CN209559041U - A kind of missile flight device folding wings - Google Patents
A kind of missile flight device folding wings Download PDFInfo
- Publication number
- CN209559041U CN209559041U CN201920114061.9U CN201920114061U CN209559041U CN 209559041 U CN209559041 U CN 209559041U CN 201920114061 U CN201920114061 U CN 201920114061U CN 209559041 U CN209559041 U CN 209559041U
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- aerofoil
- backing pin
- pedestal
- rotation
- lockable mechanism
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Abstract
A kind of missile flight device folding wings, including pedestal and rotation aerofoil, pedestal and rotation aerofoil are attached by shaft, it is provided in the shaft for providing the torsion spring mechanism of expansion power, lockable mechanism is provided between pedestal and rotation aerofoil, when the lockable mechanism is opened, rotation aerofoil can be made to be folded on pedestal, it puts into storage device by storage device internal space restraint, constraint of the rotary wings emaciated face from storage device when transmitting, it is driven and is unfolded by torsion spring mechanism, lockable mechanism can lock rotation aerofoil.The utility model structure is simple, and after rotation aerofoil expansion, lockable mechanism can lock rotation aerofoil, prevent aerofoil in guided missile operational process from shaking, reliable in operational process, is no different with traditional integrated molding formula aerofoil.
Description
Technical field
The utility model belongs to missile flight device manufacturing field, and in particular to a kind of missile flight device folding wings.
Background technique
Since the span of aircraft is a key parameter for influencing aircraft lift, the span is bigger, should under square one
The lift that guided missile generates is also bigger, and lift resistance ratio is also bigger, and aircraft flight efficiency is also higher.Therefore, aircraft meet it is other
Spanwise extent as big as possible is needed on the basis of performance requirement, but requires to set in aircraft when vehicle launch and storage
In firing box, spanwise extent is bigger, and space required in transmitting and storage is also bigger, this will lead to other a series of
System parameter it is bigger than normal, it would therefore be highly desirable to which the span face for how improving missile flight device on the basis of using existing space studied
Product.
Utility model content
The purpose of this utility model is that being directed to above-mentioned the problems of the prior art, a kind of missile flight device folding is provided
The wing, structure is simple, can effectively increase the span area of missile flight device folding wings, and required space is small when storage, runs
Journey is reliable.
To achieve the goals above, the technical solution adopted in the utility model are as follows:
Including pedestal and rotation aerofoil, pedestal and rotation aerofoil are attached by shaft, are provided in the shaft
For providing the torsion spring mechanism of expansion power, it is provided with lockable mechanism between pedestal and rotation aerofoil, the lockable mechanism is beaten
When opening, it can make to rotate aerofoil and be folded on pedestal, put into storage device by storage device internal space restraint, when transmitting revolves
Constraint of the rotor emaciated face from storage device is driven by torsion spring mechanism and is unfolded, and lockable mechanism can lock rotation aerofoil.
Two fixed blocks are set on the pedestal, are provided with movable block, movable block and rotary wings between two fixed blocks
Face connection, the torsion spring mechanism includes two oppositely oriented torsional springs, and torsional spring is mounted in the hole slot of fixed block and movable block.
The lockable mechanism includes mobile screw and backing pin, and backing pin is described by moving screw limit in rotation aerofoil
Pedestal on offer backing pin hole, mobile screw drives backing pin to open lockable mechanism when being detached from backing pin hole.
The backing pin is mounted on one end connection pressure spring in rotation aerofoil, is held out against its other end in backing pin by pressure spring
In hole.
Backing pin is vertically arranged with mobile screw, and dialing up mobile screw can make backing pin be detached from backing pin hole, lockable mechanism
It opens.
The lockable mechanism pedestal and rotation aerofoil between be arranged side by side have it is multiple.
Compared with prior art, the utility model is with following the utility model has the advantages that using the rotation being rotatably connected on pedestal
Rotor face provides expansion power by torsion spring mechanism, rotation aerofoil is folded on pedestal, missile flight device is put into storage device
It is constrained by storage device inner space, and constraint of the rotary wings emaciated face from storage device when transmitted, torsion spring mechanism drive
Aerofoil expansion is rotated, increases the span area of missile flight device on the basis of using existing space with this.In addition, this is practical
New structure is simple, lockable mechanism is provided between pedestal and rotation aerofoil, after rotation aerofoil expansion, lockable mechanism can be incited somebody to action
It is locked to rotate aerofoil, prevents aerofoil in guided missile operational process from shaking, it is reliable in operational process, with traditional integrated molding formula wing
Face is no different.
Detailed description of the invention
The side view of Fig. 1 the utility model folding wings；
The positive view of Fig. 2 the utility model folding wings；
The front view of Fig. 3 the utility model folding wings；
The cross-sectional view of Fig. 4 the utility model lockable mechanism；
In attached drawing: 1- rotates aerofoil；2- pedestal；3- shaft；4- fixed block；5- movable block；The left-handed button spring of 6-；7- dextrorotation button
Spring；8- pressure spring；9- moves screw；10- backing pin.
Specific embodiment
The following describes the utility model in further detail with reference to the accompanying drawings.
