A high-overload deployment and locking mechanism for a folded tail fin of a gun-launched missile

Abstract

The application provides a folding tail wing high-overload unfolding and locking mechanism of a gun-launched missile, which comprises tail wings installed outside a missile tail and n locking latches installed inside the missile tail; the n tail wings are hinged on the missile tail, the missile tail is provided with a guide groove, the tail wings are provided with latch holes, and the tail of the locking latches extends out of the guide groove and the latch holes in sequence; the tail of the locking latches is arc-shaped, the front end of the locking latches is lower than the height of the lower end surface of the latch hole, and the rear end is higher than the height of the upper end surface of the latch hole and is provided with a spring; the locking latches are installed on a sliding sleeve, the outer diameter of the sliding sleeve is the same as the inner diameter of the missile tail and the sliding sleeve is installed in the missile tail, the sliding sleeve and the missile tail are both provided with pin hole with the center line in the same plane, the rear end of the sliding sleeve is provided with a spring, and the tail of the missile tail is closed. The unfolding and locking of the tail wings are both completed by the locking latches, the power of the locking latches and most of the positions of the locking latches are hidden in the missile tail, so the volume of the outer wall of the missile is not increased, and the tail wings do not need to be fixed by a missile support, so the charging space is not occupied.

Description

Technical Field

[0001] This invention relates to a high-overload deployment and locking mechanism for the folding tail fins of a gun-launched missile. Background Technology

[0002] The tail fins of a missile are stabilizing devices during flight. Currently, artillery-launched missiles often use torsion springs as the power source for deploying their folding tail fins. The installation of torsion springs increases the volume of the contact area between the tail fins and the missile, resulting in a larger frontal area for the artillery-launched missile. Furthermore, because the folding tail fins require a sabot to limit their deployment after folding, the amount of propellant is reduced, affecting the missile's exit velocity from the gun barrel. The separation of the sabot also impacts the accuracy of the artillery-launched missile. Due to the limited size of the torsion springs, the weak power can lead to delayed tail fin deployment, easily resulting in insufficient launch accuracy or even launch failure. Summary of the Invention

[0003] To solve the above-mentioned technical problems, the present invention provides a high overload deployment and locking mechanism for the folding tail fin of a gun-launched missile. The mechanism unlocks the folding tail fin during the launch of the gun-launched missile, while the folding tail fin does not deploy during the movement inside the gun barrel. After the gun-launched missile leaves the gun barrel, the launch overload disappears and the folding tail fin deploys.

[0004] The present invention is achieved through the following technical solutions.

[0005] This invention provides a high-overload deployment and locking mechanism for a gun-launched missile's folding tail fin, comprising a tail fin mounted outside the missile tail and n locking tongues mounted inside the missile tail; the n tail fins are hinged to the missile tail, the missile tail has guide grooves, and the tail fins have locking tongue holes, the ends of the locking tongues extending sequentially out of the guide grooves and locking tongue holes; the ends of the locking tongues are arc-shaped, the front end of the locking tongue is lower than the lower end face of the locking tongue hole, the rear end is higher than the upper end face of the locking tongue hole and has a latch, the locking tongues are mounted on a sliding sleeve, the outer diameter of the sliding sleeve is the same as the inner diameter of the missile tail and is mounted inside the missile tail, both the sliding sleeve and the missile tail have pin holes with their center lines on the same plane, the rear end of the sliding sleeve is equipped with a spring, and the end of the missile tail is closed.

[0006] The tail fin includes a fixed end and a movable end. The n fixed ends are vertically fixed to the tail of the projectile and parallel to the axis of the tail. The movable end is hinged to the fixed end and can only be folded in one direction on the fixed end.

[0007] The guide grooves are machined on the bullet tail, and one side of each guide groove is connected to the bullet tail with its adjacent fixed end. The connecting edge of the movable end is folded to one side on the same plane. There are n locking tongue holes, and both sides of the locking tongue holes are parallel to the guide grooves.

[0008] The guide groove and the rear end of the latch hole are on the same plane, and the length of the guide groove is greater than the length of the latch hole.

[0009] The diameter of the rotating shaft is the same as the width of the connection between the fixed end and the movable end, and the portion of the rotating shaft within the projection range of the guide groove is not covered.

[0010] The beneficial effects of this invention are as follows: the deployment and locking of the tail fin are both accomplished by the locking tongue, and the power of the locking tongue and most of its position are hidden in the missile tail, so it does not increase the volume of the missile's outer wall, and at the same time, it does not require the tail fin to be fixed by the sabot, so it does not occupy the space for the propellant. Attached Figure Description

[0011] Figure 1 This is a schematic diagram of the tail fin in the folded state of the present invention;

[0012] Figure 2 This is a schematic diagram of the tail fin deployment state of the present invention;

[0013] Figure 3 This is a schematic diagram of the locking tongue structure of the present invention;

[0014] In the diagram: 1-tail fin, 11-fixed end, 12-movable end, 13-locking tongue hole, 2-locking tongue, 21-arc edge, 22-buckle, 3-pin hole, 4-rotating shaft, 5-compression spring, 6-sliding sleeve, 7-spring tail, 8-guide groove. Detailed Implementation

[0015] The technical solution of the present invention is further described below, but the scope of protection is not limited to what is described.

