CN210162264U - Guided missile hanging frame and guided missile hanging structure - Google Patents
Guided missile hanging frame and guided missile hanging structure Download PDFInfo
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- CN210162264U CN210162264U CN201920631442.4U CN201920631442U CN210162264U CN 210162264 U CN210162264 U CN 210162264U CN 201920631442 U CN201920631442 U CN 201920631442U CN 210162264 U CN210162264 U CN 210162264U
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Abstract
The utility model discloses a guided missile stores pylon and guided missile carry structure belongs to guided missile loading technical field. The missile hanging rack of the utility model comprises a first connecting rod, wherein a first hinge part is arranged in the middle of the first connecting rod, and the first connecting rod can rotate relative to the first hinge part; the middle part of the second connecting rod is provided with a second hinge part, and the second connecting rod can rotate relative to the second hinge part; one end of the third connecting rod is hinged with the upper end of the first connecting rod, and the other end of the third connecting rod is hinged with the upper end of the second connecting rod; the missile locking device comprises a first connecting rod, a second connecting rod and a third connecting rod, wherein a supporting column is fixedly connected to the first connecting rod, the supporting column can be driven to rotate when being driven to move, and a first hook is further arranged at the lower end of the first connecting rod and used for locking a missile to be loaded. The missile mounting structure of the utility model is simple, light in weight and convenient to install.
Description
Technical Field
The utility model belongs to the technical field of the weapon installation technique and specifically relates to a guided missile stores pylon and guided missile carry structure is related to.
Background
The missile has ultrahigh destructive power, and the safety of the missile is an important consideration before the missile is thrown. Before the guided missile is put in, the guided missile is generally fixedly mounted on a carrier, in order to ensure the safety of the guided missile, the conventional hanger is quite complex in general structure, and if the hanger is mounted on a carrier with weak bearing capacity (such as an unmanned aerial vehicle), the weight of the hanger is too large, so that the normal operation of the carrier can be influenced.
Therefore, there is a need for a missile hanger with simple structure and stable fixation.
SUMMERY OF THE UTILITY MODEL
In order to solve the defects of the prior art, the embodiment of the utility model provides a simple structure's guided missile stores pylon.
The embodiment of the utility model provides a solve the technical scheme who above-mentioned technical problem took and be: the missile hanging rack comprises a first connecting rod, wherein a first hinge part is arranged in the middle of the first connecting rod, and the first connecting rod can rotate relative to the first hinge part; the middle part of the second connecting rod is provided with a second hinge part, and the second connecting rod can rotate relative to the second hinge part; one end of the third connecting rod is hinged with the upper end of the first connecting rod, and the other end of the third connecting rod is hinged with the upper end of the second connecting rod; the missile locking device comprises a first connecting rod, a second connecting rod and a third connecting rod, wherein a supporting column is fixedly connected to the first connecting rod, the supporting column can be driven to rotate when being driven to move, and a first hook is further arranged at the lower end of the first connecting rod and used for locking a missile to be loaded.
As a further improvement of the above technical solution, the second link is in an L-shaped structure, and the second hinge portion is disposed at a junction of two free arms of the second link.
As a further improvement of the above technical solution, the device further comprises a triggering device, and the triggering device is located at the lower end of the second connecting rod.
As a further improvement of the above technical solution, the upper end of the third connecting rod and/or the second connecting rod is provided with a limiting hole.
As a further improvement of the technical scheme, the limiting hole is provided with a clamp spring which is elastic along the radial direction of the limiting hole.
As a further improvement of the above technical solution, the lower end of the first link is further connected with a first elastic member, one end of the first elastic member is fixedly disposed, and the other end of the first elastic member is connected to a side of the first link back to the hook.
As a further improvement of the above technical solution, the device further comprises a first guide frame and a second elastic member arranged on the upper portion of the first guide frame, wherein one end of the second elastic member is fixedly arranged, and the other end of the second elastic member is connected to the upper end of the first guide frame.
As a further improvement of the technical scheme, the novel multifunctional hook further comprises a second hook, a third hinge part is arranged on the second hook, the second hook can rotate relative to the third hinge part, and the upper part of the second hook is connected with a poke rod.
The embodiment of the utility model provides a missile carry structure is still provided, include carrier, guided missile and as above the guided missile stores pylon, the guided missile stores pylon install in on the carrier, the guided missile install in on the guided missile stores pylon.
As a further improvement of the above technical scheme, the carrier is an unmanned aerial vehicle.
