CN116552852B - Wing unfolding and up-turning mechanism and aircraft - Google Patents

Abstract

The application discloses a wing unfolding and up-reflecting mechanism and an aircraft. The technical problems of low structural efficiency and large occupied space of the wing unfolding and upward reversing mechanism in the prior art are solved. The device comprises a base, a driving assembly, two driving rings and a guiding assembly, wherein the driving assembly is arranged on the base, the two driving rings are connected to the driving assembly through radial rotating shafts and are configured to rotate around the axes of the driving rings in opposite directions under the driving of the driving assembly, the two driving rings are respectively connected with two wings, each wing extends along the radial direction of the corresponding driving ring, and the guiding assembly is arranged on the base and is abutted with the two driving rings so as to guide the two driving rings rotating in opposite directions to rotate around the radial rotating shafts. The radial rotating shaft drives the wing to be unfolded, and simultaneously provides installation, positioning and rotation for the upper reverse direction of the wing. Therefore, the wing unfolding and upward reversing mechanism provided by the embodiment of the application realizes synchronous progress of upward reversing action and unfolding action, and has the advantages of higher precision and reliability, high structural efficiency, small space occupation, high stability and reliability.

Description

Wing unfolding and up-turning mechanism and aircraft

Technical Field

The application relates to the technical field of aircrafts, in particular to a wing unfolding and up-reflecting mechanism and an aircraft.

Background

Wings are components that provide lift. The wings are folded and converged in the protective cover under the normal state, the protective cover is separated when the wing is used, the wings on two sides are synchronously and reversely unfolded, and meanwhile, the wing is reversely unfolded, and an unfolding and reverse-lifting mechanism of the wing plays a vital role in the whole machine development as a core technology.

However, in the prior art, the wing unfolding and the up-reversing usually need to be performed through two sets of mechanisms, and after the unfolding mechanism is driven in place, the up-reversing mechanism starts to act, and the wings at the two sides are respectively performed. Therefore, the existing unmanned aerial vehicle wing unfolding and lifting mechanism needs a plurality of driving sources to drive the unfolding and lifting actions of the wings at two sides respectively, and the unfolding and lifting mechanisms only realize the functions of parts of the wing unfolding and lifting mechanisms respectively, so that the structural efficiency is low and the occupied space is large. In addition, the unfolding and upper reaction of the existing wing are mostly used as secondary structures, loads are required to be transmitted to the fuselage through the in-place locking mechanism, bending moments of the wings at two sides are required to be balanced through the fuselage design additional structures, and weight gain of the aircraft structure is caused.

Disclosure of Invention

The embodiment of the application solves the technical problems of low structural efficiency and large occupied space of the wing unfolding and lifting mechanism in the prior art by providing the wing unfolding and lifting mechanism and the aircraft.

In a first aspect, an embodiment of the application provides a wing unfolding and turning-up mechanism, which comprises a base, a driving assembly, two driving rings and a guiding assembly, wherein the driving assembly is mounted on the base, the two driving rings are connected to the driving assembly through radial rotating shafts and are configured to rotate around self axes in opposite directions under the driving of the driving assembly, the two driving rings are respectively connected with two wings, each wing extends along the radial direction of the corresponding driving ring, and the guiding assembly is mounted on the base and is abutted with the two driving rings so as to guide the two driving rings rotating reversely to rotate around the radial rotating shafts.

With reference to the first aspect, in one possible implementation manner, the driving assembly includes a power piece, a driving gear and two sleeves, the power piece is installed in the base, an output end of the power piece extends out of a side wall of the base, the driving gear is installed at the output end of the power piece, the two sleeves are rotationally sleeved on the outer side of the base and are provided with a plurality of transmission teeth meshed with the driving gear at the end face facing along the driving gear, and the two transmission rings are respectively connected to the two sleeves through radial rotating shafts and are in clearance with the sleeves.

