CN109405643A - A kind of laterally folded formula aerofoil of high rigidity - Google Patents
A kind of laterally folded formula aerofoil of high rigidity Download PDFInfo
- Publication number
- CN109405643A CN109405643A CN201811545095.XA CN201811545095A CN109405643A CN 109405643 A CN109405643 A CN 109405643A CN 201811545095 A CN201811545095 A CN 201811545095A CN 109405643 A CN109405643 A CN 109405643A
- Authority
- CN
- China
- Prior art keywords
- wing
- outer wing
- shaft
- high rigidity
- locking pin
- Prior art date
- 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.)
- Pending
Links
- 238000009434 installation Methods 0.000 claims abstract description 5
- 210000003781 tooth socket Anatomy 0.000 claims description 3
- 229910001069 Ti alloy Inorganic materials 0.000 abstract description 3
- 238000010276 construction Methods 0.000 abstract description 3
- 241001646071 Prioneris Species 0.000 description 8
- 239000000126 substance Substances 0.000 description 6
- 230000000694 effects Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910000861 Mg alloy Inorganic materials 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F7/00—Launching-apparatus for projecting missiles or projectiles otherwise than from barrels, e.g. using spigots
Abstract
The laterally folded formula aerofoil of a kind of high rigidity provided by the invention, including outer wing and inner wing；Outer wing can be rotated by shaft relative to inner wing, and the power device of outer wing rotation is equipped in the shaft, the locking device of the restricted outer wing rotation of installation in the outer wing or inner wing.By the present invention in that adding covering as airfoil structure with using titanium alloy framework, reduce construction weight while ensure that aerofoil rigidity；Shaft is the central link part of outer wing and inner wing, transmits and bear the load from outer wing；Using torsion bar as expansion power resources, occupied space is few, and expansion mode is simple, reliable；Locking mechanism is using twin-lock rationed marketing as locking part, and as a source of power with compressed spring, locking pin is tapered cylinder, and stiffness characteristics are good after locking.For the laterally folded formula aerofoil of high rigidity while realizing folder function, rigidity is higher, and the ability of anti-flutter is stronger, is able to achieve higher flying speed.
Description
Technical field
The present invention relates to a kind of laterally folded formula aerofoils of high rigidity.
Background technique
Collapsible aerofoil reduces the lateral dimension before emitting substance transmitting, ships and emits convenient for cartridge type.With emitting substance
The promotion of demand, it is desirable that folded surface can have higher rigidity, to improve the anti-flutter ability of folded surface and control precision.Gao Gang
Spend the developing direction that collapsible aerofoil is emitting substance.
Folding wings mostly use active laterally folded form, which is in the root or middle part of aerofoil, along aerofoil
Tangential that aerofoil is divided into outer wing and inner wing, outer wing part can fold or be unfolded around the shaft, and unfolding mechanism is interior to be mounted on aerofoil
Torsional spring be power.To reduce unfolding mechanism structure size, guarantee aerofoil aerodynamic configuration, it is necessary to reduce outer wing rotary inertia, one
As the aluminium alloy or magnesium alloy of low-density can be used, but its mechanical property is lower, is not able to satisfy high motor-driven, high speed emitting substance
Rigidity requirement.
The general locking mechanism using single group pinning nut of laterally folded formula rudder face uses pinning and spiral shell in the pre-deployed
Locking pin is pressed into inner pinhole by mother, and outer wing, which cuts pinning, when expansion unlocks locking pin, locking pin bullet under the action of the spring
Enter outer wing pin hole, completes locking.Due to there was only single group locking mechanism and bindiny mechanism, cause rigidity after locking lower.To guarantee
Rigidity after locking success rate and locking, locking mechanism is larger, causes aerofoil thicker, influences aeroperformance.
Summary of the invention
In order to solve the above technical problems, the present invention provides a kind of laterally folded formula aerofoils of high rigidity.
The present invention is achieved by the following technical programs.
The laterally folded formula aerofoil of a kind of high rigidity provided by the invention, including outer wing and inner wing；Outer wing can pass through shaft
It is rotated relative to inner wing, the power device of outer wing rotation is installed, installation is restricted outer in the outer wing or inner wing in the shaft
The locking device of wing rotation.
Mutually matched sawtooth or tooth socket are machined on the outer wing or inner wing, shaft is mounted on the sawtooth of outer wing or inner wing
In interior through-hole.
It is fixed in the middle part of the shaft in the sawtooth of outer wing or inner wing.
The power device is torsion bar, and torsion bar and shaft, outer wing or inner wing are opposing stationary structure.
