CN103542773A - Fragile rear cover of launching cylinder of weapon system - Google Patents
Fragile rear cover of launching cylinder of weapon system Download PDFInfo
- Publication number
- CN103542773A CN103542773A CN201310538927.6A CN201310538927A CN103542773A CN 103542773 A CN103542773 A CN 103542773A CN 201310538927 A CN201310538927 A CN 201310538927A CN 103542773 A CN103542773 A CN 103542773A
- Authority
- CN
- China
- Prior art keywords
- bonnet
- launching tube
- flange ring
- frangible
- armament systems
- 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.)
- Granted
Links
Images
Landscapes
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention relates to a rear cover and particularly to a fragile rear cover of a launching cylinder of a weapon system. The fragile rear cover of the launching cylinder of the weapon system is characterized by comprising a holder and a sealing structure which is made of composite materials; the holder comprises a flange ring and mooring plates; the plurality of mooring plates are arranged inside the flange ring in an annular mode; the mooring plate and the flange ring are connected into a whole through connecting handles; the sealing structure which is made of the composite materials fully covers internal and external lateral sides of the mooring plate in a welding mode; strip-shaped grooves are formed in gaps between the mooring plates; peripheral grooves which are vertical to the strip-shaped grooves are formed between the connecting handles. According to the fragile rear cover of the launching cylinder of the weapon system, when a missile is launched, smash of the rear cover of the launching cylinder can be discovered, the smashed rear cover can be moored on the launching cylinder, and adverse effects caused by rear cover fragments to surrounding military arrangement are avoided.
Description
Technical field
The present invention relates to a kind of bonnet, specifically, is a kind of frangible bonnet of launching tube of armament systems.
Background technology
Launching tube is the device for depositing and launching a guided missile; stack shell forms an airtight container together with protecgulum, bonnet, becomes guided missile in protection cylinder and exempts from the extraneous factor infringements such as high temperature, low temperature, moisture, corrosive medium, electric field, magnetic field barrier together with disturbing.Wherein, protecgulum, bonnet not only will have above-mentioned safeguard function, and must have frangible characteristic.The in the situation that of brute force impact and ablation, this kind of bonnet must be broken rapidly, and reliably open the some parts for decile, and under the frangible bonnet of launching tube, parts must be tethered in launching tube rear end.
The frangible bonnet of existing armament systems launching tube, generally adopts composite to make, and when guided missile is launched from launching tube, bonnet is broken, and broken bonnet fragment can drop on the ground at launching tube rear.Bonnet fragment on the ground produces interference for other combat system in operation place.Especially for aircraft carrier, often also have motor vehicles and aircraft start above deck and take off, on ground, do not allow residual any foreign material, if there is the fragment ground on the scene of dropping after bonnet fragmentation, to fighting, arranges and bring hidden danger, even produce dangerous.
Summary of the invention
The present invention aims to provide a kind of armament systems launching tube bonnet, and broken in the time of can realizing MISSILE LAUNCHING, the launching tube bonnet fragment that can realize again after fragmentation is tethered in launching tube rear end, does not fall on the ground.Avoid after bonnet fragmentation the fragment ground on the scene of dropping, to fighting, arrange that to bring hidden danger dangerous.
The present invention is by the following technical solutions:
The frangible bonnet of launching tube, is characterized in that: comprise retainer, composite material sealing structure; Described retainer comprises flange ring and captive plate, a plurality of captive plate of flange ring inner annular arranged in arrays, described captive plate by be integrally connected with it connection handle be fixedly connected with flange ring; The comprehensive welding of described composite material sealing structure covers on the interior lateral surface of captive plate: the gap location of adjacent captive plate is offered the groove of strip, locates to offer the peripheral grooves intersecting vertically with described central recess between adjacent connection handle.
When the frangible bonnet of launching tube of armament systems of the present invention is subject to after powerful impact, composite material sealing structure is broken along its central recess and peripheral grooves, outwards open, and connection handle is still firmly connected and fixed with flange ring, composite material sealing structure is divided into some after splitting, and is still attached in captive plate.
