CN111412784B

CN111412784B - Anti-rebound device suitable for bullet fixing mechanism of shrapnel separating device

Info

Publication number: CN111412784B
Application number: CN202010256135.XA
Authority: CN
Inventors: 李微微; 张保刚; 俞刘建; 夏津; 刘广; 许斌; 曾清香; 李欣益; 张宏程; 王波兰
Original assignee: Shanghai Institute of Electromechanical Engineering
Current assignee: Shanghai Institute of Electromechanical Engineering
Priority date: 2020-04-02
Filing date: 2020-04-02
Publication date: 2022-04-22
Anticipated expiration: 2040-04-02
Also published as: CN111412784A

Abstract

The invention provides an anti-bounce device suitable for a fixing and bouncing mechanism of a shrapnel separating device, which comprises a crank seat, an anti-bounce component and a four-bar linkage, wherein the crank seat is provided with a first accommodating space, the anti-bounce component is arranged in the first accommodating space, the anti-bounce component is provided with a stop pin, when a missile is launched, the four-bar linkage rotates around a fixed rotating shaft from an initial position to unlock the missile and expose the shielded anti-bounce component, and the stop pin pops out of the anti-bounce component and extends to the outside of the crank seat to limit the four-bar linkage to return to the initial position. Simple structure, safety and reliability.

Description

Anti-rebound device suitable for bullet fixing mechanism of shrapnel separating device

Technical Field

The invention relates to the technical field of anti-rebound in a weapon system, in particular to an anti-rebound device suitable for a bullet-proof mechanism of a shrapnel separating device.

Background

The missile is fixed and separated in an unlocking way through the connecting rod missile fixing mechanism in the storage, transportation and launching processes of the missile. When the missile is launched, the connecting rod missile fixing mechanism moves rightwards and downwards along the axis of the rotating shaft, the missile fixing mechanism completes unlocking, and the missile is separated from the axial restraint of the connecting rod to realize separation. In order to prevent the connecting rod from rebounding after the bullet fixing mechanism is separated and interfering the movement of the missile, a tension spring is often adopted for preventing rebounding or a rubber pad is adopted for buffering under the condition of small launching impact, and if the tension spring or the rubber pad is still adopted under the condition of large launching impact, hidden danger can be brought to the safety of missile launching because the rebounding of the bullet fixing mechanism cannot be completely inhibited.

Patent document CN201788090U discloses an automatic anti-bounce device, which aims to provide an automatic anti-bounce device for preventing model bounce from damaging equipment in an automobile safety experiment. Including the infrared inductor that is used for the sensing to pass through from the passageway object, the object can shelter from the adjustable fender of passageway and the control unit that control adjustable fender removed after passing through, adjustable fender articulates perpendicularly on the stand on bottom plate surface, the one side of passageway is located to the stand, is equipped with the spacing post that can block adjustable fender pivoted at the opposite side of passageway, the probe of infrared inductor is located in the passageway between stand and the spacing post, but this project organization is complicated, and is with high costs, designs unreasonablely.

Disclosure of Invention

Aiming at the defects in the prior art, the invention aims to provide an anti-rebound device suitable for a bullet fixing mechanism of a shrapnel separating device.

The invention provides an anti-rebound device suitable for a bullet fixing mechanism of a shrapnel separating device, which comprises a crank base 5, an anti-rebound assembly and a four-bar mechanism;

a first accommodating space is formed in the crank base 5, and the anti-rebound assembly is installed in the first accommodating space;

and the anti-bounce component is provided with a stop pin 1, when a missile 8 is launched, the four-bar mechanism rotates around the fixed rotating shaft 6 from an initial position to unlock the missile 8 and expose the shielded anti-bounce component, and at the moment, the stop pin 1 is popped out of the anti-bounce component and extends to the outside of the crank base 5 so as to limit the four-bar mechanism to return to the initial position.

Preferably, the four-bar linkage is provided with a translational connecting bar 7, a left crank 9, a right crank 11, two fixed rotating shafts 6 and two movable rotating shafts 12;

one end of each of the left crank 9 and the right crank 11 is mounted on the crank base 5 through two fixed rotating shafts 6, the other end of each of the left crank 9 and the right crank 11 is mounted on the translational connecting rod 7 through two movable rotating shafts 12, wherein the left crank 9 blocks the stop pin 1 from popping out of the anti-rebound assembly at the initial position, and when the left crank 9 rotates around the fixed rotating shafts 6 to expose the stop pin 1, the stop pin 1 pops out of the anti-rebound assembly and prevents the left crank 9 from rotating back to the initial position.

