CN110127058A - Guided missile hanger and guided missile hanging structure - Google Patents
Guided missile hanger and guided missile hanging structure Download PDFInfo
- Publication number
- CN110127058A CN110127058A CN201910366441.6A CN201910366441A CN110127058A CN 110127058 A CN110127058 A CN 110127058A CN 201910366441 A CN201910366441 A CN 201910366441A CN 110127058 A CN110127058 A CN 110127058A
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- China
- Prior art keywords
- connecting rod
- guided missile
- hook
- hanger
- articulated section
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- 238000009434 installation Methods 0.000 abstract description 2
- 125000006850 spacer group Chemical group 0.000 description 7
- 240000007643 Phytolacca americana Species 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000001066 destructive effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 230000000717 retained effect Effects 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—Arrangements 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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Load-Engaging Elements For Cranes (AREA)
Abstract
The invention discloses a kind of guided missile hanger and guided missile hanging structures, belong to guided missile and load technical field.Guided missile hanger of the invention includes first connecting rod, and the middle part of the first connecting rod is equipped with the first articulated section, and the first connecting rod can be rotated relative to first articulated section；The middle part of second connecting rod, the second connecting rod is equipped with the second articulated section, and the second connecting rod can be rotated relative to second articulated section；The upper end of third connecting rod, one end of the third connecting rod and the first connecting rod is articulated and connected, and the upper end of the other end of the third connecting rod and the second connecting rod is articulated and connected；Wherein, supporting rod is fixedly connected on the first connecting rod, supporting rod will drive the first connecting rod when mobile by driving and rotate, and the lower end of the first connecting rod is additionally provided with the first hook, for locking the guided missile for needing carry.Guided missile hanging structure of the invention is simple, light-weight, easy for installation.
Description
Technical field
The present invention relates to weapon mounting technique fields, more particularly, to a kind of guided missile hanger and guided missile hanging structure.
Background technique
Guided missile has the destructive power of superelevation, and before dispensing, the safety of guided missile is highly important Consideration.Guided missile is launched
It is fixedly mounted on carrier as previous by hanger, in order to guarantee the safety of guided missile, existing hanger general structure is very multiple
Miscellaneous, if be mounted on the weaker carrier of bearing capacity (such as unmanned plane), the weight of hanger itself is excessive, influences whether carrier
It operates normally.
Therefore, it is necessary to provide the guided missile hanger that a kind of structure is simple, light-weight.
Summary of the invention
In order to solve the deficiencies in the prior art, the embodiment of the present invention provides the guided missile hanger that a kind of structure is simple, light-weight.
The embodiment of the present invention solves the technical solution that above-mentioned technical problem is taken are as follows: a kind of guided missile hanger is provided, including
First connecting rod, the middle part of the first connecting rod are equipped with the first articulated section, and the first connecting rod can relatively described first articulated section turn
It is dynamic；The middle part of second connecting rod, the second connecting rod is equipped with the second articulated section, and the second connecting rod can relatively described second articulated section
Rotation；The upper end of third connecting rod, one end of the third connecting rod and the first connecting rod is articulated and connected, the third connecting rod it is another
One end and the upper end of the second connecting rod are articulated and connected；Wherein, supporting rod, supporting rod quilt are fixedly connected on the first connecting rod
Driving will drive the first connecting rod rotation when mobile, the lower end of the first connecting rod is additionally provided with the first hook, needs for locking
Want the guided missile of carry.
As a further improvement of the above technical scheme, the L-shaped structure of the second connecting rod, second articulated section are set to
The intersection of two free arms of the second connecting rod.
It as a further improvement of the above technical scheme, further include trigger device, the trigger device is located at described second
The lower end of connecting rod.
As a further improvement of the above technical scheme, the upper end of the third connecting rod and/or the second connecting rod is arranged
There is limit hole.
As a further improvement of the above technical scheme, the limit hole is equipped with the radially flexible card in direction
Spring.
As a further improvement of the above technical scheme, the lower end of the first connecting rod is also connected with the first elastic component, institute
The fixed setting of first elastic component one end is stated, the other end of first elastic component is connected to the first connecting rod back to the hook
Side.
