Secondary folding wing synchronous unfolding reliable locking mechanism

Abstract

The invention discloses a synchronous unfolding and reliable locking mechanism for secondary folding wings, and relates to the technical field of folding wings, the synchronous unfolding and reliable locking mechanism comprises a cabin body, a plurality of brackets are uniformly arranged on the inner wall of the cabin body, a plurality of strip-shaped openings are uniformly formed in the cabin body, and the brackets are provided with folding wing assemblies; the folding wing assembly comprises a connecting plate rotationally arranged on the support through a rotating shaft, one end of the connecting plate movably penetrates through the outside of the strip-shaped opening and is fixedly connected with a static force arm, the static force arm is rotationally provided with a power arm through a pin shaft, the power arm is fixedly connected with a wing, the static force arm is further provided with a fixing piece, and the end of the connecting plate is provided with a locking assembly; the two-stage rotating folding design of the connecting plate, the static force arm and the power arm is adopted, the automatic reset function of the torsional spring and the reset spring is combined, the wings can be folded twice in sequence and stored in the cabin body, compared with a traditional single-stage folding structure, the occupied space of the wings during storage is greatly reduced, and the wings are convenient to transport, store and carry on a carrier with limited space.

Description

Technical Field

[0001] This invention relates to the field of folding wing technology, and in particular to a reliable locking mechanism for the synchronous deployment of a secondary folding wing. Background Technology

[0002] In the fields of aerospace, drones, and other equipment, folding wings have become a key structural element in the design of various aircraft due to their ability to significantly reduce the space occupied during equipment storage, transportation, and launch, and to improve carrier efficiency. Especially for equipment that requires multiple wings to work together, the synchronicity of wing deployment, the reliability of locking, and the ease of folding directly affect the equipment's launch success rate, flight stability, and reusability. Therefore, stringent requirements are placed on the deployment and locking mechanisms of folding wings.

[0003] Currently, most existing folding wing mechanisms lack a unified guidance and drive coordination design. During deployment, multiple wings are prone to issues such as delayed action and angular deviations, leading to uneven stress on the wings. This not only affects the aerodynamic performance of the equipment but may also cause mechanism jamming or structural damage due to localized stress concentration, making it difficult to meet the precision requirements of multi-wing collaborative operation. Furthermore, existing locking structures mostly employ a single buckle or pin design, lacking a dual protection mechanism. During flight, under complex conditions such as airflow impact and vibration, locking components are prone to loosening or disengagement, resulting in unstable wing deployment and seriously threatening flight safety. Summary of the Invention

[0004] In order to solve the problems in the background art, the present invention proposes a reliable locking mechanism for the synchronous deployment of a two-folding wing.

[0005] To achieve the above objectives, the present invention adopts the following technical solution: A reliable locking mechanism for the synchronous deployment of a two-folding wing includes a cabin and further includes: The brackets are evenly arranged on the inner wall of the cabin, and the cabin has multiple strip-shaped openings evenly arranged on it. The brackets are equipped with folding wing assemblies. The folding wing assembly includes a connecting plate rotatably mounted on a bracket via a pivot, and one end of the connecting plate movably passes through the strip opening and is fixedly connected to a static arm. A power arm is rotatably mounted on the static arm via a pin, and an wing is fixedly connected to the power arm. A torsion spring is sleeved on the outer wall of the pin. The static arm is also equipped with a fixing component for fixing the wing; The end of the connecting plate is provided with a locking component for fixing the static arm.

[0006] Preferably, the fixing member includes a hinge seat disposed on the static arm, a buckle is provided in the hinge seat via a hinge pin, and a compression spring is provided between the buckle and the hinge seat; The wing is equipped with a latch that engages with the buckle.

[0007] Preferably, the locking assembly includes a base disposed on the outer wall of the connecting plate, the base having a circular cavity, a spring pin slidably disposed within the circular cavity, and a plug slidably disposed at the bottom of the spring pin, the plug being disposed within the circular cavity.

[0008] Preferably, the spring pin includes a fixed rod slidably disposed in a circular cavity and an annular limiting plate disposed on the outer wall of the fixed rod, and a compression spring is sleeved on the outer wall of the fixed rod between the annular limiting plate and the plug; The two ends of the fixing rod respectively movably pass through the circular cavity and the plug, and the end of the connecting plate is provided with an insertion hole to match the fixing rod.

[0009] Preferably, the end of the fixing rod has an arc-shaped chamfer, and the position on the connecting plate that contacts the fixing rod is an inclined surface.

[0010] Preferably, both the connecting plate and the bracket are provided with circular rods, and a return spring is provided between the circular rods.

[0011] In summary, due to the adoption of the above technical solution, the beneficial effects of the present invention are: 1. This invention adopts a two-stage rotational folding design of connecting plate, static arm and dynamic arm, combined with the automatic reset function of torsion spring and return spring. The wing can be folded twice in sequence and stored in the cabin. Compared with the traditional single-stage folding structure, it greatly reduces the space occupied when the wing is stored, making the overall size of the equipment more compact, which is convenient for transportation, storage and mounting on space-constrained carriers. 2. This invention employs a dual locking mechanism consisting of a fixing component and a locking assembly. The fixing component secures the wing after its initial deployment through the engagement of a buckle and a claw, along with the preload of a compression spring. The locking assembly utilizes a compression spring to drive a spring pin in precise engagement with a socket, achieving a secondary locking of the connecting plate. This dual locking structure effectively prevents the wing from loosening or folding due to external forces such as vibration or airflow impact during deployment, significantly improving the reliability and operational safety of the mechanism under complex working conditions.

[0012] 3. This invention provides automatic driving force for the secondary folding of the wing through a torsion spring and provides elastic potential energy for the resetting of the connecting plate through a return spring. No additional complex driving device is required. The wing can be automatically folded simply by unlocking the locking component and pressing the buckle. During the unfolding process, the spring preload and mechanical structure work together to simplify the operation steps, reduce the intensity and difficulty of manual operation, and improve the practicality and ease of use of the mechanism. Attached Figure Description

[0013] Figure 1 A three-dimensional schematic diagram of a folded state provided according to an embodiment of the present invention is shown; Figure 2 A partial structural schematic diagram from a frontal view is shown according to an embodiment of the present invention; Figure 3 A schematic diagram of the cabin structure from a top-down perspective, provided according to an embodiment of the present invention, is shown; Figure 4 A schematic diagram of the structure of a folding wing assembly provided according to an embodiment of the present invention is shown; Figure 5 A schematic diagram of the structure of a locking component provided according to an embodiment of the present invention is shown.

[0014] Legend: 1. Folding wing assembly; 11. Wing; 12. Pin; 13. Hinge pin; 14. Buckle; 15. Compression spring; 16. Connecting plate; 17. Torsion spring; 18. Static arm; 19. Dynamic arm; 2. Rotary shaft; 3. Bracket; 4. Circular rod; 5. Cabin; 6. Return spring; 7. Locking assembly; 71. Base; 72. Spring pin; 73. Compression spring; 74. Plug; 75. Chamfered corner; 76. Circular cavity; 77. Annular limiting plate; 8. Hinge seat; 9. Strip opening. Detailed Implementation

[0015] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0016] Please see Figure 1 - Figure 5 The present invention provides a technical solution: A reliable locking mechanism for the synchronous deployment of a double-folding wing includes a cabin 5 and further includes: Multiple brackets 3 are evenly fixed on the inner wall of the cabin 5 by bolts for the installation of the folding wing assembly 1; multiple strip openings 9 are evenly opened on the cabin 5 to facilitate the rotation of the connecting plate 16, thereby facilitating the folding of the wing 11; the brackets 3 are equipped with the folding wing assembly 1. The folding wing assembly 1 includes a connecting plate 16 rotatably mounted on a bracket 3 via a pivot 2. One end of the connecting plate 16 moves through the strip opening 9 and is fixedly connected to a static arm 18. A power arm 19 is rotatably mounted on the static arm 18 via a pin 12. An wing 11 is fixedly mounted on the power arm 19. A torsion spring 17 is sleeved on the outer wall of the pin 12. The use of the torsion spring 17 facilitates the automatic rotation of the wing 11, enabling the automatic folding of the wing 11 without the need for an additional complex drive device. The static arm 18 is also equipped with a fastener for fixing the wing 11. The fastener makes it easy to fix the wing 11 and prevent the wing 11 from folding again after it is deployed, thus facilitating the deployment of the wing 11.

[0017] The end of the connecting plate 16 is provided with a locking component 7 for fixing the static arm 18. The use of the locking component 7 makes it easy to fix the connecting plate 16, preventing the connecting plate 16 from folding again after unfolding, which is beneficial to the unfolding of the wing 11. The mechanism features a dual locking system consisting of a fixing component and a locking assembly 7. The fixing component secures the wing 11 after it is deployed by means of a snap-fit ​​between the buckle 14 and the claw, and the preload of the compression spring 15. The locking assembly 7 uses a compression spring 73 to drive the spring pin 72 to precisely engage with the insertion hole, thus completing the secondary locking of the connecting plate 16. This dual locking structure effectively prevents the wing 11 from loosening or folding due to external forces such as vibration and airflow impact when it is deployed, significantly improving the reliability and operational safety of the mechanism under complex working conditions.

[0018] Through the two-stage rotational folding design of the connecting plate 16, static arm 18, and dynamic arm 19, combined with the automatic reset function of the torsion spring 17 and the return spring 6, the wing 11 can be folded twice in sequence and stored in the cabin. Compared with the traditional single-stage folding structure, the space occupied by the wing 11 when it is stored is greatly reduced, making the overall size of the equipment more compact and convenient for transportation, storage and mounting on space-constrained carriers.

[0019] In this invention, the fixing component includes a hinge seat 8 disposed on the static arm 18. A buckle 14 is rotatably disposed inside the hinge seat 8 via a hinge pin 13. A compression spring 15 is disposed between the buckle 14 and the hinge seat 8. One end of the compression spring 15 is fixedly connected to the bottom surface of the buckle 14, and the other end is fixedly connected to the bottom surface inside the hinge seat 8. This is used for the automatic reset of the buckle 14, thereby allowing the buckle 14 to engage with the claws on the wing 11, thereby fixing the wing 11. The wing 11 is equipped with a claw that engages with the latch 14.

[0020] In this invention, the locking component 7 includes a base 71 disposed on the outer wall of the connecting plate 16. A circular cavity 76 is formed on the base 71. A spring pin 72 is slidably disposed in the circular cavity 76. A plug 74 is slidably disposed at the bottom of the spring pin 72. An external thread is formed on the outer wall of the plug 74. An internal thread is formed on the inner wall of the circular cavity 76 to cooperate with the external thread. Through the mutual cooperation of the internal thread and the external thread, the plug 74 is fixed in the circular cavity 76, thereby installing the spring pin 72 in the circular cavity 76. The plug 74 is disposed in the circular cavity 76.

[0021] In this invention, the spring pin 72 includes a fixed rod slidably disposed in the circular cavity 76 and an annular limiting plate 77 disposed on the outer wall of the fixed rod. The use of the annular limiting plate 77 facilitates the compression of the compression spring 73, thereby realizing the movement of the fixed rod and further facilitating the fixing of the connecting plate 16. The compression spring 73 is sleeved on the outer wall of the fixed rod between the annular limiting plate 77 and the plug 74. The use of the compression spring 73 facilitates the compression of the annular limiting plate 77, thereby facilitating the insertion of the fixed rod into the insertion hole on the connecting plate 16 and realizing the fixing of the connecting plate 16. The two ends of the fixing rod movably pass through the circular cavity 76 and the plug 74, respectively. The end of the connecting plate 16 is provided with an insertion hole to match the fixing rod. Through the cooperation of the fixing rod, the compression spring 73 and the plug 74, the connecting plate 16 can be automatically fixed.

[0022] In this invention, the end of the fixing rod is provided with an arc-shaped chamfer 75, and the position on the connecting plate 16 that contacts the fixing rod is an inclined surface. By setting the arc-shaped chamfer 75 and the inclined surface on the connecting plate 16, it is easy for the connecting plate 16 to squeeze the fixing rod into the circular cavity 76, and then, under the action of the compression spring 73, the fixing rod is inserted into the insertion hole on the connecting plate 16, thereby fixing the connecting plate 16.

[0023] In this invention, both the connecting plate 16 and the bracket 3 are provided with circular rods 4, and a return spring 6 is provided between the circular rods 4. Each circular rod 4 is provided with two return springs 6 for automatic folding of the connecting plate 16.

