CN113357962B - Auxiliary supporting device for restraining radial runout of guided missile - Google Patents

Abstract

The invention provides an auxiliary supporting device for inhibiting radial runout of a missile, which comprises a positioning seat, a breakable mechanism, a shell, a rotary pressing block, a torsional spring, a supporting mechanism and a signal connector, wherein the positioning seat is installed on the shell, an accommodating groove is formed in one end of the positioning seat, the breakable mechanism is installed in the accommodating groove, the signal connector is installed at the other end of the positioning seat, one end of the breakable mechanism is fixedly connected with the positioning seat, the other end of the breakable mechanism is in rotating fit with one end of the rotary pressing block, the other end of the rotary pressing block, one end of the supporting mechanism and the torsional spring are sleeved on a rotating shaft, when the breakable mechanism is in a non-broken state, the other end of the supporting mechanism is in a missile vibration inhibition state, and when the breakable mechanism is broken, the other end of the supporting mechanism is in a missile vibration non-inhibition state.

Description

Auxiliary supporting device for restraining radial runout of guided missile

Technical Field

The invention relates to the technical field of guided missile auxiliary support of weapon systems, in particular to an auxiliary support device for inhibiting guided missile radial runout.

Background

With the rapid development of missile weapon systems, the performance requirements of various military classes on missile weapon systems are continuously improved, wherein the problem of missile vibration in a launching device is widely concerned in the transportation process of the weapon systems.

In the transportation process, the missile is fixed in a guide rail groove in the launching device through the sliding block, and the missile is in a severe vibration environment for a long time under the transportation working condition due to a certain gap between the missile sliding block and the guide rail groove, so that the performance of related equipment on the missile is influenced to a certain extent. At present, the problem is solved by adopting a mode of eliminating or reducing the gap, but the phenomenon of jamming of the missile during launching can be caused by the too small gap, and even the launching failure can be caused. Therefore, there is a need to provide a new device to solve the problem of vibration caused by the radial runout of the missile during transportation, and the device will not affect the launching safety.

Patent document CN 106643290B discloses an integrated sand-prevention and grease-storage missile linkage locking device, which includes a plurality of locking units connected in sequence, where each locking unit includes: a base; the screw rod is rotatably fixed in the base, two ends of the screw rod respectively extend out of two ends of the base and are connected with corresponding ends of the screw rods of adjacent locking units, a pressing block is sleeved on the screw rod, the screw rod and the pressing block form a spiral motion pair, the pressing block is in fit contact with a self-locking inclined plane of an external storage and transportation launching cylinder clamping part, a storage and transportation launching cylinder positioning surface is arranged at a corresponding position outside the storage and transportation launching cylinder clamping part, the screw rod is rotated, the pressing block moves along the axial direction of the base, and the storage and transportation launching cylinder clamping part is supported or separated from the storage and transportation launching cylinder positioning surface after being pushed outwards or retracted inwards, but the locking device is very easy to damage a surface coating of a projectile body.

Disclosure of Invention

Aiming at the defects in the prior art, the invention aims to provide an auxiliary supporting device for inhibiting the radial runout of a missile.

The invention provides an auxiliary supporting device for inhibiting radial runout of a guided missile, which comprises a positioning seat, a breakable mechanism, a shell, a rotary pressing block, a torsion spring, a supporting mechanism and a signal connector, wherein the positioning seat is arranged on the shell;

the positioning seat is installed on the shell, an accommodating groove is formed in one end of the positioning seat, the breakable mechanism is installed in the accommodating groove in a matched mode, and the signal connector is installed at the other end of the positioning seat;

one end of the breakable mechanism is fixedly connected with the positioning seat, the other end of the breakable mechanism is in rotating fit with one end of the rotary pressing block, the other end of the rotary pressing block, one end of the supporting mechanism and the torsional spring are all sleeved on the rotating shaft, wherein the torsional spring is provided with a first connecting end and a second connecting end, the first connecting end is connected with the supporting mechanism, and the second connecting end is installed on the shell;

when the breakable mechanism is in a non-broken state, the other end of the supporting mechanism is in a missile vibration suppression state;

when the breakable mechanism is broken, one end of the rotary pressing block moves to contact the signal connector, and the other end of the rotary pressing block rotates around the rotating shaft to drive one end of the supporting mechanism to drive the other end to be in a missile vibration non-suppression state.

