Folding control surface one-way locking mechanism

Abstract

The utility model relates to a folding control surface one-way locking mechanism which is characterized in that the folding control surface one-way locking mechanism is composed of a stop block 2, a support 3 and a fastener, the stop block 2 comprises a sleeving hole 2-1, a mounting hole 2-2 and a stop surface 2-3, the support 3 comprises a sleeving boss 3-1, a mounting hole 3-2 and a cabin mounting surface 3-4, the sleeving hole 2-1 is connected with the sleeving boss 3-1 in a sleeving mode, and the mounting hole 2-2 is connected with the cabin mounting surface 3-4 in a sleeving mode. The mounting hole 2-2 of the stop block 2 and the mounting hole 3-2 of the support 3 are fixedly connected into a whole through a fastener, the stop surface 2-3 and the control surface are conformal in appearance, and the cabin mounting surface 3-4 and the cabin 1 are conformal in appearance. The mechanism limits the one-way rotation angle of the control surface, large-angle rotation of the control surface around a shaft caused by friction force between a guided missile and a box body in the launching process in the cylinder can be avoided, and the control surface does not need to be unlocked or unfolded in place under the action of a power source after being separated from the cylinder.

Description

Technical Field

[0001] This utility model relates to the field of rudder surface control technology, specifically to a folding rudder surface one-way locking mechanism. Background Technology

[0002] Due to the requirements of missile use, the missile must be in a folded state when loaded into the launch container, and it is not allowed to rotate around its axis during launch to prevent the servo motor function from being affected after the missile exits the container, thus leading to launch mission failure. Due to the limitations of the operating environment, a locking mechanism is required to ensure that the control surfaces are locked at an angle during the launch process after the missile exits the container, and that the control surfaces can reliably unfold into their final positions without unlocking after the missile exits the container. Summary of the Invention

[0003] The purpose of this utility model is...

[0004] This invention proposes a folding control surface one-way locking mechanism to avoid large-angle rotation of the control surface around the axis caused by friction between the missile and the housing during launch from inside the tube. After leaving the tube, the control surface does not need to be unlocked or unfolded into place under the action of a power source.

[0005] Technical solution of this utility model

[0006] A folding control surface one-way locking mechanism comprises a stop block 2, a support 3, and fasteners. The stop block 2 includes a socket hole 2-1, a mounting hole 2-2, and a stop surface 2-3. The support 3 includes a socket boss 3-1, a mounting hole 3-2, and a cabin mounting surface 3-4. The socket hole 2-1 is sleeved with the socket boss 3-1. The mounting hole 2-2 of the stop block 2 and the mounting hole 3-2 of the support 3 are fixed together as a whole by fasteners. The stop surface 2-3 is conformal to the shape of the control surface, and the cabin mounting surface 3-4 is conformal to the shape of the cabin 1.

[0007] Preferably, the stop block 2 is a non-metallic material with a buffering function.

[0008] Preferably, the non-metallic material is polytetrafluoroethylene.

[0009] Preferably, the non-metallic material is silicone rubber.

[0010] Preferably, the support 3 is made of metal.

[0011] Preferably, the stop block 2 includes a support mating surface 2-4, and the support 3 includes a stop block mating surface 3-3, wherein the support mating surface 2-4 and the stop block mating surface 3-3 are in clearance fit.

[0012] Preferably, the fastener is a combination of a fastening screw and a bolt.

[0013] Technical effects of this utility model

[0014] The folding control surface one-way locking mechanism of this utility model can lock the control surface during the sliding process of the control surface of the box-type missile inside the box. It has the advantages of simple structure, easy processing and molding, convenient disassembly and replacement, and reliability. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of a one-way locking mechanism for folding rudder surfaces.

[0016] Figure 2 This is a cross-sectional view of the folding rudder surface one-way locking mechanism.

[0017] Figure 3 This is a schematic diagram of the components of the stop block in the one-way locking mechanism of the folding rudder surface.

[0018] Figure 4 This is a schematic diagram of the components of the support for the unidirectional locking mechanism of the folding rudder surface.

[0019] Figure 5 Example diagram of a unidirectional locking mechanism for folding rudder surfaces.

[0020] Figure 1 In the middle: 1. cabin; 2. stop block; 3. support.

[0021] Figure 3 In the middle: 2-1, socket hole; 2-2, stop block mounting hole; 2-3, stop surface; 2-4, support mating surface.

[0022] Figure 4 In the middle: 3-1, connecting boss; 3-2, support mounting hole; 3-3, stop block mating surface; 3-4, hull mounting surface.

[0023] Figure 5 4. Folding rudder surface one-way locking mechanism; 5. Rudder surface. Detailed Implementation

[0024] like Figures 1-4 As shown, the stop block 2, with feature 2-1, is fitted with the mounting boss 3-1 of the mounting base 3. Fasteners are used to secure it as a whole via feature 2-2 and the mounting hole 3-2. Feature 2-3 conforms to the shape of the control surface, and feature 3-4 conforms to the shape of the hull 1, and is secured to the hull 1 by fasteners. The support 3 has a mounting boss 3-1, a mounting hole 3-2, a stop block mating surface 3-3, and a hull mounting surface 3-4. The support mating surface 2-4 and the stop block mating surface 3-3 are clearance-fitted. Figure 5 As shown, during missile launch, the friction between the control surface and the housing drives the control surface to deflect in one direction. The locking mechanism of this invention causes the front edge of the control surface to contact the stop block when the missile slides inside the housing, preventing the control surface from rotating in one direction along the axis of rotation, thus achieving one-way locking of the control surface.

Claims

1. A folding surface one-way locking mechanism, characterized in that, The application relates to a stopper (2), a support (3) and a fastener, the stopper (2) comprising a sleeving hole (2-1), a stopper (2) mounting hole (2-2) and a stop face (2-3), the support (3) comprising a sleeving boss (3-1), a support (3) mounting hole (3-2) and a cabin body mounting face (3-4), the sleeving hole (2-1) being sleeved with the sleeving boss (3-1), the stopper (2) mounting hole (2-2) and the support (3) mounting hole (3-2) being fixedly connected into an integral whole through the fastener, the stop face (2-3) being conformal with the rudder face shape, and the cabin body mounting face (3-4) being conformal with the cabin body (1) shape.

2. A folding surface one-way locking mechanism as claimed in claim 1, characterized in that, The stopper (2) is a non-metal material with a buffering function.

3. A folding surface one-way locking mechanism as claimed in claim 2, characterized in that The non-metal material is polytetrafluoroethylene.

4. A folding surface one-way locking mechanism as claimed in claim 2, wherein, The non-metal material is silicone rubber.

5. A folding surface one-way locking mechanism as claimed in claim 1, wherein, The support (3) is made of a metal material.

6. A folding surface one-way locking mechanism as claimed in claim 1, wherein, The stopper (2) comprises a support matching face (2-4), the support (3) comprises a stopper matching face (3-3), and the support matching face (2-4) and the stopper matching face (3-3) are gap-matched.

7. A folding surface one-way locking mechanism as claimed in claim 1, wherein, The fastener is a fastening screw and a bolt.

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