Preferably, the anti-rebound assembly comprises a compression spring 2, a set screw 3 and a threaded sleeve 4;

the inside of threaded sleeve 4 is provided with the second accommodation space, backing pin 1, pressure spring 2, holding screw 3 set gradually in the second accommodation space.

Preferably, the stop pin 1 is of a T-shaped structure, one end of the stop pin 1 is disposed inside the second accommodating space, and the other end of the stop pin 1 can extend to the outside of the threaded sleeve 4 under the driving of the elastic force of the pressure spring 2.

Preferably, a first internal thread is arranged inside one end of the threaded sleeve 4 where the set screw 3 is installed, an external thread is arranged on the circumference of the set screw 3, and the screw 3 is installed on the first internal thread on the threaded sleeve 4 through matching of the external thread.

Preferably, one end of the threaded sleeve 4 away from the pressure spring 2 is provided with a linear groove 10.

Preferably, the stop pin 1 and the pressure spring 2 are detachably connected or welded.

Preferably, the inner wall of the first accommodating space is provided with a second internal thread, the circumferential direction of the threaded sleeve 4 is provided with a second external thread, and the threaded sleeve 4 is mounted on the second internal thread of the first accommodating space through the second external thread in a matching manner.

Preferably, the catch pin 1 is movable between a first position and a second position, wherein the compression spring 2 is always in a compressed state.

Preferably, the threaded sleeve 4 and the stop pin 1 matched with the threaded sleeve 4 can be changed into different sizes according to actual requirements so as to meet the requirements of launching different types of missiles 8.

Compared with the prior art, the invention has the following beneficial effects:

1. according to the invention, the anti-rebound assembly is arranged on the crank base 5, and the stop pin can be automatically popped out through the combination of the spring, so that the problem of unsafe missile caused by the fact that the rebound of the fixed-bounce mechanism cannot be completely inhibited by adopting a tension spring or a rubber pad in the prior art is solved, the rebound of the four-bar mechanism is rigidly and effectively blocked, and the four-bar mechanism has a simple structure, and is safe and reliable.

2. According to the invention, the first accommodating space is arranged on the crank base 5 and is arranged in the rotating area of the left crank 9, the rebound of the four-bar mechanism is prevented through the simple stop pin 1, and the crank mechanism is simple in structure and ingenious in design.

3. Prevent bounce-back subassembly adopts including backing pin 1, pressure spring 2, holding screw 3 and threaded sleeve 4 and will backing pin 1 sets up to T type structure, has realized that backing pin 1 auto-eject stops, and the practicality is strong.

4. The invention can match the threaded sleeves 4 and the stop pins 1 with different sizes according to different missiles and the crank bases 5 so as to meet the requirements of launching the missiles 8 with different models, and has wide application range.

Drawings

Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:

FIG. 1 is a schematic structural view of the present invention;

FIG. 2 is a schematic sectional view of the structure taken along the line A-A in FIG. 1;

FIG. 3 is a schematic structural view of the anti-rebound assembly when the stop pin 1 is not ejected;

FIG. 4 is a schematic structural view of the anti-rebound assembly preventing rebound of the left crank 9;

FIG. 5 is a schematic cross-sectional view taken along line B-B of FIG. 4;

FIG. 6 is a schematic structural view of the anti-rebound assembly when the stop pin 1 is ejected;

fig. 7 is a schematic structural view of the threaded sleeve 4.

The figures show that:

Detailed Description

The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.

The invention provides an anti-rebound device suitable for a bullet separating device bullet fixing mechanism, which comprises a crank base 5, an anti-rebound assembly and a four-bar mechanism, as shown in figure 1; the four-bar mechanism is provided with a translational connecting bar 7, a left crank 9, a right crank 11 and two fixed rotating shafts 6; one ends of the left crank 9 and the right crank 11 are respectively arranged on the crank seat 5 through two fixed rotating shafts 6, and the other ends of the left crank 9 and the right crank 11 are respectively arranged on the translational connecting rod 7 through two movable rotating shafts 12; the crank base 5 is provided with a first accommodating space, and the anti-rebound assembly is installed in the first accommodating space.