Preferably, the other end of the support mechanism is in flexible contact with the missile in the missile vibration suppression state.

Preferably, the breakable mechanism adopts an explosive bolt, one end of the explosive bolt is fastened and installed on the positioning seat through a round nut, and the other end of the explosive bolt is in running fit with one end of the rotary pressing block.

Preferably, the explosion bolt is provided with a shaft shoulder, the accommodating groove is a U-shaped groove, and the shaft shoulder is attached to the end face of the U-shaped groove.

Preferably, the signal connector adopts a short-circuit connector, and the short-circuit connector is detachably mounted on the positioning seat through an arched cover plate.

Preferably, the support mechanism comprises two support blocks, which are connected and arranged in parallel by one or more support rod connecting shafts.

Preferably, the support block includes the bracing piece, the one end of bracing piece is provided with female first boss, the other end of gyration briquetting is provided with public first boss, and female first boss matches public first boss, female first boss blocks public first boss and then can order about the one end of bracing piece and revolve the rotation of axes when gyration briquetting revolves the rotation of axes.

Preferably, a rotatable roller is mounted between the other ends of the two support rods through a roller shaft, and the circumference of the roller is of an arc structure matched with the missile.

Preferably, the rollers are glued with cushion pads in the circumferential direction.

Preferably, one end of the support rod is provided with a support rod groove, and the first connecting end is embedded into the support rod groove;

the second connecting end is arranged on the shell through a torsion spring buckle shaft.

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

1. the invention effectively solves the problem of vibration caused by radial runout of the missile during transportation by adopting a flexible inhibition structure, does not affect the launching safety, and proves that the auxiliary supporting device makes up the defects of the existing product through multiple transportation tests, effectively inhibits the radial runout of the missile, and has the advantages of high safety, flexible contact, no damage to the surface coating of the missile and the like.

2. When the missile is launched, the radial constraint of the missile can be reliably relieved, and all the parts are conventional parts, so that the cost is low.

3. The structure of the invention can adjust the pre-tightening state between the support mechanism and the missile through the round nut, and can adapt to various missile models through the buffer layer, the torsion spring and other parts, thus having strong practicability.

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 side view of the support mechanism of the present invention in a missile vibration suppression configuration;

FIG. 2 is a schematic structural diagram of the receiving slot of the present invention, wherein the support mechanism is in a missile vibration suppression state;

FIG. 3 is a schematic view of the torsion spring coupled to the torsion spring shaft;

FIG. 4 is a side view of the support rod;

FIG. 5 is a schematic top view of the support rod;

FIG. 6 is a schematic view of a rotary briquette;

FIG. 7 is a schematic structural diagram of the support mechanism in a non-missile vibration suppression state.

The figures show that:

1-positioning seat 1201-male boss

101-accommodating groove 13-torsion spring

2-explosive bolt cover plate 14-support block

3-arched cover 1401-support bar

4-explosive bolt 1402-support rod connecting shaft

5-round nut 1403-support bar groove

6-roller 1404-female head boss

7-roller shaft 15-buffer

8-shell 16-missile

9-shaft 17-short circuit connector

10-torsion spring buckle shaft 18-first connection end

11-pin 19-second connection end

12-rotating briquetting

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.

Example 1:

the invention provides an auxiliary supporting device for inhibiting radial runout of a missile, which comprises a positioning seat 1, a breakable mechanism, a shell 8, a rotary press block 12, a torsional spring 13, a supporting mechanism and a signal connector, wherein the positioning seat 1 is installed on the shell 8, one end of the positioning seat 1 is provided with an accommodating groove 101, the breakable mechanism is installed in the accommodating groove 101 in a matching manner, the signal connector is installed at the other end of the positioning seat 1, one end of the breakable mechanism is fixedly connected with the positioning seat 1, the other end of the breakable mechanism is in rotating fit with one end of the rotary press block 12, and the other end of the rotary press block 12, one end of the supporting mechanism and the torsional spring 13 are all sleeved on a rotating shaft 9.