As a further improvement of the above technical scheme, further include the first leading truck and be set to first leading truck on
Second elastic component in portion, one end fixed setting of second elastic component, the other end of second elastic component is connected to described
The upper end of first leading truck.
It as a further improvement of the above technical scheme, further include the second hook, second hook is equipped with third and cuts with scissors
Socket part, second hook can be rotated relative to the third articulated section, and the top of second hook is connected with poke rod.
The embodiment of the present invention also provides a kind of guided missile hanging structure, including carrier, guided missile and guided missile as described above are hung
Frame, the guided missile hanger are installed on the carrier, and the guided missile is installed on the guided missile hanger.
As a further improvement of the above technical scheme, the carrier is unmanned plane.
Beneficial effects of the present invention:
Guided missile loading be by the way that missile-borne top pillar is locked, in the embodiment of the present invention, when loading guided missile, guided missile and guided missile
Hanger is mutually drawn close, and missile-borne top pillar jacks up the supporting rod being connected on first connecting rod upwards, so that first connecting rod rotates,
Second connecting rod, the third connecting rod associated movement with the movement of first connecting rod, and will be missile-borne by the hook on first connecting rod
Top pillar is caught on, to easily realize the loading of guided missile, guided missile hanging structure of the invention is simple, light-weight, easy for installation.
Detailed description of the invention
Present invention will be further explained below with reference to the attached drawings and examples.
Fig. 1 is the structural schematic diagram of guided missile hanger one embodiment of the invention.
Specific embodiment
It is carried out below with reference to technical effect of the embodiment and attached drawing to design of the invention, specific structure and generation clear
Chu, complete description, to be completely understood by the purpose of the present invention, scheme and effect.It should be noted that the case where not conflicting
Under, the features in the embodiments and the embodiments of the present application can be combined with each other.
It should be noted that unless otherwise specified, when a certain feature referred to as " fixation ", " connection " are in another feature,
It can directly fix, be connected to another feature, and can also fix, be connected to another feature indirectly.In addition, this
The descriptions such as up, down, left, right, before and after used in invention are only relative to the mutual of each component part of the invention in attached drawing
For positional relationship.
In addition, unless otherwise defined, the technology of all technical and scientific terms used herein and the art
The normally understood meaning of personnel is identical.Term used in the description is intended merely to description specific embodiment herein, without
It is to limit the present invention.Term " and or " used herein includes the arbitrary of one or more relevant listed items
Combination.
In general, guided missile is designed to general structure, such as Fig. 1, guided missile includes ontology 1 and the top pillar that is set on ontology 1
10, in practical applications, guided missile may be designed to a variety of different moulding, but top pillar 10 can be retained as standard connector
Get off, in order to the assembly of guided missile.
Such as Fig. 1, the present invention is intended to provide a kind of structure is simple, the guided missile hanger of own wt can be effectively reduced, including the
One connecting rod 200, second connecting rod 300 and third connecting rod 400, the middle part of first connecting rod 200 are equipped with the first articulated section 210, and first
Connecting rod 200 itself can be rotated relative to the first articulated section 210, and the middle part of second connecting rod 300 is equipped with the second articulated section 310, and second connects
Bar 300 itself can be rotated relative to the second articulated section 310, and third connecting rod 400 is set between first connecting rod 200 and second connecting rod 300,
One end of third connecting rod 400 and the upper end of first connecting rod 200 are articulated and connected, the other end and second connecting rod 300 of third connecting rod 400
Upper end articulated connection, wherein be installed with supporting rod 220 on first connecting rod 200, when guided missile loads, top pillar 10 jacks up support upwards
Holding column 220 upward deflects supporting rod, and first connecting rod 200 is rotated relative to the first articulated section 210 therewith, under first connecting rod 200
End is equipped with the first hook 230, and when first connecting rod 200 is rotated by driving, the first hook 230 is rotated towards top pillar 10, and is hooked
Top pillar 10 locks guided missile and guided missile hanger.
