阅读说明：本技术 一种逆向发射导弹多自由度约束辅助支撑装置 (Multi-degree-of-freedom constraint auxiliary supporting device for reverse-launched missile ) 是由 李微微 张保刚 俞刘建 夏津 刘广 许斌 蒋君庭 陶勇鹏 胡珊 王波兰 于 2020-04-02 设计创作，主要内容包括：本发明提供了一种逆向发射导弹多自由度约束辅助支撑装置,包括导轨,导轨紧固安装在发射装备内,导轨上设有凹槽,导轨上紧固设有轴向限位块；推板位于所述轴向限位块与凹槽之间,轴向限位块与所述推板紧密接触,推板与所述凹槽紧密接触；平行四边形机构包括底板、第一转轴、第二转轴、第三转轴、第四转轴、第一连杆、第二连杆和弧形挡板装置；底板紧固安装于发射装备上,第一连杆和第二连杆通过第一转轴和第二转轴与所述底板连接；第一连杆和第二连杆通过第三转轴和第四转轴与所述弧形挡板装置连接；第一连杆和第二连杆通过所述第一转轴、第二转轴、第三转轴和第四转轴进行联动。本发明实现导弹多自由度全约束,提升产品运输安全性。(The invention provides a multi-degree-of-freedom constraint auxiliary supporting device for a reverse launching missile, which comprises a guide rail, wherein the guide rail is tightly installed in launching equipment, a groove is formed in the guide rail, and an axial limiting block is fixedly arranged on the guide rail; the push plate is positioned between the axial limiting block and the groove, the axial limiting block is in close contact with the push plate, and the push plate is in close contact with the groove; the parallelogram mechanism comprises a bottom plate, a first rotating shaft, a second rotating shaft, a third rotating shaft, a fourth rotating shaft, a first connecting rod, a second connecting rod and an arc-shaped baffle device; the bottom plate is fixedly arranged on the launching equipment, and the first connecting rod and the second connecting rod are connected with the bottom plate through a first rotating shaft and a second rotating shaft; the first connecting rod and the second connecting rod are connected with the arc-shaped baffle device through a third rotating shaft and a fourth rotating shaft; the first connecting rod and the second connecting rod are linked through the first rotating shaft, the second rotating shaft, the third rotating shaft and the fourth rotating shaft. The invention realizes missile multi-degree-of-freedom full restraint and improves the product transportation safety.)

1. The utility model provides a supplementary strutting arrangement of reverse launch guided missile multi freedom restraint which characterized in that includes:

the guide rail is tightly installed in the launching equipment, a groove is formed in the guide rail, a sliding block on the missile can be installed in the groove, the missile further comprises a push plate, the push plate is located between the axial limiting block and the groove, the guide rail is fixedly provided with the axial limiting block, the axial limiting block is tightly contacted with the push plate, the push plate is tightly contacted with the groove, and the axial limiting block limits the push plate and the missile to move horizontally;

the parallelogram mechanism comprises a bottom plate, a first rotating shaft, a second rotating shaft, a third rotating shaft, a fourth rotating shaft, a first connecting rod, a second connecting rod and an arc-shaped baffle device; the bottom plate is fixedly arranged on the launching equipment, and the first connecting rod and the second connecting rod are connected with the bottom plate through the first rotating shaft and the second rotating shaft; the first connecting rod and the second connecting rod are connected with the arc-shaped baffle device through a third rotating shaft and a fourth rotating shaft; the first connecting rod and the second connecting rod are linked through the first rotating shaft, the second rotating shaft, the third rotating shaft and the fourth rotating shaft.

2. The counter-launched missile multi-degree-of-freedom constraint auxiliary support device as recited in claim 1, wherein: the parallelogram mechanism further comprises a connecting piece, the connecting piece is tightly mounted on the bottom plate, and a pressing block is fixedly arranged on the connecting piece.

3. The counter-launched missile multi-degree-of-freedom constraint auxiliary support device as recited in claim 2, wherein: the parallelogram mechanism further comprises an explosive bolt, one end of the explosive bolt is arranged on the connecting piece and the pressing block, and the other end of the explosive bolt is sleeved on the third rotating shaft.

4. The counter-launched missile multi-degree-of-freedom constraint auxiliary support device as recited in claim 1, wherein: the pair of tension springs are correspondingly arranged at two ends of the second rotating shaft; one end of the tension spring is connected with the second connecting rod, and the other end of the tension spring is connected with the bottom plate.

5. The counter-launched missile multi-degree-of-freedom constraint auxiliary support device as recited in claim 4, wherein: the two ends of the base and the second connecting rod are respectively provided with a pair of spring seats, and the tension spring is connected with the base and the second connecting rod through the spring seats.

6. The counter-launched missile multi-degree-of-freedom constraint auxiliary support device as recited in claim 1, wherein: the arc-shaped baffle plate assembly comprises an axial pre-tightening screw, a rubber layer, a transfer block, a radial pre-tightening screw, a guide pin and a baffle plate; the rubber layer is vulcanized on the inner arc surface of the baffle; the transfer block is fixedly connected with the guide pin; the axial pre-tightening screw is in close contact with the adapter block, and the radial pre-tightening screw is in close contact with the axial pre-tightening screw.

