CN107816914B - A stranded tail cowl separation device based on large-impulse collision braking and buffering - Google Patents

Abstract

The invention discloses a stranded tail cowl separation device based on large-impulse collision braking and buffering, which belongs to the technical field of missile launching, and comprises: an accommodation shell, a metal shearing sheet group, a positioning block, a force transmission seat and a limiting column; The tail cover is installed on the outer circumference of the missile body; both the missile body and the tail cover are installed in the launch tube; the vertical part of one side of the force transmission seat is opposite to the tail cover, and the horizontal part of the other side is cut with the metal The long metal sheets of the sheet group are opposite; the positioning block is installed on the upper surface of the horizontal part of the force transmission base, one end of the two or more limit posts is installed in the positioning block, and the other end passes through the through hole of the metal shearing sheet group; The casing is a casing with two side openings and one end face opening. After the accommodating casing is fastened on the positioning block and the metal shearing plate group through its end face openings, it is fixedly connected with the launching cylinder; the device is simple in principle, compact in structure, And the missile body and tail cover can be separated quickly, safely and reliably.

Description

A stranded tail cowl separation device based on large-impulse collision braking and buffering

technical field

The invention belongs to the technical field of missile launching, and in particular relates to a stranded tail cowl separating device based on large-impulse collision braking and buffering.

Background technique

The missile body is pushed and ejected by the high temperature and high pressure gas generated by the ejection power device at the bottom of the launch cylinder. In order to avoid the high temperature and high pressure gas from causing damage to the engine and electromechanical equipment at the tail end of the missile during ejection, a tail cover is usually used to protect and bear the missile body. effect. When the missile body is out of the barrel, the tail cover must be separated in time to make the engine ignition work.

At present, there are two main ways to separate the tail cover: 1) Separation side push method: first, the explosion bolt is unlocked, the tail cover is separated from the tail end of the missile body by the pre-tightening force of the separation spring, and then the small rocket inside the tail cover is ignited to make the tail cover The cover is far away from the launch vehicle; 2) Rotation separation method: first, the explosion bolt is unlocked, and then the tail cover is rotated around the swivel lug on one side of the projectile by the pre-tightening force of the separation spring, and the tail cover is separated from the missile when it turns to a certain safe separation angle. body and away from the launch vehicle. Both of these two tail cover separation schemes are carried out after the missile body exits the barrel, and the separation device is complicated. However, the tail cover separation is the first separation link of the missile separation sequence, and its requirements are fast, reliable and safe. , the existing tail cowl separation device fails to meet this requirement.

SUMMARY OF THE INVENTION

In view of this, the present invention provides a stagnant tail cowl separation device based on large impulse collision braking and buffering, which is simple in principle, compact in structure, and can quickly, safely and reliably separate the missile body from the tail cowl.

The present invention is achieved through the following technical solutions:

A stranded tail cowl separating device based on large-impulse collision braking and buffering, comprising: an accommodating shell, a metal shearing plate group, a positioning block, a force transmission seat, a positioning pin and a limit column;

The overall connection relationship is as follows: the tail cover is installed on the outer circumferential surface of the missile body through the positioning pin; the missile body and the tail cover are both installed in the launch cylinder; hole;

The force transmission seat is a T-shaped structure, the lower surface of the horizontal part is fitted on the outer circumferential surface of the launch cylinder, and the vertical part passes through the bar-shaped through hole of the launch cylinder, which is not the same as the outer circumferential surface of the missile body. contact, and the force transmission seat can move along the axial direction of the launch cylinder in the strip through hole of the launch cylinder;

The metal shearing piece group is formed by long metal pieces and short metal pieces arranged at intervals; the metal cutting piece group is installed on the outer circumferential surface of the launch cylinder, and the long metal pieces and the short metal pieces are closely arranged along the axial direction of the missile body. Arrangement; more than two through holes along the axial direction of the missile body are machined on the metal shearing plate group;

The vertical part of one side of the force transmission seat is opposite to the tail cover, and the horizontal part of the other side is opposite to the long metal sheet of the metal shearing plate group;

The positioning block is installed on the upper surface of the horizontal part of the force transmission seat, one end of the two or more limit posts is installed in the positioning block, and the other end passes through the through hole of the metal shearing plate group;

The accommodating shell is a shell with two side openings and one end face opening. The accommodating shell is fastened to the positioning block and the metal shearing sheet group through the end face openings. The two side openings are distributed along the axial direction of the missile body. , which is fixedly connected to the launch tube.

