CN220288427U - Rear tail fin of light high-hardness missile - Google Patents

Abstract

The utility model relates to the technical field of missile empennages and discloses a light high-hardness missile rear empennage, which comprises a missile body, wherein the surface of the missile body is fixedly connected with a fixing ring, the surface of the fixing ring is fixedly connected with a missile wing, the surface of the missile body is provided with an adjusting device, when the light high-hardness missile rear empennage is installed, a mounting hole formed in the surface of a mounting plate is aligned with a pre-mounting bolt, a unidirectional nut is aligned with the pre-mounting bolt to be mounted, when the unidirectional nut is clockwise rotatably mounted, an inclined clamping block can rotate clockwise along with the unidirectional nut, the inclined clamping block can abut against a triangular groove to continuously rotate the unidirectional nut, the inclined surface of the inclined clamping block abuts against the triangular groove, and meanwhile the inclined clamping block is contracted through a spring, so that the unidirectional nut can be continuously mounted, but when the missile flies, the inclined clamping block is tightly clamped with the triangular groove due to the inclined reverse rotation, and the unidirectional nut cannot rotate anticlockwise when the missile body flies.

Description

Rear tail fin of light high-hardness missile

Technical Field

The utility model relates to the technical field of missile empennages, in particular to a light high-hardness missile rear empennage.

Background

The missile is an aircraft which carries a warhead, is propelled by a self-powered device, guides and controls a flight path by a guidance system, guides a target and destroys the target. Missiles are typically comprised of warheads, control systems, engine units, and projectiles.

The payload of the target for missile destruction is a warhead (or warhead) which may be a nuclear charge, a conventional charge, a chemical warfare agent, a biological warfare agent, or an electromagnetic pulse warhead. Wherein, the common missile is filled with common charges; core-loaded missile. The outstanding performance characteristics of missile weapons are long range, high precision, high power and strong burst prevention capability.

But the missile is when the installation of fin, needs to guarantee stability and accuracy when flying through multiple connected modes such as welding and threaded connection, and vibrations when many bolts are after the installation, probably lead to the loosening of bolt, and ordinary fin also can't accomplish the speed-up effect simultaneously.

Disclosure of Invention

The utility model aims to provide a light high-hardness missile rear tail wing so as to solve the problems in the background technology.

In order to achieve the above purpose, the present utility model provides the following technical solutions: the utility model provides a fin behind light high rigidity guided missile, includes the body, the fixed ring of fixed surface fixedly connected with of body, the fixed surface fixedly connected with missile wing of ring, the surface of body is provided with adjusting device, adjusting device includes: the mounting panel, the mounting panel is laminated mutually with the surface of projectile body, and the mounting hole has been seted up on the surface of mounting panel, the fixed surface of mounting panel is connected with the fin, the water conservancy diversion hole has been seted up on the surface of fin, the fin is kept away from the one end fixed surface of mounting panel and is connected with the water conservancy diversion piece, be run through by branch in the water conservancy diversion hole that the fin surface was seted up, and branch and fin fixed connection, branch runs through the guide plate, and branch and guide plate rotate to be connected, and the projectile body is when flying, through the water conservancy diversion hole, makes the air current in flight remove along the water conservancy diversion hole, and the air current can promote the guide plate simultaneously, makes the guide plate strut to make whole projectile body rotate, makes the speed of projectile body accelerate, also more stable simultaneously.

Preferably, the surface fixedly connected with of elastomer is the installation bolt in advance, installation bolt threaded connection has one-way nut in advance, the triangular groove has been seted up on the screw thread of installation bolt in advance, one-way nut inner wall fixedly connected with quarter butt, the quarter butt runs through oblique fixture block, one side surface fixedly connected with spring that the oblique fixture block is close to the quarter butt, the one end and the inner wall fixed connection of one-way nut of oblique fixture block are kept away from to the spring, the one-way nut is run through to the oblique fixture block, and oblique fixture block and one-way nut sliding connection, with mounting hole and the installation bolt alignment of installing plate surface, install one-way nut alignment installation bolt simultaneously, continue to rotate one-way nut, the inclined plane and the triangular groove conflict of oblique fixture block.

Preferably, the number of the inclined clamping blocks is two, and the two inclined clamping blocks are symmetrically arranged by taking the central line of the unidirectional nut as a symmetrical axis respectively, the unidirectional nut is continuously rotated, the inclined surface of the inclined clamping block is abutted against the triangular groove, and the inclined clamping block is abutted against the triangular groove to be clamped when the inclined clamping block reversely rotates in the missile flight.

Preferably, the number of the tail wings is four, and the four tail wings are arranged in a circumferential array by taking the central line of the projectile body as an axis.

Preferably, the number of the missile wings is six, and the six missile wings are arranged in a circumferential array by taking the central line of the fixed ring as an axis.

Preferably, the number of the unidirectional nuts is eighteen, every two unidirectional nuts are nine groups, and the nine groups of unidirectional nuts are respectively in threaded connection with the pre-installation bolts.

