CN110127058B - Missile hanger and missile mounting structure - Google Patents
Missile hanger and missile mounting structure Download PDFInfo
- Publication number
- CN110127058B CN110127058B CN201910366441.6A CN201910366441A CN110127058B CN 110127058 B CN110127058 B CN 110127058B CN 201910366441 A CN201910366441 A CN 201910366441A CN 110127058 B CN110127058 B CN 110127058B
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- missile
- connecting rod
- link
- hook
- hanger
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- 230000000694 effects Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000005856 abnormality Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000001066 destructive effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D7/00—Arrangement of military equipment, e.g. armaments, armament accessories or military shielding, in aircraft; Adaptations of armament mountings for aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/15—UAVs specially adapted for particular uses or applications for conventional or electronic warfare
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Load-Engaging Elements For Cranes (AREA)
Abstract
The invention discloses a missile hanger and a missile mounting structure, and belongs to the technical field of missile loading. The missile hanger 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 first connecting rod is fixedly connected with a supporting column, the supporting column can drive the first connecting rod 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 mounted. The missile loading structure is simple, light and convenient to install.
Description
Technical Field
The invention relates to the technical field of weapon installation, in particular to a missile hanger and a missile mounting structure.
Background
The missile has ultrahigh destructive power, and the safety of the missile is an important consideration before being put in. Before the missile is put in, the missile is generally fixed on a carrier through a hanging frame, so that the safety of the missile is guaranteed, the conventional hanging frame is quite complex in general structure, and if the missile is installed on the carrier with weaker bearing capacity (such as an unmanned aerial vehicle), the weight of the hanging frame is too large, so that the normal operation of the carrier can be influenced.
Therefore, there is a need for a simple, lightweight missile pylon.
Disclosure of Invention
In order to solve the defects in the prior art, the embodiment of the invention provides the missile hanger which is simple in structure and light in weight.
The technical scheme adopted by the embodiment of the invention for solving the technical problems is as follows: the missile hanger 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 first connecting rod is fixedly connected with a supporting column, the supporting column can drive the first connecting rod 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 mounted.
As a further improvement of the above technical solution, the second connecting rod has an L-shaped structure, and the second hinge portion is disposed at a junction of two free arms of the second connecting rod.
As a further improvement of the above technical solution, the device further comprises a triggering device, wherein the triggering device is located at the lower end of the second connecting rod.
As a further improvement of the technical scheme, the upper end of the third connecting rod and/or the upper end of 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 clamping spring with elasticity along the radial direction.
As a further improvement of the technical scheme, the lower end of the first connecting rod is also connected with a first elastic piece, one end of the first elastic piece is fixedly arranged, and the other end of the first elastic piece is connected to one side, opposite to the hook, of the first connecting rod.
As a further improvement of the technical scheme, the device further comprises a first guide frame and a second elastic piece arranged on the upper portion of the first guide frame, one end of the second elastic piece is fixedly arranged, and the other end of the second elastic piece is connected to the upper end of the first guide frame.
As a further improvement of the technical scheme, the novel lifting 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 a poking rod is connected to the upper portion of the second hook.
The embodiment of the invention also provides a missile-mounted structure, which comprises a carrier, a missile and the missile pylon as described above, wherein the missile pylon is mounted on the carrier, and the missile is mounted on the missile pylon.
As a further improvement of the above technical solution, the carrier is an unmanned aerial vehicle.
The invention has the beneficial effects that:
In the embodiment of the invention, when the missile is loaded, the missile and the missile hanger are mutually closed, the prop on the missile props up the propping column connected to the first connecting rod, so that the first connecting rod rotates, the second connecting rod and the third connecting rod move together along with the movement of the first connecting rod, and the prop on the missile is hooked by the hook on the first connecting rod, thereby conveniently realizing the missile loading.
Drawings
The invention will be further described with reference to the drawings and examples.
FIG. 1 is a schematic view of one embodiment of a missile pylon according to the present invention.
Detailed Description
The conception, specific structure, and technical effects produced by the present application will be clearly and completely described below with reference to the embodiments and the drawings to fully understand the objects, aspects, and effects of the present application. It should be noted that, without conflict, the embodiments of the present application and features of the embodiments may be combined with each other.
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 or indirectly fixed or connected to the other feature. Further, the descriptions of the upper, lower, left, right, front, rear, etc. used in the present invention are merely with respect to the mutual positional relationship of the respective constituent elements 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 presented herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The term "and/or" as used herein includes any combination of one or more of the associated listed items.