Further, the upper surface of the horizontal portion of the force transmission seat is flush with the lower end surface of the short metal pieces of the metal shearing piece group.

Further, a set distance is left between the upper surface of the horizontal part of the force transmission seat and the lower end surface of the short metal pieces of the metal shearing piece group.

Further, when the missile body moves toward the outlet end of the launch cylinder, the tail cover drives the horizontal part of the force transmission base to collide with the metal shearing plate group.

Beneficial effects: (1) When the missile body of the present invention is ejected from the launch cylinder, the tail cover cuts the metal shearing sheet group through the force transmission seat to make it break and deform, and the tail cover is blocked from continuing to advance, so as to realize the missile body and the tail cover. The relative speed difference of the missile body and the tail cover can be achieved naturally and safely.

(2) The present invention adopts the metal shearing plate group as the buffer device, which can effectively brake the tail cover, shorten the buffering time, and improve the buffering efficiency.

(3) The tail cowl of the present invention stays in the launch tube, which avoids the uncertainty of the tail cowl being thrown out of the tube, and the uncertainty of its high-altitude fall, and the risk of smashing instruments and equipment and casualties, and improving the safety of tail cowl separation. sex.

(4) The missile body and the tail cover of the present invention are connected by positioning pins, and the structure is simple, so that the separation reliability of the missile body and the tail cover is increased, and the economic cost is also reduced.

Description of drawings

Fig. 1 is a structural composition diagram of the present invention.

FIG. 2 is a schematic view of the structure of the present invention installed on the launch tube.

FIG. 3 is a working principle diagram of the present invention.

Among them, 1- missile body, 2- tail cover, 3- launch tube, 4- receiving shell, 5- metal shearing plate group, 6- positioning block, 7- power transmission seat, 8- positioning pin, 9- limit post.

Detailed ways

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

The present invention provides a stagnant tail cowl separation device based on large-impulse collision braking and buffering, referring to FIG. 1 , including: an accommodating shell 4 , a metal shearing sheet group 5 , a positioning block 6 , a force transmission seat 7 , a positioning Pin 8 and limit post 9;

The overall connection relationship is as follows: Referring to Figure 2, the tail cover 2 is installed on the outer circumferential surface of the missile body 1 through the positioning pin 8; the missile body 1 and the tail cover 2 are both installed in the launch cylinder 3; the circumference of the outlet end of the launch cylinder 3 The surface is machined with strip through holes along its axial direction;

The force transmission seat 7 is a T-shaped structure, and the lower surface of its horizontal part is attached to the outer circumferential surface of the launch cylinder 3, and its vertical part passes through the bar-shaped through hole of the launch cylinder 3, and is connected to the outer circumference of the missile body 1. The surfaces are not in contact, and the force transmission base 7 can move along the axial direction of the launch cylinder 3 in the bar-shaped through hole of the launch cylinder 3;

The metal shearing plate group 5 is composed of twenty groups of metal shearing plates, all of which are installed on the outer circumferential surface of the launch cylinder 3 and are closely arranged along the axial direction of the missile body 1; The set of metal shearing pieces are all made of a long metal piece and a short metal piece. The long metal piece and the short metal piece have the same size along the circumferential direction of the missile body 1, and the heights along the radial direction of the missile body 1 are different. In this embodiment, the thickness of the long metal sheet along the axial direction of the missile body 1 is 3 mm, the thickness of the short metal sheet along the axial direction of the missile body 1 is 2 mm, and the total thickness of the metal shearing sheet group 5 is 100 mm; The slice group 5 is machined with more than two circular through holes penetrating through its thickness;

Among them, the vertical part of one side of the power transmission seat 7 is opposite to the tail cover 2, the horizontal part of the other side is opposite to the long metal sheet of the metal shearing plate group 5, and the upper surface of the horizontal part of the power transmission seat 7 is opposite to the metal The lower end surface of the short metal pieces of the shearing blade group 5 is flush or the upper surface of the horizontal part of the force transmission base 7 is lower than the lower end surface of the short metal pieces of the metal shearing blade group 5;

The positioning block 6 is installed on the upper surface of the horizontal part of the force transmission base 7. The positioning block 6 is machined with circular through holes uniformly distributed along the circumference of the missile body 1. The axial direction of the circular through hole is the same as that of the missile body 1. Axial consistency;

One end of the two or more limiting columns 9 is located in the circular through hole of the positioning block 6, and the other end passes through the circular through hole of the metal shearing sheet group 5;

The accommodating casing 4 is a casing with two side openings and one end face opening. The accommodating casing 4 is fastened on the positioning block 6 and the metal shearing sheet group 5 through its end face openings, and its two side openings are along the missile body 1. After the axial distribution, it is fixedly connected with the launch cylinder 3.