With reference to the first aspect, in one possible implementation manner, the guide assembly includes a spiral sliding table, the spiral sliding table is mounted on the base and is provided with a spiral ascending surface and a spiral descending surface facing the driving ring, the driving ring includes sliding blocks, the two sliding blocks are connected to the driving ring and are located on two sides of the radial rotating shaft, and each sliding block is respectively provided with a sliding inclined surface abutting against the spiral ascending surface and the spiral descending surface.

With reference to the first aspect, in one possible implementation manner, a cross-sectional area of the slider is smaller than a sliding inclined plane of the spiral ascending surface and the spiral descending surface.

With reference to the first aspect, in a possible implementation manner, a blocking structure is provided between the spiral ascending surface and the spiral descending surface, and is used for blocking the sliding block.

With reference to the first aspect, in a possible implementation manner, the blocking structure comprises a step, the highest position of the spiral ascending surface is lower than the highest position of the spiral descending surface, the step is formed by the juncture of the highest position of the spiral ascending surface and the highest position of the spiral descending surface, the highest position of the spiral ascending surface is adjacent to the highest position of the spiral descending surface, and/or the blocking structure comprises a limiting block, and the limiting block is arranged at the juncture of the lowest position of the spiral ascending surface and the lowest position of the spiral descending surface, and the lowest position of the spiral ascending surface is adjacent to the lowest position of the spiral descending surface.

With reference to the first aspect, in one possible implementation manner, the spiral rising surface gradually transitions to an inner low and outer high setting, the spiral falling surface gradually transitions to an inner high and outer low setting, and the inclination of the spiral rising surface and the spiral falling surface increases with the rising of the spiral surface.

With reference to the first aspect, in a possible implementation manner, the base comprises a fixed cylinder and rotating assemblies, wherein the rotating assemblies are installed at two ends of the fixed cylinder and are configured to provide rotating space for the sleeves, the power piece is installed in the fixed cylinder, and the two sleeves are sleeved on the outer sides of the fixed cylinder in a rotating mode.

With reference to the first aspect, in one possible implementation manner, the rotating assembly includes a flange, a pressure plate and a thrust bearing, the thrust bearing is sleeved at one end of the sleeve, which is far away from the driving gear, and is configured to provide a rotating space for the sleeve, the pressure plate is mounted at the outer side of the thrust bearing and is configured to press the thrust bearing, and the flange is fixedly connected with the pressure plate and is arranged at two ends of the fixed cylinder.

In a second aspect, embodiments of the present application provide an aircraft comprising a wing deployment and retraction mechanism according to the first aspect or any one of the possible implementations of the first aspect.

One or more technical solutions provided in the embodiments of the present application at least have the following technical effects or advantages:

The wing unfolding and up-reflecting mechanism provided by the embodiment of the application comprises a base, a driving assembly, a guiding assembly and two driving rings. The driving assembly of the embodiment of the application drives the driving ring to rotate in the opposite direction, so that the wing can be driven to rotate and spread in the opposite direction. The radial rotating shaft drives the wing to be unfolded, and simultaneously provides installation, positioning and rotation for the upper reverse direction of the wing. The scheme of the embodiment of the application has high integration, direct force transmission and high structural efficiency, and the bending moment generated by the wing due to the lifting force is self-balanced at the radial rotating shaft, so that the influence on the machine body structure is avoided, and the weight of the whole device is reduced. The guiding component provides an upper counter limit for the upper counter of the wing on one hand and an upper counter slide rail for the upper counter of the wing on the other hand. Therefore, the wing unfolding and upward reversing mechanism provided by the embodiment of the application can realize synchronous progress of upward reversing action and unfolding action through the driving component, and has the advantages of higher precision and reliability, high structural efficiency, small space occupation, high stability and reliability.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for the description of the embodiments of the present application will be briefly described, and it is obvious that the drawings in the following description are some embodiments of the present application, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic structural view of an aircraft according to an embodiment of the present application;

FIG. 2 is a schematic structural view of a wing deployment and wind-up mechanism provided by an embodiment of the present application;

FIG. 3 is a cross-sectional view of a wing deployment and wind up mechanism provided by an embodiment of the present application;

fig. 4 is a schematic structural view of a fixing barrel according to an embodiment of the present application;

fig. 5 is a schematic structural diagram of a spiral sliding table located below according to an embodiment of the present application;

fig. 6 is a schematic structural diagram of an upper spiral sliding table according to an embodiment of the present application;

FIG. 7 is a schematic view of an upper sleeve according to an embodiment of the present application;

FIG. 8 is a schematic view of a lower sleeve according to an embodiment of the present application;

FIG. 9 is a schematic structural view of a wing provided in an embodiment of the present application;

FIG. 10 is a top view of a wing deployment and wind up mechanism provided by an embodiment of the present application.

