A mechanism for controlling multiple angle states of a wing and a folding wing

Abstract

The present application discloses a mechanism for controlling the multi-angle state of a wing and a folding wing, belonging to the field of folding wings, and capable of solving the problems of high cost and large impact of the existing mechanism for controlling the multi-angle deployment state of a folding wing. The mechanism includes a housing, a locking structure, a pin structure intelligently driven by a shape memory alloy wire, a hinge seat, and two sets of transmission structures; one end of the locking structure is fixed to the housing, and a plurality of radial locking holes are arranged along its own axial direction; the hinge seat is fixed to the other end of the locking structure; the first ends of the two sets of transmission structures are respectively hinged to both sides of the hinge seat, the bottoms of the second ends are fixed to the housing, and the tops of the second ends are respectively fixed to a wing; the front end of the pin structure can be inserted into or withdrawn from the locking hole, and each locking hole corresponds to an angle state of a wing. When the front end of the pin structure withdraws from the locking hole, the locking structure can drive the hinge seat to move along its own axial direction. The present application has a lower cost and a small impact.

Description

Technical Field

[0001] This application relates to the technical field of folding wings, and particularly to a mechanism for controlling the multi-angle state of wings and a folding wing. Background Art

[0002] Compared with traditional fixed wings, folding wings not only facilitate the storage and transportation of unmanned aerial vehicles (UAVs), but also broaden the launching methods of UAVs, such as shipborne launching, airborne dropping, etc. The development of folding wing technology has greatly enriched the application scope and combat types of UAVs.

[0003] Currently, most of the mechanisms for controlling the multi-angle deployment state of folding wings are pyrotechnics, which are costly. At the same time, the impact during the explosion of pyrotechnics is large. Since the precision payloads such as flexible sensors and optical devices carried by UAVs are extremely sensitive to the vibration and impact of the mechanism for controlling the multi-angle deployment state of folding wings, the current mechanism for controlling the multi-angle deployment state of folding wings can no longer meet the requirements of new folding wings. Summary of the Invention

[0004] By providing a mechanism for controlling the multi-angle state of wings and a folding wing in an embodiment of this application, the problems of high cost and large impact of the existing mechanism for controlling the multi-angle deployment state of folding wings can be solved.

[0005] In a first aspect, an embodiment of the present invention provides a mechanism for controlling the multi-angle state of wings, including a housing, a locking structure, a pin structure, a hinge seat, and two sets of transmission structures; one end of the locking structure is fixed to the housing, and a plurality of radial locking holes are arranged along its own axis; the hinge seat is fixed to the other end of the locking structure; the first ends of the two sets of transmission structures are respectively hinged to both sides of the hinge seat, the bottoms of the second ends are fixed to the housing, and the tops of the second ends are respectively fixed to a wing; the front end of the pin structure can be inserted into or withdrawn from the locking hole, and each locking hole corresponds to an angle state of a wing. When the front end of the pin structure withdraws from the locking hole, the locking structure can drive the hinge seat to move along its own axis.

[0006] In combination with the first aspect, in a possible implementation manner, the locking structure includes a housing, an elastic component, and a locking column; one end of the housing is fixed to the housing; the locking column is provided with a plurality of the locking holes along its own axis and is arranged in the inner cavity of the housing; the hinge seat is fixed to the first end of the locking column, and this first end is located at the opening of the housing; both ends of the elastic component respectively abut against the first end of the locking column and the bottom surface of the housing.

[0007] In combination with the first aspect, in a possible implementation, the locking structure also includes a first shape memory alloy wire; the locking column is provided with a through hole running through the locking column in a radial direction; the first shape memory alloy wire is passed through the through hole, and both ends are respectively fixed to the shell.

[0008] In combination with the first aspect, in a possible implementation, the locking structure also includes a plurality of guide posts; one end of the plurality of guide posts is fixed to the shell, and the other end is provided with a guide through hole; the first shape memory alloy wire is passed through the guide through hole.

[0009] In combination with the first aspect, in a possible implementation manner, the elastic component includes four first elastic members; the four first elastic members are distributed in a ring array around the central axis of the locking column.

