Automatic wing unfolding mechanism of patrolling device, patrolling device and patrolling device set
By installing wing mounting bases and torsion spring limiting mechanisms on the loitering munition, the wings can be quickly deployed and folded, solving the problem of large transport and storage space requirements and improving its flexibility and flight stability.
Patent Information
- Application Number
- CN202520540889.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-03-25
- Publication Date
- 2026-01-13
- Estimated Expiration
- 2035-03-25
AI Technical Summary
The existing loitering munitions have large wing designs that take up a lot of space during transport and storage, which limits their use and versatility. In addition, the traditional fixed wing design is not convenient for quick deployment and folding, which affects their flexibility and stealth in complex environments.
The loitering wing adopts an automatic wing deployment mechanism. By setting wing mounting bases and fixed shafts on the fuselage, the wings can be quickly deployed and folded using torsion springs and limiting mechanisms. When the wings are folded, they rotate to be parallel to the fuselage. After launch, they automatically deploy and lock under the action of torsion springs to ensure flight stability.
It significantly reduces the size and storage space requirements of the loitering vehicle, improves its flexibility and adaptability, reduces operating costs, and ensures flight stability and reliability.
Smart Images
Figure CN223791766U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of aerospace technology, specifically to an automatic wing deployment mechanism for a loitering pod, a loitering pod, and a loitering pod kit. Background Technology
[0002] A loitering munition is a type of munition (or submunition) deployed using existing weapons, capable of patrolling a target area and undertaking single or multiple missions such as surveillance, reconnaissance, battle damage assessment, airborne radio relay, and target attack. During launch and storage, the folding wing design of loitering munitions reduces their footprint, facilitating deployment on limited launch platforms (such as ships and submarines). Furthermore, the foldable wing design allows for more flexible operation in complex environments such as urban or mountainous areas, improving mission success rates. Advances in folding wing technology have given loitering munitions greater stealth and flexibility in combat, enabling them to better cope with the changing environments of modern warfare. The folding wing design concept is not limited to loitering munitions but can also be extended to small aircraft such as drones, improving their adaptability and functionality. This enhances the rapid response capabilities of military forces.
[0003] Currently, most wing designs are significant in improving aircraft takeoff and landing performance, reducing storage space, and increasing fuel efficiency. Traditional fixed-wing designs often occupy a large amount of space during transport and storage, limiting the aircraft's usability and versatility. To meet the requirements of easy portability and rapid transport and launch of loitering munitions, developing a rapidly deployable and foldable wing system is particularly important.
[0004] In summary, there is an urgent need to design an automatic wing deployment mechanism for a loitering wing, a loitering wing, and a loitering wing kit to overcome the aforementioned technical problems. Utility Model Content
[0005] The purpose of this invention is to provide an automatic wing deployment mechanism for a loitering wing system with a rapidly deployable and foldable wing system, a loitering wing, and a loitering wing kit.
[0006] To achieve the above objectives, the technical solution adopted by this utility model is: an automatic wing deployment mechanism for a loitering glider, comprising:
[0007] A wing mounting base is fixedly installed on the fuselage, and a fixed shaft is provided in the middle of the wing mounting base;
[0008] The left wing has one end rotatably fitted onto the lower outer wall of the fixed shaft;
[0009] The right wing has one end rotatably fitted onto the upper outer wall of the fixed shaft. The opposite faces of the right and left wings near the fixed shaft are respectively provided with a first annular groove and a second annular groove. The first and second annular grooves are both surrounding the outside of the fixed shaft and are coaxial with the fixed shaft. A torsion spring is provided in the first and second annular grooves. The two ends of the torsion spring are respectively fixedly connected to the inner walls of the first and second annular grooves. The torsion spring has a rotational force that drives the left and right wings to unfold.
[0010] A limiting mechanism is used to limit the rotation angle of the left and right wings.
[0011] The purpose of this utility model and the technical problems to be solved can be further achieved by the following technical measures.
[0012] Optionally, the limiting mechanism includes a first hook and a second hook respectively disposed on the windward edges of the right wing and the left wing when deployed, and a first block and a second block respectively stacked on the wing mounting base;
[0013] When the right and left wings are deployed, the first hook and the second hook are respectively engaged with the first and the second locking blocks.
[0014] Optionally, the limiting mechanism further includes a first arc-shaped clearance groove and a second arc-shaped clearance groove. The ends of the right wing and the left wing near the fixed shaft are both provided with arc-shaped edges, and the first arc-shaped clearance groove and the second arc-shaped clearance groove are respectively provided on the arc-shaped edges of the right wing and the left wing. The first locking block and the second locking block move in the first arc-shaped clearance groove and the second arc-shaped clearance groove respectively.