Further, the anti-bounce component is provided with a stop pin 1, when a missile 8 is launched, as shown in fig. 1 and 4, the translational connecting rod 7 is controlled to drive the left crank 9 and the right crank 11 to simultaneously rotate around the fixed rotating shaft 6 from the initial positions so as to unlock the missile 8, the anti-bounce component shielded by the left crank 9 is exposed along with the rotation of the left crank 9 around the fixed rotating shaft 6, as shown in fig. 1, 2, 5 and 6, at the moment, the stop pin 1 is ejected out of the anti-bounce component and extends to the outside of the crank seat 5 due to the elasticity of the compression spring 2, so that the left crank 9 is limited to return to the initial position.

Further, in a preferred embodiment, as shown in fig. 1, a second internal thread is provided on the inner wall of the first accommodating space, a second external thread is provided on the circumferential direction of the threaded sleeve 4, the threaded sleeve 4 is mounted on the second internal thread of the first accommodating space through the second external thread in a matching manner, wherein one end of the threaded sleeve 4, which is far away from the pressure spring 2, is provided with a linear groove 10, as shown in fig. 7, so that the installation and the disassembly can be conveniently performed by using a flat screwdriver or the like, the structure is simple, and the operation is convenient.

Specifically, as shown in fig. 2 and fig. 3, the anti-rebound assembly includes a pressure spring 2, a set screw 3 and a threaded sleeve 4, a second accommodating space is provided inside the threaded sleeve 4, a stop pin 1, the pressure spring 2 and the set screw 3 are sequentially arranged in the second accommodating space, in a preferred embodiment, the stop pin 1 is of a T-shaped structure, one end of the stop pin 1 is arranged inside the second accommodating space, and the other end of the stop pin 1 can extend to the outside of the threaded sleeve 4 under the driving of the elastic force of the pressure spring 2.

Furthermore, the stop pin 1 and the pressure spring 2 can be detachably connected or welded according to actual requirements.

Specifically, the inside first internal thread that is provided with of one end of the set screw 3 of the installation of threaded sleeve 4, the circumference of set screw 3 is provided with the external screw thread, screw 3 is installed on the first internal thread on threaded sleeve 4 through the external screw thread matching.

Specifically, the stop pin 1 can move between a first position and a second position, wherein the first position is a state that one side of the stop pin 1 far away from the set screw 3 is flush with the end surface of the threaded sleeve 4, as shown in fig. 3; the second position is a state that one side of the stop pin 1, which is far away from the set screw 3, moves to the farthest position outside the end face of the threaded sleeve 4, as shown in fig. 6, wherein the pressure spring 2 is always in a compressed state, the working effectiveness of the anti-rebound assembly is ensured, and the stop pin 1 can be popped out in time as required.

In particular, in practical application, different missiles are matched with different crank bases 5, so that the threaded sleeve 4 and the stop pin 1 matched with the threaded sleeve 4 can be changed into different sizes according to actual requirements, and the requirements of launching different types of missiles 8 are met.

Further, according to actual needs, the compression spring 2 can be replaced by springs with different rigidity coefficients according to needs to meet the requirements of the invention, and meanwhile, the compression degree of the compression spring 2 can be adjusted by screwing or loosening the set screw 3.

In order to check the reliability of the action and the convenience of installation and operation of the anti-rebound device of the bullet-fixing mechanism, the verification work is carried out by utilizing a tool, and after the bullet-fixing mechanism is quickly unlocked and separated, the anti-rebound assembly can firmly prevent the rebound of the four-bar mechanism, so that the movement of a missile 8 is not interfered, and the expected design requirements are met during an ejection test.

The working principle of the invention is as follows:

the bullet fixing mechanism adopts a four-bar mechanism, as shown in figures 1, 2 and 2, a stop pin 1 and a pressure spring 2 are sequentially placed in a threaded sleeve 4, a set screw 3 is screwed into the position of the thread on the inner cylinder surface of the threaded sleeve 4, then the threaded sleeve 4 provided with the stop pin 1, the pressure spring 2 and the set screw 3 is screwed into a threaded hole of a crank base 5 by using a tool and utilizing a linear groove 10, the end surface of the linear groove 10 on the threaded sleeve 4 after installation is outward, a missile 8 is loaded in place in the reverse direction, a translational connecting rod 7 on the four-bar mechanism is tightly attached to the tail end surface of the missile 8, a left crank 9 on the four-bar mechanism completely presses the stop pin 1 into the threaded sleeve 4, the pressure spring 2 is compressed and shortened at the moment, the four-bar mechanism is turned over rightwards and downwards under the action of impact force after the missile 8 is relieved, and the left crank 9 rotates clockwise around a crank fixing rotating shaft 6 in the turnover process of the four-bar mechanism, as shown in figure 4, after the four-bar mechanism rotates for a certain angle, the stop pin 1 pops up under the spring force of the pressure spring 2, and after the four-bar mechanism touches the bottom and rebounds, the stop pin 1 firmly stops, so that the four-bar mechanism is prevented from rebounding continuously, and the condition that the missile launching is influenced because the four-bar mechanism rebounds back to the initial position is effectively prevented.

