A retractable lateral folding wing surface

Abstract

This invention discloses a retractable, laterally folding wing surface, relating to the field of aerospace technology. Specifically, it includes: a wing surface body comprising a first wing surface and a second wing surface, the first wing surface being rotatably engaged with the second wing surface via a torsion bar assembly; when the wing surface body is deployed, the side surface of the second wing surface is flush with the side surface of the first wing surface; when the wing surface body is folded, the second wing surface is perpendicular to the first wing surface; an deployment locking mechanism, the telescopic end of which is connected to the bottom of the first wing surface; and a baffle assembly, which is sleeved on the outside of the telescopic end of the deployment locking mechanism and contacts the bottom of the first wing surface. The first and second wing surfaces of this invention are designed as laterally folding wing surfaces, with the wing surface body folding circumferentially towards the aircraft, making efficient use of the space outside the aircraft and further reducing the outer envelope of the wing surface body during aircraft loading.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and more specifically to a retractable, laterally folding wing surface. Background Technology

[0002] Airfoils are controllable aerodynamic surfaces installed on the exterior of aircraft (such as airplanes, rockets, and other spacecraft or aircraft). Their main function is to change the aircraft's flight attitude, trajectory, or stability by generating aerodynamic forces when deflected. Airfoils generally protrude from the outer surface of the aircraft. To increase the aircraft's packing density, airfoils are often folded for packing and then unfolded after launch, improving space utilization and reducing the volume and weight of the launch canister (tube).

[0003] Based on the folding method, common folding wing surface solutions can generally be divided into longitudinal folding and lateral folding. Longitudinal folding is suitable for wings with an aspect ratio greater than 1. Longitudinal folding utilizes the space inside the cabin, but requires an opening in the cabin. The wing surface is folded longitudinally along the wing axis towards the cabin, and after folding, part or all of the wing surface is integrated into the cabin. However, the cabin opening is easily affected by airflow after unfolding. The folding angle of longitudinal folding is limited by the space of the unfolding and locking mechanism, with most folding angles controlled at 90°. Lateral folding has no aspect ratio requirement. Lateral folding folds the wing surface laterally along the wing axis, and after folding, the wing surface remains outside the cabin. Lateral folding has now evolved to multi-segment folding, which is unlocked via control commands. The unfolding and locking structures are complex and cumbersome to control, and the folded wing surface still occupies a significant amount of space outside the cabin. While existing longitudinal and lateral folding wings reduce the external installation space of the aircraft, the wing surface cannot retract or extend along the wing axis (cabin radial direction), failing to fully utilize the internal space of the cabin to further reduce the aircraft's external installation envelope.

[0004] From the perspective of deployment and locking methods, traditional deployment and locking methods include deployment using pyrotechnics, deployment using compression springs with a self-locking mechanism, deployment using torsion springs with a cam mechanism, and deployment using torsion bars with a locking mechanism. Deployment using pyrotechnics requires significant deployment force but has a complex structure. If the wing needs repeated folding, multiple pyrotechnics must be added, greatly increasing costs. Deployment using torsion springs with a cam mechanism has a lower torsional torque, reducing wing deployment time, but cam mechanism locking can easily lead to incomplete locking and wing movement after locking. Compression spring deployment also has limited preload force and requires considerable installation space to achieve rapid deployment. Torsion bar deployment requires deep holes to be machined on the corresponding wing surface, resulting in poor manufacturability. Furthermore, existing locking mechanisms typically use wall-mounted electromagnetic locks or spring pins. Electromagnetic locks require electrical control and have a complex structure; spring pins have a simple structure but are easily affected by deployment impacts, causing them to fail to insert properly into the locking hole. Summary of the Invention

[0005] The purpose of this invention is to provide a retractable, laterally folding wing surface to solve the problems mentioned in the background art.

[0006] The technical solution of the present invention to solve the above-mentioned technical problems is as follows:

[0007] A retractable, laterally folding wing surface, comprising:

[0008] The wing body includes a first wing surface and a second wing surface. The first wing surface is rotatably engaged with the second wing surface through a torsion bar assembly. When the wing body is unfolded, the side of the second wing surface is flush with the side of the first wing surface. When the wing body is folded, the second wing surface is perpendicular to the first wing surface.

[0009] Deploy the locking mechanism; the telescopic end of the locking mechanism is connected to the bottom of the first wing surface.

[0010] And a baffle assembly, which is sleeved on the outside of the telescopic end of the deployment locking mechanism and contacts the bottom of the first wing surface.

[0011] Furthermore, the aforementioned deployment and locking mechanism includes a telescopic drive shaft, a bushing, and an electric detonator, with the telescopic drive shaft connected to the bottom of the first wing surface;

[0012] The telescopic drive shaft includes a first column, a second column, a third column, and a fourth column that are axially connected from top to bottom, and the outer diameter of the telescopic drive shaft decreases from the first column to the fourth column.