The utility model has the advantages that:
the guided missile loads and is through the fore-set locking on the guided missile, the embodiment of the utility model provides an in, when loading the guided missile, guided missile and guided missile stores pylon draw close each other, and the fore-set on the guided missile will be connected and support the post jack-up that makes progress on first connecting rod for first connecting rod rotates, and second connecting rod, third connecting rod move jointly along with the motion of first connecting rod, and catch on the fore-set on with the guided missile through the couple on the first connecting rod, thereby the loading of convenient realization guided missile, the utility model discloses a guided missile carry simple structure, light in weight, simple to operate.
Drawings
The present invention will be further explained with reference to the drawings and examples.
Fig. 1 is a schematic structural view of an embodiment of the missile hanger of the present invention.
Detailed Description
The conception, specific structure and technical effects of the present invention will be described clearly and completely with reference to the accompanying drawings and embodiments, so as to fully understand the objects, aspects and effects of the present invention. It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict.
It should be noted that, unless otherwise specified, when a feature is referred to as being "fixed" or "connected" to another feature, it may be directly fixed or connected to the other feature or indirectly fixed or connected to the other feature. Furthermore, the description of the upper, lower, left, right, front, rear, etc. used in the present invention is only relative to the mutual position relationship of the components of the present invention in the drawings.
Furthermore, unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art. The terminology used in the description herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the term "and/or" includes any combination of one or more of the associated listed items.
Generally, the missile is designed into a universal structure, as shown in fig. 1, the missile comprises a body 1 and a top pillar 10 arranged on the body 1, and in practical application, the missile can be designed into various different shapes, but the top pillar 10 is reserved as a standard connecting piece so as to facilitate the assembly of the missile.
Referring to fig. 1, the present invention provides a missile hanging rack with a simple structure and capable of effectively reducing its own weight, including a first connecting rod 200, a second connecting rod 300 and a third connecting rod 400, wherein the middle portion of the first connecting rod 200 is provided with a first hinge portion 210, the first connecting rod 200 is rotatable relative to the first hinge portion 210, the middle portion of the second connecting rod 300 is provided with a second hinge portion 310, the second connecting rod 300 is rotatable relative to the second hinge portion 310, the third connecting rod 400 is disposed between the first connecting rod 200 and the second connecting rod 300, one end of the third connecting rod 400 is hinged to the upper end of the first connecting rod 200, the other end of the third connecting rod 400 is hinged to the upper end of the second connecting rod 300, wherein the first connecting rod 200 is fixedly provided with a support column 220, when a missile is loaded, the support column 10 upwardly supports the support column 220 to upwardly deflect the support column, the first connecting rod 200 is rotated relative to the first hinge portion 210, the lower end of the first connecting rod 200 is provided with a first hook 230, when the first link 200 is driven to rotate, the first hook 230 rotates toward the top post 10 and hooks the top post 10 to lock the missile with the missile hanger.
The second link 300 is preferably designed to be L-shaped, and the second hinge 310 is disposed at the intersection of two free arms of the second link 300, and the rotation of one free arm of the second link 300 will drive the rotation of the other free arm of the second link 300.
The first link 200 is a bar-shaped structure as a whole, and the third link 400 is transversely disposed between the first link 200 and the second link 300.
Preferably, the missile hanger in the embodiment of the present invention further includes a trigger device 500, the trigger device 500 is located at the lower end of the second connecting rod 300, as shown in fig. 1, the trigger device 500 or a component in the trigger device 500 has a capability of moving to the right, when the missile is unlocked, the component in the trigger device 500 or the trigger device 500 moves to the right, the second connecting rod 300 is pushed, the second connecting rod 300 is rotated counterclockwise, the third connecting rod 400 is rotated clockwise by the second connecting rod 300, and the first connecting rod 200 is driven to rotate counterclockwise, so that the first hook 230 at the lower end of the first connecting rod 200 is disengaged from the locking of the top post 10.
In one embodiment, the triggering device 500 may be a cylinder, and a movable end of the cylinder is disposed at a lower end of the second connecting rod 300, and when the cylinder is operated, the movable end of the cylinder extends to push the second connecting rod 300 to move; in another embodiment, the triggering device 500 may include a spring, a push post and a fixing member for locking the spring, one end of the spring is fixedly disposed, the other end of the spring is connected to the push post, the push post is disposed at the lower end of the second connecting rod 200, the spring is locked by the fixing member in a certain compressed state, and the push post pushes the second connecting rod 200 to move under the action of the spring by driving the fixing member to leave the locking position.
