Tightening type rudder wing mechanism

Abstract

The utility model discloses a tending type rudder wing mechanism which comprises a movable rudder surface and a fixed rudder surface, the movable rudder surface and the fixed rudder surface are rotationally connected through a connecting shaft, a limiting part is arranged between the movable rudder surface and the fixed rudder surface and comprises a first clamping block, a second clamping block and a torsion spring, the first clamping block is arranged at the bottom of the movable rudder surface, and the second clamping block is arranged at the bottom of the fixed rudder surface. The first clamping block is arranged on the top of the fixed control surface, the second clamping block is arranged on the top of the fixed control surface, the first clamping block is fixedly connected with the connecting shaft through the fixing pin, the second clamping block is rotationally connected with the connecting shaft, a groove is formed in the first clamping block, convex teeth are arranged on the second clamping block and matched with the groove, one end of the torsional spring is connected with the fixed control surface, and the other end of the torsional spring is connected with the connecting shaft. And the other end is connected with the connecting shaft. A rotating shaft is arranged at the bottom of the fixed control surface. The problems that an existing folding wing is complex in control structure and high in cost are solved.

Description

Technical Field

[0001] The utility model relates to the field of aircraft tail wing structures, in particular to a tightening type rudder wing mechanism. Background Technique

[0002] The current rudder wing mechanisms are mainly foldable structures, including a movable rudder surface and a fixed rudder surface, and the movable rudder surface is folded to meet various usage requirements.

[0003] The Chinese patent application with the publication number CN116147426A discloses a lateral folding rudder wing mechanism, which uses multiple springs and locking blocks for control to achieve folding.

[0004] The Chinese patent application with the publication number CN116477046A discloses a rudder surface side folding and unfolding mechanism, which locks the upper rudder surface by sliding the locking shaft into the positioning groove, automatically eliminates the fitting clearance, and reaches a wedging state.

[0005] Generally speaking, the current folding wing control structure is complex, the cost is high, and at the same time, its strength is difficult to guarantee. Content of the Utility Model

[0006] The purpose of the utility model is to provide a tightening type rudder wing mechanism to solve the problems of complex control structure and high cost of the existing folding wing.

[0007] To achieve the above purpose, the utility model provides the following technical solution: A tightening type rudder wing mechanism, including a movable rudder surface and a fixed rudder surface, the movable rudder surface and the fixed rudder surface are rotationally connected through a connecting shaft, a limiting component is arranged between the movable rudder surface and the fixed rudder surface, the limiting component includes a first clamping block, a second clamping block and a torsion spring, the first clamping block is arranged at the bottom of the movable rudder surface, the second clamping block is arranged at the top of the fixed rudder surface, the first clamping block is fixedly connected with the connecting shaft through a fixing pin, the second clamping block is rotationally connected with the connecting shaft, a groove is opened on the first clamping block, a convex tooth is arranged on the second clamping block, the convex tooth is matched with the groove, and one end of the torsion spring is connected with the fixed rudder surface and the other end is connected with the connecting shaft.

[0008] As a further improvement of the above technical solution:

[0009] A rotating shaft is arranged at the bottom of the fixed rudder surface.

[0010] The first clamping block and the movable rudder surface are integrally formed, a reinforcing mounting plate is arranged outside the first clamping block, the reinforcing mounting plate is installed through a connecting screw, one end of the reinforcing mounting plate is connected with the first clamping block, and the other end is connected with the movable rudder surface.

[0011] Anti-wear gaskets are arranged on the contact surfaces of the groove and the convex tooth.

[0012] Compared with the prior art, the beneficial effects of the utility model are:

[0013] Simple structure and convenient operation: Through the design of torsion springs and limiting components, the flipping and limiting between the movable rudder surface and the fixed rudder surface are realized, which is convenient for operation and maintenance.

[0014] Enhanced limiting effect: Through the cooperation of convex teeth and grooves, the limiting of the movable rudder surface and the fixed rudder surface at a specific angle is realized, ensuring the stability and safety of the rudder wing mechanism.

[0015] Improved structural strength and service life: The strengthened mounting plate enhances the strength of the groove. Even in the case of groove fracture, the normal use of the mechanism can still be guaranteed, extending the service life.

[0016] Prevent wear and improve reliability: The anti-wear cushion layer effectively reduces the wear of the contact surface between the groove and the convex teeth, improving the reliability and durability of the rudder wing mechanism.