[0013] The bushing includes a first shaft cavity and a second shaft cavity. A second column, a third column, and a fourth column are located in the first shaft cavity. An electric detonator is disposed in the second shaft cavity. A connecting hole is provided between the first shaft cavity and the second shaft cavity. An axial locking assembly for locking with the bushing is symmetrically disposed on the side wall of the fourth column.

[0014] Furthermore, the first column has an annular groove on its bottom outer wall near the second column, the second column has two symmetrical arc-shaped limiting blocks on its bottom outer wall near the third column, the third column has two symmetrical flat keys on its outer wall, and the flat keys correspond to the arc-shaped limiting blocks. The fourth column has two symmetrical second mounting holes on its outer wall, and two sets of axial locking components are provided and installed in the two second mounting holes respectively. The bottom outer wall of the fourth column has an annular sealing groove for installing the sealing ring.

[0015] The first shaft cavity includes an upper chamber and a lower chamber from top to bottom. The inner diameter of the upper chamber is larger than that of the lower chamber. The inner diameter of the lower chamber matches the outer diameter of the third column. The top inner wall of the upper chamber is symmetrically provided with two limiting arc-shaped rings for limiting the position of the arc-shaped limiting block. The inner wall of the lower chamber near the upper chamber is symmetrically provided with two keyways that match the flat key.

[0016] Furthermore, the aforementioned axial locking assembly includes a first spring installed in the second mounting hole and an axial pin connected to the first spring, and the inner wall of the lower chamber is provided with an axial positioning hole corresponding to and matching the axial pin.

[0017] Furthermore, the aforementioned baffle assembly includes a bearing sleeved on the outer wall of the first column, a retaining ring installed in the annular groove and located below the bearing, a baffle sleeved on the outside of the bearing and in contact with its bottom, and two fixing blocks located on the top of the baffle and respectively engaged with the top sides of the bearing. The fixing blocks are connected to the baffle by screws, and the top of the fixing blocks is in contact with the bottom of the first wing surface.

[0018] Furthermore, the aforementioned baffle includes an arc-shaped ring located at the bottom of the bearing, and horizontal plates symmetrically arranged on both sides of the arc-shaped ring and in contact with the outer wall of the bearing. The horizontal plates correspond one-to-one with the fixing blocks, and the fixing blocks are located at the top of the horizontal plates.

[0019] A clearance groove is provided on one side of the bottom of the first wing surface. The end face of one horizontal plate away from the arc ring is flush with the end face of the first wing surface, and the end face of the other horizontal plate away from the arc ring is flush with the side wall of the clearance groove.

[0020] Furthermore, the outer side of the aforementioned bushing is provided with two symmetrical double forks.

[0021] Furthermore, the aforementioned torsion bar assembly includes an elastic torsion bar and a torsion bar locking screw. The outer wall of the first end of the elastic torsion bar is symmetrically milled with two first planes, and the outer wall of the second end is milled with a second plane.

[0022] The top of the first wing surface is provided with a groove, and one side of the top of the first wing surface is provided with a mounting groove. The side wall of the groove away from the mounting groove is provided with a positioning hole that matches the first end of the elastic torsion bar, and the side wall of the groove near the mounting groove is provided with a first shaft hole that matches the rod part of the elastic torsion bar.

[0023] The bottom of the second wing surface is provided with a first boss and a second boss that match the groove and the mounting groove respectively. The first end of the elastic torsion bar passes through the second boss, the first shaft hole and the first boss in sequence and is inserted into the positioning hole. The torsion bar locking screw passes through the outer wall of the second boss and is connected to the second plane.

[0024] Furthermore, the bottom wall of the groove and the bottom wall of the mounting groove are respectively provided with a first mounting hole, the bottom wall of the first mounting hole is provided with a second spring, the top of the second spring is connected with a wing-surface positioning pin, and the bottom of the first boss and the second boss are respectively provided with wing-surface positioning holes corresponding to and matching the wing-surface positioning pin.

[0025] When the wing body is deployed, the top of the wing positioning pin is inserted into the corresponding wing positioning hole; when the wing body is folded, the second spring is compressed, and the wing positioning pin contacts the surface of the second wing.

[0026] Furthermore, the sidewall of the first wing surface is provided with a first through groove corresponding to and communicating with the two first mounting holes, and the sidewall of the first wing surface is provided with a second through groove perpendicular to and communicating with the first through groove, and the top outer diameter of the wing surface positioning pin matches the groove diameter of the second through groove.

[0027] The top side of the first wing surface is provided with a first rounded corner, and the first boss and the second boss are respectively provided with a second rounded corner corresponding to the first rounded corner.