Further, described connection handle has aduncate radian.
Further, described connection handle and flange ring are welded and fixed, and the welding position of connection handle is than all the other position wider width.
Further, in described captive plate, offer at least one welding reinforced hole.
Further, described captive plate is fan-shaped, and described peripheral grooves is circular arc.
Further, the quantity of described captive plate is 6-8 piece.
Further, described composite is formed by glass fiber sheets bonding stack melting pressing layer by layer.
Further, the degree of depth of described peripheral grooves and central recess is 1-3mm, and width is 2-5mm.
Further, on described flange ring, be also provided with the external screw thread meshing with launching tube, on described flange ring, offer the installing technological hole of engagement in rotation, on described flange ring, also offer seal groove.
Beneficial effect of the present invention is:
1) during MISSILE LAUNCHING, can realize the fragmentation of launching tube bonnet, can realize again bonnet and be tethered on launching tube after fragmentation, and not fall on the ground.
2) avoid mixed and disorderly unordered bonnet fragment on ground the operation on naval vessel to be arranged to the adverse effect of bringing.
3) novel structure, is skillfully constructed.
4) through evidence, bonnet percentage of damage 100%, and drop without fragment, reliability and uniformity are high.
Accompanying drawing explanation
Fig. 1 is the perspective view of retainer.
Fig. 2 is the retainer schematic diagram of side view directions inwardly.
Fig. 3 is the schematic diagram of the frangible bonnet medial surface of the launching tube of armament systems of the present invention view directions.Wherein, because composite material sealing structure has certain transparency, therefore can see captive plate and the connection handle that it is inner.Central recess 2b and peripheral grooves 2a on the medial surface of composite material sealing structure, have been offered.
Fig. 4 is the upward view of Fig. 3.
Fig. 5 is the partial schematic sectional view of Fig. 4.Wherein, central recess 2b and captive plate 3 reality are not on a section.
Fig. 6 is the schematic diagram of the flange ring part in Fig. 4.
Fig. 7 is that the frangible bonnet of the launching tube of armament systems is subject to guided missile kick and splits along central recess and peripheral grooves, and the schematic diagram outwards strutting.Captive plate with split after composite material sealing structure be all tethered on flange ring.
Fig. 8 is the partial schematic sectional view of the vertical plane of central recess length direction.
Fig. 9 is the schematic diagram of captive plate.
Figure 10 is the enlarged diagram in left part region in Fig. 5.
Wherein, 1. flange ring, 2. composite material sealing structure, 3. captive plate, 2a. peripheral grooves, 2b. central recess.
The specific embodiment
Below in conjunction with the specific embodiment, the present invention is further described.
Referring to Fig. 1-10, the frangible bonnet of a kind of launching tube of armament systems, comprises retainer, composite material sealing structure 2 together.
The structure of retainer as shown in Figure 1, 2, described retainer comprises flange ring 1 and captive plate, an openend at flange ring 1, somely be fan-shaped captive plate 3 and be connected to evenly and at intervals a week of flange ring 1, the fan-shaped drift angle of each captive plate 3 points to the center of flange ring 1, each fan-shaped circular arc intermediate radial is stretched out connection handle and is weldingly fixed on flange ring 1, and polymer compound layer 2 covers the surface of captive plate 3 inside and outside both sides in melting and solidification mode, forms the structure of approximate flange cap; At the medial surface of polymer compound layer 2, the strip triangle groove 2b that is center emitting shape is offered in the center, gap between adjacent two captive plate 3 limits; In the junction of captive plate 3 connection handles and flange ring 1, offer a circle groove, groove disconnects respectively at each connection handle place and forms some sections of circular arcs formation peripheral grooves 2a, and each peripheral grooves 2a is connected with T font with corresponding central recess 2b.
Referring to Fig. 1,5, described connection handle has aduncate radian.It is consistent that this aduncate radian and bonnet self have certain aduncate radian, and connection handle is better merged mutually with composite material sealing structure 2, is conducive to mooring.