The reference numerals comprise a 1-base, a 11-fixed cylinder, a 111-mounting groove, a 12-rotating component, a 121-flange plate, a 122-pressure plate, a 123-thrust bearing, a 2-driving component, a 21-power piece, a 22-driving gear, a 23-sleeve, 231-driving teeth, a 3-driving ring, a 31-sliding block, a 4-guiding component, a 41-spiral sliding table, a 411-spiral ascending surface, a 412-spiral descending surface, a 42-blocking structure, a 421-step, a 422-limiting block, a 5-radial rotating shaft and a 6-wing.

Detailed Description

The following description of the embodiments of the present application will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are some, but not all embodiments of the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.

In the description of the embodiments of the present application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," "outer," and the like indicate or are based on the orientation or positional relationship shown in the drawings, merely to facilitate description of the embodiments of the present application and simplify description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present application. The terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance. The terms "mounted," "connected," "coupled," and "connected" are used in a broad sense, and may be, for example, fixedly connected, detachably connected, or integrally connected, mechanically connected, electrically connected, directly connected, or indirectly connected via an intermediate medium, or may be in communication with the interior of two elements. The specific meaning of the above terms in the embodiments of the present application will be understood by those of ordinary skill in the art according to specific circumstances.

As shown in fig. 1, the wing unfolding and up-reflecting mechanism provided by the embodiment of the application comprises a base 1, a driving assembly 2, a guiding assembly 4 and two transmission rings 3. The drive assembly 2 is mounted to the base 1. Both drive rings 3 are connected to the drive assembly 2 by means of radial shafts 5 and are configured to rotate in opposite directions about their own axes under the drive of the drive assembly 2. The two driving rings 3 are respectively connected with two wings 6, each wing 6 extends along the radial direction of the corresponding driving ring 3, and the guiding component 4 is installed on the base 1 and is abutted with the two driving rings 3 so as to guide the two driving rings 3 rotating reversely to rotate around the radial rotating shaft 5.

It should be noted that, the driving assembly 2 in the embodiment of the present application drives the driving ring 3 to rotate in the opposite direction, so as to drive the wing 6 to rotate and expand in the opposite direction. Typically, the wing 6 is deployed at an angle of 90 °. The radial rotating shaft 5 drives the wing 6 to be unfolded, and simultaneously provides installation, positioning and rotation for the upper back of the wing 6. The scheme of the embodiment of the application has high integration, direct force transmission and high structural efficiency, and the bending moment generated by the wing 6 due to the lifting force is self-balanced at the radial rotating shaft 5, so that the weight of the whole device is reduced. The guide assembly 4 provides on the one hand an upper counter stop for the upper counter of the wing 6 and on the other hand an upper counter rail for the upper counter of the wing 6. Therefore, the wing unfolding and upward reversing mechanism provided by the embodiment of the application can realize synchronous progress of upward reversing action and unfolding action, and has the advantages of higher precision and reliability, high structural efficiency, small space occupation, high stability and reliability.