[0010] In combination with the first aspect, in a possible implementation, the locking column is a hexahedron; the four edges of the locking column are radially concave, and a blocking platform is provided at the top of the four edges; the four first elastic members are respectively provided in the concave parts, and the two ends respectively abut against the blocking platform and the bottom surface of the shell.

[0011] In combination with the first aspect, in a possible implementation, the latch structure includes a latch, a fixed tube, a second elastic member, a base plate and a second shape memory alloy wire; the latch is clamped at one end of the fixed tube, and the other end is fixed to the base plate; the latch can move along the axial direction of the fixed tube, the front end can be inserted into or withdrawn from the locking hole, and the rear end is connected to the second shape memory alloy wire; the other end of the second shape memory alloy wire passes through the base plate; the second elastic member is arranged in the inner cavity of the fixed tube, and the two ends are respectively against the latch and the base plate.

[0012] In combination with the first aspect, in a possible implementation, the plurality of locking holes are respectively arranged on opposite sides of the locking structure, and the locking holes on both sides are staggered; the latch structure is divided into two groups, and the two groups of latch structures are respectively arranged on both sides of the locking structure, and the front ends can be inserted into or withdrawn from the locking holes on the corresponding sides.

[0013] In combination with the first aspect, in a possible implementation, the transmission structure includes a fixed support, a bearing, a bolt, a rocker and a connecting rod; one end of the connecting rod is hinged to one side of the hinged seat as the first end of the transmission structure, and the other end is connected to one end of the rocker; the bottom of the fixed support is fixed to the shell as the bottom of the second end of the transmission structure, and a bearing mounting hole is provided in the middle of the upper surface; the bearing is clamped in the bearing mounting hole; the bolt is clamped in the inner hole of the bearing; the middle part of the rocker is sleeved on the bolt; the rocker is fixed to the wing as the top of the second end of the transmission structure.

[0014] In a second aspect, another embodiment of the present invention provides a folding wing, including the mechanism for controlling the multi-angle state of the wing described above.

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

[0016] In the mechanism for controlling the multi-angle state of the wing provided in the embodiment of the present invention, one end of the locking structure is fixed to the housing. The locking structure is provided with a plurality of radial locking holes along its own axis. The hinge seat is fixed to the other end of the locking structure. The first ends of the two sets of transmission structures are respectively hinged to both sides of the hinge seat, the bottoms of the second ends are fixed to the housing, and the tops of the second ends are respectively fixed to a wing. The front end of the pin structure can be inserted into or withdrawn from the locking hole, and each locking hole corresponds to an angle state of a wing. The wing is installed on the fuselage. When the wing is fully retracted, the front end of the pin structure is inserted into the locking hole of the locking structure close to the hinge seat, which is convenient for the wing to be buried in the cabin. After the cruise missile is launched, the front end of the pin structure of the mechanism in this application withdraws from the locking hole, releasing the locking of the pin structure on the locking structure. The locking structure can drive the hinge seat to move along its own axis. Since the first ends of the two sets of transmission structures are respectively hinged to both sides of the hinge seat and the tops of the second ends are respectively fixed to a wing, the hinge seat drives the transmission structure to move, and the wing is deployed. Each locking hole corresponds to an angle state of a wing. When the front end of the pin structure is inserted into another locking hole, the wing is maintained in the angle state corresponding to the locking hole. The mechanism for controlling the multi-angle state of the wing in the embodiment of this application controls the wing to maintain a multi-angle state through a pure mechanical structure, with low cost and small impact. Description of the Drawings

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

[0018] Figure 1 Structural schematic of the mechanism for controlling the multi-angle state of the wing provided in the embodiment of this application Figure 1 ;

[0019] Figure 2 Structural schematic of the mechanism for controlling the multi-angle state of the wing provided in the embodiment of this application Figure 2 ;

[0020] Figure 3 Structural schematic of the mechanism for controlling the multi-angle state of the wing provided in the embodiment of this application Figure 3 ;

[0021] Figure 4 Structural schematic of the mechanism for controlling the multi-angle state of the wing provided by the embodiment of the present application Figure 4 .

