CN214582821U

CN214582821U - Tail pipe separating mechanism of engine

Info

Publication number: CN214582821U
Application number: CN202022744157.9U
Authority: CN
Inventors: 毕冬艳; 彭湃; 张立; 王迎
Original assignee: Beijing Aerospace Jiacheng Precision Technology Development Co ltd
Current assignee: Beijing Aerospace Jiacheng Precision Technology Development Co ltd
Priority date: 2020-11-24
Filing date: 2020-11-24
Publication date: 2021-11-02
Anticipated expiration: 2030-11-24

Abstract

The utility model discloses an engine tail pipe separating mechanism, which comprises a wing seat, a wing plate, a locking pin, a spring, a main spring and a tail pipe; the wing piece is arranged on the wing seat, when the wing piece is in a folded state, one end of the locking pin is in contact with the wing piece, the spring is compressed through the wing piece, and the other end of the locking pin is pressed into the clamping groove of the tail pipe, so that the tail pipe is connected with the wing seat and limited, and the main spring is compressed in the main spring mounting groove; the wing gradually loses the limit on the locking pin in the rotating and unfolding process, and the locking pin is displaced under the action of the spring to separate from the clamping groove of the tail pipe to unlock the tail pipe; after the wing piece is unfolded in place, the locking pin enters the pin hole of the wing piece to lock the wing piece. The utility model discloses a locking tail pipe is accomplished in the action that the fin expandes, unblock tail pipe and a series of actions of locking fin, and simple structure, overall arrangement are compact, do not influence pneumatic appearance, ensure that the shell stably flies.

Description

Tail pipe separating mechanism of engine

Technical Field

The utility model relates to an engine tail pipe that uses on the increase range shell breaks away from mechanism, the mechanism that makes the tail pipe break away from when concretely relates to utilizes folding fin to launch.

Background

The conventional range-extended cannonball comprises an engine, a spray pipe of the engine is positioned in the middle of a cannonball tail, and a tail pipe can influence the normal work of the spray pipe when the engine works, so that a tail pipe separating mechanism is often adopted. The tail pipe is used for installing propellant powder to ensure that the chamber pressure meets the use requirement when the projectile is launched; when flying, the tail pipe is separated from the engine by the tail pipe separating mechanism, so that the flying resistance of the cannonball is reduced.

The tail pipe separating mechanism is difficult to ensure that the tail pipe does not shake after being installed, propellant powder is influenced to excite ignition if the tail pipe shakes seriously, in addition, the separating time of the conventional tail pipe separating mechanism is uncontrollable, the flying resistance of the cannonball is increased if the time is too long, and the shooting range and the striking precision of the cannonball are directly influenced.

SUMMERY OF THE UTILITY MODEL

In view of this, the utility model provides an engine tail pipe breaks away from mechanism, the fin is in the tail pipe locking of mechanism when fold condition, accomplishes to the tail pipe unblock break away from and lock a series of actions of fin through the expansion actuating mechanism of fin, breaks away from simple structure, overall arrangement compactness, does not influence the aerodynamic shape to ensure the stable flight of shell.

A tail pipe release mechanism of an engine comprises a wing seat, a wing, a locking pin, a spring, a main spring and a tail pipe;

the wing seat is provided with a sinking platform matched with the tail pipe, the wing seat is also provided with a radial mounting hole communicated with the inner cavity of the sinking platform, and the mounting hole is used for mounting a spring and a locking pin; a main spring mounting groove is processed on the end face of one end, matched with the upper sinking platform of the wing seat, of the tail pipe, and a circumferential clamping groove is processed on the outer circular face of the end;

the wing piece is arranged on the wing seat, when the wing piece is in a folded state, one end of the locking pin is in contact with the wing piece, the spring is compressed through the wing piece, and the other end of the locking pin is pressed into the clamping groove of the tail pipe, so that the tail pipe is connected with the wing seat and limited, and the main spring is compressed in the main spring mounting groove; the wing gradually loses the limit on the locking pin in the rotating and unfolding process, and the locking pin is displaced under the action of the spring to separate from the clamping groove of the tail pipe to unlock the tail pipe; after the wing piece is unfolded in place, the locking pin enters the pin hole of the wing piece to lock the wing piece.