As shown in fig. 2 and 3, the drive assembly 2 includes a power member 21, a drive gear 22, and two sleeves 23. The power member 21 is installed in the base 1, and an output end of the power member 21 protrudes from a side wall of the base 1, and the driving gear 22 is installed at the output end of the power member 21. As shown in fig. 7 and 8, the two sleeves 23 are rotatably fitted to the outside of the base 1, and a plurality of transmission teeth 231 engaged with the drive gear 22 are provided on the end face facing along the drive gear 22. The two sleeves 23 serve not only as rotating sleeves 23 for the deployment of the wing 6, but also as mounting base structures for the radial shaft 5. The two driving rings 3 are respectively connected to the two sleeves 23 through radial rotating shafts 5, and gaps exist between the driving rings 3 and the sleeves 23. The gap between the drive ring 3 and the sleeve 23 provides space for rotation of the drive ring 3. The two sleeves 23 of the embodiment of the application are located above and below the drive gear 22, respectively. The driving gear 22 and the transmission gear 231 form a gear pair, and the output end of the power piece 21 drives the gear pair to rotate, so that the sleeve 23 positioned above and the sleeve 23 positioned below are driven to synchronously and reversely rotate, and further synchronous and reverse unfolding of the wing 6 can be realized.

In particular, as shown in fig. 1 and 3, the drive assembly 2 includes two drive gears 22. The power member 21 includes a double-output-shaft synchronous reversing gear motor, and two drive gears 22 are respectively mounted on two output shafts of the double-output-shaft synchronous reversing gear motor. The two identical driving gears 22 are installed on the output shafts of the two sides of the double-output-shaft synchronous reversing gear motor, and the driving gears 22 respectively form a precise gear pair with the transmission teeth 231 positioned above and the transmission teeth 231 positioned below. In the process of rotating the output shafts on two sides of the double-output-shaft synchronous reversing gear motor, the gear pair is driven, so that the sleeve 23 positioned above and the sleeve 23 positioned below are driven to synchronously and reversely rotate, and synchronous and reverse unfolding of the wing 6 can be realized. The embodiment of the application relies on the high reliability of the gear pair transmission, thereby ensuring the high reliability and high stability of the wing 6 in the unfolding process.

Specifically, the gear pair of the embodiment of the application is a straight bevel gear transmission.

Of course, the power element 21 of the embodiment of the present application is not limited by the dual-output shaft synchronous reversing gear motor, and the power element 21 of the embodiment of the present application may be a single-output shaft gear motor, and be matched with a driven stabilizing gear pair. The power member 21 of the embodiment of the present application may be two identical synchronous single-output-shaft gear motors.

In one implementation of the embodiment of the application, the guiding assembly 4 comprises a helical ramp 41. The screw slide table 41 is attached to the base 1, and is provided with a screw rising surface 411 and a screw falling surface 412 facing the drive ring 3. The spiral lifting surface 411 of the present embodiment provides an upward counter rail for the upward counter of the wing 6. The spiral descent surface 412 limits the upward reversal of the wing 6 and also provides the primary load bearing capacity for the wing 6 after the upward reversal is in place.

As shown in fig. 9, the drive ring 3 includes a slider 31. The two sliding blocks 31 are connected to the transmission ring 3 and located at two sides of the radial rotating shaft 5, and each sliding block 31 is respectively provided with a sliding inclined surface which is abutted against the spiral ascending surface 411 and the spiral descending surface 412.

Further, fig. 6 shows an embodiment of a spiral sliding table 41 with a driving ring 3 at the upper side abutting against, wherein the left side of the spiral sliding table 41 is a spiral ascending surface 411, and the right side of the spiral sliding table 41 is a spiral descending surface 412. The spiral slipway 41 is installed in the below of driving ring 3, and when driving ring 3 follows sleeve 23 rotatory expansion, the slider 31 of driving ring 3 can receive the extrusion of spiral slip way 41 for driving ring 3 left side rises and right side descends simultaneously, and spiral slip way 41 is in real-time tangential extrusion state with slider 31, thereby makes wing 6 realize the anti-function of turning up. Specifically, a plurality of first connection through holes are provided on a side of the screw slide table 41 away from the upper transmission ring 3, and first connection screw holes corresponding to the first connection through holes are provided on the base 1. The first connection hole is screwed to the first connection screw hole by a screw, so that the screw slide table 41 can be fixedly connected to the base 1.