[0022] Reference numerals: 1 - housing; 2 - locking structure; 21 - outer shell; 211 - prism cylinder; 212 - fixing piece; 22 - elastic component; 221 - first elastic member; 23 - locking column; 231 - retaining platform; 232 - locking hole; 24 - first shape memory alloy wire; 25 - guiding column; 251 - guiding through hole; 3 - pin structure; 31 - pin; 32 - fixing cylinder; 33 - second elastic member; 34 - bottom plate; 35 - second shape memory alloy wire; 4 - hinge seat; 5 - transmission structure; 51 - fixing support; 52 - bolt; 53 - rocker; 531 - cylinder body; 532 - rod body; 54 - connecting rod; 6 - wing. Detailed implementation manners

[0023] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0024] In the description of the embodiments of the present invention, 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 invention 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 thus should not be construed as a limitation of the present invention. The terms "first" and "second" are only used for descriptive purposes and cannot be construed 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 invention can be understood according to specific circumstances.

[0025] The mechanism for controlling the multi-angle state of the wing provided by the embodiments of the present invention is applicable to an aircraft equipped with a folding wing. In the embodiments of the present application, the aircraft is taken as an example of a loitering munition.

[0026] Please refer to Figures 1 to 4As shown in the figure, an embodiment of the present invention provides a mechanism for controlling the multi-angle state of a wing, including a housing 1, a locking structure 2, a pin structure 3, a hinge seat 4, and two sets of transmission structures 5. As Figure 1 and Figure 2 shown, the housing 1 is a hexahedron with one open side.

[0027] One end of the locking structure 2 is fixed to the housing 1, and a plurality of radial locking holes 232 are arranged along its own axial direction. The hinge seat 4 is fixed to the other end of the locking structure 2. The first ends of the two sets of transmission structures 5 are respectively hinged to both sides of the hinge seat 4, the bottoms of the second ends are fixed to the housing 1, and the tops of the second ends are respectively fixed to a wing 6. As Figure 1 shown, the hinge seat 4 is a square plate, and grooves recessed from the side are provided on the opposite sides of the square plate. The first ends of the transmission structures 5 are inserted into the grooves and are respectively hinged by bolts. A threaded through hole is provided at the center of the hinge seat 4, and a threaded blind hole is provided at the other end of the locking structure 2. The front end of the bolt passes through the threaded through hole and is then screwed into the threaded blind hole to fix the hinge seat 4 to the other end of the locking structure 2.

[0028] The front end of the pin structure 3 can be inserted into or withdrawn from the locking hole 232. Each locking hole 232 corresponds to an angular state of a wing 6. When the front end of the pin structure 3 withdraws from the locking hole 232, the locking structure 2 can drive the hinge seat 4 to move along its own axial direction.

[0029] The mechanism for controlling the multi-angle state of the wing provided by the embodiment of the present invention, one end of the locking structure 2 is fixed to the housing 1. The locking structure 2 is provided with a plurality of radial locking holes 232 along its own axial direction. The hinge seat 4 is fixed to the other end of the locking structure 2. The first ends of the two groups of transmission structures 5 are respectively hinged to both sides of the hinge seat 4, the bottoms of the second ends are fixed to the housing 1, and the tops of the second ends are respectively fixed to a wing 6. The front end of the bolt structure 3 can be inserted into or withdrawn from the locking hole 232, and each locking hole 232 corresponds to an angular state of a wing 6. The wing 6 is installed on the fuselage. When the wing 6 is fully retracted, the front end of the bolt structure 3 is inserted into the locking hole 232 of the locking structure 2 close to the hinge seat 4, which is convenient for the wing 6 to be buried in the cabin. After the cruise missile is launched, the front end of the bolt structure 3 of the mechanism of the present application withdraws from the locking hole 232, releasing the locking of the bolt structure 3 on the locking structure 2. The locking structure 2 can drive the hinge seat 4 to move along its own axial direction. Since the first ends of the two groups of transmission structures 5 are respectively hinged to both sides of the hinge seat 4 and the tops of the second ends are respectively fixed to a wing 6, the hinge seat 4 drives the transmission structure 5 to move, and the wing 6 is deployed. Each locking hole 232 corresponds to an angular state of a wing 6. When the front end of the bolt structure 3 is inserted into another locking hole 232, the wing 6 is maintained in the angular state corresponding to the locking hole 232. The mechanism for controlling the multi-angle state of the wing provided by the embodiment of the present application controls the wing 6 to maintain a multi-angle state through a pure mechanical structure, with low cost and small impact.

