CN105737685A - Wing face double-direction double-position folding structure - Google Patents
Wing face double-direction double-position folding structure Download PDFInfo
- Publication number
- CN105737685A CN105737685A CN201610090468.3A CN201610090468A CN105737685A CN 105737685 A CN105737685 A CN 105737685A CN 201610090468 A CN201610090468 A CN 201610090468A CN 105737685 A CN105737685 A CN 105737685A
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- China
- Prior art keywords
- double
- pressurized strut
- piston
- suction nozzle
- piston shaft
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/60—Steering arrangements
- F42B10/62—Steering by movement of flight surfaces
- F42B10/64—Steering by movement of flight surfaces of fins
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
- F42B10/16—Wrap-around fins
Abstract
Disclosed is a wing face double-direction double-position folding structure. A fixed wing is connected with a folding wing, a power actuating cylinder is fixed to the fixed wing, one end of a piston shaft is fixedly provided with a cylindrical pin located in a sliding groove, a folding wing joint is arranged on the sliding groove, and the positions, at the two ends of the sliding groove, of the piston shaft are each provided with a guide assembly in a sleeving manner; a self-locking assembly is arranged in the power actuating cylinder and is connected with the piston shaft, a left clamping groove and a right clamping groove are formed in the two sides of the self-locking assembly correspondingly, a double-piston body is arranged below the power actuating cylinder, a gas left air inlet nozzle for being connected with a left gas generator is arranged at the inner left end of the double-piston body, and a gas right air inlet nozzle for being connected with a right gas generator is formed in the inner right end of the double-piston body; meanwhile, the gas left air inlet nozzle, the gas right air inlet nozzle and the power actuating cylinder are communicated, an air exhausting assembly is arranged in the double-piston body, and an air exhausting hole is formed in the lower portion of the air exhausting assembly; the power actuating cylinder which does double-direction motion and is provided with the self-locking assembly is used, and therefore double-direction double-position unfolding and folding of the wing face can be achieved; and the wing face is accurate in positioning and reliable in locking.
Description
Technical field
The present invention relates to Missile folded wing technical field, particularly relate to a kind of two-way dibit foldable structure of aerofoil.
Background technology
Folding wings is widely used on guided missile, folding wings is used to be possible not only to reduce the physical dimension of guided missile, and be easy to guided missile box type storing dress, transport and launch, save the storing space of guided missile simultaneously, increase vehicle and carrier-borne carrying capacity, reduce position number of vehicles, the mobility improving guided missile is had great significance.
From the actual combat of guided missile, the attack precision of guided missile is extremely crucial, in the end flight course of guided missile, using folding wings can increase the lateral maneuvering capability of guided missile thus completing big angle of fall target of attack, improving the attack precision of guided missile.But current domestic each type of missile is folding before the use of folding wings only rests on outlet, the unidirectional unit folding phase launched after outlet, folded state is in casing for guided missile, launches after outlet, at flight latter end, the situation that aerofoil carries out twice-folded is not also had.Additionally, folding wings is applied also extremely wide in aircraft, satellite etc.；Therefore, how at flight latter end, aerofoil being carried out twice-folded, the attack precision improving guided missile has become as the major issue that those skilled in the art are urgently to be resolved hurrily.
Summary of the invention
Technical problem solved by the invention is in that to provide a kind of two-way dibit foldable structure of aerofoil, to solve the shortcoming in above-mentioned background technology.
Technical problem solved by the invention realizes by the following technical solutions:
A kind of two-way dibit foldable structure of aerofoil, including fixed-wing, folding wings, power pressurized strut, piston shaft, double-piston, guidance set, left gas generator and right gas generator；Wherein, fixed-wing is connected with folding wings, power pressurized strut is fixed on fixed-wing, one end of piston shaft is fixed with the straight pin being positioned at chute, chute is provided with folding wings joint, and on the piston shaft at chute two ends, it being respectively installed with guidance set, piston shaft is for linear motion along axis by guidance set, is driven the folding wings joint of chute to rotate by straight pin；It is provided with in power pressurized strut from lock set, is connected with piston shaft from lock set, and be respectively arranged with left draw-in groove and right draw-in groove from lock set both sides, when piston shaft is by folding movement to expansion position, be stuck in the right draw-in groove of power pressurized strut from lock set；When piston shaft by launch position move to folding position time, be stuck in the left draw-in groove of power pressurized strut from lock set；And it is being arranged below suction nozzle from lock set, power pressurized strut is provided with the relief valve for pressure release, power pressurized strut is arranged below double-piston, in double-piston, left end is provided with the left suction nozzle of the combustion gas for connecting left gas generator, and in double-piston, right-hand member is provided with the right suction nozzle of the combustion gas for connecting right gas generator；The left suction nozzle of combustion gas, the right suction nozzle of combustion gas connect with power pressurized strut simultaneously, are provided with gas deflation assembly in double-piston, and gas deflation assembly is arranged below steam vent.