Similarly, fig. 5 shows an embodiment of a spiral sliding table 41 where the transmission ring 3 located below is abutted, the right side of the spiral sliding table 41 is a spiral ascending surface 411, and the left side of the spiral sliding table 41 is a spiral descending surface 412. The screw slipway 41 is installed in the below of drive ring 3, and screw slipway 41 installs in the below of drive ring 3, and when drive ring 3 followed sleeve 23 rotation and expanded, the slider 31 of drive ring 3 can receive the extrusion of the helicoid of screw slipway 41 for drive ring 3 right side rises while the left side descends, and screw slipway 41 is in real-time tangential extrusion state with slider 31, thereby makes wing 6 realize the anti-function. Specifically, a plurality of second connection through holes are provided on the side of the screw slide table 41 away from the transmission ring 3 below, and a second connection screw hole corresponding to the second installation through hole is provided on the base 1. The second connection through hole is screwed to the second connection screw hole by a screw, so that the fixed connection of the screw slide table 41 and the base 1 can be realized.

Of course, the embodiment of the present application is not limited to the structure of fig. 6, and the spiral sliding table 41 may be disposed above the upper driving ring 3, which is the same as the principle of fig. 5.

In one implementation of the embodiment of the present application, the cross-sectional area of the slider 31 is smaller than the sliding slopes of the spiral ascending surface 411 and the spiral descending surface 412.

In one implementation of the embodiment of the present application, a blocking structure 42 is provided between the spiral ascending surface 411 and the spiral descending surface 412 for blocking the slider 31. The blocking structure 42 can block the rotation of the sliding block 31, so that the rotation of the wing 6 can be blocked, and further the dihedral angle of the wing 6 can be accurately limited.

In one implementation of an embodiment of the present application, blocking structure 42 includes a step 421. The highest position of the spiral ascending surface 411 is lower than the highest position of the spiral descending surface 412, so that a step 421 is formed by the junction of the highest position of the spiral ascending surface 411 and the highest position of the spiral descending surface 412, and the highest position of the spiral ascending surface 411 is adjacent to the highest position of the spiral descending surface 412, and/or the blocking structure 42 comprises a limiting block 422, wherein the limiting block 422 is arranged at the junction of the lowest position of the spiral ascending surface 411 and the lowest position of the spiral descending surface 412, and the lowest position of the spiral ascending surface 411 is adjacent to the lowest position of the spiral descending surface 412. When the wing 6 rotates up and is reversed in place, the limiting block 422 can accurately limit the wing 6 by 90 degrees.

The application realizes the synchronous proceeding of the reverse and unfolding actions on the wing 6 through the single driving component 2, and has higher precision and reliability. Meanwhile, the embodiment of the application well merges the mechanism which does not normally bear force with the main bearing structure of the aircraft, the overall structure has high efficiency and small space occupation, and the unfolding and upward-reflecting stability and reliability of the wing 6 are high.

The blocking structure 42 may be formed by the step 421, or the blocking structure 42 may be formed by the stopper 422. Of course, the blocking structure 42 may also be formed by the step 421 and the stopper 422 together. The blocking structure 42 can control the deployment angle of the wing 6, and thus the flip angle of the wing 6 can be precisely controlled. In addition, the blocking structure 42 also solves the problem of having to carry the main loads when the wing 6 is in the anti-windup position.

In one implementation manner of the embodiment of the present application, as shown in fig. 5 and 6, the spiral ascending surface 411 gradually transitions to an inner low and outer high setting, the spiral descending surface 412 gradually transitions to an inner high and outer low setting, and the inclination of the spiral ascending surface 411 and the spiral descending surface 412 increases with the ascending of the spiral surface, so that an upward rolling effect can be achieved. Specifically, the side of the spiral rising surface 411 closer to the base 1 is lower than the side farther from the base 1, and the width is sufficiently larger than the surface of the slider 31 that is engaged with it all the time. The spiral pitch of the spiral ascending surface 411 can be designed according to different requirements to meet different pitch angle requirements. The spiral lifting surface 411 provides an upward counter-sliding track for the wing 6.

The side of the spiral descending surface 412 near the base 1 is higher than the side far from the base 1, and the width is sufficiently larger than the surface of the slider 31 which is engaged with it all the time. The spiral descending height of the spiral descending surface 412 is identical to the spiral ascending height of the spiral ascending surface 411. The spiral descent surface 412 serves to limit the wing 6 against upward rotation, and also provides a primary load bearing capacity for the wing 6 after upward rotation.