Second connecting rod 300 is preferably designed to L-shaped structure, and the second articulated section 310 is set to two of second connecting rod 300
The intersection of free arm, second connecting rod 300 a free arm rotation, will drive second connecting rod 300 another free arm with
Rotation.
The whole elongated structure of first connecting rod 200, third connecting rod 400 are horizontally set at first connecting rod 200 and second and connect
Between bar 300.
Preferably, guided missile hanger further includes trigger device 500 in the embodiment of the present invention, and trigger device 500 is located at second and connects
The lower end of bar 300 is solving as shown in Figure 1, the component in trigger device 500 or trigger device 500 has the ability to move right
When locking guided missile, the component in trigger device 500 or trigger device 500 moves right, and second connecting rod 300 is pushed, the second company is made
Bar 300 rotates counterclockwise, and third connecting rod 400 integrally rotates clockwise under the drive of second connecting rod 300, and drives first connecting rod
200 rotate counterclockwise, so that the first hook 230 of the lower end of first connecting rod 200 is detached from the locking to top pillar 10.
In one embodiment, trigger device 500 can be cylinder, and the movable end of cylinder is set under second connecting rod 300
End, when cylinder operation, the movable end of cylinder stretches out, and second connecting rod 300 is pushed to move；In another embodiment, triggering dress
Setting 500 may include spring, the fixing piece for pushing away column and locking spring, and spring one end is fixedly installed, and other end connection pushes away column, push away
Column is set to the lower end of second connecting rod 200, and spring is with certain compressive state fixture locking, by driving fixing piece to leave lock
Stop bit is set, and pushes second connecting rod 200 to move under the action of the spring so that pushing away column.
In a preferred embodiment, the free arm Yu third connecting rod 400 on the top of second connecting rod 300 is in same straight line
On, free arm and the trigger device 500 of the lower part of second connecting rod 300 support, at this point, trigger device 500 prevents second connecting rod 300
In clockwise direction rotate.It, can only be one between the free arm on the top of third connecting rod 400 and second connecting rod 300 based on this
Movement, the range in range are as follows: third connecting rod 400 and the free arm on the top of second connecting rod 300 are arrived in the position of straight line
The free arm on the top of third connecting rod 400 and second connecting rod 300 integrally upward deflects certain angle, i.e., second connecting rod 300 is upper
The free arm in portion is moved without the interior zone of normal direction first connecting rod 200 and second connecting rod 300, and third connecting rod 400 is also without normal direction the
The interior zone of one connecting rod 200 and second connecting rod 300 moves.
In a preferred embodiment, when loading guided missile, the top pillar 10 of guided missile jacks supporting rod 220, first connecting rod 200 upwards
It rotates clockwise, third connecting rod 400 is whole to be rotated counterclockwise, i.e., from the top of first connecting rod 200 and second connecting rod 300 towards the
One connecting rod 200 and the direction of the inside of second connecting rod 300 rotate, and second connecting rod 200 then rotates clockwise, until second connecting rod
The free arm of 200 lower part is supported with trigger device 500, at this point, first connecting rod 200, second connecting rod 300, third connecting rod 400 by
To resist force stop motion, and third connecting rod 400 and the free arm on 300 top of second connecting rod are on same straight line, and third connects
Dead point is formed between bar 400 and second connecting rod 300, at this moment, either jacking supporting rod 220 or guided missile are whole upwards for top pillar 10
Apply external force to first connecting rod 200, third connecting rod 400 and the free arm on 300 top of second connecting rod can not all be made to leave dead point position
It sets, therefore, at this time in firm connection status between guided missile and guided missile hanger, the two can not occur mutually to move, and utilize the
The peace under guided missile loads has been effectively ensured in the dead point structure formed between the free arm and third connecting rod 400 on two connecting rods, 300 top
Quan Xing.