[0028] The present invention has the following beneficial effects:

[0029] 1. This invention provides a retractable, laterally folding wing surface that simultaneously utilizes both the internal and external spaces of an aircraft, reducing the aircraft's external envelope and improving installation space utilization. The wing surface body can move inwards into the aircraft. During flight, an electric detonator drives the telescopic drive shaft and cabin cover to extend simultaneously, and an axial locking assembly locks the telescopic drive shaft, fully utilizing the internal space of the cabin and achieving cabin closure, thus reducing the wing surface body's external envelope during aircraft loading. The first and second wing surfaces of this invention are designed as laterally folding wings, with the wing surface body folding circumferentially towards the aircraft, making reasonable use of the external space and further reducing the wing surface body's external envelope during aircraft loading. The second wing surface is deployed using a torsion bar assembly to provide deployment power, and then locked by a second spring and wing surface positioning pins, without increasing the wing surface's external space. It has the advantages of high driving force, high reliability, and small size, improving installation space utilization.

[0030] 2. The baffle assembly of the present invention is installed on the outside of the first column of the telescopic transmission shaft. When the electric detonator drives the telescopic transmission shaft to extend, it will simultaneously drive the bearing, snap ring, baffle and fixing block to extend, and fill the opening on the cabin with the two horizontal plates on the baffle. At this time, the cabin shape has no gaps, which ensures the aerodynamic characteristics of the aircraft during flight. Attached Figure Description

[0031] Figure 1 This is a schematic diagram of the structure when the retractable, laterally folding wing surface is deployed.

[0032] Figure 2 This is a schematic diagram of the front view cross-sectional structure of the retractable lateral folding wing when it is deployed.

[0033] Figure 3 for Figure 2 A magnified structural diagram at point A;

[0034] Figure 4 for Figure 2 A magnified structural diagram at point B;

[0035] Figure 5 for Figure 2 A magnified structural diagram at point C;

[0036] Figure 6 A schematic diagram of the left-hand cross-sectional structure of the retractable, laterally folding wing when deployed;

[0037] Figure 7 This is a schematic diagram of the structure of the telescopic drive shaft and the first wing surface;

[0038] Figure 8 This is a schematic diagram of the structure of the first wing surface;

[0039] Figure 9 This is a schematic diagram of the second wing surface.

[0040] Figure 10 This is a cross-sectional view of the bushing.

[0041] Figure 11 This is a schematic diagram of the structure of an elastic torsion bar;

[0042] Figure 12 This is a schematic diagram of the block's structure;

[0043] Figure 13 This is a schematic diagram of the baffle structure;

[0044] Figure 14 This is a schematic diagram of the structure of a retractable, laterally folding wing when it is folded.

[0045] Figure 15 for Figure 14 A magnified structural diagram at point D.

[0046] In the diagram: 1. First wing surface; 11. Clearance groove; 12. Groove; 121. Positioning hole; 122. First shaft hole; 13. Mounting groove; 14. First mounting hole; 15. Second spring; 16. Wing surface positioning pin; 17. First through groove; 18. Second through groove; 19. Limiting rod; 2. Second wing surface; 21. First boss; 22. Second boss; 23. Wing surface positioning hole; 3. Torsion bar assembly; 31. Elastic torsion bar; 311. First plane; 312. Second plane; 32. Torsion bar locking screw; 4. Baffle assembly; 41. Bearing; 42. Snap ring; 43. Baffle; 431. Arc ring; 4 32. Horizontal plate; 44. Fixing block; 45. Screw; 5. Telescopic drive shaft; 51. First column; 511. Annular groove; 52. Second column; 521. Arc-shaped limiting block; 53. Third column; 531. Flat key; 54. Fourth column; 541. Second mounting hole; 542. Annular sealing groove; 6. Bushing; 61. First shaft cavity; 611. Upper chamber; 612. Lower chamber; 613. Limiting arc-shaped ring; 614. Keyway; 615. Axial positioning hole; 62. Second shaft cavity; 63. Connecting hole; 7. Electric detonator; 8. Axial locking assembly; 81. First spring; 82. Axial pin; 9. Double fork. Detailed Implementation

[0047] The principles and features of the present invention are described below with reference to the accompanying drawings. The examples given are only for explaining the present invention and are not intended to limit the scope of the present invention.

[0048] like Figures 1 to 15 As shown, an embodiment of the present invention provides a retractable lateral folding wing surface, comprising:

[0049] The wing body includes a first wing surface 1 and a second wing surface 2. The first wing surface 1 is rotatably engaged with the second wing surface 2 through a torsion bar assembly 3. When the wing body is unfolded, the side of the second wing surface 2 is flush with the side of the first wing surface 1, and at the same time, the two ends of the first wing surface 1 are flush with the two ends of the second wing surface 2. When the wing body is folded, the second wing surface 2 is perpendicular to the first wing surface 1.

