Folding wing and rudder unfolding and locking mechanism

Abstract

The utility model discloses a folding wing and rudder unfolding and locking mechanism which comprises a connecting handle, an elastic torsion spring and a rotating shaft. A connector is fixedly connected to one side of the connecting handle, and a locking head and a connector are arranged on the two sides of the bottom of the folding wing or the folding rudder respectively; the two ends of the rotating shaft are movably connected with the connector and the locking head respectively, the connecting handle is connected with the rotating shaft, a mounting groove is formed in the connecting handle, an upper locking groove is formed in one side of the connecting handle, a locking protrusion is arranged on the locking head, and the locking protrusion is matched with the upper locking groove; the elastic torsional spring is arranged in the mounting groove, the two ends of the elastic torsional spring are connected with the connecting handle and the connector respectively, and the elastic torsional spring is used for driving the folding wing or the folding rudder to rotate and reset and enabling the folding wing or the folding rudder to move and reset in the axial direction of the rotating shaft. Wherein the elastic torsional spring can provide elastic force and torsional force, the folding wing and the rudder are assisted to overcome interference to complete unfolding under external interference such as vibration and impact, and the locking groove and the locking protrusion are matched to form a reliable locking mechanism, so that the overall unfolding stability can be enhanced.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft structural design technology, specifically a folding wing and rudder deployment locking mechanism. Background Technology

[0002] In the fields of modern aerospace and missile technology, the application of folding wings and folding rudders is becoming increasingly widespread. As equipment develops towards miniaturization and multi-functionality, higher requirements are placed on the deployment and locking mechanisms of folding wings and rudders.

[0003] Traditional folding wing and rudder deployment and locking mechanisms have many limitations. From a structural design perspective, some mechanisms are overly complex, leading to high manufacturing and assembly difficulties and costs. Furthermore, maintaining these complex structures during long-term use presents challenges. In terms of reliability, some mechanisms are prone to incomplete deployment when subjected to external disturbances such as vibration or impact, severely impacting flight safety and mission performance.

[0004] Patent application CN202311533272.3 discloses a rotation locking structure for an aircraft folding rudder; the structure includes a rotation mechanism and a locking mechanism; the rotation mechanism includes a rotation shaft and a torsion spring; the locking mechanism includes an elastic locking element and a locking shaft. This rotation locking structure, with its torsion spring and spring, both connected to locking pins, is prone to incomplete unfolding when subjected to external disturbances such as vibration or impact. Utility Model Content

[0005] The purpose of this invention is to provide a folding wing and rudder deployment locking mechanism to solve the following technical problems mentioned in the background art:

[0006] Existing deployment and locking mechanisms are prone to failure to deploy properly when subjected to external disturbances such as vibration and impact.

[0007] To solve the above-mentioned technical problems, the technical solution adopted by this utility model is as follows:

[0008] A folding wing and rudder deployment locking mechanism includes a connecting handle, a torsion spring, and a rotating shaft. Locking heads and connecting heads are respectively provided on both sides of the bottom of the folding wing or rudder. The two ends of the rotating shaft are movably connected to the connecting heads and locking heads, respectively. The connecting handle is connected to the rotating shaft, and a mounting groove is provided on the connecting handle. An upper locking groove is provided on one side of the connecting handle. A locking protrusion is provided on the locking head, and the locking protrusion cooperates with the upper locking groove. The torsion spring is disposed in the mounting groove, and its two ends are respectively connected to the connecting handle and the connecting head. The torsion spring is used to drive the folding wing or rudder to rotate and reset, and to cause the folding wing or rudder to move and reset along the axial direction of the rotating shaft.

[0009] Furthermore, a lower locking groove is provided on the side of the connecting handle near the connector head, and a locking block is provided on the connector head, with the lower locking groove cooperating with the locking block.

[0010] Furthermore, both the upper and lower locking slots are square slots.

[0011] Furthermore, the upper and lower locking slots are arranged in a cross shape.