The guided missile hanger of the embodiment of the present invention is additionally provided with limit hole 600, limit hole 600 be set to second connecting rod 300 with
The top of third connecting rod 400, it is preferred that limit hole 600 corresponds to the free arm and third connecting rod 400 on 300 top of second connecting rod
Hinged place setting, 300 top of second connecting rod free arm and third connecting rod 400 be in same straight line when, prevent second company
Bar 300 and third connecting rod 400 are to ionized motion, specifically, at the free arm and third connecting rod 400 on 300 top of second connecting rod
In same linear, be inserted into limit hole 600 with spacer pin (not shown), spacer pin will prevent second connecting rod 300 with
Third connecting rod 400 is rotated up, to reliably limit the movement of second connecting rod 300 Yu third connecting rod 400, both avoid because
For abnormal cause overcomes the braking at dead point and moves.
Preferably, circlip is provided in limit hole 600, circlip has the morphotropism to limit hole 600 in the radial direction, not
When being inserted into spacer pin, the spacing between circlip is less than the pore size of limit hole, and when being inserted into spacer pin, circlip is flared, and
After spacer pin completes insertion, the restoring force of circlip is acted on spacer pin, guarantees the stability of the position of spacer pin.
In one embodiment, in order to guarantee the unlock efficiency of guided missile, first connecting rod 200 is also connected with the first elastic component
240, one end of the first elastic component 240 be connected to first connecting rod 200 back to first hook 230 side, the first elastic component 240
Other end fixed setting, when guided missile is loaded on guided missile hanger, the first elastic component 240 is in elongation state, trigger device 500
When triggering unlock, second connecting rod 300 is rotated counterclockwise, and second connecting rod 300 and third connecting rod 400 is made to be detached from dead-centre position, the
Under the action of one elastic component 240, first connecting rod 200 is quickly rotated counterclockwise, and guided missile is made to be detached from guided missile hanger.
In an embodiment of the invention, guided missile hanger further includes the second leading truck 800 and the first leading truck 700, and second
Leading truck 800 and the first leading truck 700 are located at the two sides of first connecting rod 200, and three is located along the same line.
In one embodiment, the second leading truck 800 is fixedly installed, and preset length is arranged in the second leading truck 800, this is pre-
If length be guided missile when being loaded on guided missile hanger, top pillar 10 exposes the length of the part of guided missile hanger, the first leading truck 700
Setting can be slided in the up-down direction, specifically, the upper end of the first leading truck 700 is connected with the second elastic component 710, the second bullet
Property part 710 one end fixed setting, the other end of the second elastic component 710 connect with the first leading truck 700, in the mistake of guided missile loading
Cheng Zhong, top pillar 10 jack upwards, and the movement of the first top pillar of leading truck 700 years old 10, which synchronizes, to be moved upwards, and compress the second elastic component
710, after the jacking of top pillar 10 is to predetermined position, the second leading truck 700, the first leading truck 800 are in same level, and paste
The upper surface for closing guided missile, makes the ontology 1 of guided missile remain horizontality.
Preferably, it is additionally provided with the second hook 720, the second hook 720 is set to the side of the first leading truck 700, and second hangs
Hook 720 is equipped with third articulated section (not shown), and the second hook 720 can be rotated relative to third articulated section, to hook the
Two hooks 720, with the position of the first leading truck of locking 700.Preferably, the top of the second hook 720 is connected with poke rod 730,
Poke rod 730 and the second hook 720 are arranged with certain oblique angle, in order to which operator operates.
Based on above-mentioned guided missile hanger, the embodiment of the present invention also provides a kind of guided missile hanging structure comprising carrier, guided missile
And guided missile hanger as described above, wherein guided missile hanger is installed on carrier, and guided missile is installed on guided missile hanger.
Preferably, carrier includes unmanned plane.
It is to be illustrated to what preferable implementation of the invention carried out, but the invention is not limited to the implementation above
Example, those skilled in the art can also make various equivalent variations on the premise of without prejudice to spirit of the invention or replace
It changes, these equivalent deformations or replacement are all included in the scope defined by the claims of the present application.
Claims (10)
1. a kind of guided missile hanger, which is characterized in that including
First connecting rod, the middle part of the first connecting rod are equipped with the first articulated section, and the first connecting rod can be relatively described first hinged
Portion's rotation；
Second connecting rod, the middle part of the second connecting rod are equipped with the second articulated section, and the second connecting rod can be relatively described second hinged
Portion's rotation；
The upper end of third connecting rod, one end of the third connecting rod and the first connecting rod is articulated and connected, the third connecting rod it is another
One end and the upper end of the second connecting rod are articulated and connected；
Wherein,
Supporting rod is fixedly connected on the first connecting rod, supporting rod will drive the first connecting rod when mobile by driving and rotate,
The lower end of the first connecting rod is additionally provided with the first hook, for locking the guided missile for needing carry.