Furthermore, the axis of the locking pin is positioned at the front end of the axis of the rotating shaft of the wing, so that moment for promoting the unfolding of the wing is generated, and the wing is assisted to be smoothly unfolded.

Further, the axis of the rotating shaft of the fin is perpendicular to the moving direction of the locking pin.

Furthermore, four wing panels are arranged on the wing seat and are evenly distributed along the circumferential direction of the wing seat.

Further, the radial mounting hole on the wing seat is composed of two sections of hole sections with different diameters, the locking pin is composed of two sections of cylindrical sections with different diameters, the small-diameter section of the locking pin is matched with the small-hole section of the radial mounting hole, the large-diameter section of the locking pin is matched with the large-hole section of the radial mounting hole, the spring is sleeved on the small-diameter section of the locking pin and is positioned in a gap between the small-diameter section and the large-hole section, and two ends of the spring are respectively abutted to the step surface of the radial mounting hole and the step surface of the locking pin.

Has the advantages that:

1. the utility model discloses a series of motions that produce when utilizing the fin on the engine folding, expand lock the tail pipe respectively, unblock tail pipe, only to having carried out local structure processing on wing seat and the tail pipe, do not increase new mechanism and accomplish above-mentioned function, consequently can not influence the holistic pneumatic appearance of engine, do not increase the negative quality of engine.

2. The utility model is provided with four folding wing panels in the circumferential direction of the wing seat, and four locking pins can be used to evenly distribute in the circumferential direction to lock the tail pipe, so as to ensure the radial compression of the tail pipe without shaking, thereby ensuring the reliable installation of the propellant powder and the stable pressure of the projectile chamber; the tail pipe and the wing seat are longer in sleeved connection, so that the tail pipe is ensured to be installed reliably and free of radial shaking.

3. The utility model discloses well fitting pin's direction of motion and fin rotation axis do not coincide, and fitting pin pushes away the fin under the spring action always, produces the moment that promotes the fin and expand, and the auxiliary wing piece expandes smoothly. After the wing piece is unfolded in place, one end of the locking pin extends into the locking hole of the wing piece under the action of the spring, and the wing piece is reliably locked.

Drawings

FIG. 1 is a schematic view of a wing folding locking tail pipe and a wing unfolding unlocking tail pipe with a certain angle;

FIG. 2 is a schematic view of the locking pin locking tab after the tab is deployed in place;

FIG. 3 is a schematic view of a tailpipe structure;

fig. 4 is a schematic view of the fitting relationship between the locking pin and the spring in the mounting hole.

Wherein, 1-wing seat, 2-wing, 3-locking pin, 4-spring, 5-main spring, 6-tail tube.

Detailed Description

The present invention will be described in detail with reference to the accompanying drawings.

As shown in fig. 1 and 2, the utility model provides an engine tail pipe separation mechanism, which comprises a wing seat 1, a wing piece 2, a locking pin 3, a spring 4, a main spring 5 and a tail pipe 6;

the wing seat 1 is provided with a circular sinking platform matched with the tail pipe 6, the wing seat 1 is also provided with a radial mounting hole communicated with the inner cavity of the sinking platform, and the mounting hole is used for mounting the spring 4 and the locking pin 3; as shown in fig. 4, the radial mounting hole on the wing seat 1 is composed of two hole sections with different diameters; the locking pin 3 is of a head cap structure and consists of two cylindrical sections with different diameters, the small diameter section of the locking pin 3 is matched with the small hole section of the radial mounting hole, the large diameter section of the locking pin 3 is matched with the large hole section of the radial mounting hole, and the front end of the large diameter section of the locking pin 3 is of a ball head structure and is convenient to enter the locking hole of the fin 2; the spring 4 is sleeved on the small-diameter section of the locking pin 3 and is positioned in a gap between the small-diameter section and the large-hole section, and two ends of the spring 4 are respectively abutted against the step surface of the radial mounting hole and the step surface on the locking pin 3.

