A wing deployment and dihedral mechanism and an aircraft

Abstract

The present application discloses a wing deployment and dihedral mechanism and an aircraft. It solves the technical problems of low structural efficiency and large space occupation of the wing deployment and dihedral mechanism in the prior art. A driving assembly is installed on a base; two transmission rings are both connected to the driving assembly through radial rotating shafts and are configured to rotate in opposite directions around their own axes under the drive of the driving assembly; two wings are respectively connected to the two transmission rings, and each wing extends radially along the corresponding transmission ring; and a guiding assembly is installed on the base and abuts against the two transmission rings to guide the two transmission rings rotating in opposite directions to rotate around the radial rotating shafts. The radial rotating shafts not only drive the wings to deploy, but also provide installation positioning and rotation for the dihedral of the wings. Therefore, the wing deployment and dihedral mechanism provided by the embodiments of the present application realizes the synchronous progress of dihedral actuation and deployment actuation, has high precision and reliability, high structural efficiency, small space occupation, high stability and reliability.

Description

Technical Field

[0001] This application relates to the technical field of aircraft, and particularly to a wing deployment and upward-turning mechanism and an aircraft. Background Art

[0002] The wing is a component that provides lift. In the normal state, the wings are folded and retracted within the protective cover. When in use, the protective cover disengages, and the two wings are synchronously deployed in opposite directions and simultaneously turned upward. Its deployment and upward-turning mechanism, as the core technology, plays a crucial role in the development of the whole aircraft.

[0003] However, in the prior art, the deployment and upward-turning of the wings usually need to be performed by two sets of mechanisms. After the deployment mechanism is driven in place, the upward-turning mechanism starts to actuate, and the two wings are respectively operated. Therefore, the wing deployment and upward-turning mechanisms of existing unmanned aircraft require multiple drive sources to respectively drive the deployment and upward-turning actions of the two wings, and their deployment and upward-turning mechanisms only perform their respective partial functions, resulting in low structural efficiency and large occupied space. In addition, the deployment and upward-turning of existing wings are mostly used as secondary structures, and it is necessary to transfer the load to the fuselage through a positioning and locking mechanism. The bending moments of the two wings need to be balanced by designing additional structures on the fuselage, resulting in an increase in the weight of the aircraft structure. Summary of the Invention

[0004] Embodiments of this application provide a wing deployment and upward-turning mechanism and an aircraft, which solve the technical problems of low structural efficiency and large occupied space of the wing deployment and upward-turning mechanisms in the prior art.

[0005] In a first aspect, embodiments of this application provide a wing deployment and upward-turning mechanism, including: a base; a drive assembly installed on the base; two transmission rings, both connected to the drive assembly through radial rotating shafts and configured to rotate in opposite directions around their own axes under the drive of the drive assembly; two of the transmission rings are respectively connected to two wings, and each wing extends radially along the corresponding transmission ring; and a guiding assembly installed on the base and abutting against the two transmission rings to guide the two reversely rotating transmission rings to rotate around the radial rotating shafts.

[0006] In combination with the first aspect, in a possible implementation, the drive assembly includes a power member, a drive gear, and two sleeves; the power member is installed inside the base, and the output end of the power member extends out from the side wall of the base; the drive gear is installed on the output end of the power member; the two sleeves are rotatably sleeved outside the base, and are provided with a plurality of transmission teeth meshing with the drive gear on the end face facing along the drive gear; the two transmission rings are respectively connected to the two sleeves through the radial rotating shafts, and there is a gap between the transmission ring and the sleeve.

[0007] In combination with the first aspect, in a possible implementation manner, the guiding component includes a spiral slide; the spiral slide is installed on the base and is provided with a spiral rising surface and a spiral falling surface facing the transmission ring; the transmission ring includes sliders; both of the two sliders are connected to the transmission ring and are located on both sides of the radial rotating shaft, and each slider is respectively provided with a sliding inclined surface abutting against the spiral rising surface and the spiral falling surface.