In general, the missile is designed into a general structure, as shown in fig. 1, the missile comprises a body 1 and a jack post 10 arranged on the body 1, and in practical application, the missile can be designed into various shapes, but the jack post 10 can be reserved as a standard connecting piece so as to facilitate the assembly of the missile.
As shown in fig. 1, the present invention aims to provide a missile hanger capable of effectively reducing its own weight with simple structure, comprising a first link 200, a second link 300 and a third link 400, wherein a first hinge part 210 is provided at the middle of the first link 200, the first link 200 itself can rotate relative to the first hinge part 210, a second hinge part 310 is provided at the middle of the second link 300, the second link 300 itself can rotate relative to the second hinge part 310, the third link 400 is provided between the first link 200 and the second link 300, one end of the third link 400 is hinged with the upper end of the first link 200, the other end of the third link 400 is hinged with the upper end of the second link 300, wherein a supporting post 220 is fixedly provided on the first link 200, the supporting post 220 is lifted upwards when the missile is loaded, the first link 200 rotates relative to the first hinge part 210, a first hook 230 is provided at the lower end of the first link 200, and when the first link 200 is driven to rotate, the first hook 230 rotates towards the supporting post 10, and hooks the missile hanger 10 to lock the missile hanger.
The second link 300 is preferably designed as an L-shaped structure, and the second hinge 310 is disposed at the junction of two free arms of the second link 300, and one free arm of the second link 300 rotates to drive the other free arm of the second link 300 to rotate.
The first link 200 has an overall elongated structure, and the third link 400 is disposed laterally between the first link 200 and the second link 300.
Preferably, the missile hanger in the embodiment of the present invention further includes a triggering device 500, where the triggering device 500 is located at the lower end of the second link 300, as shown in fig. 1, the triggering device 500 or a component in the triggering device 500 has a rightward movement capability, when the missile is unlocked, the triggering device 500 or a component in the triggering device 500 moves rightward, pushes the second link 300 to rotate the second link 300 counterclockwise, and the third link 400 is driven by the second link 300 to rotate clockwise integrally and drive the first link 200 to rotate counterclockwise, so that the first hook 230 at the lower end of the first link 200 breaks away from the locking of the top post 10.
In one embodiment, the triggering device 500 may be a cylinder, the movable end of which is disposed at the lower end of the second connecting rod 300, and when the cylinder works, the movable end of the cylinder stretches out to push the second connecting rod 300 to move; in another embodiment, the triggering device 500 may include a spring, a pushing post, and a fixing member for locking the spring, where one end of the spring is fixedly disposed, the other end of the spring is connected to the pushing post, the pushing post is disposed at the lower end of the second link 200, the spring is locked by the fixing member in a certain compressed state, and the fixing member is driven to leave the locking position, so that the pushing post pushes the second link 200 to move under the action of the spring.
In a preferred embodiment, the free arm of the upper portion of the second link 300 is in line with the third link 400, and the free arm of the lower portion of the second link 300 abuts the triggering device 500, at which time the triggering device 500 prevents the second link 300 from rotating in a clockwise direction. Based on this, the third link 400 and the free arm at the upper part of the second link 300 can move only within a range of: the position where the free arm of the upper portion of the third link 400 and the second link 300 is in line is such that the free arm of the upper portion of the third link 400 and the second link 300 is entirely deflected upward by a certain angle, that is, the free arm of the upper portion of the second link 300 cannot move toward the inner regions of the first link 200 and the second link 300, and the third link 400 cannot move toward the inner regions of the first link 200 and the second link 300.
In the preferred embodiment, when loading the missile, the jack post 10 of the missile lifts up against the holding post 220, the first link 200 rotates clockwise, the third link 400 rotates counterclockwise as a whole, that is, from the upper parts of the first link 200 and the second link 300 toward the inside 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 triggering device 500, at this time, the first link 200, the second link 300 and the third link 400 are stopped by the abutting force, the free arms at the upper parts of the third link 400 and the second link 300 are on the same straight line, and dead points are formed between the third link 400 and the second link 300, at this time, no external force is applied to the first link 200 as a whole by the jack post 10 lifting up against the holding post 220, and no external force is applied to the third link 400 and the free arm at the upper part of the second link 300, so that the missile cannot leave the dead point position, at this time, the missile and the missile hanger are in a stable connection state, at this time, mutual movement cannot occur, and the safety of the missile is effectively loaded by the free arms at the upper part of the second link 300 and the third link 400.