[0017] Enhanced locking effect and improved safety: The magnetic adsorption layer provides an additional locking effect at the meshing position of the second block and the first block, reducing the risk of premature unlocking caused by external factors and improving the flight safety performance. Description of the Drawings

[0018] Figure 1 Schematic structural diagram of the movable rudder surface and the fixed rudder surface of the present utility model;

[0019] Figure 2 Schematic diagram of the installation position of the fixing pin of the present utility model;

[0020] Figure 3 One of the schematic assembly structures of the movable rudder surface and the fixed rudder surface of the present utility model;

[0021] Figure 4 Another schematic assembly structure of the movable rudder surface and the fixed rudder surface of the present utility model;

[0022] Figure 5 Schematic cross-sectional structure diagram of Embodiment 1 of the present utility model;

[0023] Figure 6 Schematic structure diagram of the strengthened mounting plate of Embodiment 2 of the present utility model;

[0024] Figure 7 Schematic structure diagram of the anti-wear cushion layer of Embodiment 3 of the present utility model;

[0025] Figure 8 Schematic structure diagram of the magnetic adsorption layer of Embodiment 4 of the present utility model.

[0026] Reference numerals: 1, movable rudder surface; 11, first clamping block; 12, groove; 2, fixed rudder surface; 21, second clamping block; 22, convex tooth; 3, torsion spring; 4, connecting shaft; 5, fixing pin; 13, reinforcing mounting plate; 6, rotating shaft; 7, anti-wear cushion layer; 8, magnetic adsorption layer. Detailed implementation manners

[0027] In order to make the technical means, creative features, achieved purposes and functions of the present utility model easy to understand, the present utility model will be further described below in conjunction with specific implementation manners.

[0028] In the description of the present utility model, it should be noted that the orientation or position relationships indicated by the terms "upper", "lower", "inner", "outer", "front end", "rear end", "both ends", "one end", "the other end", etc. are based on the orientation or position relationships shown in the drawings. It is only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation of the present utility model. In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance.

[0029] In the description of the present utility model, it should be noted that unless otherwise clearly specified and defined, the terms "installation", "provided with", "connection", etc. should be understood in a broad sense. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific situations.

[0030] Next, the technical solutions in the embodiments of the present utility model will be clearly and completely described in conjunction with the drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present utility model without creative efforts shall fall within the protection scope of the present utility model.

[0031] Embodiment 1

[0032] As Figures 1 to 5As shown in the figure, the tightening rudder wing mechanism of this embodiment includes a movable rudder surface 1 and a fixed rudder surface 2. The movable rudder surface 1 and the fixed rudder surface 2 are rotatably connected by a connecting shaft 4. A limiting component is arranged between the movable rudder surface 1 and the fixed rudder surface 2. The limiting component includes a first clamping block 11, a second clamping block 21 and a torsion spring 3. The first clamping block 11 is arranged at the bottom of the movable rudder surface 1, the second clamping block 21 is arranged at the top of the fixed rudder surface 2. The first clamping block 11 is fixedly connected to the connecting shaft 4 through a fixing pin 5, the second clamping block 21 is rotatably connected to the connecting shaft 4. A groove 12 is formed on the first clamping block 11, a convex tooth 22 is arranged on the second clamping block 21, and the convex tooth 22 is matched with the groove 12. One end of the torsion spring 3 is connected to the fixed rudder surface 2, and the other end is connected to the connecting shaft 4.

[0033] A rotating shaft 6 is arranged at the bottom of the fixed rudder surface 2. During use, the limit is achieved through the cooperation of the convex tooth 22 and the groove 12. As Figure 3 shown in the figure, the torsion spring 3 is compressed at this time and the convex tooth 22 is not combined with the groove 12, and the movable rudder surface 2 can be flipped. After the movable rudder surface 2 is flipped, the torsion spring 3 elastically returns, and the convex tooth 22 and the groove 12 will be in contact. The convex tooth 22 and the groove 12 are at a certain angle (usually considered to be 90°) at this time in the unfolded state. The elastic force of the torsion spring 3 makes the movable rudder surface 1 in the folded state. When it is necessary to flip the movable rudder surface 1 to align with the fixed rudder surface 2, a tool is used to overcome the elastic force of the torsion spring 3, and the movable rudder surface 1 is flipped so that the groove 12 and the convex tooth 22 are aligned. Under the support of the compression force of the torsion spring 3, the groove 12 and the convex tooth 22 are tightly combined to play a limiting role. When flipping next time, the torsion spring 3 needs to be compressed first to separate the groove 12 and the convex tooth 22 before flipping can be achieved.

