CN207180499U - A kind of torsion bar townhouse formula Missile folded wing - Google Patents
A kind of torsion bar townhouse formula Missile folded wing Download PDFInfo
- Publication number
- CN207180499U CN207180499U CN201720874551.XU CN201720874551U CN207180499U CN 207180499 U CN207180499 U CN 207180499U CN 201720874551 U CN201720874551 U CN 201720874551U CN 207180499 U CN207180499 U CN 207180499U
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- torsion bar
- wing
- driven shaft
- missile
- driving shaft
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Abstract
It the utility model is related to a kind of torsion bar townhouse formula Missile folded wing, including support arm, outer wing, bonnet, hollow form driving shaft, hollow form driven shaft and torsion bar, driven shaft is by arranged in linear arrays on outer wing, gear is equipped with driving shaft and driven shaft, driving shaft is connected with support arm, driven shaft lateral surface is connected with outer wing, two neighboring gear intermeshes, torsion bar is set with driving shaft, driven shaft, one end of torsion bar respectively with driving shaft, driven axis connection, the other end of torsion bar is connected with bonnet, and bonnet is installed on outer wing；Use Missile folded wing of the present utility model, with it is compact-sized the characteristics of, when guided missile is positioned on launching tube or launcher, because the constrained caused restraining force of guided missile is converted to elastic potential energy, and it is allocated in a plurality of torsion bar and stores, when Missile folded wing deploys, the elastic potential energy of storage concentrates release again in torsion bar, the overall expansion moment of torsion of Missile folded wing is increased, missile wing is reliably deployed, it is ensured that guided missile is with high speed normal flight.
Description
Technical field
It the utility model is related to military equipment technical field, more particularly to a kind of torsion bar townhouse formula Missile folded wing.
Background technology
Guided missile is promoted by self power device, is guided by guidance system, is controlled its trajectory, warhead is oriented to
And the weapon of target is destroyed, belong to precision guided weapon, have the characteristics that far firing range, speed are fast, precision is high, power is big, at present,
Countries in the world pay much attention to develop missilery, and the quality and appearance and size of guided missile reflect the manufacturing technology level of guided missile,
With the development of missilery, in order to reduce missile overall dimensions, folding wing extensive use in guided missile, this folding wing
The lateral dimension of launch canister can be reduced, develops the condition of creating towards the direction of integration for launching tube and guided missile, rolls over
The operation principle of folded missile wing is when guided missile is in launching tube or on launcher, and part or all for making missile wing is rolled over
It is folded, and use restraint, and after guided missile flies away from launching tube or launcher, the folded portion of missile wing is rapid contiguity constraint, automatically
It is deployed on precalculated position, and requires the ability for bearing load dynamic and static enough, it is existing to ensure the normal flight of guided missile
In technology, Missile Folding missile wing is commonly applied on polytype guided missile such as ground-to-air missile, air-to-air missile, general using single
Root torsion bar is as elasticity of torsion part, and when guided missile is constrained on launching tube or launcher, torsion bar changes the restraining force of guided missile
Be elasticity of torsion potential energy storage in torsion bar, when guided missile flies away from launching tube or launcher, elastic potential energy release, so that missile wing
Automatic-expanding, by taking ground-to-air missile as an example, because body goes out the exhibition that a speed is smaller, and folding wing goes out with missile flight after cylinder
Suffered aerodynamic drag is smaller in open procedure, and folding wing typically can ensure missile wing within the defined time using single torsion bar
Expansion, if however, when this folding wing is used for into air-to-air missile, because the flying speed of air-to-air missile is very high, leads
Suffered gas-flow resistance is very big after bullet transmitting, relies solely on the elastic potential energy of a torsion bar storage and gas-flow resistance can not be overcome to make
Missile wing reliably deploys, the capacity for the elastic potential energy that can be stored to increase torsion bar, then needs to increase the diameter and length of torsion bar
Degree, the increase of volume is unfavorable for the installation of torsion bar, and reduces the rigidity of torsion bar, when torsion bar twists up to or overstepped the extreme limit angle
When, then the destruction of torsion bar can be caused to be broken.