Further, the torsion spring 13 is provided with a first connection end 18 and a second connection end 19, the first connection end 18 is connected with the support mechanism, the second connection end 19 is mounted on the housing 8, one end of the support bar 1401 is preferably provided with a support bar groove 1403, the first connection end 18 is embedded in the support bar groove 1403, and the second connection end 19 is preferably mounted on the housing 8 through the torsion spring buckle shaft 10.

When the breakable mechanism is in a non-broken state, the other end of the support mechanism is in a missile vibration suppression state, and in the missile vibration suppression state, the other end of the support mechanism is in flexible contact with the missile 16, so that the vibration of the missile 16 and the like can be effectively suppressed. When the breakable mechanism is broken, under the combined action of the torsion spring 13 and the impact force when the breakable mechanism is broken, one end of the rotary pressing block 12 moves to contact with the signal connector, so that the suppression state of the missile can be relieved, and meanwhile, the other end of the rotary pressing block 12 rotates around the rotating shaft 9 to drive one end of the supporting mechanism to drive the other end of the supporting mechanism to be in a non-suppression state of the missile vibration.

The auxiliary supporting device for inhibiting the radial runout of the guided missile can effectively inhibit the radial runout of the guided missile and reduce the vibration degree of the guided missile when a guided missile weapon system is transported and hoisted, and the device is in flexible contact with the surface of a guided missile 16 by adopting the cushion pad 15, so that the damage of a coating or a paint layer on the surface of a missile body is effectively avoided. The auxiliary supporting device is proved to meet the design requirement and the use requirement through the examination of a multistage road transportation test, a hoisting test and an ejection test.

In this embodiment, the breakable mechanism uses the explosive bolt 4, and the upper end of the rotary press block 12 can be driven to move towards the signal connector by the explosive impact force generated when the explosive bolt 4 is broken. The one end of explosion bolt 4 passes through round nut 5 fastening installation on positioning seat 1, and the other end of explosion bolt 4 and the one end normal running fit of gyration briquetting 12 are provided with the shaft shoulder on the explosion bolt 4, and holding tank 101 is the U-shaped groove, the terminal surface laminating in shaft shoulder and U-shaped groove. The signal connector adopts a short-circuit connector 17, and the short-circuit connector 17 is detachably arranged on the positioning seat 1 through an arched cover plate 3.

Specifically, the supporting mechanism includes two supporting block bodies 14, two supporting block bodies 14 are connected and arranged in parallel through one or more supporting rod connecting shafts 1402, supporting block body 14 includes supporting rod 1401, the one end of supporting rod 1401 is provided with female head boss 1404, the other end of gyration briquetting 12 is provided with public head boss 1201, female head boss 1404 matches public head boss 1201, female head boss 1404 blocks public head boss 1201 and then can order about the one end of supporting rod 1401 to rotate around pivot 9 when gyration briquetting 12 rotates around pivot 9. The other ends of the two support rods 1401 are provided with a rotatable roller 6 through a roller shaft 7, the circumference of the roller 6 is an arc structure matched with the missile 16, and the circumference of the roller 6 is glued with a cushion pad 15.

Can effectively restrain radial runout caused by clearance in the missile transportation process, further solve the problem of missile transportation vibration, avoid damage of equipment on the missile, effectively remove radial restraint when implementing launching, and realize safe launching

Example 2:

this embodiment is a preferred embodiment of embodiment 1.

In the embodiment, as shown in fig. 1 to 6, the invention is arranged in a missile launching device, and comprises a positioning seat 1, a shell 8, an explosion bolt cover plate 2, an arched cover plate 3, an explosion bolt 4, a round nut 5, a roller 6, a roller shaft 7, a rotating shaft 9, a torsion spring buckle shaft 10, a pin shaft 11, a rotary press block 12, a torsion spring 13, a support block 14, a cushion pad 15 and a short-circuit connector 17.