As shown in fig. 3, the base 1 includes a stationary barrel 11 and a rotating assembly 12. The rotating assemblies 12 are mounted at both ends of the fixed cylinder 11 and configured to provide a rotating space for the sleeve 23. The power piece 21 is installed in the fixed cylinder 11, and the two sleeves 23 are sleeved on the outer side of the fixed cylinder 11 in a rotating mode.

In one implementation of the embodiment of the present application, as shown in fig. 4, the side surface of the fixed cylinder 11 is provided with a mounting groove 111 whose bottom surface is a plane. The output end of the power member 21 protrudes from the mounting groove 111. The driving gear 22 is installed in the installation recess 111, so that installation space can be saved, the whole structure is more compact, and the occupied space is small.

As shown in fig. 3, the rotating assembly 12 includes a flange 121, a pressure plate 122, and a thrust bearing 123. The thrust bearing 123 is sleeved on an end of the sleeve 23 remote from the drive gear 22, and is configured to provide a rotational space for the sleeve 23. The pressure plate 122 is mounted on the outer side of the thrust bearing 123, and is configured to press the thrust bearing 123. The flange 121 is fixedly connected with the pressure plate 122 and is arranged at two ends of the fixed cylinder 11. The flange 121 and the fixed cylinder 11 are installed into a whole through screws, and can be installed and fixed on a machine body structure as a main stress and installation positioning reference structure of the whole mechanism.

It should be noted that, as shown in fig. 5, the end of the pressure plate 122 away from the flange plate 121 may be provided with a spiral sliding table 41, which may provide a sliding rail and a limit for the upward and downward movement of the wing 6. Further, a flange surface is provided at one end of the sleeve 23 far from the driving gear 22, and the flange surface is pressed against the fixed cylinder 11 by the thrust bearing 123, so that the reliability and stability of the rotation of the sleeve 23 can be improved.

The load transmitted by the wing 6 according to the embodiment of the present application is mainly lift force and bending moment generated by the lift force. Under the current structure, the bending moment generated by the lifting force of the two wings 6 is self-balanced at the radial rotating shaft 5, and no additional structure is needed, so that the whole weight of the mechanism can be reduced. Therefore, the wing unfolding and up-reflecting mechanism of the embodiment of the application is highly integrated, the force transmission is direct, and the structural efficiency is high.

The main load of the wing 6 is aerodynamic lift during flight. Therefore, the wing 6 needs to be limited in deployment and in the upward direction. On the one hand, to ensure the precision of the unfolding and the dihedral angles of the wing 6, and on the other hand, to make the bearing capacity more stable and reliable. The wing unfolding and upper reversing mechanism not only meets the precision requirements of the wing 6 unfolding and upper reversing, but also can be used as a main structure bearing piece.

As shown in fig. 1 and 10, an embodiment of the present application provides an aircraft including the wing deployment and lift-up mechanism described above. The overall weight and size of the aircraft in the embodiment of the application meet the requirement of light weight, and can bear larger load.

In this specification, each embodiment is described in a progressive manner, and the same or similar parts of each embodiment are referred to each other, and each embodiment is mainly described as a difference from other embodiments.

The foregoing embodiments are only for illustrating the technical solution of the present application, but not for limiting the same, and although the present application has been described in detail with reference to the foregoing embodiments, it will be understood by those skilled in the art that modifications may be made to the technical solution described in the foregoing embodiments, or equivalents may be substituted for some or all of the technical features thereof, without departing from the spirit of the corresponding technical solution from the scope of the technical solution of the present application.

