Low-disturbance laterally-folded empennage stabilizing device

Abstract

The invention discloses a low-disturbance laterally-folded empennage stabilizing device which comprises an empennage frame, an empennage, a fixing seat fixed to the outer wall of the empennage frame, a supporting lug fixed to the bottom of the empennage, a torsion rod used for being rotationally connected with the empennage frame and the empennage, and a compression spring used for driving the empennage to axially move relative to the empennage frame. The sliding block is used for locking the empennage; the empennage overturns around the axis of the torsion bar under the action of the torsion bar; the turning angle of the empennage is limited through an angle limiting convex block of the fixed seat; when the empennage is in a folded state, the sliding block slides into the sliding block receding notch of the fixing base and compresses the compression spring. When the empennage is in an unfolded state, the compressed spring pushes the sliding block to slide into the right end of the supporting lug, and the unfolded state of the empennage is locked. According to the lateral folding empennage stabilizing device, the disturbance effect of empennage unfolding on the flying stage that a rocket pops out of a muzzle is reduced.

Description

Technical Field

[0001] This invention belongs to the field of stabilization device technology, specifically relating to a low-disturbance lateral folding tail fin stabilization device. Background Technology

[0002] Rockets rely on the tail fins of their stabilizing device to generate lift, shifting the center of pressure to the center of mass and creating a stabilizing torque to ensure stable flight. Foldable stabilizing devices reduce the projectile's diameter, resulting in a more compact structure for the projectile and launcher. Currently, traditional lateral folding stabilizing devices typically consist of tail fins, a tail fin mount, a pivot, and a compression-torsion spring. Their operating mechanism is as follows: the compression-torsion spring acts as the sole power source, causing the tail fins to rotate around the pivot while simultaneously moving axially, ultimately securing themselves to the tail fin mount via a wedge-shaped fit.

[0003] Traditional lateral folding stabilization devices have problems: the tail fins need to rotate and move axially, and when the tail fins are in place, they will cause a large axial impact on the projectile, which will cause significant disturbance to the rocket during the flight phase after it leaves the muzzle. Summary of the Invention

[0004] The purpose of this invention is to solve the problem that when the tail fin of a traditional lateral folding stabilizing device is inserted into the slot, it will cause a large axial impact on the projectile body and cause significant disturbance during the rocket's flight phase after exiting the gun muzzle. Therefore, this invention provides a low-disturbance lateral folding tail fin stabilizing device.

[0005] The objective of this invention is achieved through the following technical solution:

[0006] The present invention provides a low-disturbance lateral folding tail fin stabilization device, comprising a tail fin frame, a tail fin, a fixing seat fixed to the outer wall of the tail fin frame, a support lug fixed to the bottom of the tail fin, a torsion bar for rotatably connecting the tail fin frame and the tail fin, a compression spring for driving the tail fin to move axially relative to the tail fin frame, and a slider for locking the tail fin.

[0007] The fixed seat has a torsion bar connection hole axially opened in the middle part, a spring mounting cavity is provided at the left end of the inner cavity of the fixed seat, a slider clearance notch is axially opened inward along the upper outer edge of the left port of the fixed seat, and an angle limiting protrusion extending outward along the lower outer edge of the left port of the fixed seat.

[0008] The middle part of the support lug has an axially opened torsion bar connection hole, and the right end of the support lug is provided with a positioning protrusion extending outward in an axial direction.

[0009] The middle part of the slider is a connecting cylinder whose inner diameter matches the outer diameter of the torsion bar, and the outer wall of the slider is provided with a locking protrusion whose shape matches the inner shape of the slider clearance notch of the fixed seat.

[0010] The two ends of the torsion bar are respectively installed in the torsion bar connecting holes of the support lug and the fixed seat, so that the tail wing flips around the axis of the torsion bar under the action of the torsion bar; the positioning protrusion of the support lug and the angle limiting protrusion of the fixed seat are located in the same radial plane, and the tail wing's flipping angle is limited by the angle limiting protrusion of the fixed seat; a compression spring is installed in the compression spring mounting cavity of the fixed seat, and the slider is sleeved on the torsion bar; when the tail wing is in the closed state, the locking protrusion of the slider slides into the slider clearance notch of the fixed seat and compresses the compression spring; when the tail wing is in the deployed state, the compression spring pushes the left end of the slider locking protrusion into the gap between the positioning protrusion of the support lug and the angle limiting protrusion of the fixed seat to lock the deployed state of the tail wing.

[0011] Beneficial effects:

[0012] The lateral folding tail fin stabilizing device of the present invention uses a torsion bar and a compression spring as the power source for tail fin deployment. Tail fin deployment only requires rotation, avoiding axial impact of the tail fin on the projectile body and greatly reducing the disturbance effect of tail fin deployment on the rocket's flight phase after exiting the muzzle. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the lateral folding tail fin stabilization device.

[0014] Figure 2 This is an axonometric view of the mounting base in the lateral folding tail fin stabilization device;

[0015] Figure 3 This is an axonometric view of the lugs in the lateral folding tail fin stabilization device;

[0016] Figure 4 This is an axonometric view of the slider in the lateral folding tail fin stabilization device;

[0017] Figure 5 A schematic diagram of the folded tail fin stabilization device.