In the embodiment, the shell 8 is fixed in the launching device through a screw, the positioning seat 1 is fixed in the shell 8 through a screw, the middle part of the positioning seat 8 is provided with an accommodating groove 101, the accommodating groove 101 is of a U-shaped structure, the explosive bolt 4 is installed in the accommodating groove 101 on the positioning seat 8, the explosive bolt 4 is provided with a shaft shoulder, the shaft shoulder is attached to the end face of the accommodating groove 101, the left side and the right side of the shaft shoulder of the explosive bolt 4 are both provided with a section of thread, and the leftmost end of the explosive bolt 4 is provided with a shaft hole; the round nut 5 is connected with the thread section on the right side of the shaft shoulder on the explosive bolt 4, and after the round nut 5 is installed in place, the end surface of the round nut 5 is attached to the end surface of the shaft shoulder of the explosive bolt 4; the explosive bolt cover plate 2 is fixed on the positioning seat 1 through screws, and the installation position of the explosive bolt cover plate 2 is positioned at the upper part of the explosive bolt 4.

Further, the arched cover plate 3 is fixed on the positioning seat 1 through screws; the short-circuit connector 17 is fixed on the arched cover plate 3, the support block 14 is composed of a support rod 1401 and a support rod connecting shaft 1402, the support rod 1401 is a symmetrical piece, two sides of the support rod are respectively provided with one, two support rod connecting shafts 1402 are provided, the two support rods 1401 are connected into a whole through welding, and support rod grooves 1403 are respectively arranged on the two support rods 1401; the roller 6 is connected with the support block 14 through a roller shaft 7, the outer contour of the roller 6 is arc-shaped and is matched with the outer diameter of the missile 16; the buffer pads 15 are fixed on the rollers 6 by gluing; the upper part of the supporting block body 14 is connected with the lower part of the rotary press block 12 through the rotating shaft 9, the lower part of the rotary press block 12 is provided with a male boss 1201, the upper part of the supporting rod 1401 is provided with a female boss 1404, and the side surface of the male boss 1201 is attached to the side surface of the female boss 1404 after installation; the shaft 9 passes through the housing 8 and is mounted on the housing 8.

The upper part of the rotary pressing block 12 is connected with the left end of the explosive bolt 4 through a pin shaft 11; the torsion spring buckle shaft 10 is arranged on the shell 8 and is positioned on the left side of the rotating shaft 9; the torsion spring 13 is sleeved on the rotating shaft 9, a torsion hook on a first connecting end 18 of the torsion spring 13 is installed in the support bar groove 1403 on the support block body 14, and a torsion spring buckle on a second connecting end 19 of the torsion spring 13 is installed on the torsion spring buckle shaft 10.

The working principle of the invention is as follows:

as shown in fig. 1 to fig. 3, arrows in the figures indicate that when a missile 16 is loaded in a launching device in place, a support block 14 is rotated clockwise until a cushion pad 15 on a roller 6 is attached to the surface of the missile 16, then an explosive bolt 4 is connected with a rotary pressing block 12 through a pin shaft 11, the explosive bolt 4 is fastened in a containing groove 101 on a positioning seat 1 through a round nut 5, a torsion spring 13 has a counterclockwise torsional force in the state, and then an explosive bolt cover plate 2 is installed in place to protect the explosive bolt 4. And finally, the arched cover plate 3 provided with the short-circuit connector 17 is installed and fixed at the position shown in the figure on the positioning seat 1, so that the installation of the auxiliary supporting device is completed, the radial runout inhibition of the missile 16 is realized, and the vibration phenomenon in the transportation process is reduced.

As shown in fig. 7, the arrow in the figure indicates that when a missile 16 launches, the explosive bolt 4 is detonated and disintegrated into a left part and a right part, the right part is continuously fastened in the accommodating groove 101 on the positioning seat 1 through the round nut 5, the left part is left on the rotary press block 12 through the pin shaft 11, under the action of explosive impact of the explosive bolt and the torsional force of the torsion spring 13, under the cooperation of the male boss 1201 on the rotary press block 12 and the female boss 1404 on the support block 14, the rotary press block 12 drives the support block 14 to rotate counterclockwise around the rotating shaft 9, finally, the roller 6 with the cushion 15 glued on the surface releases radial constraint on the missile 16, the upper end of the rotary press block 12 impacts the short-circuit connector 17 in the state, the short-circuit connector 17 is changed from the disconnected state to the short-circuit state, a signal that the radial constraint is released is provided for the missile 16, and safe launching of the missile 16 is realized.