Utility model content
In order to solve the above technical problems, the utility model provides a kind of torsion bar townhouse formula Missile folded wing.
The utility model provides a kind of torsion bar townhouse formula Missile folded wing, including support arm, outer wing, bonnet, hollow form master
Moving axis, hollow form driven shaft and torsion bar, the driven shaft by arranged in linear arrays on the outer wing, the driving shaft and from
Gear is equipped with moving axis, the driving shaft is connected with the support arm, and the driven shaft lateral surface is connected with the outer wing, adjacent
Two gears are intermeshed, and the torsion bar is set with driving shaft, driven shaft, one end of torsion bar respectively with driving shaft, from
Moving axis is connected, and the other end of torsion bar is connected with bonnet, and bonnet is installed on the outer wing.
The torsion bar both ends are respectively equipped with rectangle clamping head.
The clamping head is fixed on the outer peripheral face of the driving shaft or driven shaft by the clamping head using holding screw.
The gear set on the driving shaft or driven shaft, fixed the gear using holding screw by the gear
On the outer peripheral face of the driving shaft or driven shaft.
The gear is integrative-structure with the driving shaft or driven shaft.
The Missile folded wing also includes locking device.
The locking device includes sleeve, spacer pin, spring, position-limiting drum, and sleeve is fixedly installed in the support arm, spacing
Cylinder is installed on the side of the support arm, and spacer pin is set in position-limiting drum, one end of spring and sleeve connection, the other end of spring
With spacing pin connection.
The Missile folded wing also includes bushing, and the bushing is set with the driving shaft or driven shaft, and respectively
The position for securing the bushing to be close with the gear using holding screw.
The torsion bar quantity is 4.
The beneficial effects of the utility model are：
Using torsion bar townhouse formula Missile folded wing provided by the utility model, including support arm, outer wing, bonnet, hollow form
Driving shaft, hollow form driven shaft and torsion bar, the driven shaft by arranged in linear arrays on the outer wing, the driving shaft and
Gear is equipped with driven shaft, the driving shaft is connected with the support arm, and the driven shaft lateral surface is connected with the outer wing, phase
Adjacent two gears are intermeshed, and the torsion bar is set with driving shaft, driven shaft, one end of torsion bar respectively with driving shaft,
Driven axis connection, the other end of torsion bar are connected with bonnet, and bonnet is installed on the outer wing；Use technical side of the present utility model
Case, in the case where keeping Missile folded wing appearance and size limited, the ultimate torque inside Missile folded wing is added, works as guided missile
It is positioned on launching tube or launcher, because the constrained caused restraining force of guided missile is converted to elastic potential energy, and is allocated in a plurality of
Stored in torsion bar, when Missile folded wing deploys, the elastic potential energy of storage concentrates release again in torsion bar, increases Missile folded wing
Overall expansion moment of torsion, makes missile wing be enough to overcome the gas-flow resistance born after MISSILE LAUNCHING and reliably deploy, it is ensured that guided missile
With high speed normal flight, and the utility model is compact-sized, and installation is simple, and cost is cheap, and reliability is high.
Brief description of the drawings
Fig. 1 is structural representation of the present utility model；
Fig. 2 is the cross section view of the utility model front view；
Fig. 3 is the structural representation of the utility model locking device；
Fig. 4 is structural representation of the utility model along torsion bar radial direction cutting；
Fig. 5 is the structural representation of the utility model torsion bar.
In figure：1- support arms, 2- outer wings, 3- bonnets, 4- driving shafts, 5- driven shafts, 6- torsion bars, 7- gears, 8- locking devices,
9- sleeves, 10- spacer pins, 11- springs, 12- position-limiting drums, 13- power transmission shafts, 61- clamping heads.
Embodiment
The technical solution of the utility model is described further below in conjunction with accompanying drawing, but required protection domain is not
It is confined to described；
The utility model provides a kind of torsion bar townhouse formula Missile folded wing, as shown in Figure 1, Figure 2, Figure 4 shows, including support arm 1,
Outer wing 2, bonnet 3, hollow form driving shaft 4, hollow form driven shaft 5 and torsion bar 6, driven shaft 5 is by arranged in linear arrays in outer wing 2
On, gear 7 is equipped with driving shaft 4 and driven shaft 5, driving shaft 4 is connected with support arm 1, and the lateral surface of driven shaft 5 is connected with outer wing 2,
Two neighboring gear 7 is intermeshed, and torsion bar 6 is set with driving shaft 4, driven shaft 5, one end of torsion bar 6 respectively with actively
Axle 4, driven shaft 5 are connected, and the other end of torsion bar 6 is connected with bonnet 3, and bonnet 3 is installed on outer wing 2.Using of the present utility model
Technical scheme, support arm 1 are installed on missile airframe, and torsion bar is preferably manufactured using spring steel material, have preferable toughness, can
More elastic potential energy is stored, in the case where keeping Missile folded wing appearance and size limited, is added inside Missile folded wing
Ultimate torque, when guided missile is positioned on launching tube or launcher, due to guided missile it is constrained caused by restraining force be converted to elasticity
Potential energy, and be allocated in a plurality of torsion bar and store, the elastic potential energy of storage is concentrated again when Missile folded wing deploys, in torsion bar releases
Put, increase the overall expansion moment of torsion of Missile folded wing, make missile wing be enough to overcome the gas-flow resistance born after MISSILE LAUNCHING and
Reliably deploy, it is ensured that guided missile is with high speed normal flight, and the utility model is compact-sized, and installation is simple, and cost is cheap, reliably
Property it is high.
As shown in figure 5, the both ends of torsion bar 6 are respectively equipped with rectangle clamping head 61.Using the technical solution of the utility model, preferably
Torsion bar 6 is arranged on inside folding wings, and one of clamping head 61 is fixedly connected using straight pin with driving shaft or driven shaft, another
Individual clamping head 61 can reverse with the rotation of outer wing, and clamping head 61 is preferably rectangular, when especially square, be advantageous to processing system
When making, convenient installation, and reversing torsion bar, the torsion that the outer peripheral face of torsion bar is born more is evenly distributed in the circumference of torsion bar
On face, the service life of torsion bar is extended.
Clamping head 61 is fixed on the outer peripheral face of driving shaft 4 or driven shaft 5 by clamping head 61 using holding screw.Use this
The technical scheme of utility model, clamping head 61 is preferably rectangular, when especially square, is advantageous to fabricate, convenient installation,
And when reversing torsion bar, the torsion that the outer peripheral face of torsion bar is born more is evenly distributed on the periphery of torsion bar, is extended
The service life of torsion bar, on the other hand, clamping head 61 is fixed on to the outer peripheral face of driving shaft 4 or driven shaft 5 using holding screw
On, when body aerofoil deploys, holding screw is limited to the fastening force of clamping head 61, enables the elastic potential energy being stored in torsion bar
It is enough fully fully to discharge, with the gas-flow resistance run into when overcoming body outer wing to deploy.
Gear 7 is set on driving shaft 4 or driven shaft 5, gear 7 using holding screw by gear 7 be fixed on driving shaft 4 or
On the outer peripheral face of driven shaft 5.Using the technical solution of the utility model, when support arm rotates relative to outer wing, driving shaft turns therewith
Dynamic, the rotation of driving shaft is transferred on driven shaft by gear driving pair, and the gearratio of gear driving pair is preferably 1, due to turning round
One end of bar is fixedly connected with driving shaft and driven shaft respectively, and the other end of torsion bar is connected with bonnet, after the rectangular opening that covers compel
Torsion bar is set not rotate, so, the rotation of driving shaft and driven shaft forces torsion bar to reverse, and torsion bar itself is flexible, thus compels
Make the torsion on driving shaft be converted to elastic potential energy and be transferred on each torsion bar by gear to store, in addition, gear 7 can also make
Manufactured with elastomeric material, gear 7 can be configured to multipair, make a part of elasticity of torsion potential energy storage in gear, the bullet in gear 7
Property potential energy release when, due to gear 7 reference diameter be more than torsion bar external diameter, its elastic potential energy discharged is in identical bar
Torque is bigger under part, is advantageous to overcome run into gas-flow resistance when deploying body outer wing.