[0012] Furthermore, ventilation holes are provided on the locking head.

[0013] Furthermore, a limit stop is provided on the side of the rotating shaft near the connector, and a limit hole is provided on the side of the connecting handle, with a limit pin installed in the limit hole.

[0014] Furthermore, a limiting stage is fixedly attached to the side of the connecting handle near the connecting head.

[0015] Furthermore, the torsion spring is made of high-strength alloy steel, and its surface is nitrided.

[0016] Furthermore, the mating surfaces of the locking block and the lower locking groove are both provided with a wear-resistant coating, which is a tungsten carbide coating with a thickness of 0.05-0.1 mm.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] The spring-torsion spring of this invention provides elasticity and torsional force, helping the folding wing and rudder overcome external interference such as vibration and impact to complete deployment, reducing the possibility of incomplete deployment. The locking groove and locking protrusion cooperate to form a reliable locking mechanism, which can maintain the deployed state under normal external interference, avoiding displacement due to interference and thus enhancing the overall deployment stability. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the overall structure of the present invention in use;

[0020] Figure 2 This is a partial structural diagram of the present invention in use;

[0021] Figure 3 This is a schematic diagram of the overall structure of this utility model;

[0022] Figure 4 This is a cross-sectional view of the present invention in use.

[0023] The markings in the diagram are: 1-connecting handle, 2-locking protrusion, 3-vent hole, 4-locking head, 5-torsion spring, 6-connecting head, 7-rotating shaft, 8-limit stop, 9-upper locking groove, 10-limiting platform, 11-lower locking groove, 12-installation groove, 13-limiting hole. Detailed Implementation

[0024] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0025] Example:

[0026] A folding wing and rudder deployment locking mechanism includes a connecting handle 1, a torsion spring 5, and a rotating shaft 7. Locking heads 4 and connecting heads 6 are respectively provided on both sides of the bottom of the folding wing or rudder. The two ends of the rotating shaft 7 are movably connected to the connecting heads 6 and locking heads 4, respectively. The connecting handle 1 is connected to the rotating shaft 7. A mounting groove 12 is provided on the connecting handle 1, and an upper locking groove 9 is provided on one side of the connecting handle 1. A locking protrusion 2 is provided on the locking head 4, and the locking protrusion 2 cooperates with the upper locking groove. The torsion spring 5 is disposed within the mounting groove 12, and its two ends are respectively connected to the connecting handle 1 and connecting heads 6. The torsion spring 5 is used to drive the folding wing or rudder to rotate and reset, and to move the folding wing or rudder along the axial direction of the rotating shaft 7 to reset.

[0027] The connecting handle 1 is connected to the locking head 4 and the connecting head 6 via the rotating shaft 7, which is located at the bottom of the folding wing or folding rudder. The torsion spring 5 is used to rotate and reset the folding wing or folding rudder, and to move it axially along the rotating shaft 7. Specifically, during use, when the folding rudder or folding wing is folded, it moves forward first, causing the locking protrusion 2 to disengage from the upper locking groove 9. Simultaneously, the torsion spring generates locking force and torsional force; the folding rudder or folding wing is within the envelope after folding. When unfolded, the folding rudder or folding wing disengages from the envelope and automatically unfolds under the action of the torsion spring. Simultaneously, the torsion spring 5 pushes the folding rudder or folding wing to move and reset, causing the upper locking groove to engage with the locking protrusion 2. The mating part between the locking groove and the locking protrusion 2 bears the load during flight. Because the mechanism is equipped with the torsion spring 5, whose two ends are connected to the connecting handle 1 and the connecting head 6 respectively, it can not only rotate and reset the folding wing or folding rudder, but also move it axially along the rotating shaft 7. During deployment, even under external interference such as vibration and impact, the elastic and torsional forces provided by the torsion spring 5 continue to act, pushing the folding wing or rudder to overcome the interference and move towards the correct deployment position, ensuring it is fully deployed as much as possible and reducing the possibility of incomplete deployment due to interference. Secondly, the connecting handle 1 is equipped with an upper locking groove 9, and the locking head 4 is equipped with a locking protrusion 2. These two components cooperate with each other, and during deployment, the torsion spring 5 pushes the folding wing or rudder to move and reset, causing the upper locking groove and locking protrusion 2 to engage. This groove and protrusion engagement provides a stable locking mechanism for the deployed state of the folding wing or rudder. When facing vibration and impact, as long as the external interference force does not exceed the limit that the groove and protrusion engagement can withstand, the folding wing or rudder will remain in the deployed position, preventing loosening or displacement due to interference, thus avoiding incomplete deployment.