One end of the torsion bar is fixed in shaft, and the other end passes through not to be had in through-hole and outer wing and inner wing inside shaft
The wing of fixed rotating shaft is fixed.
The locking device includes locking pin, locking pin be mounted on outer wing adjacent on inner wing or inner wing adjacent to outer wing
End face groove in, outer wing is equipped at locking pin to be machined with pin hole or inner wing and be equipped at locking pin in outer wing in inner wing to be added
Work has a pin hole, and locking pin is relative to being provided with device for ejecting between outer wing or inner wing.
The locking pin is set as circular platform type relative to outer wing or inner wing outlet end end.
Pinning is also equipped on the axis of the locking pin, one end of pinning is fixed on the groove-bottom on outer wing or inner wing
Portion, the other end of pinning are equipped with nut and locking pin are locked in groove.
The shaft is preferably fixed in outer wing.
The locking pin is preferably fixed in inner wing.
The beneficial effects of the present invention are: add covering as airfoil structure by using using titanium alloy framework, ensure that
Reduce construction weight while aerofoil rigidity；Shaft is the central link part of outer wing and inner wing, transmits and bears from outer
The load of the wing；Using torsion bar as expansion power resources, occupied space is few, and expansion mode is simple, reliable；Locking mechanism uses
Twin-lock rationed marketing is as locking part, and as a source of power with compressed spring, locking pin is tapered cylinder, stiffness characteristics after locking
It is good.For the laterally folded formula aerofoil of high rigidity while realizing folder function, rigidity is higher, and the ability of anti-flutter is stronger, energy
Realize higher flying speed.
Detailed description of the invention
Fig. 1 is structural schematic diagram of the invention；
Fig. 2 is the local perspective view at Figure 1A of the present invention；
Fig. 3 is torsion bar structure schematic diagram of the invention；
In figure: 1- outer wing, 2- inner wing, 3- shaft, 4- torsion bar, 41- connector, 5- locking pin, 6- pressure spring, 7- rear cover, 8-
Screw I, 9- screw II, 10- screw III, 11- screw IV, 12- pinning, 13- nut.
Specific embodiment
Be described further below technical solution of the present invention, but claimed range be not limited to it is described.
As shown in Figures 1 to 3, the laterally folded formula aerofoil of a kind of high rigidity, including outer wing 1 and inner wing 2；Outside outer wing 1 and inner wing 2
The wing and inner wing are all made of titanium alloy framework and add stressed-skin construction, and outer wing 1 can be rotated by shaft 3 relative to inner wing 2, the shaft 3
The power device of the rotation of outer wing 1, the locking device that the restricted outer wing 1 of installation rotates in the outer wing 1 or inner wing 2 are inside installed.
Mutually matched sawtooth or tooth socket are machined on the outer wing 1 or inner wing 2, shaft 3 is mounted on outer wing 1 or inner wing 2
Sawtooth in through-hole in.
The middle part of the shaft 3 is fixed in the sawtooth of outer wing 1 or inner wing 2.
The power device is torsion bar 4, and torsion bar 4 and shaft 3, outer wing 1 or inner wing 2 are opposing stationary structure.When outer wing is rolled over
When folded, drive torsion bar to reverse to certain angle, generate the twisting resistance that outer wing can be made to be unfolded.Linkage section there are two bindiny mechanism is total,
Improve the torsion stiffness of aerofoil.
One end of the torsion bar 4 is fixed in shaft 3, and the other end passes through through-hole and outer wing 1 and inner wing 2 inside shaft 3
In there is no the wing of fixed rotating shaft 3 to fix.
The locking device includes locking pin 5, and locking pin 5 is mounted on outer wing 1 adjacent to adjacent on inner wing 2 or inner wing 2
In in the groove of the end face of outer wing 1, outer wing 1 is equipped at locking pin 5 in inner wing 2 and is machined with pin hole or inner wing 2 in the installation of outer wing 1
Have and be machined with pin hole at locking pin 5, locking pin 5 is relative to device for ejecting, device for ejecting is provided between outer wing 1 or inner wing 2
Spring of the pinning pin relative to bottom portion of groove.During expansion, outer wing cuts pinning, when outer wing is expanded to pin hole and locking pin pair
Qi Shi, locking pin is slided into rapidly in outer foramen alare along pin hole under pressure spring effect and is limited by bellmouth, to lock outer wing.Two
Locking pin locks jointly, improves aerofoil bending stiffness.