In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.

The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.

Claims

1. An anti-rebound device suitable for a bullet fixing mechanism of a shrapnel separating device is characterized by comprising a crank base (5), an anti-rebound assembly and a four-bar mechanism;

a first accommodating space is formed in the crank base (5), and the anti-rebound assembly is installed in the first accommodating space;

the anti-bounce component is provided with a stop pin (1), when a missile (8) is launched, the four-bar mechanism rotates around the fixed rotating shaft (6) from an initial position to unlock the missile (8) and expose the shielded anti-bounce component, and at the moment, the stop pin (1) is ejected from the anti-bounce component and extends to the outside of the crank base (5) so as to limit the four-bar mechanism to return to the initial position;

the four-bar mechanism is provided with a translational connecting bar (7), a left crank (9), a right crank (11), two fixed rotating shafts (6) and two movable rotating shafts (12);

one ends of the left crank (9) and the right crank (11) are respectively installed on the crank seat (5) through two fixed rotating shafts (6), the other ends of the left crank (9) and the right crank (11) are respectively installed on the translational connecting rod (7) through two movable rotating shafts (12), wherein the left crank (9) blocks the stop pin (1) from popping out of the anti-rebound assembly at the initial position, and when the left crank (9) rotates around the fixed rotating shafts (6) to expose the stop pin (1), the stop pin (1) pops out of the anti-rebound assembly and prevents the left crank (9) from rotating back to the initial position;

the anti-rebound assembly comprises a pressure spring (2), a set screw (3) and a threaded sleeve (4);

the threaded sleeve (4) is internally provided with a second accommodating space, and the stop pin (1), the pressure spring (2) and the set screw (3) are sequentially arranged in the second accommodating space.

2. The anti-rebounding device suitable for the bullet-proof mechanism of the shrapnel separating device according to claim 1, wherein the stop pin (1) is of a T-shaped structure, one end of the stop pin (1) is arranged inside the second accommodating space, and the other end of the stop pin (1) can extend to the outside of the threaded sleeve (4) under the driving of the elastic force of the compression spring (2).

3. The anti-rebounding device suitable for the bullet-proof mechanism of the shrapnel separating device is characterized in that a first internal thread is arranged inside one end of the threaded sleeve (4) where the set screw (3) is installed, an external thread is arranged on the circumference of the set screw (3), and the screw (3) is installed on the first internal thread on the threaded sleeve (4) in a matching mode through the external thread.

4. The anti-rebounding device suitable for the bullet-holding mechanism of the shrapnel separating device according to claim 1, wherein one end of the threaded sleeve (4) far away from the compression spring (2) is provided with a linear groove (10).

5. The anti-rebounding device suitable for the bullet-holding mechanism of the shrapnel separating device in accordance with claim 1, wherein the stop pin (1) and the compression spring (2) are detachably connected or welded.

6. The anti-rebounding device suitable for the bullet-proof mechanism of the shrapnel separating device according to claim 1, wherein the inner wall of the first accommodating space is provided with a second internal thread, the circumferential direction of the threaded sleeve (4) is provided with a second external thread, and the threaded sleeve (4) is mounted on the second internal thread of the first accommodating space in a matching manner through the second external thread.

7. Anti-recoil arrangement suitable for a shrapnel separating device mechanism according to claim 1, characterized in that the catch pin (1) is movable between a first position and a second position, wherein the compression spring (2) is always in a compressed state.

8. The anti-rebounding device suitable for the bullet-arresting mechanism of the shrapnel separating device according to claim 1 is characterized in that the threaded sleeve (4) and the stop pin (1) matched with the threaded sleeve (4) can be changed into different sizes according to actual requirements so as to meet the launching requirements of missiles (8) of different models.