Working principle: Referring to Figure 3, when the missile body 1 moves to the outlet end of the launch tube 3, the tail cover 2 is driven to hit the vertical part of the force transmission seat 7 at a set speed, and the force transmission seat 7 is driven to launch along the The bar-shaped through hole of the barrel 3 moves, and then the horizontal part of the force transmission seat 7 collides with the metal shearing plate group 5; under the reaction force of the metal shearing plate group 5 to the tail cover 2, the tail cover 2 and the missile body 1 A relative speed difference is formed between the two, the positioning pins 8 connected between the two begin to bend and break, and the tail cover 2 and the missile body 1 begin to separate; the tail cover 2 continues to drive the force transmission seat 7 to cut the metal shearing piece group under the action of inertia. 5. At the same time, after the metal shearing plate group 5 absorbs energy, it blocks the tail cover 2 and the force transmission seat 7 from further advancing until the tail cover 2 decelerates to a standstill, so as to realize the buffer braking effect on the tail cover 3 and realize the missile body. 1 and the tail cover 2 are quickly, safely and reliably separated, and the tail cover 3 is retained in the launch tube 3.

To sum up, the above are only preferred embodiments of the present invention, and are not intended to limit the protection scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims (4)

1. a kind of detention hood separator based on big momentum collision brake buffering,

Hood (2) is mounted on the outer circumference surface of missile airframe (1) by positioning pin (8)；Missile airframe (1) and hood (2) are pacified In launching tube (3)；It is characterized in that, separator further include: accommodate shell (4), metal shears slice group (5), locating piece (6), force-transmitting seat (7) and limited post (9)；It is machined on the periphery of launching tube (3) outlet end along its axial strip through-hole；

The force-transmitting seat (7) is T-shaped structure, and horizontal component lower surface is jointly mounted to the outer circumference surface of launching tube (3), After vertical portion passes through the strip through-hole of launching tube (3), do not contacted with the outer circumference surface of missile airframe (1), and force-transmitting seat (7) energy The interior axial movement along launching tube (3) of enough strip through-holes in launching tube (3)；

The metal shears slice group (5) is alternatively arranged by long sheet metal and short sheet metal；Metal shears slice group (5) is mounted on On the outer circumference surface of launching tube (3), the axial close-packed arrays of long sheet metal and short sheet metal along missile airframe (1)；Metal sheet slitting More than two through-holes along missile airframe (1) axial direction are machined in piece group (5)；

The vertical portion of the side of force-transmitting seat (7) and hood (2) relatively, the horizontal component and metal shears slice group (5) of the other side Long sheet metal it is opposite；

Locating piece (6) is mounted on the horizontal component upper surface of force-transmitting seat (7), and one end of more than two limited posts (9) is mounted on In locating piece (6), the other end passes through the through-hole of metal shears slice group (5)；

The shell that shell (4) are two side openings and end face opening is accommodated, shell (4) is accommodated and passes through its end face opening button In locating piece (6), metal shears slice group (5), two side is open after the axial distribution of missile airframe (1), with hair Shooting cylinder (3) is fixedly connected.

2. a kind of detention hood separator based on big momentum collision brake buffering as described in claim 1, feature It is, the upper surface of force-transmitting seat (7) horizontal component is concordant with the lower end surface of short sheet metal of metal shears slice group (5).

3. a kind of detention hood separator based on big momentum collision brake buffering as described in claim 1, feature Be, the lower end surface of the short sheet metal of the upper surface and metal shears slice group (5) of force-transmitting seat (7) horizontal component there are setting away from From.

4. a kind of detention hood separator based on big momentum collision brake buffering as described in claim 1, feature It is, when missile airframe (1) is mobile to the outlet end of launching tube (3), hood (2) drives the horizontal component of force-transmitting seat (7) to hit To metal shears slice group (5).