The missile hanger according to the embodiment of the present invention is further provided with a limiting hole 600, wherein the limiting hole 600 is disposed at the upper portions of the second connecting rod 300 and the third connecting rod 400, preferably, the limiting hole 600 is disposed corresponding to the hinge position of the free arm at the upper portion of the second connecting rod 300 and the third connecting rod 400, when the free arm at the upper portion of the second connecting rod 300 and the third connecting rod 400 are in the same straight line, the second connecting rod 300 and the third connecting rod 400 are prevented from moving upwards, specifically, a limiting pin (not shown in the figure) is inserted into the limiting hole 600, and the limiting pin prevents the second connecting rod 300 and the third connecting rod 400 from rotating upwards, thereby reliably limiting the movement of the second connecting rod 300 and the third connecting rod 400, and avoiding the movement of the second connecting rod 300 and the third connecting rod 400 due to abnormality and overcoming the dead center braking.
Preferably, a snap spring is arranged in the limiting hole 600, the snap spring has deformability in the radial direction of the limiting hole 600, when the limiting pin is not inserted, the distance between the snap springs is smaller than the aperture of the limiting hole, when the limiting pin is inserted, the snap spring is opened, and after the limiting pin is inserted, the restoring force of the snap spring acts on the limiting pin, so that 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 connecting rod 200 is further connected with a first elastic member 240, one end of the first elastic member 240 is connected to one side of the first connecting rod 200 opposite to the first hook 230, 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, and when the triggering device 500 triggers unlocking, the second connecting rod 300 rotates anticlockwise, so that the second connecting rod 300 and the third connecting rod 400 are separated from the dead point position, and under the action of the first elastic member 240, the first connecting rod 200 rotates anticlockwise rapidly, so that the missile is separated from the missile hanger.
In one embodiment of the present invention, the missile hanger further includes a second guide frame 800 and a first guide frame 700, wherein the second guide frame 800 and the first guide frame 700 are located at two sides of the first link 200, and the three are located on the same straight line.
In one embodiment, the second guide frame 800 is fixedly arranged, the second guide frame 800 is provided with a preset length, the preset length is the length of a part of the jack post 10 exposed out of the missile hanger when the missile is loaded on the missile hanger, the first guide frame 700 is arranged in the upper and lower direction and can slide, specifically, the upper end of the first guide frame 700 is connected with the second elastic piece 710, one end of the second elastic piece 710 is fixedly arranged, the other end of the second elastic piece 710 is connected with the first guide frame 700, the jack post 10 is lifted upwards in the missile loading process, the movement of the jack post 10 of the first guide frame 700 moves upwards synchronously and compresses the second elastic piece 710, and after the jack post 10 is lifted to a preset position, the second guide frame 700 and the first guide frame 800 are positioned on the same horizontal plane and are attached to the upper surface of the missile, so that the body 1 of the missile always maintains the horizontal state.
Preferably, a second hook 720 is further provided, the second hook 720 is disposed on a side surface of the first guide frame 700, a third hinge portion (not shown in the figure) is disposed on the second hook 720, and the second hook 720 can rotate relative to the third hinge portion to hook the second hook 720, so as to lock the position of the first guide frame 700. Preferably, the second hook 720 has a toggle lever 730 connected to an upper portion thereof, and the toggle lever 730 and the second hook 720 are disposed at an inclination angle so as to be convenient for an operator to operate.
Based on the missile pylon, the embodiment of the invention also provides a missile mounting structure, which comprises a carrier, a missile and the missile pylon, wherein the missile pylon is arranged on the carrier, and the missile is arranged on the missile pylon.
Preferably, the carrier comprises a drone.
While the application has been described with reference to the preferred embodiments, it will be understood by those skilled in the art that various changes and substitutions may be made therein without departing from the spirit of the application and that these changes and substitutions are intended in the scope of the application as defined by the appended claims.
Claims (10)
1. A missile hanger, 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 first connecting rod is fixedly connected with a supporting column, the supporting column can drive the first connecting rod 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 mounted;
When a missile is loaded, the propping column of the missile upwards props up the propping column to enable the propping column to deflect upwards, the first connecting rod rotates relative to the first hinge part, and when the first connecting rod is driven to rotate, the first hook rotates towards the propping column and hooks the propping column to lock the missile and the missile hanger;
The missile hanger further comprises a trigger device, when the missile is unlocked, the trigger device pushes the second connecting rod to enable the second connecting rod to rotate anticlockwise, and the third connecting rod is driven by the second connecting rod to rotate clockwise integrally and drive the first connecting rod to rotate anticlockwise, so that the first hook at the lower end of the first connecting rod breaks away from locking of the top column.
2. The missile hanger of claim 1, wherein the second link has an L-shaped configuration, and the second hinge is provided at the junction of two free arms of the second link.
3. The missile pylon according to claim 2 wherein the trigger means is located at the lower end of the second link.
4. Missile hanger according to claim 2, wherein the upper end of the third link and/or the second link is provided with a limiting hole.