[0050] It should be noted that the first wing surface 1 includes a connecting part and a wing panel integrally formed with the connecting part. When the wing surface body is unfolded, the front and rear sides of the second wing surface 2 are flush with the front and rear sides of the wing panel, and the two ends of the second wing surface 2 are flush with the two ends of the wing panel. The top of the wing panel of the first wing surface 1 is rotatably engaged with the bottom of the second wing surface 2, and the length of the wing panel of the first wing surface 1 is equal to the length of the second wing surface 2.

[0051] Among them, such as Figure 3 and Figure 11As shown, the torsion bar assembly 3 includes an elastic torsion bar 31 and a torsion bar locking screw 32. The elastic torsion bar 31 is made of a material with a certain elastic deformation capability and has a cylindrical structure. The outer wall of the first end of the elastic torsion bar 31 is symmetrically milled with two first planes 311 and the outer wall of the second end is milled with a second plane 312.

[0052] like Figure 7 and Figure 8 As shown, a groove 12 is provided on the top of the first wing surface 1, and a mounting groove 13 is provided on one side of the top of the first wing surface 1. A positioning hole 121 matching the first end of the elastic torsion bar 31 is provided on the side wall of the groove 12 away from the mounting groove 13. A first shaft hole 122 matching the rod portion of the elastic torsion bar 31 is provided on the side wall of the groove 12 near the mounting groove 13. It should be noted that both the groove 12 and the mounting groove 13 are provided on the top of the wing panel of the first wing surface 1, and the mounting groove 13 is located at one end of the wing panel. The positioning hole 121 matches the first end of the elastic torsion bar 31, and the rotation between the first end of the elastic torsion bar 31 and the first wing surface 1 is restricted by the positioning hole 121.

[0053] like Figure 9 As shown, the bottom of the second wing surface 2 is provided with a first boss 21 and a second boss 22 that match the groove 12 and the mounting groove 13 respectively. The first boss 21 and the second boss 22 are each provided with a shaft hole that matches the rod part of the elastic torsion bar 31. The first end of the elastic torsion bar 31 passes through the second boss 22, the first shaft hole 122 and the first boss 21 in sequence and is inserted into the positioning hole 121. The outer wall of the second boss 22 is provided with a first threaded hole that corresponds to the second plane 312 of the elastic torsion bar 31. The torsion bar locking screw 32 passes through the outer wall of the second boss 22 and is connected to the second plane 312.

[0054] It should be noted that a second threaded hole corresponding to the first threaded hole on the outer wall of the second boss 22 may be provided on the second plane 312. The torsion bar locking screw 32 passes through the first threaded hole and connects with the second threaded hole. At the same time, the torsion bar locking screw 32 can also abut against the second plane 312, mainly used to limit the rotation between the second end of the elastic torsion bar 31 and the second wing surface 2.

[0055] The bottom wall of the groove 12 and the bottom wall of the mounting groove 13 are respectively provided with a first mounting hole 14. The bottom wall of the first mounting hole 14 is provided with a second spring 15. The top of the second spring 15 is connected to a wing positioning pin 16. The bottom of the first boss 21 and the second boss 22 are respectively provided with wing positioning holes 23 corresponding to and matching the wing positioning pin 16. When the wing body is unfolded, the top of the wing positioning pin 16 is inserted into the corresponding wing positioning hole 23. When the wing body is folded, the second spring 15 is compressed and the wing positioning pin 16 contacts the surface of the second wing 2. The wing positioning pin 16 is used to lock the unfolded second wing 2.

[0056] The locking mechanism is deployed, and the telescopic end of the locking mechanism is connected to the bottom of the first wing surface 1; the telescopic end of the locking mechanism is connected to the bottom of the connecting part of the first wing surface 1.

[0057] And a baffle assembly 4, which is sleeved on the outside of the telescopic end of the deployment locking mechanism and contacts the bottom of the first wing surface 1.

[0058] Specifically, such as Figure 2 , Figure 5 , Figure 6 , Figure 7 , Figure 10 As shown, the deployment and locking mechanism includes a telescopic drive shaft 5, a bushing 6, and an electric detonator 7. The telescopic drive shaft 5 is connected to the bottom of the first wing surface 1. The telescopic drive shaft 5 serves as the telescopic end of the deployment and locking mechanism and is connected to the bottom of the connecting part in the first wing surface 1.

[0059] The telescopic drive shaft 5 includes a first column 51, a second column 52, a third column 53 and a fourth column 54 connected axially from top to bottom, and the outer diameter of the telescopic drive shaft 5 decreases from the first column 51 to the fourth column 54.