[0008] In combination with the first aspect, in a possible implementation manner, the cross-sectional area of the slider is smaller than the sliding inclined surfaces of the spiral rising surface and the spiral falling surface.

[0009] In combination with the first aspect, in a possible implementation manner, a blocking structure is provided between the spiral rising surface and the spiral falling surface for blocking the slider.

[0010] In combination with the first aspect, in a possible implementation manner, the blocking structure includes a step; the highest point of the spiral rising surface is lower than the highest point of the spiral falling surface, so that the intersection of the highest point of the spiral rising surface and the highest point of the spiral falling surface forms the step, and the highest point of the spiral rising surface is adjacent to the highest point of the spiral falling surface; and / or, the blocking structure includes a limiting block; the limiting block is provided at the intersection of the lowest point of the spiral rising surface and the lowest point of the spiral falling surface, and the lowest point of the spiral rising surface is adjacent to the lowest point of the spiral falling surface.

[0011] In combination with the first aspect, in a possible implementation manner, the spiral rising surface is gradually transitioned to be lower inside and higher outside, the spiral falling surface is gradually transitioned to be higher inside and lower outside, and the inclination of the spiral rising surface and the spiral falling surface increases as the spiral surface rises.

[0012] In combination with the first aspect, in a possible implementation manner, the base includes a fixed cylinder and a rotating component; the rotating component is installed at both ends of the fixed cylinder and is configured to provide a rotating space for the sleeve; the power component is installed inside the fixed cylinder, and the two sleeves are rotatably sleeved outside the fixed cylinder.

[0013] In combination with the first aspect, in a possible implementation manner, the rotating component includes a flange plate, a pressure plate and a thrust bearing; the thrust bearing is sleeved on the end of the sleeve away from the driving gear and is configured to provide a rotating space for the sleeve; the pressure plate is installed outside the thrust bearing and is configured to press the thrust bearing; the flange plate is fixedly connected to the pressure plate and is provided at both ends of the fixed cylinder.

[0014] In a second aspect, an embodiment of the present application provides an aircraft, including the wing deployment and dihedral mechanism described in the first aspect or any possible implementation manner of the first aspect.

[0015] One or more technical solutions provided in the embodiments of the present application have at least the following technical effects or advantages:

[0016] The wing deployment and dihedral mechanism provided in the embodiment of the present application includes a base, a drive assembly, a guiding assembly, and two transmission rings. The drive assembly in the embodiment of the present application drives the transmission rings to rotate in opposite directions, so as to drive the wings to rotate and deploy in opposite directions. The radial rotating shaft not only drives the wings to deploy, but also provides installation positioning and rotation for the dihedral of the wings. The solution in the embodiment of the present application is highly integrated, with direct force transmission and high structural efficiency. It self-balances the bending moment generated by the lift of the wings at the radial rotating shaft, thus avoiding affecting the airframe structure and further reducing the weight of the overall device. The guiding assembly on the one hand provides dihedral limit for the dihedral of the wings; on the other hand, it provides a dihedral slide rail for the dihedral of the wings. Therefore, the wing deployment and dihedral mechanism provided in the embodiment of the present application can achieve synchronous dihedral actuation and deployment actuation through the drive assembly, with high precision, high reliability, high structural efficiency, small space occupation, high stability and high reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for describing the embodiments of the present application will be briefly introduced below. Obviously, the drawings in the following description are some embodiments of the present application. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0018] Figure 1 It is a schematic structural diagram of the aircraft provided by the embodiment of the present application;

[0019] Figure 2 It is a schematic structural diagram of the wing deployment and dihedral mechanism provided by the embodiment of the present application;

[0020] Figure 3 It is a cross-sectional view of the wing deployment and dihedral mechanism provided by the embodiment of the present application;