[0016] A high-overload deployment and locking mechanism for a gun-launched missile's folding tail fin includes a tail fin 1 mounted outside the tail fin 7 and n locking tongues 2 mounted inside the tail fin 7. The n tail fins 1 are hinged to the tail fin 7, which has a guide groove 8. The tail fins 1 have locking tongue holes 13. The ends of the locking tongues 2 extend out of the guide groove 8 and the locking tongue holes 13 in sequence. The ends of the locking tongues 2 are arc-shaped. The height of the front end of the locking tongue 2 is lower than the height of the lower end face of the locking tongue hole 13, and the height of the rear end is higher than the height of the upper end face of the locking tongue hole 13 and is machined with a buckle 22. The locking tongues 2 are mounted on a sliding sleeve 6. The outer diameter of the sliding sleeve 6 is the same as the inner diameter of the tail fin 7 and is mounted inside the tail fin 7. The sliding sleeve 6 and the tail fin 7 are both machined with pin holes 3 whose center lines are on the same plane. A spring is installed at the rear end of the sliding sleeve 6, and the end of the tail fin 7 is closed.

[0017] The tail fin 1 includes a fixed end 11 and a movable end 12. The n fixed ends 11 are vertically fixed to the tail 7 and parallel to the axis of the tail 7. The movable end 12 is hinged to the fixed end 11 and can only be folded in one direction on the fixed end 11.

[0018] The guide groove 8 has n grooves machined on the spring tail 7. One side of each guide groove 8 is connected to the spring tail 7 with its adjacent fixed end 11, and the connecting edge of the movable end 12 is on the same plane. There are n locking tongue holes 13, and both sides of them are parallel to the guide groove 8.

[0019] The guide groove 8 and the rear end of the latch hole 13 are on the same plane, and the length of the guide groove 8 is greater than the length of the latch hole 13.

[0020] The diameter of the rotating shaft 4 is the same as the width at the connection between the fixed end 11 and the movable end 12, and the portion of the rotating shaft 4 within the projection range of the guide groove 8 is not covered.

[0021] In its normal state, the missile's locking tongue is secured by pins inserted into pin holes in the sliding sleeve 6 and the tail 7, respectively. The spring that pushes the locking tongue through the sliding sleeve is in a compressed, energy-stored state, and the latch at the tail of the locking tongue limits the folding tail fin, keeping it folded. During missile launch, the immense chamber pressure generates a significant overload, causing the sliding sleeve to continue sliding rearward, leading to pin breakage. Inside the gun barrel, the overload persists, and the latch continues to limit the folding tail fin. Once the missile exits the barrel and is no longer subjected to chamber pressure, the overload disappears, and the locking tongue continues to slide forward. During this slide, the locking tongue pushes the folding tail fin to unfold rapidly in a counter-clockwise direction. After unfolding, the locking tongue continues to move forward and presses against the side of the folding tail fin, completing the locking of the folding tail fin.

Claims

1. A high-overload deployment and locking mechanism for a gun-launched missile's folding tail fin, comprising a tail fin (1) mounted outside the missile tail (7) and n locking tongues (2) mounted inside the missile tail (7), characterized in that: n tail fins (1) are hinged to the tail (7). The tail (7) has a guide groove (8) and a locking tongue hole (13). The end of the locking tongue (2) extends out of the guide groove (8) and the locking tongue hole (13) in sequence. The end of the locking tongue (2) is arc-shaped. The height of the front end of the locking tongue (2) is lower than the height of the lower end face of the locking tongue hole (13), and the height of the rear end is higher than the height of the upper end face of the locking tongue hole (13) and is equipped with a buckle (22). The locking tongue (2) is installed on the sliding sleeve (6). The outer diameter of the sliding sleeve (6) is the same as the inner diameter of the tail (7) and is installed inside the tail (7). The sliding sleeve (6) and the tail (7) are both equipped with pin holes (3) with the center lines on the same plane. The two ends of the pins extend into the pin holes (3) of the sliding sleeve (6) and the tail (7) respectively. The rear end of the sliding sleeve (6) is equipped with a spring, and the end of the tail (7) is closed. The guide groove (8) is machined on the tail (7) with n grooves. The tail fin (1) includes a fixed end (11) and a movable end (12). One side of each guide groove (8) is connected to its adjacent fixed end (11) and is on the same plane as the connecting edge of the movable end (12) which is bent to one side. There are n locking holes (13) and both sides of them are parallel to the guide groove (8). The guide groove (8) and the rear end of the latch hole (13) are on the same plane, and the length of the guide groove (8) is greater than the length of the latch hole (13).

2. The high-overload deployment and locking mechanism for the folding tail fins of a gun-launched missile as described in claim 1, characterized in that: n fixed ends (11) are vertically fixed on the tail (7) and parallel to the axis of the tail (7). The movable end (12) is hinged to the fixed end (11) and can only be folded in one direction on the fixed end (11).

3. The high-overload deployment and locking mechanism for the folding tail fins of a gun-launched missile as described in claim 1, characterized in that: The diameter of the rotating shaft (4) is the same as the width at the connection between the fixed end (11) and the movable end (12), and the part of the rotating shaft (4) within the projection range of the guide groove (8) is not covered.

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