As shown in fig. 3, a main spring mounting groove is formed on the end surface of the end of the tail pipe 6, which is matched with the upper sinking platform of the wing seat 1, and a circumferential clamping groove is formed on the outer circumferential surface of the end.

The utility model discloses a fin 2 has folding, unblock tail pipe 6, expandes three kinds of states that target in place.

When the wing piece 2 is folded, the spring 4 is in a compressed state, the locking pin 3 extends into the tail pipe 6, and the wing piece 2 is uniformly distributed at the positions 4 in the circumferential direction of the wing seat 1 to reliably lock the tail pipe 6; after the wing piece 2 is discharged from the gun muzzle, the 15-degree locking pin 3 is radially displaced under the action of the spring 4 and is separated from the clamping groove of the tail pipe 6, and then the tail pipe 6 is unlocked, and the locking pin 3 promotes the wing piece 2 to be unfolded along the rotating shaft because the rotating moment generated by the locking pin 3 under the action of the spring 4 to the thrust of the wing piece 2 is positive moment; after the tail pipe 6 is unlocked by the locking pin 3, the tail pipe 6 is quickly separated from the projectile under the action of the main spring 5; along with the continued expansion of fin 2, fin 2 front end face and the contact of wing seat 1 rear end face, fin 2 expandes to target in place, and the locking pin 3 stretches into in the locking hole of fin 2 under the effect of spring 4 this moment, reliably locks fin 2.

In fig. 1, the wing pieces 2 are respectively in two states of folding and unfolding for unlocking the tail pipe 6 by a certain angle. The wing piece 2 is pressed the fitting pin 3 to lock the tail pipe 6 when being folded, after the projectile exits from the muzzle, the wing piece 2 starts to be unfolded under the action of the unfolding mechanism, the fitting pin 3 pushes the wing piece 2 to be unfolded around the wing piece rotating shaft under the action of the spring 4, a certain auxiliary effect is achieved, when the wing piece is unfolded by 15 degrees, the fitting pin 3 unlocks the tail pipe 6, and the tail pipe 6 is separated from the projectile under the action of the main spring 5.

In fig. 2, the wing piece 2 is unfolded in place under the action of the unfolding mechanism, the front end surface of the wing piece 2 is contacted with the rear end surface of the wing seat 1, the rotation is stopped, and the locking pin 3 locks the wing piece 2 in time under the action of the spring 4. The tail pipe 6 is locked under the starting state of the locking pin 3, the tail pipe 6 is unlocked in time along with the expansion of the wing piece 2, the wing piece 2 is locked finally, the structure is simple in form and multipurpose, and the locking pin 3 and the spring 4 are located on the inner side of the wing seat 1 and do not affect the pneumatic appearance of the projectile.

In summary, the above is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. The tail pipe separating mechanism of the engine is characterized by comprising a wing seat, a wing, a locking pin, a spring, a main spring and a tail pipe;

2. The tail pipe release mechanism according to claim 1, wherein the axis of the locking pin is located at a front end of the axis of the rotary shaft of the wing, and a moment for promoting the unfolding of the wing is generated to assist the smooth unfolding of the wing.

3. The engine tailpipe release mechanism according to claim 2, wherein the axis of the rotation shaft of said tab is perpendicular to the direction of movement of the locking pin.

4. The tail pipe release mechanism according to claim 3, wherein the wing seat is provided with four wings, and the wings are uniformly distributed in the circumferential direction of the wing seat.

5. The tail pipe release mechanism according to claim 4, wherein the radial mounting hole of the wing seat is formed by two hole sections having different diameters, the locking pin is formed by two cylindrical sections having different diameters, a small diameter section of the locking pin is engaged with a small hole section of the radial mounting hole, a large diameter section of the locking pin is engaged with a large hole section of the radial mounting hole, the spring is fitted over the small diameter section of the locking pin and positioned in a gap between the small diameter section and the large hole section, and both ends of the spring are respectively abutted against a step surface of the radial mounting hole and a step surface of the locking pin.