[0030] As Figures 1 to 3 shown, the locking structure 2 provided by the embodiment of the present invention includes a housing 21, an elastic component 22 and a locking column 23. One end of the housing 21 is fixed to the housing 1. Among them, the housing 21 includes a prism barrel 211 and a fixing piece 212. Since each surface of the prism barrel 211 is a plane, it is convenient for the setting and fixing of the housing 21. One end of the prism barrel 211 is fixed to the fixing piece 212, and the setting of the fixing piece 212 facilitates the fixing of the housing 21 on the housing 1.

[0031] The locking column 23 is provided with a plurality of locking holes 232 along its own axial direction and is arranged in the inner cavity of the housing 21. The hinge seat 4 is fixed to the first end of the locking column 23, and this first end is located at the opening of the housing 1. The two ends of the elastic component 22 respectively abut against the first end of the locking column 23 and the bottom surface of the housing 1, and the elastic component 22 is in a compressed state.

[0032] The locking structure 2 provided by the embodiment of the present application has one end of the housing 21 fixed to the housing 1, and a plurality of locking holes 232 are arranged along the axial direction of the locking column 23. When the front end of the plug structure 3 exits the current locking hole 232, the elastic component 22 releases elastic force. Since the two ends of the elastic component 22 respectively abut against the first end of the locking column 23 and the bottom surface of the housing 1, the elastic component 22 pushes the locking column 23 to move. When the locking hole 232 corresponding to the angular state of the next wing 6 is located at the front end of the plug structure 3, the front end of the plug structure 3 is inserted into the locking hole 232, so that the wing 6 is maintained in the angular state corresponding to the locking hole 232. The locking structure 2 provided by the embodiment of the present application has a simple and ingenious structure.

[0033] Referring to Figures 1 to 4 As shown, the locking structure 2 further includes a first shape memory alloy wire 24. The locking column 23 is provided with a through hole penetrating its own radial direction. The first shape memory alloy wire 24 is inserted into the through hole, and both ends are fixed to the housing 1 respectively. Specifically, as Figure 3 shown, the two ends of the first shape memory alloy wire 24 passing through the through hole are arranged parallel to the side surface of the fixed locking structure 2 of the housing 1, and then are bent and parallel to the two side surfaces of the housing 1, and then fixed to the opposite side surfaces of the fixed locking structure 2 of the housing 1.

[0034] When the plug structure 3 is inserted into the locking hole 232 of the locking column 23 close to the housing 1, the wing 6 is deployed to the maximum angle. However, in practice, it is also necessary to fold the wing 6 completely back. The setting of the first shape memory alloy wire 24, which is inserted into the through hole on the locking column 23 and both ends are fixed to the housing 1. When the front end of the plug structure 3 exits the locking hole 232 of the housing 1 and the first shape memory alloy wire 24 is heated, the first shape memory alloy wire 24 shrinks, driving the locking column 23 to move rapidly in the direction towards the housing 1, and the front end of the plug structure 3 is inserted into the locking hole 232 of the locking structure 2 close to the hinge seat 4 again, completing the reset of the wing 6.

[0035] Continuing to refer to Figures 1 to 4 As shown, the locking structure 2 further includes a plurality of guide posts 25. One end of the plurality of guide posts 25 is fixed to the housing 1, and the other end is provided with a guide through hole 251. The first shape memory alloy wire 24 is inserted into the guide through hole 251.

[0036] The setting of the guide post 25 can play a guiding role for the first shape memory alloy wire 24. As Figure 3 shown, one end of the guide post 25 is provided with an external thread, and the housing 1 is provided with an internal thread. The guide post 25 is screwed into the housing 1, and then a nut is sleeved, so that one end of the guide post 25 can be fixed to the housing 1, and the housing 21 can be fixed to the housing 1.

