CN107816914B - A kind of detention hood separator based on big momentum collision brake buffering - Google Patents
A kind of detention hood separator based on big momentum collision brake buffering Download PDFInfo
- Publication number
- CN107816914B CN107816914B CN201711039142.9A CN201711039142A CN107816914B CN 107816914 B CN107816914 B CN 107816914B CN 201711039142 A CN201711039142 A CN 201711039142A CN 107816914 B CN107816914 B CN 107816914B
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- CN
- China
- Prior art keywords
- hood
- force
- slice group
- metal
- launching tube
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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
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
Abstract
The invention discloses a kind of detention hood separators based on big momentum collision brake buffering, belong to MISSILE LAUNCHING technical field, comprising: accommodate shell, metal shears slice group, locating piece, force-transmitting seat and limited post；Hood is mounted on the outer circumference surface of missile airframe；Missile airframe and hood are installed in launching tube；The vertical portion of the side of force-transmitting seat is opposite with hood, and the horizontal component of the other side is opposite with the long sheet metal of metal shears slice group；Locating piece is mounted on the horizontal component upper surface of force-transmitting seat, and one end of more than two limited posts is mounted in locating piece, and the other end passes through the through-hole of metal shears slice group；Receiving shell is that the shell of two sides openings and end face opening is fixedly connected after receiving shell is open spiral-lock in locating piece, metal shears slice group by its end face with launching tube；The principle of device is simple, compact-sized and missile airframe and hood can be made quickly, reliably and securely to separate.
Description
Technical field
The invention belongs to MISSILE LAUNCHING technical fields, and in particular to a kind of detention based on big momentum collision brake buffering
Hood separator.
Background technique
Missile airframe pushes pop-up by the high-temperature high-pressure fuel gas that launching tube bottom ejection power plant generates, to avoid launching
When high-temperature high-pressure fuel gas cause damages to the engine and electromechanical equipment of guided missile tail end, usually using hood come to missile airframe rise
Protection and load effect.After missile airframe goes out cylinder, hood separation must be carried out in time, so that engine ignition works.
At present there are mainly two types of hood separation schemes: 1) separation side pushes away mode: blasting bolt unlocks first, by separation bullet
Spring pretightning force separates hood with missile airframe tail end, then pencil rocket ignition operation on the inside of hood, makes hood far from transmitting
Vehicle；2) rotating separation mode: blasting bolt unlocks first, then makes hood returning around body side by cut spring pretightning force
Turn trunnion rotation, hood is detached from missile airframe and far from car launcher when going to certain safe separating angle.Both hoods point
It is all to go out cylinder laggard end of line cover separation in missile airframe from scheme, separator is complicated, however when hood separation is guided missile separation
First separation link of sequence, the requirement to it be it is quick, reliable, safe, existing hood separator fails to reach this
It is required that.
Summary of the invention
In view of this, the present invention provides a kind of detention hood separator based on big momentum collision brake buffering,
The principle of device is simple, compact-sized and missile airframe and hood can be made quickly, reliably and securely to separate.
The present invention is achieved through the following technical solutions:
A kind of detention hood separator based on big momentum collision brake buffering, comprising: accommodate shell, metal sheet slitting
Piece group, locating piece, force-transmitting seat, positioning pin and limited post；
Integrated connection relationship is as follows: hood is mounted on the outer circumference surface of missile airframe by positioning pin；Missile airframe and tail
Cover is installed in launching tube；It is machined on the periphery of launching tube outlet end along its axial strip through-hole；
The force-transmitting seat is T-shaped structure, and horizontal component lower surface is jointly mounted to the outer circumference surface of launching tube, is erected
After the strip through-hole for directly partially passing through launching tube, do not contacted with the outer circumference surface of missile airframe, and force-transmitting seat can be in launching tube
Strip through-hole in along launching tube axial movement；
The metal shears slice group is alternatively arranged by long sheet metal and short sheet metal；Metal shears slice group is mounted on hair
On the outer circumference surface of shooting cylinder, the axial close-packed arrays of long sheet metal and short sheet metal along missile airframe；Add in metal shears slice group
There are two above along the through-hole of missile airframe axial direction for work；
The vertical portion of the side of force-transmitting seat is opposite with hood, the horizontal component of the other side and the long gold of metal shears slice group
It is opposite to belong to piece；
Locating piece is mounted on the horizontal component upper surface of force-transmitting seat, and one end of more than two limited posts is mounted on locating piece
In, the other end passes through the through-hole of metal shears slice group；
Accommodating shell is the shell that two sides are open and an end face is open, and accommodates shell and passes through its end face opening spiral-lock
In locating piece, metal shears slice group, two side is open after the axial distribution of missile airframe, with the fixed company of launching tube
It connects.
Further, the upper surface of force-transmitting seat horizontal component is concordant with the lower end surface of short sheet metal of metal shears slice group.
Further, there are set for the lower end surface of the upper surface of force-transmitting seat horizontal component and the short sheet metal of metal shears slice group
Set a distance.
Further, when missile airframe is mobile to the outlet end of launching tube, hood drives the horizontal component of force-transmitting seat to hit
To metal shears slice group.