The locking pin 5 is set as circular platform type relative to outer wing 1 or 2 outlet end end of inner wing.
Pinning 12 is also equipped on the axis of the locking pin 5, one end of pinning 12 is fixed on outer wing 1 or inner wing 2
Bottom portion of groove, the other end of pinning 12 are equipped with nut 13 and locking pin 5 are locked in groove, and pinning 12 stretches out pinning pin 5
One end is machined with the structure easily snapped off in 5 exit or is to easily snap off material.
The shaft 3 is preferably fixed in outer wing 1.
The locking pin 5 is preferably fixed in inner wing 2.
Embodiment: outer wing 1 opens up two rectangular saw-tooths, and inner wing 2 opens up two U-lags, and middle part opens up cylindrical logical
Hole, shaft 3 are mounted in through-hole and connect outer wing 1 with inner wing 2；Bellmouth is opened up in 1 rectangular saw-tooth of outer wing and locking pin 5 cooperates
Lock outer wing.
The unfolding mechanism of outer wing 1 includes shaft 3, the torsion bar 4 with certain elasticity, rear cover 7, screw I 8, screw II 9 and spiral shell
Follow closely IV 11 equal compositions.Coaxial aperture of the shaft 3 on inner wing 2, outer wing 1 connects, and is fixed on outer wing 1 using screw IV 11
On, prevent it from relatively rotating and horizontally slipping；Torsion bar 4 packs into shaft to 1 end corresponding aperture position of outer wing, utilizes screw II 9
4 one end of torsion bar is fixed in sleeve, torsion bar play backward is prevented；The other end is mounted on the rear cover 7 of inner wing rear end, utilizes spiral shell
It follows closely I 8 rear cover is fixed on inner wing.When locking pin 5 is fully retracted the interior span into cylindrical hole, outer wing just can turn around axis rotation
And torsion bar is driven to reverse, realize outer wingfold.
Undeployed configuration locking mechanism is made of locking pin 5, pressure spring 6, pinning 12 and nut 13.The one of vertical cylindrical hole
Side opens up two threaded holes, and locking mechanism is fixed on inner wing by screw III 10, and bottom opens up threaded hole, to install
Pinning 12.There is through-hole on locking pin, pinning is cooperated by this through-hole and nut 13, and locking pin is pressed into inner wing.
Working principle: folding wings of the invention use the initial procedure on the emitting substance that original state needs volume very little
In, outer wing folds into designated position, and torsion bar reverses accumulation of energy under the action of outer wing.Meanwhile locking pin is in the work of pinning and nut
Inner wing is pressed under.When emitting substance transmitting, outer wing is unfolded rapidly under torsion bar effect, outer wing cutting lock during expansion
Nail, when outer wing, which is expanded to pin hole, to be aligned with locking pin, locking pin slides into rapidly in outer wing bellmouth under the effect of pressure spring elastic force,
Outer wing is locked.
Claims (10)
1. a kind of laterally folded formula aerofoil of high rigidity, including outer wing (1) and inner wing (2), it is characterised in that: outer wing (1) can lead to
It crosses shaft (3) to rotate relative to inner wing (2), the power device of outer wing (1) rotation, the outer wing (1) is installed in the shaft (3)
Or the locking device that the restricted outer wing (1) of installation rotates in inner wing (2).
2. the laterally folded formula aerofoil of high rigidity as described in claim 1, it is characterised in that: on the outer wing (1) or inner wing (2)
It is machined with mutually matched sawtooth or tooth socket, shaft (3) is mounted in the through-hole in the sawtooth of outer wing (1) or inner wing (2).
3. the laterally folded formula aerofoil of high rigidity as described in claim 1, it is characterised in that: the middle part of the shaft (3) is fixed
In the sawtooth of outer wing (1) or inner wing (2).
4. the laterally folded formula aerofoil of high rigidity as described in claim 1, it is characterised in that: the power device is torsion bar (4),
Torsion bar (4) and shaft (3), outer wing (1) or inner wing (2) are opposing stationary structure.
5. the laterally folded formula aerofoil of high rigidity as claimed in claim 4, it is characterised in that: one end of the torsion bar (4) is fixed
On shaft (3), the other end, which passes through in shaft (3) internal through-hole and outer wing (1) and inner wing (2), does not have fixed rotating shaft (3)
The wing is fixed.
