Anti-springback folding control surface self-locking device

Abstract

The anti-springback folding control surface self-locking device comprises a fixed rudder and a movable rudder, a groove is machined in the end, opposite to the movable rudder, of the fixed rudder, a protrusion corresponding to the groove is machined in the end, opposite to the fixed rudder, of the movable rudder, and the movable rudder is hinged to a torsion element through a rotating shaft; a torsion element is installed in the rotating shaft, a guide groove is further machined in the bottom of the groove, a lock hole opposite to the guide groove and concentric with the guide groove is formed in the protrusion, a locking pin is arranged in the guide groove, and a compression spring is arranged between the locking pin and the guide groove. A locking assembly is further arranged on the side face of the lock hole, the unfolded movable rudder is locked through a locking pin, the locking pin prevents the movable rudder from rebounding through a self-locking key, and the requirement for reliable locking when the missile executes a task and bears the pneumatic alternating load through the folding control surface is met.

Description

Technical Field

[0001] This invention relates to a self-locking device for folding control surfaces that prevents rebound. Background Technology

[0002] Using folding control surfaces is an effective method to reduce the outer envelope size of missiles and has been widely used in various models. Folding control surfaces consist of fixed control surfaces, moving control surfaces, rotating shafts, locking pins, compression springs, torque elements, fasteners, etc. The moving control surfaces are driven to rotate around the rotating shaft by the torque elements, and the locking pins move along the locking hole axis under the action of the compression springs, cooperating with the moving control pin holes to achieve locking of the moving and fixed control surfaces.

[0003] To facilitate the engagement of the locking pin and the moving rudder during deployment, the existing locking pin end and the moving rudder locking hole are both round lock heads with a certain angle. During the missile's mission, the folding control surface is subjected to aerodynamic alternating loads. Due to the presence of the lock head, the locking pin is subjected to a component force pointing towards the fixed rudder, which may cause the locking pin to spring back, causing the fixed rudder to lose lock and resulting in flight mission failure. Summary of the Invention

[0004] The purpose of this invention is to address the problem that existing locking pins spring back after locking, and to provide a highly reliable, versatile, simple, and easy-to-implement device to prevent the locking pins from springing back when the folded control surface is subjected to aerodynamic alternating loads during mission execution.

[0005] The technical solution of this invention: A self-locking device for a folding rudder surface with anti-rebound capability includes a fixed rudder and a moving rudder. A groove is machined at one end of the fixed rudder relative to the moving rudder, and a protrusion corresponding to the groove is machined at the other end of the moving rudder relative to the fixed rudder. The moving rudder and a torque element are hinged together via a pivot shaft. The torque element is installed inside the pivot shaft. A guide groove is also machined at the bottom of the groove. A locking hole, co-centered with the guide groove, is provided inside the protrusion. A locking pin is provided inside the guide groove, and a compression spring is provided between the locking pin and the guide groove. A locking assembly is also provided on the side of the locking hole.

[0006] The locking assembly includes a self-locking key and a torsion spring. One end of the self-locking key is machined with a torsion spring receiving groove, and pivot holes are machined on both sides of the torsion spring receiving groove. The other end of the self-locking key is machined with a hook hole, and a pin hole I is machined on the outer side of the hook hole. The torsion spring includes a spring body, and the outer arms I and II at both ends of the spring body form an acute angle. The spring body is placed in the torsion spring receiving groove and hinged to the rudder through a pivot. The outer arm I is hinged to the pin II through the hook at its end. The pin II is placed above the pivot. The outer arm II is placed in the hook groove on the self-locking key and fixed by the pin I.

[0007] The self-locking key is placed in the lock groove, which is machined on the side of the lock hole.

[0008] The top of the locking pin is provided with a lock head, and the lock head and the lock hole are tapered with the same specifications. The lock head has a fan-shaped groove machined on the side opposite to the self-locking key.

[0009] The bottom of the locking pin is machined with a spring groove, and the spring is installed in the spring groove.