The utility model has the advantages that hood shears metal sheet slitting by force-transmitting seat when (1) missile airframe of the invention ejects launching tube
Piece group makes its deformation that fractures, and retardance hood moves on, and realizes the relative speed difference of missile airframe and hood, and then realize guided missile
The separation of body and hood nature, safety.
(2) using metal shears slice group as buffering device, energy effective brake hood shortens buffer time, mentions the present invention
High buffering efficiency.
(3) hood of the invention is stranded in launching tube, is avoided hood and is spilled over outside cylinder, and falling from high altitude is not known
Property, there is the risk for smashing instrument and equipment and casualties, improves the safety of hood separation.
(4) by positioning pin connection, structure is simple for missile airframe of the invention and hood, so that missile airframe and hood
It separates reliability to increase, while also reducing economic cost.
Detailed description of the invention
Fig. 1 is structure composition figure of the invention.
Fig. 2 is the structural schematic diagram that the present invention is mounted on launching tube.
Fig. 3 is the working principle of the invention figure.
Wherein, 1- missile airframe, 2- hood, 3- launching tube, 4- accommodate shell, 5- metal shears slice group, 6- locating piece, 7-
Force-transmitting seat, 8- positioning pin, 9- limited post.
Specific embodiment
The present invention will now be described in detail with reference to the accompanying drawings and examples.
The present invention provides a kind of detention hood separators based on big momentum collision brake buffering, referring to attached drawing 1,
It include: to accommodate shell 4, metal shears slice group 5, locating piece 6, force-transmitting seat 7, positioning pin 8 and limited post 9；
Integrated connection relationship is as follows: referring to attached drawing 2, hood 2 is mounted on the outer circumference surface of missile airframe 1 by positioning pin 8；
Missile airframe 1 and hood 2 are installed in launching tube 3；It is machined on the periphery of 3 outlet end of launching tube along its axial bar shaped
Through-hole；
Force-transmitting seat 7 is T-shaped structure, and horizontal component lower surface is jointly mounted to the outer circumference surface of launching tube 3, vertical
It after the strip through-hole for partially passing through launching tube 3, is not contacted with the outer circumference surface of missile airframe 1, and force-transmitting seat 7 can be in launching tube
Along the axial movement of launching tube 3 in 3 strip through-hole；
Metal shears slice group 5 is made of 20 groups of metal shears slices, and 20 groups of metal shears slices are installed in launching tube 3
On outer circumference surface, and along the axial close-packed arrays of missile airframe 1；Wherein, every group of metal shears slice by a length of a film sheet metal and
A piece of short sheet metal is bonded, and long sheet metal and short sheet metal are identical along the size of 1 circumferencial direction of missile airframe, along Missile Body
The radial height of body 1 is different, and in the present embodiment, long sheet metal is along 1 axial direction of missile airframe with a thickness of 3mm, short sheet metal edge
Missile airframe 1 it is axial with a thickness of 2mm, the overall thickness of metal shears slice group 5 is 100mm；Two are machined in metal shears slice group 5
A above circular through hole for running through its thickness；
Wherein, the vertical portion of the side of force-transmitting seat 7 and hood 2 are opposite, and the horizontal component and metal shears of the other side are sliced
The long sheet metal of group 5 is opposite, and the lower end surface of the short sheet metal of the upper surface of 7 horizontal component of force-transmitting seat and metal shears slice group 5
Lower end surface of concordant or 7 horizontal component of force-transmitting seat the upper surface lower than the short sheet metal of metal shears slice group 5；
Locating piece 6 is mounted on the horizontal component upper surface of force-transmitting seat 7, is machined on locating piece 6 circumferential along missile airframe 1
The circular through hole of even distribution, the axial direction of the circular through hole are axial consistent with missile airframe 1；
One end of more than two limited posts 9 is located in the circular through hole of locating piece 6, and the other end passes through metal shears slice group
5 circular through hole；
The shell that shell 4 is two side openings and end face opening is accommodated, shell 4 is accommodated and passes through its end face opening button
In locating piece 6, metal shears slice group 5, two side is open after the axial distribution of missile airframe 1, solid with launching tube 3
Fixed connection.
Working principle: referring to attached drawing 3, when missile airframe 1 is mobile to the outlet end of launching tube 3, hood 2 is driven to set
Speed hits the vertical portion of force-transmitting seat 7, and force-transmitting seat 7 is driven to move along the strip through-hole of launching tube 3, and then force-transmitting seat 7
Horizontal component hits metal shears slice group 5；Under the reaction force of metal shears slice 5 pairs of hoods 2 of group, hood 2 and missile airframe 1
Between form relative speed difference, the positioning pin 8 of the two connection starts bending fracture, and hood 2 is initially separated with missile airframe 1；Tail
Cover 2 continues that force-transmitting seat 7 is driven to cut metal shears slice group 5 under the action of inertia, meanwhile, after 5 energy-absorbing of metal shears slice group
Retardance hood 2 and force-transmitting seat 7 are advanced further, until hood 2 is decelerated to static, are made to realize to the buffer-braking of hood 3
With, realize missile airframe 1 and hood 2 it is quick, reliably and securely separate, and hood 3 is trapped in launching tube 3.