[0034] Embodiment 2

[0035] As Figure 6 shown in the figure, the first clamping block 11 and the movable rudder surface 1 are integrally formed. A reinforcing mounting plate 13 is arranged outside the first clamping block 11. The reinforcing mounting plate 13 is installed through connecting screws. One end of the reinforcing mounting plate 13 is connected to the first clamping block 11, and the other end is connected to the movable rudder surface 1. In order to enhance the strength of the groove 12, the reinforcing mounting plate is provided. After the groove 12 is broken, normal use can still be guaranteed, the structural strength is enhanced, and the service life is extended.

[0036] Embodiment 3

[0037] As Figure 7 shown in the figure, an anti-wear cushion layer 7 is arranged on the contact surface of the groove 12 and the convex tooth 22. An anti-wear gasket made of corrosion-resistant and impact-resistant materials is added at the edge of the groove 12 as the anti-wear cushion layer 7. Similarly, an anti-wear layer is arranged on the contact surface of the convex tooth 22. When the convex tooth 22 is embedded in the groove 12, it plays a role in increasing friction and surface protection, and avoids the problem of function degradation caused by wear during normal work.

[0038] Embodiment 4

[0039] AsFigure 8 As shown, a magnetic adsorption layer 8 is provided at the meshing position of the second clamping block 21 and the first clamping block 11. In order to enhance the locking effect generated when the second clamping block 21 and the first clamping block 11 are meshed and closed, a magnetic adsorption mechanism is introduced, that is, an appropriate amount of small magnets or magnet film materials are arranged in the area close to the end faces of the two, which can play an auxiliary grasping and locking effect to prompt the entire mechanism to quickly enter the ready state, and avoid the threat to the safety flight performance index of the aircraft caused by factors such as external air flow interference leading to premature unlocking.

[0040] The above are only the embodiments of the present invention, and common knowledge such as the specific structures and characteristics known in the solutions is not described in detail here. For those skilled in the art, it is obvious that the present invention is not limited to the details of the above exemplary embodiments, and can be implemented in other specific forms without departing from the spirit or basic characteristics of the present invention. Therefore, from any point of view, the embodiments should be regarded as exemplary and non-limiting. The scope of the present invention is defined by the appended claims rather than the above description. Therefore, all changes falling within the meaning and scope of the equivalent elements of the claims are intended to be included in the present invention. Any reference signs in the claims should not be regarded as limiting the claimed rights.

Claims

1. A tightening rudder wing mechanism, characterized in that: The invention comprises a moving rudder surface (1) and a fixed rudder surface (2), wherein the moving rudder surface (1) and the fixed rudder surface (2) are rotatably connected via a connecting shaft (4), a limiting component is arranged between the moving rudder surface (1) and the fixed rudder surface (2), the limiting component comprises a first clamping block (11), a second clamping block (21) and a torsion spring (3), wherein the first clamping block (11) is arranged at the bottom of the moving rudder surface (1), the second clamping block (21) is arranged at the top of the fixed rudder surface (2), the first clamping block (11) is fixedly connected to the connecting shaft (4) via a fixing pin (5), the second clamping block (21) is rotatably connected to the connecting shaft (4), a groove (12) is provided on the first clamping block (11), a convex tooth (22) is provided on the second clamping block (21), the convex tooth (22) matches the groove (12), one end of the torsion spring (3) is connected to the fixed rudder surface (2), and the other end is connected to the connecting shaft (4).

2. The tightening rudder wing mechanism according to claim 1, characterized in that: A rotating shaft (6) is provided at the bottom of the fixed rudder surface (2).

3. The tightening rudder wing mechanism according to claim 1, characterized in that: The first clamping block (11) and the dynamic steering surface (1) are integrally formed, a reinforcing mounting plate (13) is provided outside the first clamping block (11), the reinforcing mounting plate (13) is installed by means of connecting screws, one end of the reinforcing mounting plate (13) is connected to the first clamping block (11), and the other end is connected to the dynamic steering surface (1).

4. The tightening rudder wing mechanism according to claim 2, characterized in that: The contact surfaces of the groove (12) and the convex teeth (22) are provided with an anti-wear pad layer (7).

5. The tightening rudder wing mechanism according to claim 2 or 3, characterized in that: A magnetic adsorption layer (8) is provided at the meshing position between the second clamping block (21) and the first clamping block (11).

Images