7. The counter-launched missile multi-degree-of-freedom constraint auxiliary support device as recited in claim 1, wherein: the axial limiting block is installed on the guide rail through a screw.

8. The counter-launched missile multi-degree-of-freedom constraint auxiliary support device as recited in claim 2, wherein: the pressing block is installed on the connecting piece through a screw.

9. The counter-launched missile multi-degree-of-freedom constraint auxiliary support device as recited in claim 6, wherein: the transfer block is connected with the guide pin through welding.

10. The counter-launched missile multi-degree-of-freedom constraint auxiliary support device as recited in claim 5, wherein: the spring seats are symmetrically arranged at two ends of the bottom plate and the second connecting rod.

Technical Field

The invention relates to the technical field of guided missile auxiliary support, in particular to a reverse launching guided missile multi-degree-of-freedom constraint auxiliary support device.

Background

Missile transport, also known as "missile handling" or "missile transfer". The process of turning a missile from one location to another by means of a vehicle such as a car, train, airplane, ship, etc.

At present, the missile is fixed through a missile fixing mechanism in the transportation process, but the missile fixing mechanism is single in function, most of missiles can only be restricted by aiming at a single degree of freedom, and the other five degrees of freedom still have a certain movement range, so that the reliable restriction of the full degree of freedom of the missiles cannot be realized, and the firmness is reduced and the danger is increased in the transportation process of the missiles. Therefore, the development of the missile multi-freedom-degree constraint auxiliary supporting device has important significance for improving the reliability of missile transportation.

The publication number is CN109404691A, the name is a steplessly adjustable supporting mechanism with guide, the patent document discloses a steplessly adjustable supporting mechanism with guide, which comprises a supporting support for supporting a test piece, a base, a top rod, a supporting plate, an auxiliary support and a compression screw, the base is a structure that vertical plates are symmetrically and vertically arranged at two ends of a flat plate seat, the opposite inner sides of the two vertical plates are respectively provided with a groove extending along the vertical direction, the supporting plate is a structure that the two ends of the flat plate symmetrically extend out and are provided with a convex edge, the supporting plate can move up and down along the groove by respectively extending the convex edges at the two ends into the two grooves, the middle part of the lower surface of the flat plate seat is provided with a blind hole, one end of the top rod is connected on a platform in a threaded manner, the other end of the top rod is screwed into a threaded hole of the blind hole and then abuts against the bottom of the blind hole, the two vertical plate walls are respectively provided with a thread through hole, and the end parts of the threaded rods of the two compression screws can be respectively screwed into the two thread through holes and then compressed and abutted against the two side walls of the support bracket. The patent document discloses a stepless adjustable support mechanism with guide, which does not solve the problems of insufficient freedom degree constraint, low firmness and the like in the missile transportation process, and has poor reliability in the missile transportation process.

Disclosure of Invention

Aiming at the defects in the prior art, the invention aims to provide a reverse-launched missile multi-degree-of-freedom constraint auxiliary supporting device.

The invention provides a reverse launching missile multi-degree-of-freedom constraint auxiliary supporting device, which comprises:

the missile launching device comprises a guide rail, a push plate and a guide rail, wherein the guide rail is tightly installed in launching equipment, a groove is formed in the guide rail, a sliding block on a missile can be installed in the groove, an axial limiting block is fixedly arranged on the guide rail, the push plate is positioned between the axial limiting block and the groove, the axial limiting block is tightly contacted with the push plate, the axial limiting block limits the push plate and the missile to move horizontally, and the push plate is tightly contacted with the groove;

the parallelogram mechanism comprises a bottom plate, a first rotating shaft, a second rotating shaft, a third rotating shaft, a fourth rotating shaft, a first connecting rod, a second connecting rod and an arc-shaped baffle device; the bottom plate is fixedly arranged on the launching equipment, and the first connecting rod and the second connecting rod are connected with the bottom plate through the first rotating shaft and the second rotating shaft; the first connecting rod and the second connecting rod are connected with the arc-shaped baffle device through a third rotating shaft and a fourth rotating shaft; the first connecting rod and the second connecting rod are linked through the first rotating shaft, the second rotating shaft, the third rotating shaft and the fourth rotating shaft.

Preferably, the parallelogram mechanism further comprises a connecting piece, the connecting piece is tightly installed on the bottom plate, and a pressing block is tightly and fixedly arranged on the connecting piece.

Preferably, the parallelogram mechanism further comprises an explosion bolt, one end of the explosion bolt is installed on the connecting piece and the pressing block, and the other end of the explosion bolt is sleeved on the third rotating shaft.

Preferably, the device further comprises a pair of tension springs, and the pair of tension springs are correspondingly arranged at two ends of the second rotating shaft; one end of the tension spring is connected with the second connecting rod, and the other end of the tension spring is connected with the bottom plate.