[0037] Referring to Figure 4As shown, the elastic component 22 includes four first elastic members 221. The four first elastic members 221 are annularly arrayed around the central axis of the locking post 23, so that when the elastic component 22 releases elastic force, the thrust on the locking post 23 can be made uniform. The first elastic member 221 can be a compression spring.

[0038] Continue to refer to Figure 4 As shown, the locking post 23 is a hexahedron. The four edges of the locking post 23 are recessed radially inward, and a blocking platform 231 is provided at the top of the four edges. The four first elastic members 221 are respectively arranged in the recesses, and the two ends respectively abut against the blocking platform 231 and the bottom surface of the housing 1, so that the installation of the four first elastic members 221 can be facilitated. At the same time, the four sides of the locking post 23 are vacated to facilitate the setting of the locking holes 232. Further, the recess is an arc surface, so that when the first elastic member 221 is a compression spring, the recess can better fit the shape of the compression spring.

[0039] As Figure 3 shown, the plug structure 3 includes a plug 31, a fixed cylinder 32, a second elastic member 33, a bottom plate 34 and a second shape memory alloy wire 35. One end of the fixed cylinder 32 is clamped with the plug 31, and the other end is fixed to the bottom plate 34. The second elastic member 33 can be a compression spring. Refer to Figure 3 As shown, a retaining ring is provided at the end of the fixed cylinder 32 where the plug 31 is clamped, so that a shoulder is formed at this end of the fixed cylinder 32. The plug 31 includes a pin body and a convex ring, and the convex ring is sleeved on the pin body and integrally connected with the pin body. The outer diameter of the convex ring is larger than the inner diameter of the retaining ring and smaller than the diameter of the inner cavity of the fixed cylinder 32. The convex ring is arranged in the inner cavity of the fixed cylinder 32, so that the plug 31 can move axially along the fixed cylinder 32, and the front end can extend out of the fixed cylinder 32, but the shoulder can block the convex ring, so that the plug 31 will not come out of the fixed cylinder 32.

[0040] The plug 31 can move axially along the fixed cylinder 32, the front end can be inserted into or withdrawn from the locking hole 232, and the rear end is connected to the second shape memory alloy wire 35. The other end of the second shape memory alloy wire 35 passes through the bottom plate 34. The second elastic member 33 is arranged in the inner cavity of the fixed cylinder 32, and the two ends respectively abut against the plug 31 and the bottom plate 34.

[0041] When the front end of the bolt 31 is inserted into the locking hole 232, the second elastic member 33 is in its natural state. When it is necessary for the front end of the bolt 31 to withdraw from the locking hole 232, the second shape memory alloy wire 35 is energized, and the second shape memory alloy wire 35 contracts. Since the rear end of the bolt 31 is connected to the second shape memory alloy wire 35, the second shape memory alloy wire 35 drives the bolt 31 to retract into the inner cavity of the fixed cylinder 32, and the locking structure 2 is unlocked. At this time, the second elastic member 33 is compressed. When it is necessary for the front end of the bolt 31 to be inserted into another locking hole 232 again, the second shape memory alloy wire 35 is de-energized, and the second elastic member 33 releases its elastic force. Since the two ends of the second elastic member 33 respectively abut against the bolt 31 and the bottom plate 34, and the bottom plate 34 is fixed, the second elastic member 33 thus pushes the bolt 31 to move, and the front end of the bolt 31 can be inserted into another locking hole 232. The bolt structure 3 provided by the embodiment of the present application is simple and ingenious.

[0042] Continue to refer to Figure 3 As described above, a plurality of locking holes 232 are respectively arranged on opposite sides of the locking structure 2, and the locking holes 232 on both sides are arranged in a staggered manner. For example, it is necessary for the wing 6 to be unfolded to 30°, 45°, 60°, 90°. That is, the locking holes 232 corresponding to 30° and 60° are arranged on one side of the locking structure 2, and the locking holes 232 corresponding to 45° and 90° are arranged on the opposite side, and along the axis, 30°, 45°, 60°, 90° are arranged in sequence in a staggered manner.