5. The missile hanger according to claim 4 wherein the limiting aperture has a snap spring having elasticity in a radial direction thereof.
6. The missile hanger according to claim 2, wherein the lower end of the first connecting rod 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 the side of the first connecting rod opposite to the hook.
7. The missile hanger according to any one of claims 1 to 6 further including a first guide frame and a second elastic member provided on an upper portion of the first guide frame, one end of the second elastic member being fixedly provided, and the other end of the second elastic member being connected to an upper end of the first guide frame.
8. The missile hanger of claim 7, further comprising a second hook, wherein a third hinge is provided on the second hook, the second hook is rotatable relative to the third hinge, and a tap lever is connected to an upper portion of the second hook.
9. A missile-mounting structure comprising a carrier, a missile and a missile pylon according to any one of claims 1 to 8, the missile pylon being mounted on the carrier, the missile being mounted on the missile pylon.
10. The missile mounting structure of claim 9, wherein the carrier is an unmanned aerial vehicle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910366441.6A CN110127058B (en) | 2019-05-05 | 2019-05-05 | Missile hanger and missile mounting structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910366441.6A CN110127058B (en) | 2019-05-05 | 2019-05-05 | Missile hanger and missile mounting structure |
Publications (2)
| Publication Number | Publication Date |
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| CN110127058A CN110127058A (en) | 2019-08-16 |
| CN110127058B true CN110127058B (en) | 2024-06-14 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910366441.6A Active CN110127058B (en) | 2019-05-05 | 2019-05-05 | Missile hanger and missile mounting structure |
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| CN (1) | CN110127058B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110631420B (en) * | 2019-09-24 | 2021-12-03 | 上海机电工程研究所 | Airborne suspended object ejection mechanism |
| CN110562463B (en) * | 2019-10-09 | 2025-04-29 | 郑州郑飞机电技术有限责任公司 | A new type of transfer beam with a stable structural system |
| CN112693612A (en) * | 2019-10-23 | 2021-04-23 | 北京东方瑞星科技发展有限公司南京分公司 | Unmanned aerial vehicle carries shell carry device based on lever locking |
| CN112693616A (en) * | 2019-10-23 | 2021-04-23 | 北京东方瑞星科技发展有限公司南京分公司 | Unmanned aerial vehicle carries shell carry device based on slider auto-lock |
| CN114739231B (en) * | 2021-12-30 | 2024-06-18 | 南京奎道科技有限公司 | Plate-frame type light-weight low-wind-resistance fast-constraint airborne suspension device |
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| GB497090A (en) * | 1937-05-07 | 1938-12-07 | Vickers Armstrongs Ltd | Improvements in or relating to means for carrying heavy bodies on and releasing themfrom aircraft |
| US5887924A (en) * | 1997-05-13 | 1999-03-30 | Green; Stephen J. | Cargo hook |
| CN210162264U (en) * | 2019-05-05 | 2020-03-20 | 哈瓦国际航空技术（深圳）有限公司 | Guided missile hanging frame and guided missile hanging structure |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US3982466A (en) * | 1974-08-14 | 1976-09-28 | Baker Curtis K | Compound action release linkage |
| DE3815022A1 (en) * | 1988-05-03 | 1989-11-16 | Messerschmitt Boelkow Blohm | DEVICE FOR SUSPENDING, CUTTING OFF AND LAUNCHING AIRCRAFT |
| DE19648609A1 (en) * | 1996-11-14 | 1998-05-20 | Bodenseewerk Geraetetech | Locking assembly in a missile launch device |
| CN105438473B (en) * | 2015-12-11 | 2017-05-10 | 中航电测仪器股份有限公司 | Quick hanging release mechanism and method thereof |
| CN109625270A (en) * | 2018-12-29 | 2019-04-16 | 中航电测仪器股份有限公司 | A kind of helicopter handling carry device and its operation method |
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2019
- 2019-05-05 CN CN201910366441.6A patent/CN110127058B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB497090A (en) * | 1937-05-07 | 1938-12-07 | Vickers Armstrongs Ltd | Improvements in or relating to means for carrying heavy bodies on and releasing themfrom aircraft |
| US5887924A (en) * | 1997-05-13 | 1999-03-30 | Green; Stephen J. | Cargo hook |
| CN210162264U (en) * | 2019-05-05 | 2020-03-20 | 哈瓦国际航空技术（深圳）有限公司 | Guided missile hanging frame and guided missile hanging structure |
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| Publication number | Publication date |
|---|---|
| CN110127058A (en) | 2019-08-16 |
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