[0015] When the right wing and left wing are deployed, one end of the first arc-shaped clearance groove and one end of the second arc-shaped clearance groove abut against one side of the first block and one side of the second block, respectively.
[0016] When the right and left wings are folded into place, the other end of the first arc-shaped clearance groove and the other end of the second arc-shaped clearance groove abut against the other side of the first block and the other side of the second block, respectively.
[0017] Optionally, the first hook and the second hook are respectively fastened to the windward edges of the right and left wings when they are deployed.
[0018] Optionally, a wing limiting cover may be installed at the end of the fixed shaft away from the wing mounting seat.
[0019] Optionally, a spacer is provided between the right wing and the left wing.
[0020] Optionally, the right wing and the left wing are respectively provided with a first through hole and a second through hole, and a graphite copper sleeve is fixedly connected in the first through hole and the second through hole. The inner wall of the graphite copper sleeve is rotatably connected to the fixed shaft.
[0021] A loitering vehicle, comprising the fuselage and the loitering vehicle wing automatic deployment mechanism;
[0022] The wing mounting base of the automatic wing deployment mechanism of the loitering vehicle is fixedly installed on the upper or lower surface of the fuselage.
[0023] A loitering device kit includes the loitering device and a transport compartment for housing the loitering device;
[0024] When the loitering device is stored in the transport cabin, the right and left wings of the loitering device's automatic wing deployment mechanism are folded onto the upper or lower surface of the loitering device's fuselage.
[0025] When the loitering drone leaves the transport capsule, the right and left wings automatically deploy.
[0026] Compared with the prior art, the beneficial effects of this utility model are:
[0027] 1. The automatic wing deployment mechanism of this utility model for a loitering munition involves setting wing mounting seats on the fuselage and a fixed shaft in the middle of the wing mounting seats. The right and left wings are vertically and rotatably mounted on the wing mounting seats. Torsion springs are installed in the first and second annular grooves on the right and left wings. By rotating the left and right wings, the wings can be rotated to be parallel to the fuselage, thereby reducing the size of the loitering munition and facilitating its storage in the transport compartment, thus reducing the space occupied during transport and storage. Furthermore, by setting a limiting mechanism, the rotation angle of the left and right wings can be limited. This allows the loitering munition, folded and stored in the transport compartment, to automatically deploy the left and right wings immediately after launch under the action of the torsion springs that have been stored during folding, maintaining a perpendicular state to the fuselage, thus enabling the loitering munition to fly stably. The aircraft folding wing technology provided by this utility model can significantly reduce the space required for aircraft parking and transportation, improve the flexibility and adaptability of aircraft, and reduce operating costs.
[0028] 2. The automatic wing deployment mechanism of this utility model for a loitering wing is achieved by setting a first hook and a second hook on the right and left wings respectively, stacking a first block and a second block on the wing mounting base, and setting a first arc-shaped clearance groove and a second arc-shaped clearance groove on the sidewalls of the right and left wings. When the right and left wings are rotated to be parallel to the fuselage, the torsion spring is in a stored state, preparing for deployment, and facilitating the storage of the loitering wing in the transport cabin, greatly reducing the storage area of the aircraft and improving the storage and portability of the aircraft. When the loitering wing is launched, the left and right wings automatically deploy under the action of the torsion spring that has been stored during folding, and the first hook and the second hook engage with the first block and the second block respectively. At the same time, the first block and the second block abut against one end of the first arc-shaped clearance groove and the second arc-shaped clearance groove respectively. The two work together to lock the wing deployment mechanism, preventing the wings from continuing to rotate, making the wings more stable and reliable after deployment, and enabling the aircraft to meet the flight requirements. Attached Figure Description
[0029] Figure 1 This is a cross-sectional structural schematic diagram of the automatic wing deployment mechanism for the loitering drone provided by this utility model;
[0030] Figure 2 This is a top view schematic diagram of the automatic wing deployment mechanism for the loitering vehicle provided by this utility model;
[0031] Figure 3 This is a partial top view schematic diagram of the connection between the left wing and the wing mounting base in an embodiment of this utility model;
[0032] Figure 4 This is a partial bottom view schematic diagram of the connection between the right wing and the wing mounting base in an embodiment of this utility model;
[0033] Figure 5 This is a partial schematic diagram of the folded wings in an embodiment of this utility model;
[0034] Figure 6 This is a schematic diagram of the overall structure of the connection between the wing mounting base and the first and second locking blocks in an embodiment of this utility model. Figure 1 ;
[0035] Figure 7 This is a schematic diagram of the overall structure of the connection between the wing mounting base and the first and second locking blocks in an embodiment of this utility model. Figure 2 ;
[0036] Figure 8 This is a top view of the loitering aircraft in the wing-deployed state in an embodiment of this utility model;
[0037] Figure 9 This is a top view of the loitering wing in the folded state of an embodiment of this utility model.