[0018] Figure 6 A schematic diagram of the lateral folding tail stabilizer in its deployed state;

[0019] In the diagram, 1-tail wing frame, 2-tail wing, 3-support lug, 31-positioning protrusion, 4-slider, 41-connecting cylinder, 42-locking protrusion, 5-compression spring, 6-torsion bar, 7-fixed seat, 71-angle limiting protrusion, 72-slider clearance notch. Detailed Implementation

[0020] The present invention will now be further described in conjunction with the accompanying drawings and embodiments.

[0021] Example

[0022] like Figure 1 As shown, a low-disturbance lateral folding tail fin stabilization device of the present invention includes a tail fin frame 1, a tail fin 2, a fixing seat 7 fixed to the outer wall of the tail fin frame 1, a support lug 3 fixed to the bottom of the tail fin 2, a torsion bar 6 for rotatably connecting the tail fin frame 1 and the tail fin 2, a compression spring 5 for driving the tail fin 2 to move axially relative to the tail fin frame 1, and a slider 4 for locking the tail fin 2.

[0023] like Figure 2 As shown, the fixed seat 7 has a torsion bar 6 connecting hole axially opened in the middle part, the fixed seat 7 has a spring mounting cavity at the left end of the inner cavity, the fixed seat 7 has a slider clearance notch 72 axially opened inward along the upper outer edge of the left port, and the fixed seat 7 has an angle limiting protrusion 71 extending outward axially along the lower outer edge of the left port.

[0024] like Figure 3 As shown, a torsion bar connection hole is axially opened in the middle of the support lug 3, and a positioning protrusion 31 extending outward in the axial direction is provided at the right end of the support lug 3.

[0025] like Figure 4 As shown, the middle part of the slider 4 is a connecting cylinder 41 whose inner diameter matches the outer diameter of the torsion bar 6, and the outer wall of the slider 4 is provided with a locking protrusion 42 whose shape matches the inner shape of the slider 4 clearance notch of the fixed seat 7.

[0026] The two ends of the torsion bar 6 are respectively installed in the torsion bar connection holes of the lug 3 and the fixing seat 7, so that the tail wing 2 flips around the axis of the torsion bar 6 under the action of the torsion bar 6; the positioning protrusion 31 of the lug 3 and the angle limiting protrusion 71 of the fixing seat 7 are located in the same radial plane, and the tail wing 2 is limited in the flipping angle by the angle limiting protrusion 71 of the fixing seat 7; a compression spring 5 is installed in the mounting cavity of the compression spring 5 of the fixing seat 7, and the slider 4 is sleeved on the torsion bar 6; when the tail wing 2 is in the closed state, the locking protrusion 42 of the slider 4 slides into the slider 4 clearance notch of the fixing seat 7 and compresses the compression spring 5, such as Figure 5 As shown; when the tail fin 2 is in the deployed state, the compression spring 5 pushes the left end of the locking protrusion 42 of the slider 4 into the gap between the positioning protrusion 31 of the support lug 3 and the angle limiting protrusion 71 of the fixing seat 7, thereby locking the deployed state of the tail fin 2. Figure 6 As shown.

Claims

1. A low-disturbance lateral folding tail fin stabilization device, characterized in that, Includes a tail fin support, a tail fin, a mounting base fixed to the outer wall of the tail fin support, a lug fixed to the bottom of the tail fin, a torsion bar for rotatably connecting the tail fin support and the tail fin, a compression spring for driving the tail fin to move axially relative to the tail fin support, and a slider for locking the tail fin. The fixed seat has a torsion bar connection hole axially opened in the middle part, a spring mounting cavity is provided at the left end of the inner cavity of the fixed seat, a slider clearance notch is axially opened inward along the upper outer edge of the left port of the fixed seat, and an angle limiting protrusion extending outward along the lower outer edge of the left port of the fixed seat. The middle part of the support lug has an axially opened torsion bar connection hole, and the right end of the support lug is provided with a positioning protrusion extending outward in an axial direction. The middle part of the slider is a connecting cylinder whose inner diameter matches the outer diameter of the torsion bar, and the outer wall of the slider is provided with a locking protrusion whose shape matches the inner shape of the slider clearance notch of the fixed seat. The two ends of the torsion bar are respectively installed in the torsion bar connecting holes of the support lug and the fixed seat, so that the tail wing flips around the axis of the torsion bar under the action of the torsion bar; the positioning protrusion of the support lug and the angle limiting protrusion of the fixed seat are located in the same radial plane, and the tail wing is limited in the flipping angle by the angle limiting protrusion of the fixed seat; a compression spring is installed in the compression spring mounting cavity of the fixed seat, and the slider is sleeved on the torsion bar; when the tail wing is in the closed state, the locking protrusion of the slider slides into the slider clearance notch of the fixed seat and compresses the compression spring; when the tail wing is in the deployed state, the compression spring pushes the left end of the locking protrusion of the slider to slide into the gap between the positioning protrusion of the support lug and the angle limiting protrusion of the fixed seat, thereby locking the deployed state of the tail wing.

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