Compared with the prior art, the utility model provides the rear tail fin of the light high-hardness missile, which has the following beneficial effects:

1. this fin behind light high rigidity guided missile is when the installation, with mounting hole and the preinstallation bolt alignment of mounting panel surface offer, install the preinstallation bolt with one-way nut alignment simultaneously, when one-way nut clockwise rotation installs, the one-way nut clockwise rotation can be followed to the skew block, the skew block can conflict with the triangular groove, continue to rotate one-way nut, the inclined plane of skew block is contradicted with the triangular groove, make the skew block shrink simultaneously through the spring, and then make one-way nut can continue to install, but when guided missile flight, because the skew block can contradict the chucking with the triangular groove when rotating in opposite directions, make the body can not lead to one-way nut anticlockwise rotation because of vibrations when flying.

2. When the rear tail wing of the light high-hardness missile flies, airflow in flying moves along the airflow guiding holes through the airflow guiding holes, meanwhile, the airflow can push the airflow guiding plates to open the airflow guiding plates, and the whole tail wing rotates through the Bernoulli effect, so that the whole missile body rotates, the speed of the missile body is accelerated, and the speed of the missile body is more stable.

Drawings

FIG. 1 is a schematic elevational view of the present utility model;

FIG. 2 is a schematic view of the tail structure of the present utility model;

FIG. 3 is a schematic view of a partial enlarged structure of the tail wing of the present utility model;

FIG. 4 is a schematic view of the enlarged structure of FIG. 3A according to the present utility model;

FIG. 5 is a schematic view of the internal structure of the one-way nut of the present utility model;

fig. 6 is a schematic front view of the unidirectional nut of the present utility model.

In the figure: 1. a shell body; 2. an adjusting device; 21. a mounting plate; 22. a tail wing; 23. a deflector aperture; 24. a flow guiding block; 25. a support rod; 26. a deflector; 27. pre-installing bolts; 28. a one-way nut; 29. triangular grooves; 210. a short bar; 211. a spring; 212. a sloping clamping block; 3. a fixing ring; 4. and the missile wing.

Detailed Description

As shown in fig. 1-6, the present utility model provides a technical solution: the utility model provides a fin behind light high hardness guided missile, includes projectile body 1, and the fixed ring 3 of fixed surface fixedly connected with of projectile body 1, the fixed ring 3 of fixed surface fixedly connected with missile wing 4, and the surface of projectile body 1 is provided with adjusting device 2, and adjusting device 2 includes: the mounting panel 21, the mounting panel 21 is laminated with the surface of projectile body 1 mutually, and the mounting hole has been seted up on the surface of mounting panel 21, the fixed surface of mounting panel 21 is connected with fin 22, the water conservancy diversion hole 23 has been seted up on the surface of fin 22, the one end fixed surface that the mounting panel 21 was kept away from to fin 22 is connected with guide block 24, be run through by branch 25 in the water conservancy diversion hole 23 that fin 22 surface was seted up, and branch 25 and fin 22 fixed connection, branch 25 runs through guide plate 26, and branch 25 and guide plate 26 rotate and are connected, during the flight of projectile body 1, make the air current in flight remove along guide hole 23 through water conservancy diversion hole 23, the air current can promote guide plate 26 simultaneously, make guide plate 26 prop up, through Bernoulli effect, make whole fin 22 rotate, thereby make whole projectile body 1 rotate, make the speed of projectile body 1 accelerate, simultaneously also more stable. The surface fixedly connected with of body 1 is the installation bolt 27 in advance, installation bolt 27 threaded connection has one-way nut 28 in advance, the triangular groove 29 has been seted up on the screw thread of installation bolt 27 in advance, one-way nut 28 inner wall fixedly connected with quarter butt 210, the quarter butt 210 runs through oblique fixture block 212, one side surface fixedly connected with spring 211 that is close to quarter butt 210 of oblique fixture block 212, the one end that spring 211 kept away from oblique fixture block 212 and the inner wall fixed connection of one-way nut 28, oblique fixture block 212 runs through one-way nut 28, and oblique fixture block 212 and one-way nut 28 sliding connection, the mounting hole that sets up on the mounting panel 21 surface aligns with installation bolt 27, install one-way nut 28 alignment installation bolt 27 simultaneously, when one-way nut 28 clockwise rotation installation, oblique fixture block 212 can follow one-way nut 28 clockwise rotation, when one-way nut 28 rotates a certain distance, oblique fixture block 212 can conflict with triangular groove 29, continue to rotate one-way nut 28, the inclined plane of oblique fixture block 212 is contradicted with triangular groove 29. The number of the inclined clamping blocks 212 is two, the two groups of inclined clamping blocks 212 are symmetrically arranged by taking the central line of the unidirectional nut 28 as a symmetrical axis, the unidirectional nut 28 is continuously rotated, the inclined surface of the inclined clamping block 212 is in conflict with the triangular groove 29, meanwhile, the inclined clamping block 212 is contracted through the spring 211, and then the unidirectional nut 28 can be continuously installed, but when a missile flies, the inclined clamping blocks 212 are in conflict clamping with the triangular groove 29 when rotating reversely. The number of the tail fins 22 is four, and the four groups of tail fins 22 are arranged in a circumferential array by taking the central line of the projectile body 1 as an axis. The number of the missile wings 4 is six, and the six missile wings 4 are arranged in a circumferential array by taking the central line of the fixed ring 3 as an axis. The number of the unidirectional nuts 28 is eighteen, and each two unidirectional nuts 28 are nine groups, and the nine groups of unidirectional nuts 28 are respectively in threaded connection with the pre-installation bolts 27.