[0060] The bushing 6 includes a first shaft cavity 61 and a second shaft cavity 62. A second post 52, a third post 53, and a fourth post 54 are located in the first shaft cavity 61. An electric detonator 7 is disposed in the second shaft cavity 62, and a connecting hole 63 is provided between the first shaft cavity 61 and the second shaft cavity 62. In this embodiment, the outer side of the electric detonator 7 is provided with an external thread, and the inner wall of the second shaft cavity 62 is provided with an internal thread that mates with its external thread. The electric detonator 7 is threadedly engaged with the second shaft cavity 62. The side wall of the fourth post 54 is symmetrically provided with axial locking components 8 for locking with the bushing 6. The axial locking components 8 are used to limit the axial position of the telescopic transmission shaft 5.

[0061] Specifically, the first column 51 has an annular groove 511 on its bottom outer wall near the second column 52, the second column 52 has two arc-shaped limiting blocks 521 symmetrically arranged on its bottom outer wall near the third column 53, the third column 53 has two flat keys 531 symmetrically arranged on its outer wall, and the flat keys 531 correspond to the arc-shaped limiting blocks 521. The fourth column 54 has two second mounting holes 541 symmetrically arranged on its outer wall, the axial locking assembly 8 has two sets and is installed in the two second mounting holes 541 respectively, and the bottom outer wall of the fourth column 54 has an annular sealing groove 542 for installing the sealing ring.

[0062] The first shaft cavity 61 includes an upper chamber 611 and a lower chamber 612 from top to bottom. The inner diameter of the upper chamber 611 is larger than the inner diameter of the lower chamber 612. The inner diameter of the lower chamber 612 matches the outer diameter of the third column 53. Two limiting arc-shaped rings 613 are symmetrically arranged on the top inner wall of the upper chamber 611 to limit the position of the arc-shaped limiting block 521. Two keyways 614 matching the flat key 531 are symmetrically opened on the inner wall of the lower chamber 612 near the upper chamber 611.

[0063] The axial locking assembly 8 includes a first spring 81 installed in the second mounting hole 541 and an axial pin 82 connected to the first spring 81. The inner wall of the lower chamber 612 has an axial positioning hole 615 corresponding to and matching the axial pin 82. When the aircraft is in flight, the telescopic drive shaft 5 and the cabin cover are simultaneously extended by the electric detonator 7, and then the axial locking assembly 8 locks the telescopic drive shaft 5, making full use of the space inside the cabin and achieving cabin closure, thus reducing the outer envelope of the wing body when the aircraft is being loaded.

[0064] like Figure 4 , Figure 12 , Figure 13 As shown, the baffle assembly 4 includes a bearing 41 sleeved on the outer wall of the first column 51, a retaining spring 42 installed in the annular groove 511 and located below the bearing 41, the retaining spring 42 is used to limit the position of the bearing 41 and prevent the bearing 41 from slipping off the first column 51; a baffle 43 sleeved on the outside of the bearing 41 and in contact with its bottom, and two fixing blocks 44 located on the top of the baffle 43 and respectively engaged with the top sides of the bearing 41. In this embodiment, the fixing blocks 44 have grooves that match the bearing 41. The fixing blocks 44 are connected to the baffle 43 by screws 45, and the top of the fixing blocks 44 is in contact with the bottom of the first wing surface 1.

[0065] Specifically, the baffle 43 includes an arc-shaped ring 431 located at the bottom of the bearing 41, and horizontal plates 432 symmetrically arranged on both sides of the arc-shaped ring 431 and in contact with the outer wall of the bearing 41. The horizontal plates 432 correspond one-to-one with the fixing blocks 44, and the fixing blocks 44 are located on the top of the horizontal plates 432. With this arrangement, the fixing blocks 44 are located on the top of the baffle 43 and the bearing 41, and the fixing blocks 44 are connected to the baffle 43 by screws 45. The arc-shaped ring 431 is located at the bottom of the bearing 41, so that the horizontal plates 432 are always located on both sides of the bearing 41. When the telescopic transmission shaft 5 extends or retracts, it drives the arc-shaped ring 431 and the horizontal plates 432 to extend or retract together through the bearing 41.

[0066] A clearance groove 11 is provided on one side of the bottom of the first wing surface 1. The end face of one horizontal plate 432 away from the arc ring 431 is flush with the end face of the first wing surface 1, and the end face of the other horizontal plate 432 away from the arc ring 431 is flush with the side wall of the clearance groove 11.

[0067] like Figure 1 As shown, in another embodiment of the present invention, two vertically symmetrical double forks 9 are provided on the outer side of the bushing 6; the double forks 9 can drive the wing body to deflect by transmitting torque. If the wing body is a fixed wing, the double forks 9 may not be provided.