[0043] There are two sets of bolt structures 3, and the two sets of bolt structures 3 are respectively arranged on both sides of the locking structure 2, and the front ends can respectively be inserted into or withdrawn from the locking holes 232 on the corresponding sides.

[0044] In practice, the front end of the bolt structure 3 extends into the locking hole 232 to lock the wing 6 and keep it in the angular state corresponding to the locking hole 232. When it is necessary for the front end of the bolt structure 3 to withdraw from the locking hole 232, the second shape memory alloy wire 35 is heated to cause the second shape memory alloy wire 35 to contract, driving the front end of the bolt structure 3 to withdraw from the locking hole 232, and the wing 6 can continue to rotate. The speed of the angle conversion of the wing 6 is very fast. After the bolt structure 3 withdraws from the previous locking hole 232, it is necessary for the bolt structure 3 to quickly reset so that when the wing 6 rotates to the next angle, the front end of the bolt structure 3 can quickly be inserted into the locking hole 232 corresponding to the next angle.

[0045] However, the cooling of the second shape memory alloy wire 35 takes time. During this cooling period, the front end of the latch structure 3 cannot extend out quickly again. However, if the rotation speed of the wing 6 is relatively fast from the current angle to the next angle, its rotation time is very short, and the front end of the previous latch structure 3 still cannot extend out. At this time, by setting another set of latch structures 3, it can be ensured that when the wing 6 rotates to the next angle, there must be a front end of the latch structure 3 that can extend out and insert into the locking hole 232 corresponding to this angle to lock the wing 6. Of course, if the rotation speed of the wing 6 is slow and it can wait until the second shape memory alloy wire 35 cools down, one set of latch structures 3 can also be set. For more convenient use, three sets, four sets, etc. of latch structures 3 can also be set. By setting two sets of latch structures 3, it can be ensured that the wing 6 can be locked at any rotated angle, and at the same time, the cost is reduced. The multiple locking holes 232 are respectively arranged on the opposite sides of the locking structure 2, which can facilitate the arrangement of the locking holes 232. At the same time, by arranging the two sets of latch structures 3 on both sides of the locking structure 2, the two sets of latch structures 3 will not affect each other's work.

[0046] As Figure 1 shown, the transmission structure 5 includes a fixed support 51, a bearing, a bolt 52, a rocker 53 and a connecting rod 54. One end of the connecting rod 54, as the first end of the transmission structure 5, is hinged to one side of the hinge seat 4, and the other end is connected to one end of the rocker 53. The bottom of the fixed support 51, as the bottom of the second end of the transmission structure 5, is fixed to the housing 1, and a bearing mounting hole is provided in the middle of the upper surface. The bearing is clamped in the bearing mounting hole. This bearing is generally a flat thrust needle bearing to reduce friction and the pressure brought by the lift of the wing 6. The bolt 52 is clamped in the inner hole of the bearing. This bolt 52 generally adopts a shoulder bolt 52. The middle of the rocker 53 is sleeved on the bolt 52. The rocker 53, as the top of the second end of the transmission structure 5, is fixed to the wing 6. As Figure 1 shown, the rocker 53 includes a cylinder body 531 and a rod body 532 that are integrally connected. The cylinder body 531 is sleeved on the bolt 52, and both ends of the rod body 532 are fixed to the wing 6 through positioning bolts 52.

[0047] When the locking structure 2 drives the hinge seat 4 to move along its own axis, since one end of each of the two connecting rods 54 is hinged to the hinge seat 4, the hinge seat 4 drives the connecting rod 54 to move, and the connecting rod 54 can rotate relative to the hinge seat 4. The other end of the connecting rod 54 is connected to one end of the rocker 53, so that the connecting rod 54 transmits power to the rocker 53. The bottom of the fixed support 51 is fixed to the housing 1, the bearing is clamped in the bearing mounting hole in the middle of the upper surface of the fixed support 51, the bolt 52 is clamped in the inner hole of the bearing, the middle of the rocker 53 is sleeved on the bolt 52, and the top is fixed to the wing 6, so that the rocker 53 transmits power to the wing 6, and the wing 6 can rotate relative to the housing 1.