Referring to Fig. 3,9, described connection handle and flange ring 1 are welded and fixed, and the welding position of connection handle is than all the other position wider width.The width of connection handle can not be too wide, because too wide meeting causes the deformation drag of outside ejection excessive, but the welding position of itself and flange ring 1 needs enough firmly, otherwise connection handle may depart from flange ring, drop, therefore firm welding degree had both been guaranteed than all the other position wider width in the welding position of connection handle, again with respect to the requirement that prevents that deformation drag is excessive.
Referring to Fig. 3,9, in described captive plate 3, offer at least one welding reinforced hole, the effect in fusion reinforcements hole is to make to keep after captive plate 3 and composite material sealing structure melting pressing the state that closely bonds, guarantees mooring.
Referring to Fig. 3,9, the main body section of described captive plate 2 is fan-shaped, and described peripheral grooves 2a is circular arc.Fan-shaped captive plate main body section is echoed mutually with annular emission cylinder, has optimized the concrete structure of captive plate, more easily breaks and mooring.
The quantity of described captive plate 3 is 6-8 piece, and the quantity setting of captive plate is more reasonable.
Described composite is formed by the glass fiber sheets melting pressing that is layering.Glass fibre good toughness, is tethered on flange ring with captive plate after being conducive to break.
As shown in Figure 7, when the frangible bonnet of armament systems launching tube is subject to after powerful impact, composite material sealing structure 2 is split along its central recess 2b and peripheral grooves 2a, outwards open, and connection handle is still firmly connected and fixed with flange ring 1, composite material sealing structure 2 is divided into some after splitting, and is still attached in captive plate.
The degree of depth of described peripheral grooves and central recess is 1-3mm, and width is 2-5mm.Test shows, groove, within the scope of this, splits after sufficient to guarantee composite material sealing structure stress, and meanwhile, the composite material sealing structure of splitting sticks in captive plate completely, does not have fragment and falls.
On described flange ring, be also provided with the external screw thread meshing with launching tube, on described flange ring, offer the installing technological hole of engagement in rotation, on described flange ring, also offer sealing ring mounting groove.When the frangible bonnet of this launching tube is installed, adopt spanner to insert in installing technological hole, rotating spanner, completes installation.
Claims (9)
1. the frangible bonnet of the launching tube of armament systems, is characterized in that:
Comprise retainer, composite material sealing structure (2);
Described retainer comprises flange ring (1), a plurality of captive plate of flange ring (1) inner annular arranged in arrays (3), and described captive plate (3) is fixedly connected with flange ring (1) by the connection handle being integrally connected with it;
Described composite material sealing structure (2) comprehensively welding covers on outer, the medial surface of captive plate (3):
The gap location of adjacent captive plate is offered the groove (2b) of strip, locates to offer the peripheral grooves (2a) intersecting vertically with described central recess (2b) between adjacent connection handle.
2. the frangible bonnet of armament systems launching tube as claimed in claim 1, is characterized in that: described connection handle has aduncate radian.
3. the frangible bonnet of armament systems launching tube as claimed in claim 2, is characterized in that: described connection handle and flange ring (1) are welded and fixed, and the welding position of connection handle is than all the other position wider width.
4. the frangible bonnet of armament systems launching tube as claimed in claim 1, is characterized in that: in described captive plate (3), offer at least one welding reinforced hole.
5. the frangible bonnet of armament systems launching tube as claimed in claim 1, is characterized in that: described captive plate (2) is fan-shaped, and described peripheral grooves (2a) is circular arc.
6. the frangible bonnet of armament systems launching tube as claimed in claim 5, is characterized in that: the quantity of described captive plate (3) is 6-8 piece.
7. the frangible bonnet of armament systems launching tube as claimed in claim 1, is characterized in that: described composite is formed by glass fiber sheets bonding stack melting pressing layer by layer.
8. the frangible bonnet of armament systems launching tube as claimed in claim 1, is characterized in that: the degree of depth of described peripheral grooves (2a) and central recess (2b) is 1-3mm, and width is 2-5mm.