[0021] Figure 4 It is a schematic structural diagram of the fixed cylinder provided by the embodiment of the present application;

[0022] Figure 5 It is a schematic structural diagram of the lower spiral slide provided by the embodiment of the present application;

[0023] Figure 6 It is a schematic structural diagram of the upper spiral slide provided by the embodiment of the present application;

[0024] Figure 7 Schematic structural diagram of the sleeve located above provided by the embodiment of the present application;

[0025] Figure 8 Schematic structural diagram of the sleeve located below provided by the embodiment of the present application;

[0026] Figure 9 Schematic structural diagram of the wing provided by the embodiment of the present application;

[0027] Figure 10 Top view of the wing unfolding and dihedral mechanism provided by the embodiment of the present application.

[0028] Reference numerals: 1 - base; 11 - fixed cylinder; 111 - mounting groove; 12 - rotating assembly; 121 - flange; 122 - pressure plate; 123 - thrust bearing; 2 - driving assembly; 21 - power member; 22 - driving gear; 23 - sleeve; 231 - transmission tooth; 3 - transmission ring; 31 - slider; 4 - guiding assembly; 41 - spiral slide; 411 - spiral rising surface; 412 - spiral descending surface; 42 - blocking structure; 421 - step; 422 - limiting block; 5 - radial rotating shaft; 6 - wing. Detailed implementation manners

[0029] 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. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present application.

[0030] In the description of the embodiments of the present application, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing the embodiments of the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation to the present application. The terms "first", "second", "third" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance. In addition, the terms "installation", "connection", and "connection" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the internal communication of two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present application can be understood according to specific circumstances.

[0031] As Figure 1 shown, the wing deployment and dihedral mechanism provided by the embodiment of the present application includes a base 1, a driving assembly 2, a guiding assembly 4, and two transmission rings 3. The driving assembly 2 is installed on the base 1. The two transmission rings 3 are both connected to the driving assembly 2 through radial rotating shafts 5 and are configured to rotate in opposite directions around their own axes under the drive of the driving assembly 2. The two transmission rings 3 are respectively connected with two wings 6, and each wing 6 extends radially along the corresponding transmission ring 3; and a guiding assembly 4, which is installed on the base 1 and abuts against the two transmission rings 3 to guide the two transmission rings 3 rotating in opposite directions to rotate around the radial rotating shaft 5.

[0032] It should be noted that the driving assembly 2 of the embodiment of the present application drives the transmission rings 3 to rotate in opposite directions, so as to drive the wings 6 to rotate and deploy in opposite directions. Usually, the deployment angle of the wing 6 is 90°. The radial rotating shaft 5 not only drives the wing 6 to deploy, but also provides installation positioning and rotation for the dihedral of the wing 6. The solution of the embodiment of the present application is highly integrated, with direct force transmission and high structural efficiency. It balances the bending moment generated by the lift of the wing 6 at the radial rotating shaft 5, thereby reducing the weight of the overall device. On the one hand, the guiding assembly 4 provides dihedral limit for the dihedral of the wing 6; on the other hand, it provides a dihedral slide rail for the dihedral of the wing 6. Therefore, the wing deployment and dihedral mechanism provided by the embodiment of the present application can realize the synchronous progress of dihedral actuation and deployment actuation, with high precision and reliability, high structural efficiency, small space occupation, high stability and reliability.

[0033] As Figure 2 and Figure 3 shown, the driving assembly 2 includes a power member 21, a driving gear 22, and two sleeves 23. The power member 21 is installed inside the base 1, and the output end of the power member 21 extends out from the side wall of the base 1, and the driving gear 22 is installed on the output end of the power member 21. As Figure 7 and Figure 8 shown, the two sleeves 23 are rotatably sleeved on the outside of the base 1 and are provided with a plurality of transmission teeth 231 meshing with the driving gear 22 on the end face facing the driving gear 22. The two sleeves 23 not only serve as the rotating sleeves 23 for the deployment of the wing 6, but also serve as the installation base structure of the radial rotating shaft 5 at the same time. The two transmission rings 3 are respectively connected to the two sleeves 23 through the radial rotating shafts 5, and there is a gap between the transmission ring 3 and the sleeve 23. The gap between the transmission ring 3 and the sleeve 23 provides space for the rotation of the transmission ring 3. The two sleeves 23 of the embodiment of the present application are respectively located above and below the driving gear 22. The driving gear 22 and the transmission teeth 231 form a gear pair, and the output end of the power member 21 drives the gear pair to rotate, so as to drive the sleeve 23 located above and the sleeve 23 located below to rotate synchronously in opposite directions, and thus the synchronous reverse deployment of the wing 6 can be realized.

[0034] Specifically, asFigure 1 and Figure 3 As shown in Figure 3 , the driving assembly 2 includes two driving gears 22. The power member 21 includes a double-output-shaft synchronous reverse reduction motor, and the two driving gears 22 are respectively mounted on the two output shafts of the double-output-shaft synchronous reverse reduction motor. Two identical driving gears 22 are mounted on the output shafts on both sides of the double-output-shaft synchronous reverse reduction motor. The driving gears 22 respectively form precise gear pairs with the transmission teeth 231 located above and the transmission teeth 231 located below. During the rotation of the output shafts on both sides of the double-output-shaft synchronous reverse reduction motor, by driving the gear pairs, the sleeves 23 located above and the sleeves 23 located below are driven to rotate synchronously and reversely, so that the synchronous reverse deployment of the wing 6 can be realized. The embodiment of the present application relies on the high reliability of the gear pair transmission, so as to ensure the high reliability and high stability of the wing 6 during the deployment process.

[0035] Specifically, the gear pair in the embodiment of the present application is a straight bevel gear transmission.

[0036] Certainly, the power member 21 in the embodiment of the present application is not limited to the double-output-shaft synchronous reverse reduction motor. The power member 21 in the embodiment of the present application can be a single-output-shaft reduction motor, paired with a driven stable gear pair. The power member 21 in the embodiment of the present application can also be two identical synchronous single-output-shaft reduction motors.

[0037] In one implementation manner of the embodiment of the present application, the guiding assembly 4 includes a spiral slide 41. The spiral slide 41 is mounted on the base 1 and is provided with a spiral rising surface 411 and a spiral descending surface 412 facing the transmission ring 3. The spiral rising surface 411 of the embodiment of the present application provides an up-turning slide rail for the up-turning of the wing 6. The spiral descending surface 412 limits the up-turning of the wing 6, and can also provide the main bearing capacity after the wing 6 reaches the up-turning position.

[0038] As Figure 9 shown, the transmission ring 3 includes sliders 31. The two sliders 31 are both connected to the transmission ring 3 and are located on both sides of the radial rotating shaft 5, and each slider 31 is respectively provided with a sliding inclined surface that abuts against the spiral rising surface 411 and the spiral descending surface 412.

[0039] Furthermore, Figure 6This is an embodiment of the spiral slide 41 that abuts against the transmission ring 3 above in the embodiment of the present application. The left side of the spiral slide 41 is a spiral ascending surface 411, and the right side of the spiral slide 41 is a spiral descending surface 412. The spiral slide 41 is installed below the transmission ring 3. While the transmission ring 3 rotates and unfolds following the sleeve 23, the slider 31 of the transmission ring 3 will be extruded by the spiral surface of the spiral slide 41, causing the left side of the transmission ring 3 to rise and the right side to fall, and the spiral slide 41 and the slider 31 are in a state of real-time fitting extrusion, so that the wing 6 realizes the upward turning function. Specifically, a plurality of first connection through holes are provided on the side of the spiral slide 41 away from the transmission ring 3 above. First connection threaded holes corresponding to the first connection through holes are provided on the base 1. The first connection through holes are threadedly connected to the first connection threaded holes by screws, so as to realize the fixed connection between the spiral slide 41 and the base 1.