In the present invention, fixed-wing is connected by rolling bearing with folding wings.
In the present invention, power pressurized strut is cylindrical sleeves.
In the present invention, chute is S type structure.
In the present invention, it is arranged below left suction nozzle and right suction nozzle from lock set.
In the present invention, left suction nozzle connects with steam vent.
In the present invention, relief valve is provided with relief hole.
nullIn the present invention，When aerofoil is by folded state to deployed condition，Power pressurized strut is in lock-out state，Left gas generator starts effect，The high-pressure gas produced is entered power pressurized strut by the left suction nozzle of combustion gas，Promotion double-piston is for linear motion，When double-piston moves to certain position，Left suction nozzle is opened，When combustion gas pressure reaches piston shaft start pressure，Unlock from lock set，Promote piston shaft for linear motion to the right，The folding wings joint driving chute rotates，Bigger impulsive force is produced to from lock set during for avoiding mechanism deploying (folding) to put in place，When crossing the relief hole in power pressurized strut from lock set，Relief valve starts effect，When pressure is 10MPa，Piston shaft continues to do to the right rectilinear motion，When folding wings is expanded to level，Snap into from lock set in the right draw-in groove of power pressurized strut，Folding wings is launched to put in place，It is in locking state；
When aerofoil is by deployed condition to folded state, right gas generator starts effect, power pressurized strut is entered by the right suction nozzle of combustion gas, promotion double-piston is for linear motion, when double-piston moves to certain position, right suction nozzle is opened, and now left suction nozzle is connected with steam vent, and the power pressurized strut left side starts aerofluxus；When combustion gas pressure reaches piston shaft start pressure, unlock from lock set, promote piston shaft for linear motion to the left, the folding wings joint driving chute rotates, when crossing the relief hole in power pressurized strut from lock set, relief valve starts effect, when pressure is 10MPa, piston shaft continues to do rectilinear motion to the left, when folding wings is folded to plumbness, snaps in the left draw-in groove of power pressurized strut from lock set, folding wings puts in place, being in locking state, folding wings can not rotate, thus completing the folding of folding wings.
Beneficial effect: the present invention is by by the rectilinear motion of the reciprocating piston shaft with straight pin, it is converted into the rotary motion with the rotatable power pressurized strut of S shape chute, utilization can come and go the power pressurized strut from lock set of bidirectional-movement band, to realize the expansion of aerofoil and folding, aerofoil accurate positioning, locking reliable, its structure breaches the limitation that the tradition unidirectional unit of folding wings is launched, it is achieved the two-way dibit of folding wings is launched, folded and reliably lock.
Accompanying drawing explanation
Fig. 1 is the structural representation of presently preferred embodiments of the present invention.
Detailed description of the invention
For the technological means making the present invention realize, creation characteristic, reach purpose and effect and be easy to understand, below in conjunction with being specifically illustrating, the present invention is expanded on further.
Referring to the two-way dibit foldable structure of a kind of aerofoil of Fig. 1, including fixed-wing 1, folding wings 2, power pressurized strut 3, relief valve 4, left draw-in groove 5, steam vent 6, gas deflation assembly 7, S type chute 8, piston shaft 9, left suction nozzle 10A, right suction nozzle 10B, straight pin 11, double-piston 12, guidance set 13, left gas generator 14, right gas generator 15, right draw-in groove 16, from lock set 17, combustion gas left suction nozzle K1 and the right suction nozzle K2 of combustion gas.