[0038] Explanation of reference numerals in the attached figures:
[0039] 1. Limiting mechanism; 11. First hook; 12. Second hook; 13. First block; 14. Second block; 15. First arc-shaped clearance groove; 16. Second arc-shaped clearance groove;
[0040] 2. Wing mounting bracket; 21. Fixed shaft;
[0041] 3. Right wing; 31. First annular groove; 32. First through hole;
[0042] 4. Torsion spring;
[0043] 5. Wing limit cover;
[0044] 6. Gaskets;
[0045] 7. Graphite copper sleeve;
[0046] 8. Left wing; 81. Second annular groove; 82. First through hole;
[0047] 9. Fasteners. Detailed Implementation
[0048] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present utility model and are not intended to limit the present utility model.
[0049] like Figures 1 to 7 As shown, an automatic wing deployment mechanism for a loitering wing includes:
[0050] The wing mounting base 2 is fixedly mounted on the fuselage, and a fixed shaft 21 is provided in the middle of the wing mounting base 2;
[0051] The left wing 8 has one end rotatably mounted on the lower outer wall of the fixed shaft 21;
[0052] The right wing 3 has one end rotatably fitted onto the upper outer wall of the fixed shaft 21. The opposite surfaces of the right wing 3 and the left wing 8 near the fixed shaft 21 are respectively provided with a first annular groove 31 and a second annular groove 81. The first annular groove 31 and the second annular groove 81 are both surrounding the outside of the fixed shaft 21 and are coaxial with the fixed shaft 21. A torsion spring 4 is provided in the first annular groove 31 and the second annular groove 81. The two ends of the torsion spring 4 are respectively fixedly connected to the inner walls of the first annular groove 31 and the second annular groove 81. The torsion spring 4 has a rotational force that drives the left wing 8 and the right wing 3 to unfold.
[0053] The limiting mechanism 1 is used to limit the rotation angle of the left wing 8 and the right wing 3.
[0054] In this invention, by rotating the left and right wings to make them parallel to the fuselage, the volume of the loitering munition is reduced, making it easier to store the loitering munition in the transport cabin and reducing the space occupied during transportation and storage. Furthermore, by setting a limiting mechanism 1, the rotation angle of the left and right wings can be limited, so that the loitering munition folded and stored in the transport cabin will automatically unfold the left and right wings under the action of the torsion spring that has been stored during folding, and keep them perpendicular to the fuselage, thereby enabling the loitering munition to fly smoothly.
[0055] Optionally, the limiting mechanism 1 includes a first hook 11 and a second hook 12 respectively provided on the windward edges of the right wing 3 and the left wing 8 when they are deployed, and a first block 13 and a second block 14 respectively stacked on the wing mounting base 2.
[0056] When the right wing 3 and left wing 8 are deployed, the first hook 11 and the second hook 12 are respectively engaged with the first locking block 13 and the second locking block 14. Figure 2 As shown, the first hook 11 and the second hook 12 are respectively located on the windward edges of the right wing 3 and the left wing 8 when they are deployed, and can be located at one end close to the fixed shaft 21.
[0057] Optionally, the limiting mechanism 1 further includes a first arc-shaped clearance groove 15 and a second arc-shaped clearance groove 16. The ends of the right wing 3 and the left wing 8 near the fixed shaft 21 are both provided with arc-shaped edges, and the first arc-shaped clearance groove 15 and the second arc-shaped clearance groove 16 are respectively opened on the arc-shaped edges of the right wing 3 and the left wing 8. The first locking block 13 and the second locking block 14 move in the first arc-shaped clearance groove 15 and the second arc-shaped clearance groove 16 respectively.
[0058] When the right wing 3 and the left wing 8 are deployed, one end of the groove wall of the first arc-shaped clearance groove 15 and one end of the groove wall of the second arc-shaped clearance groove 16 abut against one side of the first locking block 13 and one side of the second locking block 14, respectively.
[0059] When the right wing 3 and the left wing 8 are folded into place, the other end of the groove wall of the first arc-shaped clearance groove 15 and the other end of the groove wall of the second arc-shaped clearance groove 16 abut against the other side of the first locking block 13 and the other side of the second locking block 14, respectively.