[0040] Similarly, Figure 5 This is an embodiment of the spiral slide 41 that abuts against the transmission ring 3 below in the embodiment of the present application. The right side of the spiral slide 41 is a spiral ascending surface 411, and the left side of the spiral slide 41 is a spiral descending surface 412. The spiral slide 41 is installed below the transmission ring 3. While the transmission ring 3 rotates and unfolds following the sleeve 23, the slider 31 of the transmission ring 3 will be extruded by the spiral surface of the spiral slide 41, causing the right side of the transmission ring 3 to rise and the left side to fall, and the spiral slide 41 and the slider 31 are in a state of real-time fitting extrusion, so that the wing 6 realizes the upward turning function. Specifically, a plurality of second connection through holes are provided on the side of the spiral slide 41 away from the transmission ring 3 below. Second connection threaded holes corresponding to the second installation through holes are provided on the base 1. The second connection through holes are threadedly connected to the second connection threaded holes by screws, so as to realize the fixed connection between the spiral slide 41 and the base 1.

[0041] Of course, the embodiment of the present application is not limited to Figure 6 the structure. A spiral slide 41 can be provided above the transmission ring 3 above, which is the same as Figure 5 the principle.

[0042] In one implementation manner of the embodiment of the present application, the cross-sectional area of the slider 31 is smaller than the sliding inclined surfaces of the spiral ascending surface 411 and the spiral descending surface 412.

[0043] In one implementation manner 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 slider 31, thereby blocking the rotation of the wing 6, and further can accurately limit the upward turning angle of the wing 6.

[0044] In one implementation of the embodiment of the present application, the blocking structure 42 includes a step 421. The highest point of the spiral rising surface 411 is lower than the highest point of the spiral descending surface 412, so that the junction of the highest point of the spiral rising surface 411 and the highest point of the spiral descending surface 412 forms a step 421, and the highest point of the spiral rising surface 411 is adjacent to the highest point of the spiral descending surface 412; and / or, the blocking structure 42 includes a limiting block 422; the limiting block 422 is arranged at the junction of the lowest point of the spiral rising surface 411 and the lowest point of the spiral descending surface 412, and the lowest point of the spiral rising surface 411 is adjacent to the lowest point of the spiral descending surface 412. When the wing 6 rotates and is deflected upward in place, the limiting block 422 can precisely limit the wing 6 to unfold 90 degrees.

[0045] The present application realizes the synchronous operation of the upward deflection and unfolding of the wing 6 through a single driving component 2, with relatively high precision and reliability. At the same time, in the embodiment of the present application, the mechanism that usually does not bear force is well integrated with the main load-bearing structure of the aircraft, with high overall structural efficiency, small space occupation, and high stability and reliability of the unfolding and upward deflection of the wing 6.

[0046] In the embodiment of the present application, the blocking structure 42 can be formed by the step 421, or the blocking structure 42 can be formed by the limiting block 422. Of course, the blocking structure 42 can also be formed by the step 421 and the limiting block 422 together. The blocking structure 42 can control the unfolding angle of the wing 6, and thus can precisely control the upward deflection angle of the wing 6. In addition, the blocking structure 42 also solves the problem that the wing 6 needs to bear the main load when it is in the upward deflection limit position.

[0047] In one implementation of the embodiment of the present application, as Figure 5 and Figure 6 shown, the spiral rising surface 411 is gradually transitioned to be set with a lower inner side and a higher outer side, the spiral descending surface 412 is gradually transitioned to be set with a higher inner side and a lower outer side, and the inclination degrees of the spiral rising surface 411 and the spiral descending surface 412 increase as the spiral surface rises, so as to achieve the rolling effect of the upward deflection. Specifically, the side of the spiral rising surface 411 close to the base 1 is lower than the side far from the base 1, and the width is large enough to be greater than the surface with which the slider 31 is always in contact. The spiral upward deflection height of the spiral rising surface 411 can be designed according to different requirements to meet different upward deflection angle requirements. The spiral rising surface 411 provides an upward deflection slide rail for the upward deflection of the wing 6.