In the present embodiment, fixed-wing 1 is connected by rolling bearing with folding wings 2, power pressurized strut 3 is fixed on fixed-wing 1, one end of piston shaft 9 is fixed with the straight pin 11 being positioned at S type chute 8, S type chute 8 is provided with folding wings joint, and on the piston shaft 9 at S type chute 8 two ends, it being respectively installed with guidance set 13, piston shaft 9 is for linear motion along axis by guidance set 13, is driven the folding wings joint of S type chute 8 to rotate by straight pin 11；It is provided with in power pressurized strut 3 from lock set 17, it is connected with piston shaft 9 from lock set 17, and left draw-in groove 5 and right draw-in groove 16 it is being respectively arranged with from lock set 17 both sides, when piston shaft 9 is by folding movement to expansion position, it is stuck in the right draw-in groove 16 of power pressurized strut 3 from lock set 17；When piston shaft 9 is moved to folding position by expansion position, it is stuck in the left draw-in groove 5 of power pressurized strut 3 from lock set 17；Power pressurized strut 3 is provided with relief valve 4, relief valve 4 is provided with relief hole, and is being arranged below left suction nozzle 10A, right suction nozzle 10B from lock set 17；Power pressurized strut 3 is arranged below double-piston 12, and double-piston 12 left end is provided with the left suction nozzle K1 of the combustion gas for connecting left gas generator 14, and double-piston 12 right-hand member is provided with the right suction nozzle K2 of the combustion gas for connecting right gas generator 15；Combustion gas left suction nozzle K1, the right suction nozzle K2 of combustion gas connect with power pressurized strut 3 simultaneously, are provided with gas deflation assembly 7 in double-piston 12, and gas deflation assembly 7 is arranged below steam vent 6.
nullIn the present embodiment，When aerofoil is by folded state to deployed condition，Power pressurized strut 3 is in lock-out state，Left gas generator 14 starts effect，The high-pressure gas produced is entered power pressurized strut 3 by the left suction nozzle K1 of combustion gas，Promote double-piston 12 for linear motion，When double-piston 12 moves to certain position，Left suction nozzle 10A opens，When combustion gas pressure reaches piston shaft 9 start pressure，Unlock from lock set 17，Promote piston shaft 9 for linear motion to the right，The folding wings joint driving S type chute 8 rotates，For avoiding mechanism deploying (folding) to produce bigger impulsive force to from lock set 17 when putting in place，When crossing the relief hole in power pressurized strut 3 from lock set 17，Relief valve 4 starts effect，When pressure is 10MPa，Piston shaft 9 continues to do to the right rectilinear motion，When folding wings 2 is expanded to level，Snap into from lock set 17 in the right draw-in groove 16 of power pressurized strut 3，Folding wings 2 is launched to put in place，It is in locking state；
When aerofoil is by deployed condition to folded state, right gas generator 15 starts effect, power pressurized strut 3 is entered by the right suction nozzle K2 of combustion gas, promote double-piston 12 for linear motion, when double-piston 12 moves to certain position, right suction nozzle 10B opens, and now left suction nozzle 10A and steam vent 6 are connected, and power pressurized strut 3 left side starts aerofluxus；When combustion gas pressure reaches piston shaft 9 start pressure, unlock from lock set 17, promote piston shaft 9 for linear motion to the left, the folding wings joint driving S type chute 8 rotates, when crossing the relief hole in power pressurized strut 3 from lock set 17, relief valve 4 starts effect, when pressure is 10MPa, piston shaft 9 continues to do to the left rectilinear motion, when folding wings 2 is folded to plumbness, snap in the left draw-in groove 5 of power pressurized strut 3 from lock set 17, folding wings 2 puts in place, it is in locking state, folding wings 2 can not rotate, thus completing the folding of folding wings 2.
In the present embodiment, by the rectilinear motion by the reciprocating piston shaft 9 with straight pin 11, it is converted into the rotary motion with the rotatable power pressurized strut 3 of S shape chute 8, utilization can come and go the power pressurized strut 3 of bidirectional-movement locking assembly, realize the expansion of aerofoil and folding, aerofoil is inherently with controlled fold mechanism power source, can be good at realizing the expansion of aerofoil and folding, aerofoil accurate positioning, locking is reliable, its structure breaches the limitation that the tradition unidirectional unit of folding wings is launched, the two-way dibit realizing folding wings is launched, fold and reliably lock.
The ultimate principle of the present invention and principal character and advantages of the present invention have more than been shown and described.Skilled person will appreciate that of the industry; the present invention is not restricted to the described embodiments; described in above-described embodiment and description is that principles of the invention is described; without departing from the spirit and scope of the present invention; the present invention also has various changes and modifications, and these changes and improvements both fall within the claimed scope of the invention.Claimed scope is defined by appending claims and equivalent thereof.