Gear 7 is integrative-structure with driving shaft 4 or driven shaft 5.Using the technical solution of the utility model, gear 7 and master
Moving axis 4 or driven shaft 5 can be integrative-structures, be easy to manufacture, and reduce production cost, on the other hand, also make to store in gear 7
A part of elasticity of torsion potential energy, in addition, power transmission shaft 18 can be also arranged as required between driving shaft and driven shaft, on power transmission shaft 18
Gear also is provided with, the gear is meshed with the gear on driving shaft, driven shaft respectively, adds between driving shaft and driven shaft
Spacing, the interference between driven shaft and support arm is avoided, power transmission shaft 18 plays gearing, is exposed when avoiding torsion bar installation
Folded surface, more compact structure, and gear-driven efficiency is generally 97%, improves the mechanical efficiency of the present apparatus.
Further, because torsion bar and gear 7 are manufactured using elastomeric material, when torsion bar or gear 7 are in twist motion,
Torsion bar and gear 7 can absorb partial noise, make have preferably disguise during MISSILE LAUNCHING.
Missile folded wing also includes locking device 8.Using technical scheme provided by the utility model, when outer wing rotate in place
When, i.e., it can be locked in the presence of locking device 8, so as to reach the purpose of storage elasticity of torsion potential energy.
Locking device 8 includes sleeve 9, spacer pin 10, spring 11, position-limiting drum 12, and sleeve 9 is fixedly installed in support arm 1, limits
Position cylinder 12 is installed on the side of support arm 1, and spacer pin 10 is set in position-limiting drum 12, and one end of spring 11 is connected with sleeve 9, spring
11 other end is connected with spacer pin 10.Using technical scheme provided by the utility model, locking device 8 may be configured as one extremely
Multiple, preferably locking device 8 is arranged to two, is separately positioned on the both sides of support arm, as shown in figure 3, when locking device 8 is arranged to
At two, two independent locking devices 8 were both could be arranged to, it can also be provided that structure type as shown in Figure 3, spacer pin
10 points are two, and are worked in coordination in the form of male and female head, that is, share a position-limiting drum 12, when outer wing rotate in place, spring
Spacer pin is ejected from the two sides of support arm respectively, so as to lock outer wing, reaches the purpose of storage elasticity of torsion potential energy, spacer pin
10 end face, which is provided with, is oriented to chamfering, spacer pin 10 is easy to by spring ejection or retraction.
Missile folded wing also includes bushing, and the bushing is set with driving shaft 4 or driven shaft 5, and respectively using tight
Determine the position that screw secures the bushing to be close with gear 7.Using the technical solution of the utility model, bushing can be according to reality
Situation is selected, and the main function of bushing is to make installing/dismounting more convenient, and is more convenient the installation of driving shaft, driven shaft,
Avoid producing interference in assembling process.
The quantity of torsion bar 6 is 4.Using the technical solution of the utility model, when guided missile is positioned on launching tube or launcher,
Due to guided missile it is constrained caused by restraining force be converted to elastic potential energy, and be allocated in a plurality of torsion bar and store, if torsion bar quantity compared with
It is more, then the construction profile of the present apparatus is added, is unfavorable for installing, and missile airframe quality is added, it is unfavorable for guided missile and flies at a high speed
OK, it is therefore preferable that the quantity of torsion bar 6 is 4, both installed it is light, enable guided missile it is constrained caused by restraining force more equably
Elastic potential energy is converted to, and makes the compact-sized of the present apparatus, avoids volume excessive and influences missile airframe high-speed flight.