[0048] The side of the spiral descending surface 412 close to the base 1 is higher than the side far from the base 1, and the width is large enough to be greater than the surface with which the slider 31 is always in contact. The spiral descending height of the spiral descending surface 412 is exactly the same as the spiral upward deflection height of the spiral rising surface 411. The function of the spiral descending surface 412 is to limit the upward deflection of the wing 6; at the same time, it can also provide the main bearing capacity after the wing 6 is deflected upward in place.

[0049] As shown Figure 3 in FIG. 1, the base 1 includes a fixed cylinder 11 and a rotating assembly 12. The rotating assembly 12 is installed at both ends of the fixed cylinder 11 and is configured to provide a rotating space for the sleeve 23. The power member 21 is installed inside the fixed cylinder 11, and two sleeves 23 are rotatably sleeved outside the fixed cylinder 11.

[0050] In one implementation of the embodiment of the present application, as Figure 4 shown in FIG. 2, the side surface of the fixed cylinder 11 is provided with an installation groove 111 with a flat bottom surface. The output end of the power member 21 extends out from the installation groove 111. The driving gear 22 is installed in the installation groove 111, so that the installation space can be saved, the whole structure is more compact, and the occupied space is small.

[0051] As Figure 3 shown in FIG. 3, 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 from the driving gear 22 and is configured to provide a rotating space for the sleeve 23. The pressure plate 122 is installed outside the thrust bearing 123 and is configured to press the thrust bearing 123 tightly. The flange plate 121 is fixedly connected to the pressure plate 122 and is arranged at both ends of the fixed cylinder 11. The flange plate 121 and the fixed cylinder 11 are installed as a whole by screws, serving as the main force-bearing and installation positioning reference structure of the whole set of mechanisms, and can be installed and fixed on the fuselage structure.

[0052] It should be noted that, as Figure 5 shown in FIG. 4, a spiral slide 41 can be installed at one end of the pressure plate 122 far from the flange plate 121, which can provide a slide rail and limit for the upward deflection 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 tightly on 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.

[0053] The loads transmitted by the wing 6 in the embodiment of the present application are mainly lift and the bending moment generated by the lift. In the current structure, the bending moments generated by the lift of the two wings 6 are self-balanced at the radial rotating shaft 5, and no additional structure needs to be added, so that the overall weight of the mechanism can be reduced. Therefore, the wing deployment and upward deflection mechanism in the embodiment of the present application is highly integrated, the force transmission is direct, and the structural efficiency is high.

[0054] The main load of the wing 6 is the aerodynamic lift during flight. Therefore, it is necessary to limit the deployment and upward deflection of the wing 6. On the one hand, it is to ensure the accuracy of the deployment and upward deflection angles of the wing 6, and on the other hand, it is to make the bearing capacity more stable and reliable. The wing deployment and upward deflection mechanism in the embodiment of the present application not only meets the accuracy requirements for the deployment and upward deflection of the wing 6, but can also be used as the main structural load-bearing member.

[0055] As Figure 1and Figure 10 As shown, an embodiment of the present application provides an aircraft, including the above-mentioned wing deployment and dihedral mechanism. The overall weight and size of the aircraft in the embodiment of the present application meet the lightweight requirements and can carry a large load.

[0056] The various embodiments in this specification are described in a progressive manner. For the same or similar parts between the various embodiments, reference can be made to each other. The key points of each embodiment are the differences from other embodiments.

[0057] The above embodiments are only used to illustrate the technical solutions of the present application, rather than limiting the present application; although the present application has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements on some or all of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the present application.