[0060] In this embodiment, at the moment the loitering pod is launched and detaches from the transport capsule, the left and right wings automatically unfold under the action of the torsion spring 4, which has been charged during folding. The first hook 11 and the second hook 12 then engage with the first locking block 13 and the second locking block 14, respectively. Simultaneously, the first locking block 13 and the second locking block 14 abut against one end of the first arc-shaped clearance groove 15 and the second arc-shaped clearance groove 16, respectively. Together, they lock the wing deployment mechanism, preventing further wing rotation and ensuring greater stability and reliability after wing deployment, allowing the aircraft to meet flight requirements. Specifically, in conjunction with... Figure 2 , Figure 6 and Figure 7 As shown, with the left and right wings deployed, the second hook 12 of the left wing 8 firmly grips the 2d surface, and the inner wall of the second arc-shaped clearance groove 16 on the left wing 8 near the second hook 12 rests against the 2e surface to ensure that the left wing 8 is deployed and fixed; the first hook 11 on the right wing 3 firmly grips the 2b surface, and the inner wall of the first arc-shaped clearance groove 15 on the right wing 3 near the first hook 11 rests against the 2c surface to ensure that the right wing 3 is deployed and fixed, thereby enabling the left wing 8 and the right wing 3 to reach the deployed flight state and lock together.
[0061] like Figure 5 The diagram shows the wings folded inside the transport compartment, while torsion spring 4 is in a charged state, storing potential energy for wing deployment. Combined with... Figure 5 , Figure 6 and Figure 7 As shown, when the left and right wings are folded, the inner wall of the second arc-shaped clearance groove 16 on the left wing 8, which is away from the second hook 12, rests against the 2f surface to ensure that the left wing 8 is folded in place; the inner wall of the first arc-shaped clearance groove 15 on the right wing 3, which is away from the first hook 11, rests against the 2a surface to ensure that the right wing 3 is folded in place. This can prevent the left and right wings from being over-folded and ensure that they can be successfully stored in the transport cabin during loitering flight.
[0062] During the folding and unfolding process, the wing limiting cover 5 restricts the left wing 8 and the right wing 3 to the wing mounting base 2 to prevent misalignment and disintegration.
[0063] Optionally, the first hook 11 and the second hook 12 are respectively installed on the windward edges of the right wing 3 and the left wing 8 when they are deployed using fasteners 9. The fasteners 9 can be bolts, screws, rivets, or pins, etc.
[0064] Optionally, a wing limiting cover 5 is installed at the end of the fixed shaft 21 away from the wing mounting seat 2, thereby restricting the left wing 8 and the right wing 3 on the wing mounting seat 2 and the fixed shaft 21 to prevent misalignment and disintegration.
[0065] Optionally, a spacer 6 is provided between the right wing 3 and the left wing 8.
[0066] Optionally, the right wing 3 and the left wing 8 are respectively provided with a first through hole 32 and a second through hole 82. Graphite copper sleeves 7 are fixedly connected within the first through hole 32 and the second through hole 82, and the inner wall of the graphite copper sleeve 7 is rotatably connected to the fixed shaft 21. The gasket 6 and the graphite copper sleeve 7 reduce friction, and the graphite copper sleeve 7 also reduces friction with the fixed shaft 21, allowing the left wing 8 and the right wing 3 to unfold smoothly. The graphite copper sleeve 7 is fixedly connected to the first through hole 32 and the second through hole 82 (wing holes) by means of interference fit, bonding, threaded connection, and welding.
[0067] A loitering vehicle, comprising the fuselage and the loitering vehicle wing automatic deployment mechanism;
[0068] The wing mounting base of the automatic wing deployment mechanism of the loitering pod is fixedly installed on the upper or lower surface of the fuselage. For example... Figure 8 and Figure 9 As shown, both the canard and the aft wing can be equipped with the automatic deployment mechanism of the loitering wing of this application. The automatic deployment mechanism of the canard is installed on the upper surface of the front part of the fuselage, and the canard folds towards the tail of the fuselage on the upper surface of the fuselage. The automatic deployment mechanism of the aft wing is installed on the lower surface of the rear part of the fuselage, and the aft wing folds towards the nose of the fuselage on the lower surface of the fuselage.
[0069] A loitering device kit includes the loitering device and a transport compartment for housing the loitering device;
[0070] When the loitering device is stored in the transport cabin, the right and left wings of the loitering device's automatic wing deployment mechanism are folded onto the upper or lower surface of the loitering device's fuselage.
[0071] When the loitering drone leaves the transport capsule, the right and left wings automatically deploy.
[0072] The present invention has been further described above with reference to the embodiments, but the present invention is not limited to the above embodiments. Within the scope of knowledge possessed by those skilled in the art, various changes can be made without departing from the spirit of the present invention.
Claims
1. An automatic wing deployment mechanism for a loitering wing, characterized in that, It includes: A wing mounting base (2) is fixedly mounted on the fuselage, and a fixed shaft (21) is provided in the middle of the wing mounting base (2); The left wing (8) has one end rotatably fitted onto the lower outer wall of the fixed shaft (21); The right wing (3) has one end rotatably fitted onto the upper outer wall of the fixed shaft (21). The right wing (3) and the left wing (8) have a first annular groove (31) and a second annular groove (81) respectively opened on the opposite side of the end near the fixed shaft (21). The first annular groove (31) and the second annular groove (81) are both around the outside of the fixed shaft (21) and coaxial with the fixed shaft (21). The first annular groove (31) and the second annular groove (81) are provided with torsion springs (4). The two ends of the torsion springs (4) are fixedly connected to the inner walls of the first annular grooves (31) and the second annular grooves (81) respectively. The torsion springs (4) have a rotational force that drives the left wing (8) and the right wing (3) to unfold. A limiting mechanism (1) is used to limit the rotation angle of the left wing (8) and the right wing (3).
2. The automatic wing deployment mechanism for a loitering pod according to claim 1, characterized in that: The limiting mechanism (1) includes a first hook (11) and a second hook (12) respectively provided on the windward edges of the right wing (3) and the left wing (8) when they are deployed, and a first block (13) and a second block (14) respectively stacked on the wing mounting base (2); When the right wing (3) and left wing (8) are deployed, the first hook (11) and the second hook (12) are respectively connected to the first block (13) and the second block (14).
3. The automatic wing deployment mechanism for a loitering pod according to claim 2, characterized in that: The limiting mechanism (1) further includes a first arc-shaped clearance groove (15) and a second arc-shaped clearance groove (16). The ends of the right wing (3) and the left wing (8) near the fixed shaft (21) are both set as arc-shaped edges, and the first arc-shaped clearance groove (15) and the second arc-shaped clearance groove (16) are respectively opened on the arc-shaped edges of the right wing (3) and the left wing (8). The first locking block (13) and the second locking block (14) move in the first arc-shaped clearance groove (15) and the second arc-shaped clearance groove (16) respectively. When the right wing (3) and left wing (8) are deployed, one end of the groove wall of the first arc-shaped relief groove (15) and one end of the groove wall of the second arc-shaped relief groove (16) abut against one side of the first locking block (13) and one side of the second locking block (14), respectively. When the right wing (3) and left wing (8) are folded into place, the other end of the groove wall of the first arc-shaped relief groove (15) and the other end of the groove wall of the second arc-shaped relief groove (16) abut against the other side of the first locking block (13) and the other side of the second locking block (14), respectively.
4. The automatic wing deployment mechanism for a loitering pod according to claim 2, characterized in that, The first hook (11) and the second hook (12) are respectively installed on the windward edges of the right wing (3) and the left wing (8) when they are deployed by fasteners (9).
5. The automatic wing deployment mechanism for a loitering pod according to any one of claims 1-4, characterized in that, A wing limiting cover (5) is installed at the end of the fixed shaft (21) away from the wing mounting seat (2).
6. The automatic wing deployment mechanism for a loitering pod according to any one of claims 1-4, characterized in that, A gasket (6) is provided between the right wing (3) and the left wing (8).
7. The automatic wing deployment mechanism for a loitering pod according to claim 6, characterized in that, The right wing (3) and the left wing (8) are respectively provided with a first through hole (32) and a second through hole (82). Graphite copper sleeves (7) are fixedly connected in the first through hole (32) and the second through hole (82). The inner wall of the graphite copper sleeves (7) is rotatably connected to the fixed shaft (21).
8. A loitering rovers, characterized in that: Includes the fuselage and the automatic wing deployment mechanism for the loitering wing as described in any one of claims 1-7; The wing mounting base of the automatic wing deployment mechanism of the loitering vehicle is fixedly installed on the upper or lower surface of the fuselage.
9. A loitering pod kit, characterized in that: Includes the loitering vehicle as described in claim 8 and a transport compartment for housing the loitering vehicle; When the loitering device is stored in the transport cabin, the right and left wings of the loitering device's automatic wing deployment mechanism are folded onto the upper or lower surface of the loitering device's fuselage. When the loitering drone leaves the transport capsule, the right and left wings automatically deploy.