CN107816914A - 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
- CN107816914A CN107816914A CN201711039142.9A CN201711039142A CN107816914A CN 107816914 A CN107816914 A CN 107816914A CN 201711039142 A CN201711039142 A CN 201711039142A CN 107816914 A CN107816914 A CN 107816914A
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- Prior art keywords
- hood
- force
- section group
- metal
- launching tube
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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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Vibration Dampers (AREA)
Abstract
The invention discloses a kind of detention hood separator based on big momentum collision brake buffering, belong to MISSILE LAUNCHING technical field, including：Accommodate housing, metal shears section group, locating piece, force-transmitting seat and limited post；Hood is arranged 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 relative with hood, and the horizontal component of opposite side is relative with the long sheet metal of metal shears section group；Locating piece is arranged on the horizontal component upper surface of force-transmitting seat, and one end of more than two limited posts is arranged in locating piece, and the other end passes through the through hole of metal shears section group；Accommodate the housing that housing is two lateral openings and an end face opening, accommodate housing by its end face opening spiral-lock in locating piece, metal shears section group after, be fixedly connected with launching tube；The principle of device is simple, compact-sized and can make that missile airframe and hood are quick, reliably and securely separate.
Description
Technical field
The invention belongs to MISSILE LAUNCHING technical field, and in particular to a kind of detention based on big momentum collision brake buffering
Hood separator.
Background technology
Missile airframe high-temperature high-pressure fuel gas as caused by the ejection power plant of launching tube bottom promote ejection, to avoid launching
When high-temperature high-pressure fuel gas the engine and electromechanical equipment of guided missile tail end are damaged, 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.
Hood separation scheme mainly has two kinds at present：1) separation side pushes away mode：Blasting bolt unlocks first, by separation bullet
Spring pretightning force makes hood be separated with missile airframe tail end, then pencil rocket ignition operation on the inside of hood, makes hood away from transmitting
Car；2) rotating separation mode：Blasting bolt unlocks first, then makes hood returning around body side by cut spring pretightning force
Turn journal stirrup rotation, hood departs from missile airframe and away from car launcher when going to certain safe separating angle.Both hoods point
All it is to go out the separation of cylinder laggard end of line cover in missile airframe from scheme, separator is complicated, but when hood separation is guided missile separation
First separation link of sequence, the requirement to it is quick, reliable, safe, and existing hood separator fails to reach this
It is required that.
The content of the invention
In view of this, the invention provides it is a kind of based on big momentum collision brake buffering detention hood separator,
The principle of device is simple, compact-sized and can make that missile airframe and hood are quick, reliably and securely separate.
The present invention is achieved through the following technical solutions：
A kind of detention hood separator based on big momentum collision brake buffering, including：Accommodate housing, metal sheet slitting
Piece group, locating piece, force-transmitting seat, alignment pin and limited post；
Integrated connection relation is as follows：Hood is arranged on the outer circumference surface of missile airframe by alignment pin；Missile airframe and tail
Cover is installed in launching tube；It is machined with the periphery of the launching tube port of export along its axial strip through-hole；
The force-transmitting seat is T-shaped structure, and its horizontal component lower surface is jointly mounted to the outer circumference surface of launching tube, and it is perpendicular
After the straight strip through-hole for 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 interior edge launching tube axial movement；
The metal shears section group is spaced and formed by long sheet metal and short sheet metal；Metal shears section group is arranged 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 section group
Work has through hole of the two or more along missile airframe axial direction；
The vertical portion of the side of force-transmitting seat is relative with hood, the horizontal component of opposite side and the long gold of metal shears section group
It is relative to belong to piece；
Locating piece is arranged on the horizontal component upper surface of force-transmitting seat, and one end of more than two limited posts is arranged on locating piece
In, the other end passes through the through hole of metal shears section group；
It is two lateral openings and the housing of an end face opening to accommodate housing, accommodates housing and passes through its end face opening spiral-lock
In locating piece, metal shears section group, after axial direction distribution of two lateral opening along missile airframe, fix and connect with launching tube
Connect.
Further, the upper surface of force-transmitting seat horizontal component is concordant with the lower surface of the short sheet metal of metal shears section group.
Further, the upper surface of force-transmitting seat horizontal component and the lower surface of the short sheet metal of metal shears section group are left and set
Set a distance.
Further, when missile airframe moves to the port of export of launching tube, hood drives the horizontal component of force-transmitting seat to hit
To metal shears section group.
Beneficial effect：(1) when missile airframe of the invention ejects launching tube, hood shears metal sheet slitting by force-transmitting seat
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) present invention energy effective brake hood, shortens buffer time, carried using metal shears section group as buffering device
High buffering efficiency.