In a preferred embodiment, the upper free arm of the second link 300 is aligned with the third link 400, and the lower free arm of the second link 300 abuts against the trigger 500, so that the trigger 500 prevents the second link 300 from rotating clockwise. Based on this, the third link 400 and the upper free arm of the second link 300 can move only within a range: the third link 400 and the upper free arm of the second link 300 are in a straight line to the third link 400 and the upper free arm of the second link 300 are integrally deflected upward by a certain angle, that is, the upper free arm of the second link 300 cannot move towards the inner regions of the first link 200 and the second link 300, and the third link 400 cannot move towards the inner regions of the first link 200 and the second link 300.
In the preferred embodiment, when loading a missile, the top pillar 10 of the missile lifts the support pillar 220 upwards, the first link 200 rotates clockwise, the third link 400 rotates counterclockwise as a whole, i.e. from the upper parts of the first link 200 and the second link 300 to the direction of the inner parts of the first link 200 and the second link 300, the second link 200 rotates clockwise, until the free arm at the lower part of the second link 200 abuts against the trigger device 500, at this time, the first link 200, the second link 300 and the third link 400 are subjected to the abutting force to stop moving, and the free arms at the upper parts of the third link 400 and the second link 300 are in the same straight line, a dead point is formed between the third link 400 and the second link 300, at this time, no matter whether the top pillar 10 lifts the support pillar 220 upwards or the missile applies external force to the first link 200 as a whole, the free arms at the upper parts of the third link 400 and the second link 300 cannot leave the dead point position, therefore, at the moment, the missile and the missile hanging frame are in a stable connection state and cannot move mutually, and the safety of the loaded missile is effectively ensured by utilizing a dead point structure formed between the free arm at the upper part of the second connecting rod 300 and the third connecting rod 400.
The utility model discloses the guided missile stores pylon still is provided with spacing hole 600, spacing hole 600 sets up in the upper portion of second connecting rod 300 and third connecting rod 400, it is preferred, spacing hole 600 sets up with the articulated department of third connecting rod 400 corresponding to the free arm on second connecting rod 300 upper portion, when the free arm on second connecting rod 300 upper portion is in same straight line with third connecting rod 400, prevent the motion of second connecting rod 300 and third connecting rod 400 to the upper portion, it is concrete, the free arm on second connecting rod 300 upper portion is in same straight line with third connecting rod 400, insert with the spacer pin (not shown in the figure) in spacing hole 600, the spacer pin will prevent second connecting rod 300 and third connecting rod 400 to upwards rotate, thereby reliable restriction the motion of second connecting rod 300 with third connecting rod 400, avoid both to overcome the braking of dead point and take place the motion because of unusual reason.
Preferably, a clamp spring is arranged in the limiting hole 600, the clamp spring has deformability in the radial direction of the limiting hole 600, when the limiting pin is not inserted, the distance between the clamp springs is smaller than the aperture size of the limiting hole, when the limiting pin is inserted, the clamp spring is opened, after the limiting pin is inserted, the restoring force of the clamp spring acts on the limiting pin, and the stability of the position of the limiting pin is ensured.
In one embodiment, in order to ensure the unlocking efficiency of the missile, the first link 200 is further connected with a first elastic member 240, one end of the first elastic member 240 is connected to a side of the first link 200 facing away from the first hook 230, and the other end of the first elastic member 240 is fixedly arranged, when the missile is loaded on the missile hanger, the first elastic member 240 is in an extended state, when the trigger device 500 triggers the unlocking, the second link 300 rotates counterclockwise, so that the second link 300 and the third link 400 are separated from the dead point position, and under the action of the first elastic member 240, the first link 200 rapidly rotates counterclockwise, so that the missile is separated from the missile hanger.
In an embodiment of the present invention, the missile hanging rack further includes a second guiding frame 800 and a first guiding frame 700, the second guiding frame 800 and the first guiding frame 700 are located on two sides of the first connecting rod 200, and the three are located on the same straight line.
In one embodiment, the second guiding frame 800 is fixedly arranged, the second guiding frame 800 is provided with a preset length, the preset length is the length of a part of the top pillar 10 exposed out of a missile hanger when the missile is loaded on the missile hanger, the first guiding frame 700 is arranged to be capable of sliding in the vertical direction, specifically, the upper end of the first guiding frame 700 is connected with a second elastic member 710, one end of the second elastic member 710 is fixedly arranged, the other end of the second elastic member 710 is connected with the first guiding frame 700, the top pillar 10 is lifted upwards in the process of loading the missile, the movement of the top pillar 10 of the first guiding frame 700 synchronously moves upwards, the second elastic member 710 is compressed, and after the top pillar 10 is lifted to a preset position, the second guiding frame 700 and the first guiding frame 800 are positioned on the same horizontal plane and attached to the upper surface of the missile, so that the body 1 of the missile is always kept in a horizontal state.