Referring to Fig. 1-3, the missile flight device folding wings of the utility model include pedestal 2 and rotation aerofoil 1, bottom in structure
Seat 2 and rotation aerofoil 1 are attached by shaft 3, are provided in shaft 3 for providing the torsion spring mechanism of expansion power, pedestal 2
Two fixed blocks 4 of upper setting are provided with movable block 5 between two fixed blocks 4, and movable block 5 is connect with rotation aerofoil 1, torsion spring machine
Structure includes two oppositely oriented torsional springs, and torsional spring is mounted in the hole slot of fixed block 4 and movable block 5.In pedestal 2 and rotation aerofoil
Lockable mechanism is provided between 1, referring to fig. 4, lockable mechanism includes mobile screw 9 and backing pin 10, and backing pin 10 is limited by mobile screw 9
Position offers backing pin hole in rotation aerofoil 1 on pedestal 2, backing pin 10 is mounted on one end connection pressure spring 8 in rotation aerofoil 1, leads to
It crosses pressure spring 8 to hold out against its other end in backing pin hole, mobile screw 9 opens locking machine when backing pin 10 being driven to be detached from backing pin hole
Structure.Backing pin 10 is vertically arranged with mobile screw 9, and dialing up mobile screw 9 can make backing pin 10 be detached from backing pin hole, lockable mechanism
It opens.Lockable mechanism pedestal 2 and rotation aerofoil 1 between be arranged side by side have it is multiple.When lockable mechanism is opened, rotary wings can be made
Face 1 is folded on pedestal 2, is put into storage device by storage device internal space restraint, and rotation aerofoil 1 is detached from storage when transmitting
The constraint of device is driven by torsion spring mechanism and is unfolded, and lockable mechanism can lock rotation aerofoil 1.
The course of work and working principle of the utility model are as follows:
Two fixed blocks 4 are separately fixed on pedestal 2, and movable block 5 is fixed on rotation aerofoil 1, left-handed button spring 6 with
7 both ends of dextrorotation button spring are limited in respectively among the hole slot of corresponding fixed block 4 and movable block 5, and backing pin 10 is limited by mobile screw 9
In rotation aerofoil 1.If it is desired that rotation aerofoil 1 is in folding position, mobile screw 9, mobile 9 band of screw can be dialed up
Dynamic backing pin 10 is detached from the hole of pedestal 2, can move rotation aerofoil 1 and turn to folding position, and left-handed button spring 5 and dextrorotation button spring 7
In by energy storage state is turned round, guided missile can be put among transmitting and storage device, be constrained with barrel at this time.
If guided missile one is emitted, it is detached from after barrel, is played a role by torsion spring, rotation aerofoil 1 is reached into expansion
Position, backing pin 10 locks rotation aerofoil 1 under the effect of pressure spring 8 at this time.
The above is only the preferred embodiment of the present invention, not to do in any form to the utility model
It limits, it will be apparent to a skilled person that this is practical new under conditions of not departing from the spirit of the present invention and principle
Type can also carry out several modifications or simple replacement, these modifications and replacement also each fall within the model delimited by submitted claim
Within enclosing.
Claims (6)
1. a kind of missile flight device folding wings, it is characterised in that: including pedestal (2) and rotation aerofoil (1), pedestal (2) and rotation
Aerofoil (1) is attached by shaft (3), is provided in the shaft (3) for providing the torsion spring mechanism of expansion power, the bottom of at
It is provided with lockable mechanism between seat (2) and rotation aerofoil (1), when the lockable mechanism is opened, can make to rotate aerofoil (1) folding
It is stacked on pedestal (2), puts into storage device by storage device internal space restraint, rotation aerofoil (1) is detached from storage when transmitting
The constraint of device is driven by torsion spring mechanism and is unfolded, and lockable mechanism can be locked by rotation aerofoil (1).
2. missile flight device folding wings according to claim 1, it is characterised in that: two are arranged on the pedestal (2)
Fixed block (4) is provided with movable block (5) between two fixed blocks (4), and movable block (5) is connect with rotation aerofoil (1), described
Torsion spring mechanism includes two oppositely oriented torsional springs, and torsional spring is mounted in the hole slot of fixed block (4) and movable block (5).
3. missile flight device folding wings according to claim 1, it is characterised in that: the lockable mechanism includes mobile spiral shell
(9) and backing pin (10) are followed closely, by mobile screw (9) limit in rotation aerofoil (1), the pedestal opens up backing pin (10) on (2)
There is backing pin hole, mobile screw (9) drive backing pin (10) to open lockable mechanism when being detached from backing pin hole.
4. missile flight device folding wings according to claim 3, it is characterised in that: the backing pin (10) is mounted on rotation
One end in aerofoil (1) connects pressure spring (8), is held out against its other end in backing pin hole by pressure spring (8).
5. missile flight device folding wings according to claim 3, it is characterised in that: backing pin (10) and mobile screw (9) are hung down
Straight setting, dialing up mobile screw (9) can make backing pin (10) to be detached from backing pin hole, and lockable mechanism is opened.
6. missile flight device folding wings according to claim 1, it is characterised in that: the lockable mechanism is in pedestal (2)
Rotation aerofoil (1) between be arranged side by side have it is multiple.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920114061.9U CN209559041U (en) | 2019-01-23 | 2019-01-23 | A kind of missile flight device folding wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920114061.9U CN209559041U (en) | 2019-01-23 | 2019-01-23 | A kind of missile flight device folding wings |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209559041U true CN209559041U (en) | 2019-10-29 |
Family
ID=68307262
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920114061.9U Active CN209559041U (en) | 2019-01-23 | 2019-01-23 | A kind of missile flight device folding wings |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209559041U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113267093A (en) * | 2020-03-13 | 2021-08-17 | 北京星际荣耀空间科技股份有限公司 | Grid rudder structure and rocket with same |
-
2019
- 2019-01-23 CN CN201920114061.9U patent/CN209559041U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113267093A (en) * | 2020-03-13 | 2021-08-17 | 北京星际荣耀空间科技股份有限公司 | Grid rudder structure and rocket with same |
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