(3) hood of the invention is stranded in launching tube, is avoided hood and is spilled over outside cylinder, and its falling from high altitude is not known
Property, the risk for smashing instrument and equipment and casualties be present, improve the security of hood separation.
(4) missile airframe of the invention with hood by positioning pin connection, it is simple in construction so that missile airframe and hood
Reliability increase is separated, while also reduces financial cost.
Brief description of the drawings
Fig. 1 is the structure composition figure of the present invention.
Fig. 2 is the structural representation that the present invention is arranged on launching tube.
Fig. 3 is the fundamental diagram of the present invention.
Wherein, 1- missile airframes, 2- hoods, 3- launching tubes, 4- accommodate housing, 5- metal shears section groups, 6- locating pieces, 7-
Force-transmitting seat, 8- alignment pins, 9- limited posts.
Embodiment
The present invention will now be described in detail with reference to the accompanying drawings and examples.
The invention provides a kind of detention hood separator based on big momentum collision brake buffering, referring to accompanying drawing 1,
Including：Accommodate housing 4, metal shears section group 5, locating piece 6, force-transmitting seat 7, alignment pin 8 and limited post 9；
Integrated connection relation is as follows：Referring to accompanying drawing 2, hood 2 is arranged on the outer circumference surface of missile airframe 1 by alignment pin 8；
Missile airframe 1 and hood 2 are installed in launching tube 3；It is machined with the periphery of the port of export of launching tube 3 along its axial bar shaped
Through hole；
Force-transmitting seat 7 is T-shaped structure, and its horizontal component lower surface is jointly mounted to the outer circumference surface of launching tube 3, and its is vertical
After the strip through-hole for partially passing through launching tube 3, do not contacted with the outer circumference surface of missile airframe 1, and force-transmitting seat 7 can be in launching tube
The axial movement of 3 strip through-hole interior edge launching tube 3；
Metal shears section group 5 is made up of 20 groups of metal shears sections, and 20 groups of metal shears sections are installed in launching tube 3
On outer circumference surface, and along the axial close-packed arrays of missile airframe 1；Wherein, the section of every group of metal shears by a length of a film sheet metal and
A piece of short sheet metal fitting forms, and the size of long sheet metal and short sheet metal along the circumferencial direction of missile airframe 1 is identical, along Missile Body
The height of the radial direction of body 1 is different, and in the present embodiment, thickness of the long sheet metal along the axial direction of missile airframe 1 is 3mm, short sheet metal edge
The thickness of the axial direction of missile airframe 1 is 2mm, and the gross thickness of metal shears section group 5 is 100mm；Two are machined with metal shears section group 5
Run through the manhole of its thickness more than individual；
Wherein, the vertical portion of the side of force-transmitting seat 7 is relative with hood 2, and horizontal component and the metal shears of opposite side are cut into slices
The long sheet metal of group 5 is relative, and the upper surface of the horizontal component of force-transmitting seat 7 and the lower surface of the short sheet metal of metal shears section group 5
Lower surface of concordant or the horizontal component of force-transmitting seat 7 the upper surface less than the short sheet metal of metal shears section group 5；
Locating piece 6 is arranged on the horizontal component upper surface of force-transmitting seat 7, is machined with locating piece 6 circumferential along missile airframe 1
The manhole of even distribution, the axial direction of the manhole are axially consistent with missile airframe 1；
One end of more than two limited posts 9 is located in the manhole of locating piece 6, and the other end passes through metal shears section group
5 manhole；
It is two lateral openings and the housing of an end face opening to accommodate housing 4, accommodates housing 4 and passes through its end face opening button
It is solid with launching tube 3 after axial direction distribution of two lateral opening along missile airframe 1 in locating piece 6, metal shears section group 5
Fixed connection.
Operation principle：Referring to accompanying drawing 3, when missile airframe 1 moves to the port of export of launching tube 3, hood 2 is driven to set
Speed hits the vertical portion of force-transmitting seat 7, and drives strip through-hole of the force-transmitting seat 7 along launching tube 3 to move, and then force-transmitting seat 7
Horizontal component hits metal shears section group 5；Under the reaction force of metal shears section 5 pairs of hoods 2 of group, hood 2 and missile airframe 1
Between form relative speed difference, the alignment pin 8 that both connect starts bending fracture, and hood 2 is initially separated with missile airframe 1；Tail
Cover 2 continues to drive force-transmitting seat 7 to cut metal shears section group 5 in the presence of inertia, meanwhile, after the energy-absorbing of metal shears section group 5
Retardance hood 2 and force-transmitting seat 7 are advanced further, until hood 2 be decelerated to it is static, so as to realize to the buffer-braking of hood 3 work
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 summary, presently preferred embodiments of the present invention is these are only, is not intended to limit the scope of the present invention.