[0024] Working principle: When the wing 11 needs to be deployed, the wing 11 is first rotated so that it rotates toward the buckle 14. Then, the buckle 14 engages with the claw on the wing 11, realizing the first deployment of the wing 11. Then, the static arm 18 is rotated, which drives the connecting plate 16 to rotate. When the connecting plate 16 contacts the fixing rod, it pushes the fixing rod into the circular cavity 76. After the connecting plate 16 rotates 90°, the fixing rod coincides with the insertion hole on the connecting plate 16. Under the action of the compression spring 73, the fixing rod is inserted into the insertion hole, thus fixing the connecting plate 16 and fixing the wing 11, further realizing the second deployment of the wing 11. When the connecting plate 16 rotates 90°, the return spring 6 is compressed to store energy, thus facilitating the automatic reset of the connecting plate 16; then, each wing 11 is deployed according to the above operation method. When the wing 11 needs to be folded, the fixing rod is pulled outward to disengage the fixing rod from the insertion hole on the connecting plate 16, thereby releasing the fixing of the connecting plate 16. Then, under the action of the return spring 6, the connecting plate 16 is automatically reset, thereby causing the connecting plate 16 to rotate 90° around the pivot 2 into the cabin 5, realizing the first folding of the wing 11. Then press the buckle 14 to disengage the buckle 14 from the claw on the wing 11. Then, under the action of the torsion spring 17, the wing 11 rotates around the pin 12, thereby realizing the secondary folding of the wing 11.

[0025] The above description of the embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A reliable locking mechanism for the synchronous deployment of a double-folding wing, comprising a cabin (5), characterized in that, Also includes: The bracket (3) is evenly arranged on the inner wall of the cabin (5). The cabin (5) is evenly provided with multiple strip openings (9). The bracket (3) is provided with a folding wing assembly (1). The folding wing assembly (1) includes a connecting plate (16) rotatably mounted on a bracket (3) via a pivot (2), and one end of the connecting plate (16) movably passes through the strip opening (9) and is fixedly connected to a static arm (18). A power arm (19) is rotatably mounted on the static arm (18) via a pin (12), and an wing (11) is fixedly mounted on the power arm (19). A torsion spring (17) is sleeved on the outer wall of the pin (12). The static arm (18) is also provided with a fastener for fixing the wing (11); The end of the connecting plate (16) is provided with a locking component (7) for fixing the static arm (18).

2. The reliable locking mechanism for synchronous deployment of a double-folding wing according to claim 1, characterized in that, The fastener includes a hinge seat (8) mounted on the static arm (18), and a buckle (14) is provided inside the hinge seat (8) via a hinge pin (13). A compression spring (15) is provided between the buckle (14) and the hinge seat (8). The wing (11) is provided with a claw that cooperates with the buckle (14).

3. The reliable locking mechanism for synchronous deployment of a secondary folding wing according to claim 1, characterized in that, The locking assembly (7) includes a base (71) disposed on the outer wall of the connecting plate (16), a circular cavity (76) is provided on the base (71), a spring pin (72) is slidably disposed in the circular cavity (76), a plug (74) is slidably disposed at the bottom of the spring pin (72), and the plug (74) is disposed in the circular cavity (76).

4. The reliable locking mechanism for synchronous deployment of a double-folding wing according to claim 3, characterized in that, The spring pin (72) includes a fixed rod that is slidably disposed in the circular cavity (76) and an annular limiting plate (77) disposed on the outer wall of the fixed rod. A compression spring (73) is sleeved on the outer wall of the fixed rod between the annular limiting plate (77) and the plug (74). The two ends of the fixing rod respectively movably pass through the circular cavity (76) and the plug (74), and the end of the connecting plate (16) is provided with an insertion hole to match the fixing rod.

5. The reliable locking mechanism for synchronous deployment of a double-folding wing according to claim 4, characterized in that, The end of the fixed rod is provided with an arc-shaped chamfer (75), and the position on the connecting plate (16) that contacts the fixed rod is an inclined surface.

6. The reliable locking mechanism for synchronous deployment of a double-folding wing according to claim 1, characterized in that, Both the connecting plate (16) and the bracket (3) are provided with circular rods (4), and a return spring (6) is provided between the circular rods (4).

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