Preferably, a second hook 720 is further provided, the second hook 720 is provided on a side surface of the first guide frame 700, a third hinge (not shown) is provided on the second hook 720, and the second hook 720 can rotate relative to the third hinge to hook the second hook 720, so as to lock the position of the first guide frame 700. Preferably, a poke rod 730 is connected to the upper portion of the second hook 720, and the poke rod 730 and the second hook 720 are arranged obliquely at a certain inclination angle, so as to facilitate the operation of an operator.
Based on foretell guided missile stores pylon, the embodiment of the utility model provides a still provides a guided missile carry structure, its include carrier, guided missile and as above the guided missile stores pylon, wherein, the guided missile stores pylon is installed on the carrier, and the guided missile is installed on the guided missile stores pylon.
Preferably, the carrier comprises a drone.
While the invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (10)
1. A missile hanging rack is characterized by comprising
The middle part of the first connecting rod is provided with a first hinge part, and the first connecting rod can rotate relative to the first hinge part;
the middle part of the second connecting rod is provided with a second hinge part, and the second connecting rod can rotate relative to the second hinge part;
one end of the third connecting rod is hinged with the upper end of the first connecting rod, and the other end of the third connecting rod is hinged with the upper end of the second connecting rod;
wherein,
the missile locking device comprises a first connecting rod and a second connecting rod, wherein a supporting column is fixedly connected to the first connecting rod, the supporting column can be driven to rotate when being driven to move, and a first hook is further arranged at the lower end of the first connecting rod and used for locking a missile to be loaded.
2. The missile pylon of claim 1 wherein the second link is an L-shaped structure, and the second hinge portion is located at the intersection of two free arms of the second link.
3. The missile pylon of claim 2, further comprising a trigger device located at a lower end of the second link.
4. The missile pylon of claim 2, wherein the third link and/or the second link are provided at their upper ends with a limit hole.
5. The missile hanger defined in claim 4, wherein the limiting hole is provided with a circlip having elasticity in a radial direction thereof.
6. The missile hanger defined in claim 2, wherein the lower end of the first link is further connected with a first elastic member, one end of the first elastic member is fixedly arranged, and the other end of the first elastic member is connected to a side of the first link, which faces away from the hook.
7. The missile hanger defined in any one of claims 1 to 6, further comprising a first guide frame and a second elastic member disposed at an upper portion of the first guide frame, wherein one end of the second elastic member is fixedly disposed and the other end of the second elastic member is connected to an upper end of the first guide frame.
8. The missile hanger of claim 7, further comprising a second hook, wherein the second hook is provided with a third hinge, the second hook can rotate relative to the third hinge, and a poker rod is connected to the upper portion of the second hook.
9. A missile mounting structure, comprising a carrier, a missile and a missile mounting frame according to any one of claims 1 to 8, wherein the missile mounting frame is mounted on the carrier, and the missile is mounted on the missile mounting frame.
10. The missile mounting structure of claim 9, wherein the carrier is a drone.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920631442.4U CN210162264U (en) | 2019-05-05 | 2019-05-05 | Guided missile hanging frame and guided missile hanging structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920631442.4U CN210162264U (en) | 2019-05-05 | 2019-05-05 | Guided missile hanging frame and guided missile hanging structure |
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| CN210162264U true CN210162264U (en) | 2020-03-20 |
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| CN201920631442.4U Active CN210162264U (en) | 2019-05-05 | 2019-05-05 | Guided missile hanging frame and guided missile hanging structure |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110127058A (en) * | 2019-05-05 | 2019-08-16 | 哈瓦国际航空技术（深圳）有限公司 | Guided missile hanger and guided missile hanging structure |
| CN112407287A (en) * | 2021-01-25 | 2021-02-26 | 西安富沃德光电科技有限公司 | Missile hanging rack and using method thereof |
-
2019
- 2019-05-05 CN CN201920631442.4U patent/CN210162264U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110127058A (en) * | 2019-05-05 | 2019-08-16 | 哈瓦国际航空技术（深圳）有限公司 | Guided missile hanger and guided missile hanging structure |
| CN110127058B (en) * | 2019-05-05 | 2024-06-14 | 哈瓦国际航空技术（深圳）有限公司 | Missile hanger and missile mounting structure |
| CN112407287A (en) * | 2021-01-25 | 2021-02-26 | 西安富沃德光电科技有限公司 | Missile hanging rack and using method thereof |
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