Working principle: when the rear tail wing of the light high-hardness missile is installed, the installation hole formed in the surface of the installation plate 21 is aligned with the pre-installation bolt 27, meanwhile, the unidirectional nut 28 is aligned with the pre-installation bolt 27 for installation, when the unidirectional nut 28 is installed in a clockwise rotating mode, the inclined clamping block 212 can rotate clockwise along the unidirectional nut 28, when the unidirectional nut 28 rotates a certain distance, the inclined clamping block 212 can collide with the triangular groove 29 to continuously rotate the unidirectional nut 28, the inclined surface of the inclined clamping block 212 collides with the triangular groove 29, meanwhile, the inclined clamping block 212 is contracted through the spring 211, and then the unidirectional nut 28 can be continuously installed, but when the missile flies, the inclined clamping block 212 can collide with the triangular groove 29 for clamping because the inclined clamping block 212 reversely rotates, so that the unidirectional nut 28 cannot rotate anticlockwise due to vibration, meanwhile, during flying of the missile body 1, airflow moves along the guide hole 23, meanwhile, the guide plate 26 can be pushed to open by the airflow, the whole tail wing 22 rotates through the Bernoulli effect, and therefore the whole missile body 22 can rotate, and the speed of the missile body 1 is accelerated, and is stable.

The foregoing utility model has been generally described in great detail, but it will be apparent to those skilled in the art that modifications and improvements can be made thereto. Accordingly, it is intended to cover modifications or improvements within the spirit of the inventive concepts.

Claims (6)

1. The utility model provides a rear fin of light high rigidity guided missile, includes projectile body (1), its characterized in that: the surface fixedly connected with solid fixed ring (3) of elastomer (1), the surface fixedly connected with missile wing (4) of solid fixed ring (3), the surface of elastomer (1) is provided with adjusting device (2), adjusting device (2) include:

mounting panel (21), mounting panel (21) laminate with the surface of projectile body (1), and the mounting hole has been seted up on the surface of mounting panel (21), the fixed surface of mounting panel (21) is connected with fin (22), water conservancy diversion hole (23) have been seted up on the surface of fin (22), one end fixed surface that mounting panel (21) was kept away from to fin (22) is connected with water conservancy diversion piece (24), be run through by branch (25) in water conservancy diversion hole (23) that fin (22) surface was seted up, and branch (25) and fin (22) fixed connection, branch (25) run through guide plate (26), and branch (25) are rotated with guide plate (26) and are connected.

2. The rear tail of a lightweight high stiffness missile of claim 1, wherein: the surface fixedly connected with of elastomer (1) is installed bolt (27) in advance, install bolt (27) threaded connection in advance has one-way nut (28), triangular groove (29) have been seted up on the screw thread of installing bolt (27) in advance, one-way nut (28) inner wall fixedly connected with quarter butt (210), quarter butt (210) run through oblique fixture block (212), one side surface fixedly connected with spring (211) that oblique fixture block (212) are close to quarter butt (210), one end and the inner wall fixed connection of one-way nut (28) of oblique fixture block (212) are kept away from to spring (211), oblique fixture block (212) run through one-way nut (28), and oblique fixture block (212) and one-way nut (28) sliding connection.

3. A lightweight high stiffness missile rear tail according to claim 2 wherein: the number of the inclined clamping blocks (212) is two, and the two inclined clamping blocks (212) are symmetrically arranged by taking the central line of the unidirectional nut (28) as a symmetrical axis.

4. The rear tail of a lightweight high stiffness missile of claim 1, wherein: the number of the tail fins (22) is four, and the four tail fins (22) are arranged in a circumferential array by taking the central line of the projectile body (1) as an axis.

5. The rear tail of a lightweight high stiffness missile of claim 1, wherein: the number of the missile wings (4) is six, and the six missile wings (4) are arranged in a circumferential array by taking the central line of the fixed ring (3) as an axis.

6. A lightweight high stiffness missile rear tail according to claim 2 wherein: the number of the unidirectional nuts (28) is eighteen, every two unidirectional nuts (28) are nine groups, and the nine groups of unidirectional nuts (28) are respectively in threaded connection with the pre-installation bolts (27).