Claims

1. A wing deployment and dihedral mechanism, characterized in that, it includes: a base (1); a driving component (2), installed on the base (1); two transmission rings (3), both connected to the driving component (2) through radial rotating shafts (5), and configured to rotate in opposite directions around their own axes under the drive of the driving component (2); two of the transmission rings (3) are respectively connected with two wings (6), and each wing (6) extends radially along the corresponding transmission ring (3); and a guiding component (4), installed on the base (1) and abutted against the two transmission rings (3) to guide the two transmission rings (3) rotating in opposite directions to rotate around the radial rotating shaft (5); the guiding component (4) includes a spiral slide (41); the spiral slide (41) is installed on the base (1), and is provided with a spiral rising surface (411) and a spiral falling surface (412) facing the transmission ring (3); the transmission ring (3) includes a slider (31); the two sliders (31) are both connected to the transmission ring (3) and are located on both sides of the radial rotating shaft (5), and each slider (31) is respectively provided with a sliding inclined surface abutted against the spiral rising surface (411) and the spiral falling surface (412).

2. The wing deployment and dihedral mechanism according to claim 1, characterized in that, the driving component (2) includes a power member (21), a driving gear (22) and two sleeves (23); the power member (21) is installed inside the base (1), and the output end of the power member (21) extends out from the side wall of the base (1); the driving gear (22) is installed on the output end of the power member (21); the two sleeves (23) are rotatably sleeved on the outside of the base (1), and are provided with a plurality of transmission teeth (231) meshing with the driving gear (22) on the end surface facing along the driving gear (22); the two transmission rings (3) are respectively connected to the two sleeves (23) through the radial rotating shaft (5), and there is a gap between the transmission ring (3) and the sleeve (23).

3. The wing deployment and dihedral 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. The wing deployment and dihedral mechanism according to claim 3, characterized in that, a blocking structure (42) is arranged between the spiral rising surface (411) and the spiral falling surface (412) for blocking the slider (31).

5. The wing deployment and dihedral mechanism according to claim 4, characterized in that, the blocking structure (42) includes a step (421); The highest point of the helical rising surface (411) is lower than the highest point of the helical descending surface (412), so that the intersection of the highest point of the helical rising surface (411) and the highest point of the helical descending surface (412) forms the step (421), and the highest point of the helical rising surface (411) is adjacent to the highest point of the helical descending surface (412). And / or, the blocking structure (42) includes a limit block (422); the limit block (422) is arranged at the intersection of the lowest point of the helical rising surface (411) and the lowest point of the helical descending surface (412), and the lowest point of the helical rising surface (411) is adjacent to the lowest point of the helical descending surface (412).

6. The wing deployment and dihedral mechanism according to claim 5 wherein The helical rising surface (411) is gradually transitioned to be lower inside and higher outside, the helical descending surface (412) is gradually transitioned to be higher inside and lower outside, and the inclination degrees of the helical rising surface (411) and the helical descending surface (412) increase as the helical surface rises.

7. The wing deployment and dihedral mechanism according to claim 2 wherein The base (1) includes a fixed cylinder (11) and a rotating assembly (12); The rotating assembly (12) is installed at both ends of the fixed cylinder (11) and is configured to provide a rotating space for the sleeve (23); The power member (21) is installed inside the fixed cylinder (11), and the two sleeves (23) are rotatably sleeved outside the fixed cylinder (11).

8. The wing deployment and dihedral mechanism according to 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) away from the driving gear (22) and is configured to provide a rotating space for the sleeve (23); The pressure plate (122) is installed outside the thrust bearing (123) and is configured to press the thrust bearing (123); The flange plate (121) is fixedly connected to the pressure plate (122) and is arranged at both ends of the fixed cylinder (11).

9. An aircraft wherein It includes the wing deployment and dihedral mechanism according to any one of claims 1-8.

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