In conclusion the above is merely preferred embodiments of the present invention, being not intended to limit the scope of the present invention.
All within the spirits and principles of the present invention, any modification, equivalent replacement, improvement and so on should be included in of the invention
Within protection scope.
Claims (4)
1. a kind of detention hood separator based on big momentum collision brake buffering,
Hood (2) is mounted on the outer circumference surface of missile airframe (1) by positioning pin (8)；Missile airframe (1) and hood (2) are pacified
In launching tube (3)；It is characterized in that, separator further include: accommodate shell (4), metal shears slice group (5), locating piece
(6), force-transmitting seat (7) and limited post (9)；It is machined on the periphery of launching tube (3) outlet end along its axial strip through-hole；
The force-transmitting seat (7) is T-shaped structure, and horizontal component lower surface is jointly mounted to the outer circumference surface of launching tube (3),
After vertical portion passes through the strip through-hole of launching tube (3), do not contacted with the outer circumference surface of missile airframe (1), and force-transmitting seat (7) energy
The interior axial movement along launching tube (3) of enough strip through-holes in launching tube (3)；
The metal shears slice group (5) is alternatively arranged by long sheet metal and short sheet metal；Metal shears slice group (5) is mounted on
On the outer circumference surface of launching tube (3), the axial close-packed arrays of long sheet metal and short sheet metal along missile airframe (1)；Metal sheet slitting
More than two through-holes along missile airframe (1) axial direction are machined in piece group (5)；
The vertical portion of the side of force-transmitting seat (7) and hood (2) relatively, the horizontal component and metal shears slice group (5) of the other side
Long sheet metal it is opposite；
Locating piece (6) is mounted on the horizontal component upper surface of force-transmitting seat (7), and one end of more than two limited posts (9) is mounted on
In locating piece (6), the other end passes through the through-hole of metal shears slice group (5)；
The shell that shell (4) are two side openings and end face opening is accommodated, shell (4) is accommodated and passes through its end face opening button
In locating piece (6), metal shears slice group (5), two side is open after the axial distribution of missile airframe (1), with hair
Shooting cylinder (3) is fixedly connected.
2. a kind of detention hood separator based on big momentum collision brake buffering as described in claim 1, feature
It is, the upper surface of force-transmitting seat (7) horizontal component is concordant with the lower end surface of short sheet metal of metal shears slice group (5).
3. a kind of detention hood separator based on big momentum collision brake buffering as described in claim 1, feature
Be, the lower end surface of the short sheet metal of the upper surface and metal shears slice group (5) of force-transmitting seat (7) horizontal component there are setting away from
From.
4. a kind of detention hood separator based on big momentum collision brake buffering as described in claim 1, feature
It is, when missile airframe (1) is mobile to the outlet end of launching tube (3), hood (2) drives the horizontal component of force-transmitting seat (7) to hit
To metal shears slice group (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711039142.9A CN107816914B (en) | 2017-10-31 | 2017-10-31 | A kind of detention hood separator based on big momentum collision brake buffering |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711039142.9A CN107816914B (en) | 2017-10-31 | 2017-10-31 | A kind of detention hood separator based on big momentum collision brake buffering |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107816914A CN107816914A (en) | 2018-03-20 |
| CN107816914B true CN107816914B (en) | 2019-07-02 |
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ID=61604552
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711039142.9A Active CN107816914B (en) | 2017-10-31 | 2017-10-31 | A kind of detention hood separator based on big momentum collision brake buffering |
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| CN (1) | CN107816914B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112361895B (en) * | 2020-10-22 | 2022-11-25 | 湖北航天技术研究院总体设计所 | Retention type missile tail cover |
| CN113074579B (en) * | 2021-03-05 | 2022-09-30 | 湖北航天技术研究院总体设计所 | Tail cover retention device of guided missile |
| CN113551564B (en) * | 2021-07-13 | 2022-07-08 | 北京理工大学 | Radially-contractible ejection device conical buffering stop tail cover structure |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR100629930B1 (en) * | 2004-07-30 | 2006-09-29 | 국방과학연구소 | Missile ejection launching system |
| CN103292641B (en) * | 2013-05-10 | 2014-11-19 | 北京宇航系统工程研究所 | Explosive separation device used for longitudinal separation of fairing |
| CN203848761U (en) * | 2014-05-28 | 2014-09-24 | 晋西工业集团有限责任公司 | Connection and separation mechanism for rocket projectile |
| CN204788082U (en) * | 2015-04-29 | 2015-11-18 | 北京威标至远科技发展有限公司 | Guided missile is cutting device for stage separation |
| CN105857646B (en) * | 2016-04-08 | 2017-11-24 | 上海机电工程研究所 | A kind of spherical locking separating mechanism |
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2017
- 2017-10-31 CN CN201711039142.9A patent/CN107816914B/en active Active
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| CN107816914A (en) | 2018-03-20 |
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