[0068] like Figure 14 and Figure 15 As shown, in another embodiment of the present invention, the sidewall of the first wing surface 1 is provided with a first through groove 17 corresponding to and communicating with the two first mounting holes 14, and the sidewall of the first wing surface 1 is provided with a second through groove 18 perpendicular to and communicating with the first through groove 17. The first through groove 17 and the second through groove 18 are located on the same side. In this embodiment, the groove diameter of the first through groove 17 is equal to the groove diameter of the second through groove 18, and the groove diameters of the first through groove 17 and the second through groove 18 are smaller than the hole diameter of the first mounting hole 14. The length of the first through groove 17 is equal to the depth of the first mounting hole 14. The outer diameter of the upper part of the wing surface positioning pin 16 is smaller than the outer diameter of its lower part. The outer diameter of the upper part of the wing surface positioning pin 16 matches the groove diameter of the second through groove 18. The outer diameter of the lower part of the wing surface positioning pin 16 and the outer diameter of the second spring 15 match the hole diameter of the first mounting hole 14. This design facilitates the installation of the torsion bar assembly 3, the first wing surface 1, and the second wing surface 2, preventing the wing surface positioning pin 16 from popping out and interfering with the installation of the torsion bar assembly 3 and the second wing surface 2.

[0069] When assembling the second wing surface 2 and the torsion bar assembly 3, first install the second spring 15 and the wing surface positioning pin 16 into the corresponding first mounting hole 14 in sequence. At this time, the second spring 15 is in a naturally extended state, and the upper part of the wing surface positioning pin 16 extends out from the first mounting hole 14. Manually or with an external tool, move the wing surface positioning pin 16 to compress the second spring 15 and deflect it into the first through groove 17. When it is moved into the second through groove 18, the second spring 15 is compressed, and the wing surface positioning pin 16 is stuck by the side wall of the second through groove 18. Then assemble the second wing surface 2 and the torsion bar assembly 3. After the assembly is completed, make the second wing surface 2 perpendicular to the first wing surface 1. Finally, move the wing surface positioning pin 16 to reset it. At this time, the top of the reset wing surface positioning pin 16 contacts the outer surface of the second wing surface 2.

[0070] Meanwhile, the top side of the first wing surface 1 is provided with a first rounded corner, and the first boss 21 and the second boss 22 are respectively provided with a second rounded corner corresponding to the first rounded corner. When the wing surface body is folded, the rounded corner of the second wing surface 2 can rotate along the rounded corner of the first wing surface 1. When unfolded, the plane on the other side of the rounded corner can limit the second wing surface 2 to ensure that it is aligned with the wing panel of the first wing surface 1.

[0071] The installation process of the retractable lateral folding wing surface of the present invention is as follows:

[0072] (1) Installation of baffle assembly 4: Slide the bearing 41 onto the first column 51 of the telescopic drive shaft 5 until it contacts the bottom of the first wing surface 1. Then install the snap ring 42 into the annular groove 511 on the first column 51. The snap ring 42 is used to prevent the bearing 41 from coming off the telescopic drive shaft 5. Further, pass the baffle 43 through the telescopic drive shaft 5 and slide it onto the outside of the bearing 41. At the same time, make the arc ring 431 located below the bearing 41 and contact the outer edge of the snap ring 42. The two symmetrical horizontal plates 432 are located on both sides of the bearing 41. Then, the baffle 43 is offset from the first wing surface 1 by a certain angle. The two fixing blocks 44 are clamped on the top of the bearing 41 and correspond to the horizontal plates 432. The two fixing blocks 44 are connected and fixed to the corresponding two horizontal plates 432 by screws 45. After the connection is completed, the baffle 43 is aligned with the bottom of the first wing surface 1 so that its two ends are aligned with the bottom of the first wing surface 1. Thus, the assembly of the baffle assembly 4 is completed.

[0073] (2) The two sets of axial locking components 8 are respectively installed in the two second mounting holes 541. A sealing ring is installed in the annular sealing groove 542 of the fourth column 54. The sealing ring is used to ensure the airtightness between the fourth column 54 and the lower chamber 612 and to prevent gas leakage. The electric detonator 7 is screwed into the second shaft cavity 62.

[0074] Since the outer wall of the second column 52 of the telescopic drive shaft 5 is provided with two sets of arc-shaped limiting blocks 521, the telescopic drive shaft 5 requires a specific installation method: insert the telescopic drive shaft 5 into the bushing 6, rotate the telescopic drive shaft 5 in the forward direction, and make the two arc-shaped limiting blocks 521 offset from the two limiting arc-shaped rings 613 on the inner wall of the upper chamber 611 in the bushing 6 by a certain angle. Then move the telescopic drive shaft 5 into the lower chamber 612. When the two flat keys 531 of the third column 53 move to the position of the keyway 614, rotate the telescopic drive shaft 5 in the reverse direction and make the two flat keys 531 completely correspond to the keyway 614. Continue to insert the telescopic drive shaft 5 until the flat keys 531 are completely inserted into the keyway 614, thereby completing the assembly of the telescopic drive shaft 5 and the bushing 6.

[0075] (3) Install the second spring 15 and the wing positioning pin 16 into the two first mounting holes 14, move the wing positioning pin 16 to compress the second spring 15 and deflect it into the first through groove 17, and move it into the second through groove 18. When the second spring 15 is compressed, the wing positioning pin 16 is stuck by the side wall of the second through groove 18.

[0076] Further, the first boss 21 and the second boss 22 of the second wing surface 2 are respectively installed onto the groove 12 and the mounting groove 13 of the first wing surface 1. The elastic torsion bar 31 is then passed through the second boss 22, the first shaft hole 122 and the first boss 21 in sequence and inserted into the positioning hole 121. The elastic torsion bar 31 is then locked with the torsion bar locking screw 32 to complete the assembly of the torsion bar assembly 3, the first wing surface 1 and the second wing surface 2.

[0077] The folding process of the wing body of the retractable lateral folding wing of the present invention is as follows:

[0078] When the telescopic drive shaft 5 and bushing 6 are initially installed, the telescopic drive shaft 5 is in the retracted state, that is, the bottom of the fourth column 54 is in contact with the bottom of the lower chamber 612; the upper part of the wing surface positioning pin 16 is moved into the second through groove 18, and then the second wing surface 2 is rotated 90° around the first wing surface 1. At this time, the second wing surface 2 is perpendicular to the first wing surface 1, and the elastic torsion bar 31 is twisted and stored energy. Then the wing surface positioning pin 16 is moved and reset. At this time, the top of the wing surface positioning pin 16 is in contact with the outer surface of the second wing surface 2. The second wing surface 2 is limited by the stop on the mounting cylinder that cooperates with the aircraft, and the wing surface body is in a folded state.

[0079] The deployment process of the wing body of the retractable lateral folding wing of the present invention is as follows:

[0080] When the wing body is deployed, the aircraft flies out of the mounting tube. The second wing 2 is no longer limited by the stop of the mounting tube. Driven by the elastic torsion bar 31, the second wing 2 is driven to reset. At this time, the wing positioning pin 16 slides along the rounded outer wall of the two bosses. When the second wing 2 deflects to be flush with the first wing 1, the top of the wing positioning pin 16 is inserted into the wing positioning hole 23, completing the locking of the second wing 2. At this time, the second wing 2 is deployed.

[0081] When the second wing 2 unfolds, an ignition actuation command is sent to the electric detonator 7, which ignites the explosive. The explosive content is designed according to the load that the shaft extension needs to overcome. The telescopic drive shaft 5 pops outward along the bushing 6 until the two arc-shaped limit blocks 521 contact the two limit arc-shaped rings 613 respectively, and the telescopic drive shaft 5 reaches its maximum extension distance. At the same time, the axial pin 82 pops out under the action of the first spring 81 and inserts into the axial positioning hole 615, completing the axial locking of the telescopic drive shaft 5 and the bushing 6.

[0082] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A retractable, laterally folding wing surface, characterized in that, include: The wing body includes a first wing surface (1) and a second wing surface (2). The first wing surface (1) is rotatably engaged with the second wing surface (2) through a torsion bar assembly (3). When the wing body is unfolded, the side of the second wing surface (2) is flush with the side of the first wing surface (1). When the wing body is folded, the second wing surface (2) is perpendicular to the first wing surface (1). The locking mechanism is deployed, and the telescopic end of the locking mechanism is connected to the bottom of the first wing surface (1); And a baffle assembly (4), which is sleeved on the outside of the telescopic end of the deployment locking mechanism and in contact with the bottom of the first wing surface (1); The deployment locking mechanism includes a telescopic drive shaft (5), a bushing (6), and an electric detonator (7), wherein the telescopic drive shaft (5) is connected to the bottom of the first wing surface (1); The telescopic transmission shaft (5) includes a first column (51), a second column (52), a third column (53) and a fourth column (54) connected axially from top to bottom, and the outer diameter of the telescopic transmission shaft (5) decreases from the first column (51) to the fourth column (54); The bushing (6) includes a first shaft cavity (61) and a second shaft cavity (62). The second column (52), the third column (53), and the fourth column (54) are located in the first shaft cavity (61). The electric detonator (7) is disposed in the second shaft cavity (62). A connecting hole (63) is provided between the first shaft cavity (61) and the second shaft cavity (62). The side wall of the fourth column (54) is symmetrically provided with an axial locking assembly (8) for locking with the bushing (6). The bottom outer wall of the first column (51) near the second column (52) is provided with an annular groove (511). The baffle assembly (4) includes a bearing (41) sleeved on the outer wall of the first column (51), a retaining ring (42) installed in the annular groove (511) and located below the bearing (41), a baffle (43) sleeved on the outside of the bearing (41) and in contact with its bottom, and two fixing blocks (44) located on the top of the baffle (43) and respectively engaged with the top sides of the bearing (41). The fixing blocks (44) are connected to the baffle (43) by screws (45), and the top of the fixing blocks (44) is in contact with the bottom of the first wing surface (1).