[0048] In practice, when the wing 6 is deployed, the aerodynamic lift generated increases, and at the same time, the resulting drag moment also increases accordingly, making the difficulty of deploying the folding wing increase sharply. There is a positive correlation between the aerodynamic lift generated by the deployment of the wing 6 and the angle of rotation of the wing 6. When the angle of rotation of the transmission structure 5 is close to one-third of the end point, the value of the aerodynamic lift generated by the deployment of the wing 6 is the largest, and the difficulty of deploying the wing 6 is also the most obvious. The transmission structure 5 of the embodiment of the present application includes a fixed support 51, a bearing, a bolt 52, a rocker 53, and a connecting rod 54. When the angle of rotation of the rocker 53 gradually increases to 70°, the value of the torque conversion coefficient increases rapidly. When the angle of rotation approaches 70°, the value of the torque conversion coefficient approaches infinity. Thus, it can be seen that the transmission structure 5 provided by the embodiment of the present application can effectively save power. Moreover, when the wing 6 rotates close to the end position, even if the moving speed of the transmission structure 5 is relatively fast, the corresponding angular velocity of the rotation of the wing 6 is relatively small. Thus, in terms of the structural principle, it is ensured that the wing 6 operates smoothly near the end position, avoiding impact on the transmission structure 5.

[0049] Here provides an embodiment of the actual use of the present invention. In this embodiment, it is required that the wing 6 maintains the angular states of 90°, 32.8°, and 0°, and then resets to the angular state of 90°. As Figure 3 shown, the locking holes 232 at positions A, B, and C arranged in a staggered manner on the locking column 23 respectively correspond to the angular states of 90°, 32.8°, and 0°. First, the front end of the latch 31 of the latch structure 3 on the right side extends into the locking hole 232 at position A, and the wing 6 is folded and placed in the cabin while maintaining the 90° angular state.

[0050] When the wing 6 needs to be deployed to the angular state of 32.8°, the second shape memory alloy wire 35 of the latch structure 3 on the right side is electrified. The second shape memory alloy wire 35 contracts, driving the front end of the latch 31 to withdraw from the locking hole 232 at position A and compressing the second elastic member 33. The first elastic member 221 provides a thrust to push the locking column 23 upward. Since the fixed cylinder 32 of the latch structure 3 is fixed to the outer shell 21 of the locking structure 2, the latch structure 3 does not move. Then, when the locking hole 232 at position B on the locking column 23 moves to the position where the latch structure 3 on the left side is located, the second elastic member 33 releases its elastic force to push the front end of the latch 31 to extend into the locking hole 232 at position B, and the wing 6 maintains the 32.8° angular state.

[0051] When the wing 6 needs to be deployed to an angular state of 0°, the second shape memory alloy wire 35 of the left plug structure 3 is energized. The second shape memory alloy wire 35 contracts, driving the front end of the plug 31 to withdraw from the locking hole 232 at B, and compressing the second elastic member 33. The first elastic member 221 provides a thrust to continue pushing the locking column 23 upward. After the locking hole 232 at C moves to the position where the right plug structure 3 is located, the second elastic member 33 releases its elastic force to push the front end of the plug 31 into the locking hole 232 at C, and the wing 6 is maintained in the 0° angular state.

[0052] When the wing 6 needs to be reset to an angular state of 90°, the second shape memory alloy wire 35 of the right plug structure 3 is energized. The second shape memory alloy wire 35 contracts, driving the front end of the plug 31 to withdraw from the locking hole 232 at C, and compressing the second elastic member 33. The first shape memory alloy wire 24 is heated, and the first shape memory alloy wire 24 contracts to provide a pulling force to pull the locking column 23 downward. Finally, when the locking hole 232 at A moves to the position where the right plug structure 3 is located again, the second elastic member 33 releases its elastic force to push the front end of the plug 31 into the locking hole 232 at A, and the wing 6 is reset to the 90° angular state and is folded.

[0053] Another embodiment of the present invention provides a folding wing, including the mechanism for controlling the multi-angle state of the wing as described above, so that the folding wing has the advantages of low cost and low impact.