[0010] The beneficial effects of this invention are: The deployed control surfaces are locked by locking pins, which are prevented from springing back by self-locking keys, thus meeting the reliable locking requirements when the missile is subjected to aerodynamic alternating loads by the folded control surfaces during mission execution. Attached Figure Description

[0011] Figure 1 This is a partial cross-sectional view of the steering wheel locking mechanism.

[0012] Figure 2 This is a schematic diagram of the locking pin structure.

[0013] Figure 3 This is a cross-sectional view of the locking pin.

[0014] Figure 4 This is a schematic diagram of the self-locking key.

[0015] Figure 5 This is a schematic diagram of a torsion spring.

[0016] Figure 6 This is a structural diagram of the locking pin and the rudder.

[0017] Figure 7 This is a schematic diagram of the rudder when it is folded.

[0018] Figure 8 This is a schematic diagram of the structure when the rudder is deployed.

[0019] Figure 9 This is a schematic diagram of a structure where the locking pin locks the rudder and is locked by a self-locking key.

[0020] Reference numerals: 1-Locking pin, 11-Lock head, 12-Sector groove, 13-Cavity, 2-Self-locking key, 21-Pin hole I, 22-Rotating shaft hole, 23-Locking surface, 3-Torsion spring, 31-Outer arm I, 32-Outer arm II, 33-Spring body, 41-Pin I, 42-Rotating shaft, 43-Pin II, 5-Fixed rudder, 51-Guide groove, 6-Compression spring, 7-Rotating shaft, 8-Moving rudder, 81-Locking hole, 82-Rotating shaft mounting hole, 83-Pin hole II, 9-Torque element. Detailed Implementation

[0021] Example 1: Each component is made of various metal or non-metal materials, or of porous materials such as lattice or grid, to achieve reliable structure, optimal weight, and resistance to high aerodynamic alternating loads.

[0022] The locking pin 1 can be a rod-shaped structure with a circular, rectangular, or other cross-sectional shape. The locking pin 1 has a lock head 11 that mates with the locking hole 81 of the rudder 8; the locking pin 1 has a sector-shaped groove 12 for mates with the self-locking key 2; and the bottom of the locking pin 1 has a spring groove for installing the compression spring 6. The self-locking key 2 has a pin hole 121, a pivot hole 22, and a locking surface 23. A portion of its interior is hollowed out for mounting a torsion spring 3. The self-locking key 2 can rotate around the pivot 42. After locking, the locking surface 23 of the self-locking key 2 contacts a sector-shaped groove 12 of the locking pin 1, thus achieving self-locking of the locking pin 1. The torsion spring 3 has an outer arm I31, an outer arm II32, and a spring body 33. The torsion spring 3 is an energy storage element that drives the self-locking key 2 to rotate around the rotating shaft 42 and bears torsional loads; Pin I41 is a cylindrical pin, which is installed in the pin hole I21 of the self-locking key 2 and passes through the outer arm II32 of the torsion spring 3 to ensure the relative positional relationship between the self-locking key 2 and the torsion spring 3. The pivot 42 is a cylindrical pin, which is installed in the pivot hole 22 of the self-locking key 2 and the pivot mounting hole 82 in the rudder 8, and passes through the spring body 33 of the torsion spring 3 to ensure the relative positional relationship of the self-locking key 2, the torsion spring 3, and the rudder 8. Pin II43 is a cylindrical pin, which is installed in pin hole II83 of rudder 8 and passes through outer arm I31 of torsion spring 3 to ensure the relative positional relationship between torsion spring 3 and rudder 8. The fixed rudder 5 has a guide groove 51, the cross-sectional shape of which is consistent with the cross-sectional shape of the locking pin 1, which is used to install the locking pin 1 and the compression spring 6 to constrain the movement direction of the locking pin 1. The compression spring 6 is an energy storage element that drives the locking pin 1 to move along the axis of the guide groove 51 of the fixed rudder 5 and bears the compressive load. The rotating shaft 7 is a hollow cylindrical rod-shaped structure. It connects the fixed rudder 5 and the movable rudder 8, and is the rotation center of the movable rudder 8; The rudder 8 has a locking hole 81, a pivot mounting hole 82, and a pin hole II 83. The locking hole 81 is a lock head; the locking hole 81 cooperates with the locking pin 11 to lock the folding rudder surface; the pivot 42 is installed in the pivot mounting hole 82; the pin II 43 is installed in the pin hole II 83. Torque element 9 is a torsion bar, torsion plate or other components that provide the deployment torque for rudder 8.