[0028] In a preferred embodiment, a lower locking groove 11 is provided on the side of the connecting handle 1 near the connecting head 6, and a locking block is provided on the connecting head 6. The lower locking groove 11 cooperates with the locking block. During the resetting of the folding rudder or folding wing, the lower locking groove 11 can also cooperate with the locking block. This design further enhances the stability of the connection between the folding wing or folding rudder and the connecting handle 1. During the unfolding of the folding wing and rudder and subsequent flight, it can better prevent unnecessary shaking or displacement. It also assists the locking protrusion 2 in cooperating with the upper locking groove 9 to jointly bear the load during flight and ensure the reliable operation of the entire structure.

[0029] In a preferred embodiment, both the upper locking groove 9 and the lower locking groove 11 are square grooves. For the upper locking groove 9, the square structure makes the constraint in all directions more stable and clear when the locking protrusion 2 is engaged with it, which can effectively prevent the locking protrusion 2 from lateral displacement or shaking due to complex external forces during flight, ensuring the stability of the folding wing or folding rudder in the deployed and locked state, so that it can reliably withstand various loads during flight. The lower locking groove 11 also has the same advantage.

[0030] In a preferred embodiment, the upper locking groove 9 and the lower locking groove 11 are arranged in a cross shape. This cross-shaped arrangement limits and fixes the folding wing or folding rudder from two mutually perpendicular directions, greatly enhancing the stability of the overall structure. This ensures that the folding wing or folding rudder can be firmly fixed in the accurate position under different stress conditions, more reliably withstand multi-directional loads during flight, and further guarantee the stability and reliability of the deployment locking mechanism.

[0031] In a preferred embodiment, the locking head 4 is provided with a vent hole 3. The vent hole 3 is connected to the pivot hole 7 on the locking head 4 for mounting the pivot 7, thereby balancing the pressure between the pivot hole 7 and the outside environment, and facilitating the prevention of obstruction when the folding rudder or folding wing moves axially.

[0032] In a preferred embodiment, a limiting stop 8 is provided on the side of the rotating shaft 7 near the connector 6, and a limiting hole 13 is provided on one side of the connecting handle 1, with a limiting pin disposed in the limiting hole 13. Through the design of the limiting stop 8, the rotating shaft 7 can be connected to the connecting handle 1 via the pin.

[0033] In a preferred embodiment, a limiting platform 10 is also fixedly attached to the side of the connecting handle 1 near the connecting head 6. The limiting platform 10 can contact the connecting head 6 and is used to limit the axial movement range of the folding wing or folding rudder. By contacting the connecting head 6, the limiting platform 10 clearly limits the movement range of the folding wing or folding rudder in the axial direction of the rotating shaft 7, preventing excessive axial movement during deployment, folding, and flight, ensuring that its movement is always within a reasonable and controllable range, thereby ensuring the stable and reliable operation of the entire mechanism and improving the safety and stability of the overall structure.

[0034] In a preferred embodiment, the torsion spring 5 is made of high-strength alloy steel with a nitrided surface. This design improves its fatigue resistance and corrosion resistance, extends the service life of the torsion spring 5, and allows it to maintain stable elasticity and torsional force after undergoing multiple deployment and reset actions.