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, merely for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore, are not to 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 (10)

1. An auxiliary supporting device for restraining radial runout of a guided missile is characterized by comprising a positioning seat (1), a breakable mechanism, a shell (8), a rotary pressing block (12), a torsion spring (13), a supporting mechanism and a signal connector;

the positioning seat (1) is installed on the shell (8), an accommodating groove (101) is formed in one end of the positioning seat (1), the breakable mechanism is installed in the accommodating groove (101) in a matched mode, and the signal connector is installed at the other end of the positioning seat (1);

one end of the breakable mechanism is fixedly connected with the positioning seat (1), the other end of the breakable mechanism is in running fit with one end of the rotary pressing block (12), the other end of the rotary pressing block (12), one end of the supporting mechanism and the torsion spring (13) are all sleeved on the rotating shaft (9), wherein the torsion spring (13) is provided with a first connecting end (18) and a second connecting end (19), the first connecting end (18) is connected with the supporting mechanism, and the second connecting end (19) is installed on the shell (8);

when the breakable mechanism is in a non-broken state, the other end of the supporting mechanism is in a missile vibration suppression state;

when the breakable mechanism breaks, one end of the rotary pressing block (12) moves to contact the signal connector, and the other end of the rotary pressing block (12) rotates around the rotating shaft (9) to drive one end of the supporting mechanism to drive the other end to be in a missile vibration non-suppression state.

2. The missile radial runout suppression auxiliary support device as claimed in claim 1, wherein the other end of the support mechanism is in flexible contact with the missile (16) in a missile vibration suppression state.

3. The auxiliary supporting device for suppressing the radial runout of a guided missile as claimed in claim 1, wherein the breakable mechanism is an explosive bolt (4), one end of the explosive bolt (4) is tightly installed on the positioning seat (1) through a round nut (5), and the other end of the explosive bolt (4) is in running fit with one end of the rotary pressing block (12).

4. The auxiliary supporting device for suppressing the radial runout of the guided missile as claimed in claim 3, wherein the explosive bolt (4) is provided with a shaft shoulder, the accommodating groove (101) is a U-shaped groove, and the shaft shoulder is attached to the end surface of the U-shaped groove.

5. The missile runout-suppressing auxiliary support device of claim 1, wherein the signal connector is a short-circuit connector (17), and the short-circuit connector (17) is detachably mounted on the positioning seat (1) through an arched cover plate (3).

6. Auxiliary support device for the inhibition of missile radial runout according to any one of claims 1 to 5, characterized in that the support mechanism comprises two support blocks (14), the two support blocks (14) being connected and arranged in parallel by one or more support rod connection shafts (1402).

7. The missile radial runout auxiliary supporting device of claim 6, wherein the supporting block (14) comprises a supporting rod (1401), a female boss (1404) is arranged at one end of the supporting rod (1401), a male boss (1201) is arranged at the other end of the rotating pressing block (12), the female boss (1404) is matched with the male boss (1201), and when the rotating pressing block (12) rotates around the rotating shaft (9), the female boss (1404) blocks the male boss (1201) so as to drive one end of the supporting rod (1401) to rotate around the rotating shaft (9).

8. The auxiliary supporting device for suppressing the radial runout of the missile as claimed in claim 7, wherein the other ends of the two supporting rods (1401) are provided with a rotatable roller (6) through a roller shaft (7), and the circumference of the roller (6) is of an arc structure matched with the missile (16).

9. Auxiliary support device for the inhibition of missile radial runout according to claim 8, characterized in that the rollers (6) are glued circumferentially with a cushion (15).

10. The auxiliary supporting device for suppressing the radial runout of the missile of claim 7, wherein one end of the supporting rod (1401) is provided with a supporting rod groove (1403), and the first connecting end (18) is embedded into the supporting rod groove (1403);

the second connecting end (19) is installed on the shell (8) through a torsion spring buckle shaft (10).

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