2. guided missile hanger according to claim 1, which is characterized in that the L-shaped structure of second connecting rod, second hinge
Socket part is set to the intersection of two free arms of the second connecting rod.
3. guided missile hanger according to claim 2, which is characterized in that further include trigger device, the trigger device is located at
The lower end of the second connecting rod.
4. guided missile hanger according to claim 2, which is characterized in that the third connecting rod and/or the second connecting rod
Upper end is provided with limit hole.
5. guided missile hanger according to claim 4, which is characterized in that the limit hole, which is equipped with radially direction, to be had
The circlip of elasticity.
6. guided missile hanger according to claim 2, which is characterized in that the lower end of the first connecting rod is also connected with the first bullet
Property part, first elastic component one end fixed setting, the other end of first elastic component be connected to the first connecting rod back to
The side of the hook.
7. guided missile hanger according to any one of claim 1 to 6, which is characterized in that further include the first leading truck and
The second elastic component set on first leading truck top, one end fixed setting of second elastic component, second elasticity
The other end of part is connected to the upper end of first leading truck.
8. guided missile hanger according to claim 7, which is characterized in that further include the second hook, set on second hook
There is third articulated section, second hook can be rotated relative to the third articulated section, and the top of second hook, which is connected with, dials
Lever.
9. a kind of guided missile hanging structure, which is characterized in that including carrier, guided missile and as described in any one of claims 1 to 8
Guided missile hanger, the guided missile hanger is installed on the carrier, and the guided missile is installed on the guided missile hanger.
10. guided missile hanging structure according to claim 9, which is characterized in that the carrier is unmanned plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910366441.6A CN110127058A (en) | 2019-05-05 | 2019-05-05 | Guided missile hanger and guided missile hanging structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910366441.6A CN110127058A (en) | 2019-05-05 | 2019-05-05 | Guided missile hanger and guided missile hanging structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110127058A true CN110127058A (en) | 2019-08-16 |
Family
ID=67576019
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910366441.6A Pending CN110127058A (en) | 2019-05-05 | 2019-05-05 | Guided missile hanger and guided missile hanging structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110127058A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110562463A (en) * | 2019-10-09 | 2019-12-13 | 郑州郑飞机电技术有限责任公司 | Novel transition beam with stable structure system |
| CN110631420A (en) * | 2019-09-24 | 2019-12-31 | 上海机电工程研究所 | Airborne suspended object ejection mechanism |
| CN114739231A (en) * | 2021-12-30 | 2022-07-12 | 南京奎道科技有限公司 | Plate-frame type lightweight low-wind-resistance quick-restraint airborne suspension device |
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| 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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2019
- 2019-05-05 CN CN201910366441.6A patent/CN110127058A/en active Pending
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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 |
| US3982466A (en) * | 1974-08-14 | 1976-09-28 | Baker Curtis K | Compound action release linkage |
| US4922799A (en) * | 1988-05-03 | 1990-05-08 | Messerschmitt-Boelkow-Blohm Gmbh | Apparatus for suspending, strapping, and launching a flying body from a carrier |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110631420A (en) * | 2019-09-24 | 2019-12-31 | 上海机电工程研究所 | Airborne suspended object ejection mechanism |
| CN110631420B (en) * | 2019-09-24 | 2021-12-03 | 上海机电工程研究所 | Airborne suspended object ejection mechanism |
| CN110562463A (en) * | 2019-10-09 | 2019-12-13 | 郑州郑飞机电技术有限责任公司 | Novel transition beam with stable structure system |
| CN114739231A (en) * | 2021-12-30 | 2022-07-12 | 南京奎道科技有限公司 | Plate-frame type lightweight low-wind-resistance quick-restraint airborne suspension device |
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