[0054] 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 point of each embodiment is to illustrate the differences from other embodiments.

[0055] The above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit 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 mechanism for controlling the multi-angle state of a wing, characterized in that: It includes a housing, a locking structure, a latch structure, a hinge seat and two sets of transmission structures; One end of the locking structure is fixed to the housing, and a plurality of radial locking holes are arranged along its axial direction; The hinge seat is fixed to the other end of the locking structure; The first ends of the two groups of transmission structures are respectively hinged to the two sides of the hinge seat, the bottoms of the second ends are fixed to the shell, and the tops of the second ends are respectively fixed to one wing; The front end of the latch structure can be inserted into or withdrawn from the locking hole, each of the locking holes corresponds to an angle state of a wing, and when the front end of the latch structure withdraws from the locking hole, the locking structure can drive the hinge seat to move along its own axial direction; Wherein, the locking structure comprises a housing, an elastic component and a locking column; One end of the outer shell is fixed to the shell; the locking column is provided with a plurality of locking holes along its own axial direction and is arranged in the inner cavity of the shell; the hinge seat is fixed to the first end of the locking column, and the first end is located at the opening of the shell; the two ends of the elastic component are respectively against the first end of the locking column and the bottom surface of the shell; The locking structure further includes a first shape memory alloy wire; the locking column is provided with a through hole penetrating the locking column in a radial direction; the first shape memory alloy wire is passed through the through hole, and both ends of the first shape memory alloy wire are respectively fixed to the housing; The transmission structure includes a fixed support, a bearing, a bolt, a rocker and a connecting rod; one end of the connecting rod is hinged to one side of the hinged seat as the first end of the transmission structure, and the other end is connected to one end of the rocker; the bottom of the fixed support is fixed to the shell as the bottom of the second end of the transmission structure, and a bearing mounting hole is provided in the middle of the upper surface; the bearing is clamped in the bearing mounting hole; the bolt is clamped in the inner hole of the bearing; the middle part of the rocker is sleeved on the bolt; the rocker is fixed to the wing as the top of the second end of the transmission structure.

2. The mechanism for controlling the multi-angle state of the wing according to claim 1, characterized in that, The locking structure also includes a plurality of guide posts; One end of the plurality of guide posts is fixed to the housing, and the other end is provided with a guide through hole; The first shape memory alloy wire is inserted into the guide through hole.

3. The mechanism for controlling the multi-angle state of the wing according to any one of claims 1 to 2, characterized in that, The elastic component includes four first elastic members; The four first elastic members are distributed in a ring array around the central axis of the locking column.

4. The mechanism for controlling the multi-angle state of the wing according to claim 3, characterized in that, The locking column is a hexahedron; The four edges of the locking column are radially concave, and blocking platforms are provided on the tops of the four edges; The four first elastic members are respectively arranged in the inner recess, and two ends thereof are respectively against the blocking platform and the bottom surface of the shell.

5. The mechanism for controlling the multi-angle state of the wing according to claim 1, characterized in that, The latch structure comprises a latch, a fixing tube, a second elastic member, a bottom plate and a second shape memory alloy wire; One end of the fixing tube is provided with the latch, and the other end is fixed to the bottom plate; The latch can move along the axial direction of the fixing tube, the front end can be inserted into or withdrawn from the locking hole, and the rear end is connected to the second shape memory alloy wire; The other end of the second shape memory alloy wire passes through the bottom plate; The second elastic member is disposed in the inner cavity of the fixing tube, and two ends of the second elastic member are respectively against the latch and the bottom plate.

6. The mechanism for controlling the multi-angle state of the wing according to claim 1 or 5, characterized in that A plurality of the locking holes are respectively arranged on opposite sides of the locking structure, and the locking holes on both sides are arranged in a staggered manner; There are two sets of the bolt structures, and the two sets of bolt structures are respectively arranged on both sides of the locking structure, and the front ends can respectively insert into or withdraw from the locking holes on the corresponding sides.

7. A folding wing, characterized in that, It includes the mechanism for controlling the multi-angle state of the wing according to any one of claims 1 to 5.

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