Preferably, a pair of spring seats is respectively arranged at two ends of the base and the second connecting rod, and the tension spring is connected with the base and the second connecting rod through the spring seats.

Preferably, the arc-shaped baffle plate assembly comprises an axial pre-tightening screw, a rubber layer, a transfer block, a radial pre-tightening screw, a guide pin and a baffle plate; the rubber layer is vulcanized on the inner arc surface of the baffle; the transfer block is fixedly connected with the guide pin; the axial pre-tightening screw is in close contact with the adapter block, and the radial pre-tightening screw is in close contact with the axial pre-tightening screw.

Preferably, the axial limiting block is mounted on the guide rail through a screw.

Preferably, the pressing block is mounted on the connecting member by a screw.

Preferably, the transfer block is connected with the guide pin by welding.

Preferably, the spring seats are symmetrically arranged at two ends of the bottom plate and the second connecting rod.

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

1. by the design of the guide rail and the parallelogram mechanism, the problem of insufficient constraint of the degree of freedom in the missile transportation process is effectively solved, and the multi-degree-of-freedom full constraint of the missile is realized;

2. by the design of the guide rail and the parallelogram mechanism, the product transportation safety is improved;

3. through the design of the guide rail and the parallelogram mechanism, reliable constraint on the missile is effectively realized, and the requirement of reverse launching of the missile is met.

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 front view of a multi-degree-of-freedom constrained auxiliary supporting device for a reverse-launched missile according to the present invention;

FIG. 2 is an enlarged view of a part A of the structural schematic diagram of the multi-degree-of-freedom constrained auxiliary supporting device for the reverse-launched missile of the invention;

FIG. 3 is a schematic view of the installation position of a missile slider of the multi-degree-of-freedom constraint auxiliary supporting device for a reverse launching missile of the invention;

FIG. 4 is a side view of an auxiliary support shaft of the multi-degree-of-freedom constrained auxiliary support device for a reverse-launched missile of the present invention;

FIG. 5 is a right side view of an auxiliary support shaft of the reverse-launched missile multi-degree-of-freedom constraint auxiliary support device of the invention;

FIG. 6 is a D-D partial sectional view of the reverse launched missile multi-degree-of-freedom constraint auxiliary support device of the invention

FIG. 7 is a partial enlarged view of a reverse-launched missile multi-degree-of-freedom constraint auxiliary support device at the position B;

FIG. 8 is a partial cross-sectional view of the E-E of the reverse-launched missile multi-degree-of-freedom constraint auxiliary supporting device

FIG. 9 is a partial enlarged view of the position C of the multi-degree-of-freedom constrained auxiliary supporting device of the reverse launched missile of the invention;

FIG. 10 is an axial unlocking schematic diagram of the multi-degree-of-freedom constraint auxiliary supporting device for the reversely launched missile.

Shown in the figure:

a guide rail 1; 2, missile; an arc baffle assembly 3; axially pre-tightening the screw 301; a rubber layer 302; a transfer block 303; a radially preloaded screw 304; a guide pin 305; a baffle 306; a fourth rotating shaft 4; a second link 5; a tension spring 6; a spring seat 7; a bottom plate 8; a first rotating shaft 9; a second rotating shaft 16; a third rotating shaft 17; a fourth rotating shaft 18; the explosive bolt 10; a slider 11; a push plate 12; an axial stopper 13; a first link 14; a briquetting 15; a connecting piece 19.

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.

First, a basic embodiment of the multi-degree-of-freedom constrained auxiliary supporting device for the reverse launching missile is described below.

As shown in fig. 1 to 6, the multi-degree-of-freedom constrained auxiliary supporting device for a reverse launching missile provided by the invention comprises: the missile launching device comprises a guide rail 1, a push plate 12 and a guide rail, wherein the guide rail is tightly installed in launching equipment, a groove is formed in the guide rail 1, a sliding block 11 on a missile 2 can be installed in the groove, an axial limiting block 13 is fixedly arranged on the guide rail 1, the push plate 12 is positioned between the axial limiting block 13 and the groove, the axial limiting block 13 is tightly contacted with the push plate 12, the push plate 12 is tightly contacted with the groove, and the axial limiting block 13 limits the push plate 12 and the missile 2 to move horizontally; the parallelogram mechanism comprises a bottom plate 8, a first rotating shaft 9, a second rotating shaft 16, a third rotating shaft 17, a fourth rotating shaft 18, a first connecting rod 4, a second connecting rod 5 and an arc-shaped baffle device 3; the bottom plate 8 is tightly installed on a launching device, and the first connecting rod 14 and the second connecting rod 5 are connected with the bottom plate 8 through the first rotating shaft 9 and the second rotating shaft 16; the first connecting rod 14 and the second connecting rod 5 are connected with the arc baffle device 3 through a third rotating shaft 17 and a fourth rotating shaft 18; the first connecting rod 14 and the second connecting rod 5 are linked through the first rotating shaft 9, the second rotating shaft 16, the third rotating shaft 17 and the fourth rotating shaft 18.

The present invention will be described in more detail with reference to preferred examples and/or modifications of the above basic embodiment, such as embodiment 1.