Within the spirit and principles of the invention, any modification, equivalent substitution and improvements made etc., it should be included in the present invention's
Within protection domain.
Claims (4)
- A kind of 1. detention hood separator based on big momentum collision brake buffering, it is characterised in that including：Accommodate housing (4), metal shears section group (5), locating piece (6), force-transmitting seat (7), alignment pin (8) and limited post (9)；Integrated connection relation is as follows：Hood (2) is arranged on the outer circumference surface of missile airframe (1) by alignment pin (8)；Missile airframe (1) it is installed in hood (2) in launching tube (3)；It is machined with the periphery of launching tube (3) port of export along its axial bar shaped Through hole；The force-transmitting seat (7) is T-shaped structure, and its horizontal component lower surface is jointly mounted to the outer circumference surface of launching tube (3), its 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 axial movement of enough strip through-hole interior edge launching tubes (3) in launching tube (3)；The metal shears section group (5) is spaced and formed by long sheet metal and short sheet metal；Metal shears section group (5) is arranged 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 Through hole of the two or more along missile airframe (1) axial direction is machined with piece group (5)；The vertical portion of the side of force-transmitting seat (7) with hood (2) relatively, horizontal component and the metal shears section group (5) of opposite side Long sheet metal it is relative；Locating piece (6) is arranged on the horizontal component upper surface of force-transmitting seat (7), and one end of more than two limited posts (9) is arranged on In locating piece (6), the other end passes through the through hole of metal shears section group (5)；It is two lateral openings and the housing of an end face opening to accommodate housing (4), accommodates housing (4) and passes through its end face opening button In locating piece (6), metal shears section group (5), after axial direction distribution of two lateral opening along 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 claimed in claim 1, its feature It is, the upper surface of force-transmitting seat (7) horizontal component is concordant with the lower surface of the short sheet metal of metal shears section group (5).
- 3. a kind of detention hood separator based on big momentum collision brake buffering as claimed in claim 1, its feature Be, the lower surface of the upper surface of force-transmitting seat (7) horizontal component and the short sheet metal of metal shears section group (5) leave setting away from From.
- 4. a kind of detention hood separator based on big momentum collision brake buffering as claimed in claim 1, its feature It is, when missile airframe (1) moves to the port of export of launching tube (3), hood (2) drives the horizontal component of force-transmitting seat (7) to hit To metal shears section 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 true CN107816914A (en) | 2018-03-20 |
| CN107816914B CN107816914B (en) | 2019-07-02 |
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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 |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107816914B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112361895A (en) * | 2020-10-22 | 2021-02-12 | 湖北航天技术研究院总体设计所 | Retention type missile tail cover |
| CN113074579A (en) * | 2021-03-05 | 2021-07-06 | 湖北航天技术研究院总体设计所 | Tail cover retention device of guided missile |
| CN113551564A (en) * | 2021-07-13 | 2021-10-26 | 北京理工大学 | Conical buffering and stopping tail cover structure of radially-contractible ejection device |
Citations (5)
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| FR2873802A1 (en) * | 2004-07-30 | 2006-02-03 | Agency Defense Dev | Missile ejection system, has gas generator to orient gas outlet opposite to case`s missile chamber, and valve at missile`s front end, where missile is propelled by gas pressure repressed by generator from another chamber to missile chamber |
| CN103292641A (en) * | 2013-05-10 | 2013-09-11 | 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 |
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2017
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| FR2873802A1 (en) * | 2004-07-30 | 2006-02-03 | Agency Defense Dev | Missile ejection system, has gas generator to orient gas outlet opposite to case`s missile chamber, and valve at missile`s front end, where missile is propelled by gas pressure repressed by generator from another chamber to missile chamber |
| US7484449B2 (en) * | 2004-07-30 | 2009-02-03 | Government Agency For Defense Development | Missile ejection system and launching canister thereof |
| CN103292641A (en) * | 2013-05-10 | 2013-09-11 | 北京宇航系统工程研究所 | Explosive separation device used for longitudinal separation of fairing |
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Non-Patent Citations (1)
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| 晁锐等: ""一种滞留式尾罩分离技术"", 《导弹与航天运载技术》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112361895A (en) * | 2020-10-22 | 2021-02-12 | 湖北航天技术研究院总体设计所 | Retention type missile tail cover |
| CN113074579A (en) * | 2021-03-05 | 2021-07-06 | 湖北航天技术研究院总体设计所 | Tail cover retention device of guided missile |
| CN113551564A (en) * | 2021-07-13 | 2021-10-26 | 北京理工大学 | Conical buffering and stopping tail cover structure of radially-contractible ejection device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107816914B (en) | 2019-07-02 |
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