[0035] In a preferred embodiment, both the mating surfaces of the locking block and the lower locking groove 11 are provided with a wear-resistant coating, which is a tungsten carbide coating with a thickness of 0.05-0.1 mm. This design reduces wear between the locking block and the lower locking groove 11 during folding and unfolding, ensuring the accuracy and stability of their engagement, thereby further enhancing the stability of the connection between the folding wing or folding rudder and the connecting handle 1.

[0036] In a preferred embodiment, an auxiliary support structure is provided between the connecting handle 1 and the folding wing or folding rudder. The auxiliary support structure includes a support arm mounted on the connecting handle 1 and a support groove located at the bottom of the folding wing or folding rudder. One end of the support arm is hinged to the connecting handle 1, and the other end can be inserted into the support groove. After the folding wing or folding rudder is deployed, the support arm automatically inserts into the support groove, providing additional support for the folding wing or folding rudder, sharing some of the load during flight, reducing the stress on the mating parts of the locking protrusion 2 and the upper locking groove 9, and the locking block and the lower locking groove 11, thereby improving the load-bearing capacity and stability of the entire mechanism. During folding, the support arm can rotate around the hinge point without affecting the folding process.

[0037] In the description of this utility model, it should be understood that the terms "coaxial", "bottom", "one end", "top", "middle", "other end", "upper", "side", "top", "inner", "front", "center", "both ends", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0038] In this utility model, unless otherwise explicitly specified and limited, the terms "installation," "setting," "connection," "fixing," "screw connection," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Unless otherwise explicitly limited, those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0039] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A folding wing and rudder deployment locking mechanism, characterized in that: Includes a connecting handle (1), a torsion spring (5), and a pivot (7); a locking head (4) and a connecting head (6) are respectively provided on both sides of the bottom of the folding wing or folding rudder; The two ends of the rotating shaft (7) are movably connected to the connector (6) and the locking head (4) respectively. The connecting handle (1) is connected to the rotating shaft (7). The connecting handle (1) is provided with an installation groove (12). The connecting handle (1) is provided with an upper locking groove (9) on one side. The locking head (4) is provided with a locking protrusion (2). The locking protrusion (2) cooperates with the upper locking groove. The spring torsion spring (5) is set in the mounting groove (12). The two ends of the spring torsion spring (5) are connected to the connecting handle (1) and the connecting head (6) respectively. The spring torsion spring (5) is used to drive the folding wing or folding rudder to rotate and reset, and to make the folding wing or folding rudder move and reset along the axis of the rotating shaft (7).

2. The folding wing and rudder deployment locking mechanism according to claim 1, characterized in that: A lower locking groove (11) is provided on the side of the connecting handle (1) near the connecting head (6), and a locking block is provided on the connecting head (6). The lower locking groove (11) cooperates with the locking block.

3. The folding wing and rudder deployment locking mechanism according to claim 2, characterized in that: Both the upper locking groove (9) and the lower locking groove (11) are square grooves.

4. The folding wing and rudder deployment locking mechanism according to claim 2, characterized in that: The upper locking groove (9) and the lower locking groove (11) are arranged in a cross shape.

5. The folding wing and rudder deployment locking mechanism according to claim 1, characterized in that: The locking head (4) is provided with a vent hole (3).

6. The folding wing and rudder deployment locking mechanism according to claim 1, characterized in that: A limit stop (8) is provided on the side of the rotating shaft (7) near the connector (6), and a limit hole (13) is provided on one side of the connecting handle (1), with a limit pin provided in the limit hole (13).

7. The folding wing and rudder deployment locking mechanism according to claim 1, characterized in that: A limiting stage (10) is also fixed to the side of the connecting handle (1) near the connecting head (6).

8. The folding wing and rudder deployment locking mechanism according to claim 1, characterized in that: The spring (5) is made of high-strength alloy steel.

9. A folding wing and rudder deployment locking mechanism according to claim 1, characterized in that: The mating surfaces of the locking block and the lower locking groove (11) are both provided with a wear-resistant coating, which is a tungsten carbide coating with a thickness of 0.05-0.1mm.

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