[0023] The self-locking device of the folding control surface locking mechanism is placed on the moving control 8 to prevent the locking pin 1 from rebounding, thus meeting the reliable locking requirements when the missile is subjected to aerodynamic alternating loads on the folding control surface during mission execution. According to the structure of the folding control surface, the self-locking device of the folding control surface locking mechanism can be placed on the fixed control 5 to prevent the locking pin 1 from rebounding. Alternatively, according to the aerodynamic load of the folding control surface, one, two, three, or more sets of the self-locking device of the folding control surface locking mechanism can be set up to work simultaneously.

[0024] The locking process of this invention is as follows: After the missile exits the launch tube, the folding control surface loses the constraint of the inner wall of the launch tube. Under the action of the torsion element 9, the rotating shaft 7 of the moving control 8 rotates. Under the action of the compression spring 6, the locking pin 1 moves along the axis of the guide groove 51 of the fixed control 5 towards the moving control 8. The locking pin 1 enters the locking hole 81 of the moving control 8. The self-locking key 2 contacts the round lock head 11 of the locking pin 1. The self-locking key 2 rotates around the rotating shaft 42. The torsion spring 3 is compressed and stores energy. After the locking pin 1 and the locking hole 81 of the moving control 8 are in place, the energy stored in the torsion spring 3 is released. The self-locking key 2 rotates around the rotating shaft 42. The locking surface 23 of the self-locking key 2 contacts the sector groove 12 of the locking pin 1, thereby realizing the self-locking of the locking pin 1.

Claims

1. A kind of anti-rebound folding control surface self-locking device, including fixed rudder (5) and movable rudder (8), fixed rudder (5) relative to the recess of one end of movable rudder (8) is processed, movable rudder (8) relative to the protrusion of one end of fixed rudder (5) is processed with recess corresponding, movable rudder (8) and torsion element (9) between by pivot (7) articulate, it is characterized by: The torsion element (9) is installed in the rotating shaft (7), the bottom of the groove is further processed with a guide groove (51), the convex is provided with a lock hole (81) which is opposite to the guide groove (51) and concentric, the guide groove (51) is provided with a locking pin (1), and the locking pin (1) and the guide groove (51) are provided with a compression spring (6); the side of the lock hole (81) is further provided with a locking assembly.

2. The anti-back-lash folding-surface self-locking device according to claim 1, characterized in that: The locking assembly comprises a self-locking key (2) and a torsion spring (3), one end of the self-locking key (2) is processed with a torsion spring accommodating groove, both sides of the torsion spring accommodating groove are processed with rotating shaft holes (22), the other end of the self-locking key (2) is processed with a carabiner hole, the outer side of the carabiner hole is processed with a pin hole I (21); the torsion spring (3) comprises a spring body (33), the outer arm I (31) and the outer arm II (32) at both ends of the spring body (33) form an acute angle; the spring body (33) is placed in the torsion spring accommodating groove and is hinged in the rudder (8) through a rotating shaft (42), the outer arm I (31) is hinged on a pin II (43) through a carabiner at the tail end, the pin II (43) is placed above the rotating shaft (42), and the outer arm II (32) is placed in the carabiner groove on the self-locking key (2) and is fixed through a pin I (41).

3. The anti-back-lash folding-surface self-locking device according to claim 2, characterized in that: The self-locking key (2) is placed in the lock groove, and the lock groove is processed on the side of the lock hole (81).

4. The anti-back-lash folding-surface self-locking device according to claim 1, characterized in that: The top of the locking pin (1) is provided with a lock head (11), the lock head (11) and the lock hole (81) are conical with the same specifications, and the lock head (11) is processed with a fan-shaped groove (12) on one side relative to the self-locking key (2).

5. The anti-back-lash folding-surface self-locking device according to claim 1, wherein: The bottom of the locking pin (1) is processed with a compression spring groove, and the compression spring (6) is installed in the compression spring groove.

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