is fixedly connected to the hinging seat (30), the second end of the second driving source (51) can move in a direction away from the hinging seat (30), and the positioning piece (52) is connected to the second end of the second driving source (51);

When the airfoil group is switched from the folded state to the unfolded state, the second driving source (51) can push the positioning piece (52) to move away from the hinge seat (30) and abut against the upper side face of the airfoil (10) in the unfolded state.

6. An airfoil fold-and-unfold mechanism according to claim 5,

The second drive source (51) is a spring in a compressed state.

7. An airfoil fold-and-unfold mechanism according to claim 6,

The wing surface (10) is provided with a first limiting boss (12), when the wing surface group is in the folded state, the positioning piece (52) is abutted with the front surface of the first limiting boss (12), and when the wing surface group is in the unfolded state, the positioning piece (52) is abutted with the side surface of the first limiting boss (12).

8. An airfoil fold-and-unfold mechanism according to claim 1,

The hinge seat (30) comprises a limit groove (31), and the airfoil surface (10) can slide in the limit groove (31);

the limiting groove (31) comprises a first limiting surface (311) extending along the horizontal direction, and when the airfoil group is in the unfolded state, the lower side surface of the airfoil (10) is attached to the first limiting surface (311).

9. An airfoil fold-and-unfold mechanism according to claim 8,

The lower side of the airfoil (10) is also provided with a second limiting boss (13), when the airfoil group is in the unfolding state, the second limiting boss (13) is abutted with a second limiting surface of the limiting groove (31), and the second limiting surface is perpendicular to the first limiting surface (311).

10. An airfoil fold-and-unfold mechanism according to claim 1,

The first end of the airfoil surface (10) is provided with a hinge part (11), and the airfoil surface (10) is hinged with the hinge seat (30) through the hinge part (11).

11. A flying apparatus comprising the airfoil folding and unfolding mechanism as claimed in any one of claims 1 to 10.