Claims (9)

1. A wing deployment and lift mechanism comprising:

a base (1);

a drive assembly (2) mounted to the base (1);

Two transmission rings (3) are connected to the driving assembly (2) through radial rotating shafts (5) and are configured to rotate around the axis of the driving assembly (2) in opposite directions, the two transmission rings (3) are respectively connected with two wings (6), each wing (6) extends along the radial direction of the corresponding transmission ring (3), and

The guide assembly (4) is arranged on the base (1) and is abutted with the two transmission rings (3) so as to guide the two transmission rings (3) rotating reversely to rotate around the radial rotating shaft (5);

The guide assembly (4) comprises a spiral sliding table (41), wherein the spiral sliding table (41) is arranged on the base (1) and is provided with a spiral ascending surface (411) and a spiral descending surface (412) which face the transmission ring (3);

The transmission ring (3) comprises sliding blocks (31), wherein the two sliding blocks (31) are connected to the transmission ring (3) and located on two sides of the radial rotating shaft (5), and each sliding block (31) is respectively provided with a sliding inclined surface which is abutted to the spiral ascending surface (411) and the spiral descending surface (412).

2. Wing deployment and up-counter mechanism according to claim 1, characterized in that the drive assembly (2) comprises a power member (21), a drive gear (22) and two sleeves (23);

The power piece (21) is arranged in the base (1), and the output end of the power piece (21) extends out of the side wall of the base (1);

The driving gear (22) is arranged at the output end of the power piece (21);

The two sleeves (23) are sleeved on the outer side of the base (1) in a rotating way, and a plurality of transmission teeth (231) meshed with the driving gear (22) are arranged on the end face of the driving gear (22) facing to the edge;

the two transmission rings (3) are respectively connected to the two sleeves (23) through the radial rotating shafts (5), and gaps are reserved between the transmission rings (3) and the sleeves (23).

3. Wing deployment and lifting mechanism according to claim 1, characterized in that the cross-sectional area of the slider (31) is smaller than the sliding inclined surfaces of the spiral rising surface (411) and the spiral falling surface (412).

4. A wing deployment and lifting mechanism according to claim 3, characterised in that a blocking structure (42) is provided between the spiral rising surface (411) and the spiral falling surface (412) for blocking the slider (31).

5. The wing deployment and anti-wind mechanism of claim 4, wherein the blocking structure (42) comprises a step (421);

-the highest point of the spiral rising surface (411) is lower than the highest point of the spiral falling surface (412), such that the junction of the highest point of the spiral rising surface (411) and the highest point of the spiral falling surface (412) forms the step (421), and the highest point of the spiral rising surface (411) is adjacent to the highest point of the spiral falling surface (412);

And/or the blocking structure (42) comprises a limiting block (422), wherein the limiting block (422) is arranged at the junction between the lowest part of the spiral ascending surface (411) and the lowest part of the spiral descending surface (412), and the lowest part of the spiral ascending surface (411) is adjacent to the lowest part of the spiral descending surface (412).

6. The wing deployment and pitch-up mechanism of claim 5, wherein the spiral lifting surface (411) gradually transitions to an inside-low, outside-high setting, the spiral lowering surface (412) gradually transitions to an inside-high, outside-low setting, and the pitch of the spiral lifting surface (411) and the spiral lowering surface (412) increases as the spiral surface rises.

7. Wing deployment and up-counter mechanism according to claim 2, characterized in that the base (1) comprises a fixed barrel (11) and a rotating assembly (12);

The rotating assemblies (12) are mounted at two ends of the fixed cylinder (11) and are configured to provide a rotating space for the sleeve (23);

The power piece (21) is arranged in the fixed cylinder (11), and the two sleeves (23) are rotatably sleeved on the outer side of the fixed cylinder (11).

8. The wing deployment and anti-wind mechanism of claim 7, wherein the rotating assembly (12) includes a flange plate (121), a pressure plate (122), and a thrust bearing (123);

the thrust bearing (123) is sleeved at one end of the sleeve (23) far away from the driving gear (22) and is configured to provide a rotation space for the sleeve (23);

The pressure plate (122) is mounted on the outer side of the thrust bearing (123) and is configured to press the thrust bearing (123);

The flange plate (121) is fixedly connected with the pressure plate (122), and is arranged at two ends of the fixed cylinder (11).

9. An aircraft comprising a wing deployment and retraction mechanism as claimed in any one of claims 1 to 8.