2. The retractable lateral folding wing surface according to claim 1, characterized in that, The second column (52) has two arc-shaped limiting blocks (521) symmetrically arranged on the bottom outer wall near the third column (53). The outer wall of the third column (53) has two flat keys (531) symmetrically arranged, and the flat keys (531) correspond to the arc-shaped limiting blocks (521). The outer wall of the fourth column (54) has two second mounting holes (541) symmetrically opened. The axial locking assembly (8) is provided in two sets and is installed in the two second mounting holes (541) respectively. The bottom outer wall of the fourth column (54) has an annular sealing groove (542) for installing the sealing ring. The first shaft cavity (61) includes an upper chamber (611) and a lower chamber (612) from top to bottom. The inner diameter of the upper chamber (611) is larger than the inner diameter of the lower chamber (612). The inner diameter of the lower chamber (612) matches the outer diameter of the third column (53). The top inner wall of the upper chamber (611) is symmetrically provided with two limiting arc rings (613) for limiting the position of the arc-shaped limiting block (521). The lower chamber (612) is symmetrically provided with two keyways (614) that match the flat key (531) on the inner wall near the upper chamber (611).

3. The retractable lateral folding wing surface according to claim 2, characterized in that, The axial locking assembly (8) includes a first spring (81) installed in the second mounting hole (541) and an axial pin (82) connected to the first spring (81). The inner wall of the lower chamber (612) is provided with an axial positioning hole (615) corresponding to and matching the axial pin (82).

4. The retractable lateral folding wing surface according to claim 1, characterized in that, The baffle (43) includes an arc-shaped ring (431) located at the bottom of the bearing (41) and a horizontal plate (432) symmetrically arranged on both sides of the arc-shaped ring (431) and in contact with the outer wall of the bearing (41). The horizontal plate (432) corresponds one-to-one with the fixing block (44), and the fixing block (44) is located at the top of the horizontal plate (432). A clearance groove (11) is provided on one side of the bottom of the first wing surface (1). The end face of one of the horizontal plates (432) away from the arc ring (431) is flush with the end face of the first wing surface (1), and the end face of the other horizontal plate (432) away from the arc ring (431) is flush with the side wall of the clearance groove (11).

5. The retractable lateral folding wing surface according to claim 1, characterized in that, The outer side of the bushing (6) is provided with two symmetrical double forks (9).

6. The retractable lateral folding wing surface according to any one of claims 1 to 5, characterized in that, The torsion bar assembly (3) includes an elastic torsion bar (31) and a torsion bar locking screw (32). The outer wall of the first end of the elastic torsion bar (31) is symmetrically milled with two first planes (311) and the outer wall of the second end is milled with a second plane (312). The top of the first wing surface (1) is provided with a groove (12), and a mounting groove (13) is provided on one side of the top of the first wing surface (1). The side wall of the groove (12) away from the mounting groove (13) is provided with a positioning hole (121) that matches the first end of the elastic torsion bar (31). The side wall of the groove (12) near the mounting groove (13) is provided with a first shaft hole (122) that matches the rod part of the elastic torsion bar (31). The bottom of the second wing surface (2) is provided with a first boss (21) and a second boss (22) that match the groove (12) and the mounting groove (13) respectively. The first end of the elastic torsion bar (31) passes through the second boss (22), the first shaft hole (122), and the first boss (21) in sequence and is inserted into the positioning hole (121). The torsion bar locking screw (32) passes through the outer wall of the second boss (22) and is connected to the second plane (312).

7. The retractable lateral folding wing surface according to claim 6, characterized in that, The bottom wall of the groove (12) and the bottom wall of the mounting groove (13) are respectively provided with a first mounting hole (14). The bottom wall of the first mounting hole (14) is provided with a second spring (15). The top of the second spring (15) is connected to a wing-surface positioning pin (16). The bottom of the first boss (21) and the second boss (22) are respectively provided with wing-surface positioning holes (23) corresponding to and matching the wing-surface positioning pin (16). When the wing body is unfolded, the top of the wing positioning pin (16) is inserted into the corresponding wing positioning hole (23); when the wing body is folded, the second spring (15) is compressed, and the wing positioning pin (16) contacts the surface of the second wing (2).

8. The retractable lateral folding wing surface according to claim 7, characterized in that, The sidewall of the first wing surface (1) is provided with a first through groove (17) that corresponds to and communicates with the two first mounting holes (14) respectively, and the sidewall of the first wing surface (1) is provided with a second through groove (18) that is perpendicular to and communicates with the first through groove (17). The top outer diameter of the wing surface positioning pin (16) matches the groove diameter of the second through groove (18). The first wing surface (1) has a first rounded corner on one side of its top, and the first boss (21) and the second boss (22) are respectively provided with a second rounded corner corresponding to the first rounded corner.

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