6. the laterally folded formula aerofoil of high rigidity as described in claim 1, it is characterised in that: the locking device includes locking pin
(5), locking pin (5) be mounted on outer wing (1) adjacent on inner wing (2) or inner wing (2) adjacent to the groove of the end face of outer wing (1)
Interior, outer wing (1) is equipped at locking pin (5) in inner wing (2) and is machined with pin hole or inner wing (2) and is equipped with locking pin in outer wing (1)
(5) pin hole is machined at, locking pin (5) is provided with device for ejecting relative between outer wing (1) or inner wing (2).
7. the laterally folded formula aerofoil of high rigidity as claimed in claim 6, it is characterised in that: the locking pin (5) is relative to outer
The wing (1) or inner wing (2) outlet end end are set as circular platform type.
8. the laterally folded formula aerofoil of high rigidity as claimed in claim 6, it is characterised in that: on the axis of the locking pin (5)
It is also equipped with pinning (12), one end of pinning (12) is fixed on the bottom portion of groove on outer wing (1) or inner wing (2), pinning (12)
The other end is equipped with nut (13) and locking pin (5) is locked in groove.
9. the laterally folded formula aerofoil of high rigidity as claimed in claim 2, it is characterised in that: the shaft (3) is preferably fixed to
In outer wing (1).
10. the laterally folded formula aerofoil of high rigidity as claimed in claim 6, it is characterised in that: the locking pin (5) is preferred fixed
In inner wing (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811545095.XA CN109405643A (en) | 2018-12-17 | 2018-12-17 | A kind of laterally folded formula aerofoil of high rigidity |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811545095.XA CN109405643A (en) | 2018-12-17 | 2018-12-17 | A kind of laterally folded formula aerofoil of high rigidity |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109405643A true CN109405643A (en) | 2019-03-01 |
Family
ID=65459604
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811545095.XA Pending CN109405643A (en) | 2018-12-17 | 2018-12-17 | A kind of laterally folded formula aerofoil of high rigidity |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109405643A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113670138A (en) * | 2021-07-23 | 2021-11-19 | 河北汉光重工有限责任公司 | Foldable rudder capable of monitoring and optimizing flutter phenomenon |
| CN113722815A (en) * | 2021-07-24 | 2021-11-30 | 广东空天科技研究院 | Design method for separating surface of folding wing without changing aerodynamic shape |
| CN117053635A (en) * | 2023-10-11 | 2023-11-14 | 西安现代控制技术研究所 | High-bearing hypersonic folding rudder adapting to thermal deformation |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0013096A1 (en) * | 1978-12-29 | 1980-07-09 | The Commonwealth Of Australia | Deployable wing mechanism |
| US20070102567A1 (en) * | 2005-09-14 | 2007-05-10 | Agency For Defense Development | Apparatus for deploying wing of guided missile |
| CN201895770U (en) * | 2010-09-29 | 2011-07-13 | 贵州航天控制技术有限公司 | Locking and unlocking mechanism for aircraft airfoil |
| CN209605663U (en) * | 2018-12-17 | 2019-11-08 | 江南机电设计研究所 | A kind of laterally folded formula aerofoil of high rigidity |
-
2018
- 2018-12-17 CN CN201811545095.XA patent/CN109405643A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0013096A1 (en) * | 1978-12-29 | 1980-07-09 | The Commonwealth Of Australia | Deployable wing mechanism |
| US20070102567A1 (en) * | 2005-09-14 | 2007-05-10 | Agency For Defense Development | Apparatus for deploying wing of guided missile |
| CN201895770U (en) * | 2010-09-29 | 2011-07-13 | 贵州航天控制技术有限公司 | Locking and unlocking mechanism for aircraft airfoil |
| CN209605663U (en) * | 2018-12-17 | 2019-11-08 | 江南机电设计研究所 | A kind of laterally folded formula aerofoil of high rigidity |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113670138A (en) * | 2021-07-23 | 2021-11-19 | 河北汉光重工有限责任公司 | Foldable rudder capable of monitoring and optimizing flutter phenomenon |
| CN113670138B (en) * | 2021-07-23 | 2023-08-18 | 河北汉光重工有限责任公司 | Folding rudder capable of monitoring and optimizing flutter phenomenon |
| CN113722815A (en) * | 2021-07-24 | 2021-11-30 | 广东空天科技研究院 | Design method for separating surface of folding wing without changing aerodynamic shape |
| CN113722815B (en) * | 2021-07-24 | 2023-09-19 | 广东空天科技研究院 | Design method of folding wing separating surface without changing aerodynamic shape |
| CN117053635A (en) * | 2023-10-11 | 2023-11-14 | 西安现代控制技术研究所 | High-bearing hypersonic folding rudder adapting to thermal deformation |
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