Claims (9)
- A kind of 1. torsion bar townhouse formula Missile folded wing, it is characterised in that：Including support arm (1), outer wing (2), bonnet (3), hollow form Driving shaft (4), hollow form driven shaft (5) and torsion bar (6), the driven shaft (5) is by arranged in linear arrays in the outer wing (2) On, gear (7) is equipped with the driving shaft (4) and driven shaft (5), the driving shaft (4) is connected with the support arm (1), institute State driven shaft (5) lateral surface to be connected with the outer wing (2), two neighboring gear (7) is intermeshed, and the torsion bar (6) covers respectively Loaded in driving shaft (4), driven shaft (5), one end of torsion bar (6) is connected with driving shaft (4), driven shaft (5) respectively, torsion bar (6) The other end be connected with bonnet (3), bonnet (3) is installed on the outer wing (2).
- A kind of 2. torsion bar townhouse formula Missile folded wing as claimed in claim 1, it is characterised in that：Torsion bar (6) both ends point She You not rectangle clamping head (61).
- A kind of 3. torsion bar townhouse formula Missile folded wing as claimed in claim 2, it is characterised in that：The clamping head (61) uses The clamping head (61) is fixed on the outer peripheral face of the driving shaft (4) or driven shaft (5) by holding screw.
- A kind of 4. torsion bar townhouse formula Missile folded wing as claimed in claim 1, it is characterised in that：The gear (7) is set in On the driving shaft (4) or driven shaft (5), the gear (7) is fixed on the active by the gear (7) using holding screw On the outer peripheral face of axle (4) or driven shaft (5).
- A kind of 5. torsion bar townhouse formula Missile folded wing as claimed in claim 1, it is characterised in that：The gear (7) with it is described Driving shaft (4) or driven shaft (5) are integrative-structures.
- A kind of 6. torsion bar townhouse formula Missile folded wing as claimed in claim 1, it is characterised in that：The Missile folded wing also wraps Include locking device (8).
- A kind of 7. torsion bar townhouse formula Missile folded wing as claimed in claim 6, it is characterised in that：Locking device (8) bag Sleeve (9), spacer pin (10), spring (11), position-limiting drum (12) are included, sleeve (9) is fixedly installed in the support arm (1), spacing Cylinder (12) is installed on the side of the support arm (1), and spacer pin (10) is set in position-limiting drum (12), one end of spring (11) and set Cylinder (9) connection, the other end of spring (11) are connected with spacer pin (10).
- A kind of 8. torsion bar townhouse formula Missile folded wing as claimed in claim 1, it is characterised in that：The Missile folded wing also wraps Bushing is included, the bushing is set with the driving shaft (4) or driven shaft (5), and is respectively consolidated bushing using holding screw Due to the position being close with the gear (7).
- A kind of 9. torsion bar townhouse formula Missile folded wing as claimed in claim 1, it is characterised in that：Torsion bar (6) quantity is 4 Bar.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720874551.XU CN207180499U (en) | 2017-07-19 | 2017-07-19 | A kind of torsion bar townhouse formula Missile folded wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720874551.XU CN207180499U (en) | 2017-07-19 | 2017-07-19 | A kind of torsion bar townhouse formula Missile folded wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207180499U true CN207180499U (en) | 2018-04-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720874551.XU Withdrawn - After Issue CN207180499U (en) | 2017-07-19 | 2017-07-19 | A kind of torsion bar townhouse formula Missile folded wing |
Country Status (1)
| Country | Link |
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| CN (1) | CN207180499U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107289822A (en) * | 2017-07-19 | 2017-10-24 | 贵州航天风华精密设备有限公司 | A kind of missile airfoil fold mechanism with multiple rows of torsion bar |
-
2017
- 2017-07-19 CN CN201720874551.XU patent/CN207180499U/en not_active Withdrawn - After Issue
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107289822A (en) * | 2017-07-19 | 2017-10-24 | 贵州航天风华精密设备有限公司 | A kind of missile airfoil fold mechanism with multiple rows of torsion bar |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20180403 Effective date of abandoning: 20230505 |
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| AV01 | Patent right actively abandoned |
Granted publication date: 20180403 Effective date of abandoning: 20230505 |