Claims (8)
1. the two-way dibit foldable structure of aerofoil, including fixed-wing, folding wings, power pressurized strut, piston shaft, double-piston, guidance set, left gas generator and right gas generator；It is characterized in that, fixed-wing is connected with folding wings, power pressurized strut is fixed on fixed-wing, one end of piston shaft is fixed with the straight pin being positioned at chute, chute is provided with folding wings joint, and on the piston shaft at chute two ends, it being respectively installed with guidance set, piston shaft is for linear motion along axis by guidance set, is driven the folding wings joint of chute to rotate by straight pin；It is provided with in power pressurized strut from lock set, is connected with piston shaft from lock set, and be respectively arranged with left draw-in groove and right draw-in groove from lock set both sides, when piston shaft is by folding movement to expansion position, be stuck in the right draw-in groove of power pressurized strut from lock set；When piston shaft by launch position move to folding position time, be stuck in the left draw-in groove of power pressurized strut from lock set；And it is being arranged below suction nozzle from lock set, power pressurized strut is provided with the relief valve for pressure release, power pressurized strut is arranged below double-piston, in double-piston, left end is provided with the left suction nozzle of the combustion gas for connecting left gas generator, and in double-piston, right-hand member is provided with the right suction nozzle of the combustion gas for connecting right gas generator；The left suction nozzle of combustion gas, the right suction nozzle of combustion gas connect with power pressurized strut simultaneously, are provided with gas deflation assembly in double-piston, and gas deflation assembly is arranged below steam vent.
2. a kind of two-way dibit foldable structure of aerofoil according to claim 1, it is characterised in that fixed-wing is connected by rolling bearing with folding wings.
3. a kind of two-way dibit foldable structure of aerofoil according to claim 1, it is characterised in that power pressurized strut is cylindrical sleeves.
4. a kind of two-way dibit foldable structure of aerofoil according to claim 1, it is characterised in that chute is S type structure.
5. a kind of two-way dibit foldable structure of aerofoil according to claim 1, it is characterised in that be arranged below left suction nozzle and right suction nozzle from lock set.
6. a kind of two-way dibit foldable structure of aerofoil according to claim 5, it is characterised in that left suction nozzle connects with steam vent.
7. a kind of two-way dibit foldable structure of aerofoil according to claim 1, it is characterised in that be provided with the relief valve for pressure release in power pressurized strut, relief valve is provided with relief hole.
null8. the two-way dibit foldable structure of a kind of aerofoil according to any one of claim 1～7，It is characterized in that，When aerofoil is by folded state to deployed condition，Power pressurized strut is in lock-out state，Left gas generator starts effect，The high-pressure gas produced is entered power pressurized strut by the left suction nozzle of combustion gas，Promotion double-piston is for linear motion，When double-piston moves to certain position，Left suction nozzle is opened，When combustion gas pressure reaches piston shaft start pressure，Unlock from lock set，Promote piston shaft for linear motion to the right，The folding wings joint driving chute rotates，Bigger impulsive force is produced to from lock set during for avoiding mechanism deploying to put in place，When crossing the relief hole in power pressurized strut from lock set，Relief valve starts effect，When pressure is 10MPa，Piston shaft continues to do to the right rectilinear motion，When folding wings is expanded to level，Snap into from lock set in the right draw-in groove of power pressurized strut，Folding wings is launched to put in place，It is in locking state；
When aerofoil is by deployed condition to folded state, right gas generator starts effect, power pressurized strut is entered by the right suction nozzle of combustion gas, promotion double-piston is for linear motion, when double-piston moves to certain position, right suction nozzle is opened, and now left suction nozzle is connected with steam vent, and the power pressurized strut left side starts aerofluxus；When combustion gas pressure reaches piston shaft start pressure, unlock from lock set, promote piston shaft for linear motion to the left, the folding wings joint driving chute rotates, when crossing the relief hole in power pressurized strut from lock set, relief valve starts effect, when pressure is 10MPa, piston shaft continues to do rectilinear motion to the left, when folding wings is folded to plumbness, snaps in the left draw-in groove of power pressurized strut from lock set, folding wings puts in place, being in locking state, folding wings can not rotate, thus completing the folding of folding wings.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610090468.3A CN105737685B (en) | 2016-02-18 | 2016-02-18 | A kind of two-way dibit foldable structure of aerofoil |
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| CN201610090468.3A CN105737685B (en) | 2016-02-18 | 2016-02-18 | A kind of two-way dibit foldable structure of aerofoil |
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| CN105737685B CN105737685B (en) | 2017-07-21 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106225604A (en) * | 2016-07-29 | 2016-12-14 | 江西洪都航空工业集团有限责任公司 | A kind of longitudinal folding mechanism of rudder face |
| CN106839897A (en) * | 2017-01-03 | 2017-06-13 | 北京临近空间飞行器系统工程研究所 | A kind of straight-line helix unfolded wing mechanism |
| CN107128478A (en) * | 2017-05-23 | 2017-09-05 | 安徽中科中涣防务装备技术有限公司 | A kind of fast unfolding device of folded wing |
| CN108128460A (en) * | 2017-12-28 | 2018-06-08 | 宝鸡特种飞行器工程研究院有限公司 | A kind of spiral expansion unmanned plane |
| CN109131836A (en) * | 2018-09-21 | 2019-01-04 | 北京宇航系统工程研究所 | A kind of mini folding steering engine structure automating repeat function |
| EP3543640A3 (en) * | 2018-03-21 | 2020-01-08 | Diehl Defence GmbH & Co. KG | Projectile with deployable fins that are releasably held in stowed position by a common latch element rotatable around the longitudinal axis |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5240203A (en) * | 1987-10-01 | 1993-08-31 | Hughes Missile Systems Company | Folding wing structure with a flexible cover |
| JPH06101999A (en) * | 1992-09-17 | 1994-04-12 | Nissan Motor Co Ltd | Missile with stabilizing wings |
| CN201184774Y (en) * | 2008-01-08 | 2009-01-21 | 刘元媛 | Cannonball capable of being used as glider |
| CN102230765A (en) * | 2011-05-26 | 2011-11-02 | 浙江理工大学 | Longitudinal unfolding mechanism for direct-connected folding wing |
| CN203629478U (en) * | 2013-11-13 | 2014-06-04 | 湖北航天技术研究院总体设计所 | Paddle-type folding mechanism used for horizontally folding missile wings |
| CN104713426A (en) * | 2015-04-01 | 2015-06-17 | 湖北航天技术研究院总体设计所 | Slide wedge block type transverse foldable wing surface |
-
2016
- 2016-02-18 CN CN201610090468.3A patent/CN105737685B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5240203A (en) * | 1987-10-01 | 1993-08-31 | Hughes Missile Systems Company | Folding wing structure with a flexible cover |
| JPH06101999A (en) * | 1992-09-17 | 1994-04-12 | Nissan Motor Co Ltd | Missile with stabilizing wings |
| CN201184774Y (en) * | 2008-01-08 | 2009-01-21 | 刘元媛 | Cannonball capable of being used as glider |
| CN102230765A (en) * | 2011-05-26 | 2011-11-02 | 浙江理工大学 | Longitudinal unfolding mechanism for direct-connected folding wing |
| CN203629478U (en) * | 2013-11-13 | 2014-06-04 | 湖北航天技术研究院总体设计所 | Paddle-type folding mechanism used for horizontally folding missile wings |
| CN104713426A (en) * | 2015-04-01 | 2015-06-17 | 湖北航天技术研究院总体设计所 | Slide wedge block type transverse foldable wing surface |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106225604A (en) * | 2016-07-29 | 2016-12-14 | 江西洪都航空工业集团有限责任公司 | A kind of longitudinal folding mechanism of rudder face |
| CN106225604B (en) * | 2016-07-29 | 2018-01-26 | 江西洪都航空工业集团有限责任公司 | A kind of longitudinal folding mechanism of rudder face |
| CN106839897A (en) * | 2017-01-03 | 2017-06-13 | 北京临近空间飞行器系统工程研究所 | A kind of straight-line helix unfolded wing mechanism |
| CN107128478A (en) * | 2017-05-23 | 2017-09-05 | 安徽中科中涣防务装备技术有限公司 | A kind of fast unfolding device of folded wing |
| CN107128478B (en) * | 2017-05-23 | 2023-08-04 | 安徽中科中涣智能装备股份有限公司 | Quick unfolding device for folding wing |
| CN108128460A (en) * | 2017-12-28 | 2018-06-08 | 宝鸡特种飞行器工程研究院有限公司 | A kind of spiral expansion unmanned plane |
| EP3543640A3 (en) * | 2018-03-21 | 2020-01-08 | Diehl Defence GmbH & Co. KG | Projectile with deployable fins that are releasably held in stowed position by a common latch element rotatable around the longitudinal axis |
| CN109131836A (en) * | 2018-09-21 | 2019-01-04 | 北京宇航系统工程研究所 | A kind of mini folding steering engine structure automating repeat function |
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| CN105737685B (en) | 2017-07-21 |
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