9. the frangible bonnet of armament systems launching tube as claimed in claim 1, it is characterized in that: on described flange ring (1), be also provided with the external screw thread with launching tube engagement, on described flange ring (1), offer the installing technological hole of engagement in rotation, described flange ring is offered rubber seal mounting groove on (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310538927.6A CN103542773B (en) | 2013-11-04 | 2013-11-04 | Fragile rear cover of launching cylinder of weapon system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310538927.6A CN103542773B (en) | 2013-11-04 | 2013-11-04 | Fragile rear cover of launching cylinder of weapon system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103542773A true CN103542773A (en) | 2014-01-29 |
| CN103542773B CN103542773B (en) | 2015-04-01 |
Family
ID=49966471
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310538927.6A Active CN103542773B (en) | 2013-11-04 | 2013-11-04 | Fragile rear cover of launching cylinder of weapon system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103542773B (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103913098A (en) * | 2014-03-12 | 2014-07-09 | 南京航空航天大学 | Multi-petal composite material launching box cover and preparation method thereof |
| CN104913692A (en) * | 2015-06-30 | 2015-09-16 | 湖北三江航天万峰科技发展有限公司 | Fragile cap |
| TWI595909B (en) * | 2015-10-20 | 2017-08-21 | The 202Nd Arsenal Materiel Production Center | Bullet structure improved |
| CN109631669A (en) * | 2018-12-21 | 2019-04-16 | 上海燕兴科技实业有限公司 | A kind of firing box Fragile cap of guided missile simulation emission system |
| CN110697066A (en) * | 2019-10-10 | 2020-01-17 | 北京特种机械研究所 | Fragile cover with mooring, buffering and ablation-proof functions |
| CN112644111A (en) * | 2020-12-09 | 2021-04-13 | 南京航空航天大学 | Composite material plane fragile cover with mooring function and preparation method thereof |
| CN112985174A (en) * | 2021-02-10 | 2021-06-18 | 上海材料研究所 | Cylindrical orthogonal type sealing rear end cover with rectification effect on shock wave reflection |
| CN115493451A (en) * | 2022-09-26 | 2022-12-20 | 湖北三江航天万峰科技发展有限公司 | Fragile mooring cover of launching box |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0965814A2 (en) * | 1998-06-17 | 1999-12-22 | United Defense, L.P. | Multiple cell ammunition launching system |
| RU2218539C1 (en) * | 2002-03-11 | 2003-12-10 | Открытое акционерное общество "Конструкторское бюро специального машиностроения" | Destructible cover of launching tube |
| CN1844839A (en) * | 2006-04-30 | 2006-10-11 | 南京航空航天大学 | Integral impacting type composite canister cover |
| CN101650146A (en) * | 2008-08-12 | 2010-02-17 | 刘海斌 | Tube-shaped weapon sealing cover |
| CN203595451U (en) * | 2013-11-04 | 2014-05-14 | 上海燕兴科技实业有限公司 | Launch canister fragile rear cover of weapon system |
-
2013
- 2013-11-04 CN CN201310538927.6A patent/CN103542773B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0965814A2 (en) * | 1998-06-17 | 1999-12-22 | United Defense, L.P. | Multiple cell ammunition launching system |
| RU2218539C1 (en) * | 2002-03-11 | 2003-12-10 | Открытое акционерное общество "Конструкторское бюро специального машиностроения" | Destructible cover of launching tube |
| CN1844839A (en) * | 2006-04-30 | 2006-10-11 | 南京航空航天大学 | Integral impacting type composite canister cover |
| CN101650146A (en) * | 2008-08-12 | 2010-02-17 | 刘海斌 | Tube-shaped weapon sealing cover |
| CN203595451U (en) * | 2013-11-04 | 2014-05-14 | 上海燕兴科技实业有限公司 | Launch canister fragile rear cover of weapon system |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103913098A (en) * | 2014-03-12 | 2014-07-09 | 南京航空航天大学 | Multi-petal composite material launching box cover and preparation method thereof |
| CN104913692A (en) * | 2015-06-30 | 2015-09-16 | 湖北三江航天万峰科技发展有限公司 | Fragile cap |
| TWI595909B (en) * | 2015-10-20 | 2017-08-21 | The 202Nd Arsenal Materiel Production Center | Bullet structure improved |
| CN109631669A (en) * | 2018-12-21 | 2019-04-16 | 上海燕兴科技实业有限公司 | A kind of firing box Fragile cap of guided missile simulation emission system |
| CN110697066A (en) * | 2019-10-10 | 2020-01-17 | 北京特种机械研究所 | Fragile cover with mooring, buffering and ablation-proof functions |
| CN112644111A (en) * | 2020-12-09 | 2021-04-13 | 南京航空航天大学 | Composite material plane fragile cover with mooring function and preparation method thereof |
| CN112644111B (en) * | 2020-12-09 | 2021-10-15 | 南京航空航天大学 | Composite material plane fragile cover with mooring function and preparation method thereof |
| CN112985174A (en) * | 2021-02-10 | 2021-06-18 | 上海材料研究所 | Cylindrical orthogonal type sealing rear end cover with rectification effect on shock wave reflection |
| CN112985174B (en) * | 2021-02-10 | 2023-01-10 | 上海材料研究所 | Cylindrical orthogonal type sealing rear end cover with rectification effect on shock wave reflection |
| CN115493451A (en) * | 2022-09-26 | 2022-12-20 | 湖北三江航天万峰科技发展有限公司 | Fragile mooring cover of launching box |
| CN115493451B (en) * | 2022-09-26 | 2024-05-24 | 湖北三江航天万峰科技发展有限公司 | Fragile mooring cover of transmitting box |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103542773B (en) | 2015-04-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103542773B (en) | Fragile rear cover of launching cylinder of weapon system | |
| CN203595451U (en) | Launch canister fragile rear cover of weapon system | |
| JP2015501514A (en) | Battery explosion-proof device and battery pack provided with the device | |
| KR20130085907A (en) | Projectile with preformed fragment | |
| CN103662335B (en) | Including the improvement type tube head for the insert for forming barriers | |
| US20190120435A1 (en) | Pressure tank arrangement for storing and discharging compressed liquid fuels | |
| AU2014338927B2 (en) | Cartridge | |
| WO2008045125A3 (en) | Composite missile nose cone | |
| US10041440B2 (en) | Fuel injector insert | |
| CN201653274U (en) | Easy-breaking through cover of tube/box type projectile weapon | |
| CN105121292A (en) | Injectable cap | |
| CN103851287A (en) | Motor Vehicle Assembly Unit and Method for the Production of the Motor Vehicle Assembly Unit | |
| EP2878031B1 (en) | System for attaching a thermal battery to a power section of an underwater craft | |
| US9347752B2 (en) | Connecting element for a body made of composite material of a piercing projectile | |
| US9664162B2 (en) | Sealing structure | |
| CN104612180A (en) | Immersed tube section separating device for seabed immersed tunnel | |
| RU2016110442A (en) | SEALING BOLT AND SEALING SYSTEM | |
| CN218155785U (en) | Pneumatic fire extinguishing bomb | |
| CN202937804U (en) | Water chamber bucking and sealing detectable structure | |
| CN104973249A (en) | Effector With Ejectable Stealth Shell | |
| FR2953009A1 (en) | MILITARY HEAD WITH TANDEM LOADS | |
| EP2921810B1 (en) | Device for securing a shielding and shielded structure provided with such a device | |
| CN110530204B (en) | Directional separating piece and directional separating structure of integrally-broken type launching box sealing cover | |
| US20190025030A1 (en) | Warhead | |
| RU2461787C1 (en) | Damaged cover of launch tube |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C53 | Correction of patent of invention or patent application | ||
| CB02 | Change of applicant information |
Address after: 201722 Shanghai city Qingpu District Jinze Lianhu Road No. 53 Room 201, block B Applicant after: The upper petrel Industrial Co., Ltd. that makes the science and technology prosperous Address before: 201901 Shanghai Baoshan District Yang Road No. 189 building B Applicant before: The upper petrel Industrial Co., Ltd. that makes the science and technology prosperous |
|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |