CN110411288A - A kind of bait bullet folding fin - Google Patents
A kind of bait bullet folding fin Download PDFInfo
- Publication number
- CN110411288A CN110411288A CN201910822333.5A CN201910822333A CN110411288A CN 110411288 A CN110411288 A CN 110411288A CN 201910822333 A CN201910822333 A CN 201910822333A CN 110411288 A CN110411288 A CN 110411288A
- Authority
- CN
- China
- Prior art keywords
- missile wing
- empennage
- erecting bed
- bait
- bait bullet
- 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
- 230000002787 reinforcement Effects 0.000 claims abstract description 8
- 210000005069 ears Anatomy 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 4
- 238000009434 installation Methods 0.000 abstract description 4
- 230000000712 assembly Effects 0.000 description 3
- 238000000429 assembly Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000002596 correlated effect Effects 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000005619 thermoelectricity Effects 0.000 description 1
- 238000005303 weighing Methods 0.000 description 1
Classifications
-
- 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
The invention discloses a kind of bait bullet folding fin, problem to be solved by this invention is how to increase bait bullet thermal cell volume in the case where keeping bait bullet total volume and guarantee the aeroperformance after the reduction of empennage overall length.The technical scheme is that the missile wing is hinged in the mounting base of empennage erecting bed, the empennage erecting bed is cylinder, missile wing folded slot is provided on cylindrical side wall, the both ends of missile wing folded slot are provided with reinforcement boss, the missile wing is convex shape, is cooperated at the unfilled corner of convex shape missile wing with the reinforcement boss of empennage erecting bed；Effect of the invention is: improved folding fin can keep the pneumatic area of the missile wing of empennage in the case where bait projectile tail end length reduces, aeroperformance needed for guaranteeing bait bullet automatic-posture-adjustment, and be able to satisfy the intensity requirement of structure installation.
Description
Technical field:
A kind of a kind of folding fin playing adjustment posture of the present invention, and in particular to bait bullet folding fin.
Background technique:
With throwing type active decoy elasticity can continuous improvement, the quantity and performance of bait bullet internal component are also
It improves, total power consumption needed for this has resulted in bait bullet is increasing.
Throwing type active decoy bullet is that the energy is provided by self-contained battery, and total power consumption increase just implies increase thermoelectricity
The volume in pond meets the needs of big power consumption.But it is constant in bait bullet structure gross space due to the limitation of victim emitter volume
In the case where, increase the volumetric spaces of thermal cell, just certainly will need to reduce the volumetric spaces of other assemblies, if reducing other groups
The volumetric spaces of part, it is necessary to other assemblies be redesigned or reduced with the correlated performance of other assemblies, this will lead to
Bait bullet is unable to reach due effect and effect.
In order to guarantee the function of bait bullet in these cases, the volumetric spaces for reducing the bait projectile tail wing are obtained by weighing
Cost performance is highest.Since the diameter of bait bullet is constant, the total length of empennage can only be reduced.Reducing, empennage is long
In the case where degree, for the aeroperformance for guaranteeing missile wing, needs to optimize the bait projectile tail wing, empennage is made to be able to satisfy gas
Dynamic performance requirement, and it is able to satisfy the intensity requirement of structure installation.
Therefore the application problem to be solved is how to increase bait bullet heat in the case where keeping bait bullet total volume
Battery volume simultaneously guarantees the aeroperformance after the reduction of empennage overall length.
Summary of the invention
The object of the present invention is to provide a kind of bait bullet folding fins.
In order to achieve the above objectives, present invention provide the technical scheme that missile wing is hinged in the mounting base of empennage erecting bed,
The empennage erecting bed is cylinder, is provided with missile wing folded slot on cylindrical side wall, the both ends of missile wing folded slot are provided with
Reinforce boss, the missile wing is convex shape, is cooperated at the unfilled corner of convex shape missile wing with the reinforcement boss of empennage erecting bed.
The mounting ear of the missile wing is separately positioned on the both ends of convex shape protrusion, and the mounting ear is cylindrical, and two
Spring is provided between mounting ear.
Effect of the invention is: improved folding fin can keep tail in the case where bait projectile tail chord degree reduces
The pneumatic area of the missile wing of the wing, aeroperformance needed for guaranteeing bait bullet automatic-posture-adjustment, and it is able to satisfy the intensity requirement of structure installation.
Detailed description of the invention
Fig. 1 is folding fin assembling structure schematic diagram
Fig. 2 is folding fin empennage holder structure schematic diagram
Fig. 3 is missile wing structure chart
Specific embodiment
Referring to Fig. 1-3, the present invention will be further described in detail with reference to the accompanying drawings and detailed description.
Due to needing to reduce empennage length, the circular mounting seat thickness at 2 both ends of empennage erecting bed is reduced, in circle
Missile wing 1 is hinged in the mounting base of empennage erecting bed by mounting base thickness after reducing by fixed pin shaft, the empennage erecting bed
For cylinder, missile wing folded slot 6 is provided on cylindrical side wall.
It is easy to happen after causing missile wing to be unfolded due to the circular mounting seat thickness bottom reduction at empennage erecting bed both ends because circle is pacified
Situations such as fracture of circular mounting seat caused by dress seat intensity is inadequate, tearing, therefore be provided with and add at the both ends of missile wing folded slot
Strong boss 3.In order to keep the front face area of missile wing constant, missile wing is adjusted to convex shape, at the unfilled corner of convex shape missile wing and tail
The reinforcement boss of wing erecting bed cooperates.
When missile wing expansion, its area of part that missile wing stretches out empennage erecting bed is remained unchanged.
The mounting ear of the missile wing is separately positioned on the both ends of convex shape protrusion, and the mounting ear 4 is cylindrical, and two
Spring 5 is provided between mounting ear.Fixed pin shaft passes through the mounting ear and spring of circular mounting platform, missile wing, insertion empennage installation
In the reinforcement boss of platform.
The reinforcement boss of empennage erecting bed docks place with the unfilled corner position of missile wing, and there are certain gaps, to realize the fast of missile wing
The accessible folding of speed.
The foregoing is merely the schematical specific embodiment of the present invention, the range being not intended to limit the invention.It is any
Those skilled in the art, the equivalent changes and modifications made under the premise of not departing from design and the principle of the present invention,
It should belong to the scope of protection of the invention.
Claims (2)
1. a kind of bait bullet folding fin, it includes empennage erecting bed, missile wing, it is characterized in that: the missile wing is hinged on empennage peace
In the mounting base for filling platform, the empennage erecting bed is cylinder, and missile wing folded slot is provided on cylindrical side wall, and missile wing folds
The both ends of slot are provided with reinforcement boss, and the missile wing is convex shape, the reinforcement at the unfilled corner of convex shape missile wing with empennage erecting bed
Boss cooperates.
2. a kind of bait bullet folding fin according to claim 1, it is characterized in that: the mounting ear of the missile wing is respectively set
At the both ends of convex shape protrusion, the mounting ear is cylinder, is provided with spring between two mounting ears.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910822333.5A CN110411288A (en) | 2019-09-02 | 2019-09-02 | A kind of bait bullet folding fin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910822333.5A CN110411288A (en) | 2019-09-02 | 2019-09-02 | A kind of bait bullet folding fin |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110411288A true CN110411288A (en) | 2019-11-05 |
Family
ID=68369912
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910822333.5A Pending CN110411288A (en) | 2019-09-02 | 2019-09-02 | A kind of bait bullet folding fin |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110411288A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111059965A (en) * | 2019-12-27 | 2020-04-24 | 中国航天科工集团八五一一研究所 | Small-diameter missile wing piece unfolding mechanism with limiting and self-locking functions |
| CN112461057A (en) * | 2020-10-08 | 2021-03-09 | 湖北航天飞行器研究所 | Compact type high-aspect-ratio pneumatic appearance layout structure of fire extinguishing bomb and design method |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2876532B1 (en) * | 1998-04-04 | 1999-03-31 | 防衛庁技術研究本部長 | Wrap-around wing with improved performance |
| US6739548B1 (en) * | 2003-04-21 | 2004-05-25 | The United States Of America As Represented By The Secretary Of The Army | Fin lock system |
| CA2616982A1 (en) * | 2005-10-13 | 2007-04-19 | Raytheon Company | Exhaust assembly for mass ejection drive system |
| US20120048993A1 (en) * | 2010-07-16 | 2012-03-01 | Javier Velez | Aerodynamic flight termination system and method |
| KR101833681B1 (en) * | 2017-08-04 | 2018-03-02 | 국방과학연구소 | Fin locking device and method for projectiles with folded fin using a plate spring |
| KR20180047456A (en) * | 2016-10-31 | 2018-05-10 | 주식회사 한화 | Apparatus and method for locking of deployable fins |
| CN208872183U (en) * | 2018-07-23 | 2019-05-17 | 沈阳航盛科技有限责任公司 | A kind of outer throwing type active decoy bullet folding fin of machine |
| CN208887491U (en) * | 2018-07-23 | 2019-05-21 | 沈阳航盛科技有限责任公司 | The outer throwing type active decoy bullet of machine |
| CN210464230U (en) * | 2019-09-02 | 2020-05-05 | 沈阳航盛科技有限责任公司 | Folding tail wing of bait bullet |
-
2019
- 2019-09-02 CN CN201910822333.5A patent/CN110411288A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2876532B1 (en) * | 1998-04-04 | 1999-03-31 | 防衛庁技術研究本部長 | Wrap-around wing with improved performance |
| US6739548B1 (en) * | 2003-04-21 | 2004-05-25 | The United States Of America As Represented By The Secretary Of The Army | Fin lock system |
| CA2616982A1 (en) * | 2005-10-13 | 2007-04-19 | Raytheon Company | Exhaust assembly for mass ejection drive system |
| US20120048993A1 (en) * | 2010-07-16 | 2012-03-01 | Javier Velez | Aerodynamic flight termination system and method |
| KR20180047456A (en) * | 2016-10-31 | 2018-05-10 | 주식회사 한화 | Apparatus and method for locking of deployable fins |
| KR101833681B1 (en) * | 2017-08-04 | 2018-03-02 | 국방과학연구소 | Fin locking device and method for projectiles with folded fin using a plate spring |
| CN208872183U (en) * | 2018-07-23 | 2019-05-17 | 沈阳航盛科技有限责任公司 | A kind of outer throwing type active decoy bullet folding fin of machine |
| CN208887491U (en) * | 2018-07-23 | 2019-05-21 | 沈阳航盛科技有限责任公司 | The outer throwing type active decoy bullet of machine |
| CN210464230U (en) * | 2019-09-02 | 2020-05-05 | 沈阳航盛科技有限责任公司 | Folding tail wing of bait bullet |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111059965A (en) * | 2019-12-27 | 2020-04-24 | 中国航天科工集团八五一一研究所 | Small-diameter missile wing piece unfolding mechanism with limiting and self-locking functions |
| CN111059965B (en) * | 2019-12-27 | 2022-04-08 | 中国航天科工集团八五一一研究所 | Small-diameter missile wing piece unfolding mechanism with limiting and self-locking functions |
| CN112461057A (en) * | 2020-10-08 | 2021-03-09 | 湖北航天飞行器研究所 | Compact type high-aspect-ratio pneumatic appearance layout structure of fire extinguishing bomb and design method |
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| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |