CN103542769A - Manufacturing method of breakable launcher back cover of weapon system - Google Patents
Manufacturing method of breakable launcher back cover of weapon system Download PDFInfo
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- CN103542769A CN103542769A CN201310539615.7A CN201310539615A CN103542769A CN 103542769 A CN103542769 A CN 103542769A CN 201310539615 A CN201310539615 A CN 201310539615A CN 103542769 A CN103542769 A CN 103542769A
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Abstract
The invention relates to manufacturing methods of back covers, particularly to a manufacturing method of a breakable launcher back cover of a weapon system. The method comprises firstly, fabricating a flange ring and processing mounting external threads at one end of the flange ring; secondly, fabricating a holder in an approximate skullcap shape; thirdly, making prepreg glass fiber cloth into type A composite material sealing pieces and type B composite material sealing pieces, putting a plurality of the type B composite material sealing pieces inside the holder, then putting a plurality of the type B composite material sealing pieces outside the holder and further putting a plurality of the type A composite material sealing pieces outside the holder; placing the holder with the stacked composite material sealing pieces inside a mould, performing compression molding, heating and pressurizing to achieve solidification forming; lastly, performing demoulding and forming slots in the inner side of the composite material sealing layer. The launcher back cover is breakable, and the roots of broken pieces are tied to the flange ring and avoid drop-off, so that normal launching can be guaranteed, and meanwhile floor cleanliness and tidiness of a launch site can be maintained.
Description
Technical field
The present invention relates to a kind of manufacture method of launching tube bonnet, particularly the manufacture method of the frangible bonnet of a kind of armament systems launching tube.
Background technology
Launching tube is the device for depositing and launching a guided missile; stack shell forms an airtight container together with front/rear cover, 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.At present, the scheme of uncapping of launching a guided missile in launching tube mode mainly contains jettisoning lid and two kinds of technical schemes of frangible lid, and frangible lid technology is that application is at present more, this technology is to utilize combustion gas or combustion gas perturbation wave air-flow frangible lid to be blown to the fragment being broken within the scope of controlling dimension.So, forward and backward frangible lid not only will seal, existing certain mechanical strength, and must there is frangible characteristic, the in the situation that of brute force impact and ablation, this a kind of bonnet must be broken rapidly, and reliably opening the some parts for decile, 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, the general macromolecular material that adopts is made at present, and when guided missile is launched from launching tube, bonnet is broken, and broken bonnet fragment can be scattered on the ground at launching tube rear.Along with to the more and more stricter requirement of launching tube transmitter site, need to accomplish to allow launching tube bonnet broken, can allow again after the fragmentation of launching tube bonnet and in launch site, not leave any residual fragment, otherwise can affect the safe passing of follow-up operation apparatus, the carrying out smoothly of subsequent step.
Summary of the invention
The object of this invention is to provide the frangible bonnet of a kind of armament systems launching tube, this bonnet had both met frangible characteristic, can guarantee that again frangible bonnet fragment can not be scattered in launch site.
Object of the present invention is realized by following technical scheme:
A manufacture method for the frangible bonnet of armament systems launching tube, its step comprises:
The first step, flange ring is made:
By the flange ring 1 of one section of annular of machining mode processing, external screw thread 1a is installed in the outside processing of flange ring 1 one end;
Second step, retainer is made:
Circumference at the other end of flange ring 1, weld evenly and at intervals some mooring sheet 3a, described mooring sheet 3a is that metallic plate is scoop shape, the tip of mooring sheet 3a scoop is for the center of flange ring 1, the handle 3a3 of scoop is welded on flange ring 1 one weeks after being downward circular arc bending, forms the retainer 3 of approximate " skull cap " shape;
The 3rd step, stacks composite material sealing sheet;
Pre-preg glass fabric is made into A type and Type B composite material sealing sheet,
Described A type composite material sealing sheet 2a is the pre-preg glass fabric disk that diameter is greater than flange ring 1 external diameter; The pre-preg glass fabric disk that described Type B composite material sealing sheet 2b is different-diameter, on disk, offer some radial T font cylindrical void symmetrical centered by the center of circle, the vertical bar vent needle of this T font hole bar is to the center of circle, be positioned at the gap location of the scoop hypotenuse 3a1 of two adjacent mooring sheet 3a, the top rail cylindrical void of T font hole bar linearly or circular arc, radially be positioned at the outside of described mooring sheet 3a scoop back 3a2, circumferentially by the handle 3a3 of each mooring sheet 3a scoop, separated;
In the inner side of described retainer 3, place some Type B composite material sealing sheets, in the outside of retainer, place some Type B composite material sealing sheet 2b, then in outside, place again some A type composite material sealing sheet 2a;
The 4th step, compression molding;
The retainer 3 that has stacked composite material sealing sheet is placed in mould, adopts die press technology for forming, heating, cure under pressure moulding; The mould using is the fasten mould of type of die and punch.
The 5th step, the demoulding and finally processing;
After the demoulding, in the inner side of composite material sealing layer 2, the vestige of going up radial T brief note hole along Type B composite material sealing sheet 2b carries out machining, offers groove 4.
During described first step flange ring is made, by machining mode, in flange ring 1 outside, process some jack 1b for inserting wrenching bar.This structure can be inserted wrenching bar when bonnet is installed, and the larger mounting torque that screws is provided.Described in this, on flange ring 1, also offer rubber seal mounting groove.
The flange ring 1 that described first step flange ring is processed in making is highly 2-8cm, and diameter is 14-19cm.Applicable to conventional launching tube specification.
During described second step retainer is made, described mooring sheet 3a scoop shape is triangle or fan-shaped, the handle 3a3 of scoop with flange ring 1 weld than all the other position wider width, be circular-arc, at the periphery of flange ring 1, fix 3-8, on mooring sheet 3a, scattering and offer some circular holes, can be 4-10 circular holes.Certain mooring intensity is provided after can providing mooring sheet to scatter this structure, is unlikely to drop; On mooring sheet, offer some circular holes and can guarantee that mooring sheet can more closely merge in composite material sealing layer.
Described the 3rd step stacks in composite material sealing sheet, in the inner side of described retainer 3, place 5-13 sheet Type B composite material sealing sheet 2b, in the outside of retainer, place 5-10 sheet Type B composite material sealing sheet 2b, then in outside, place again 3-6 sheet A type composite material sealing sheet 2a.The method can guarantee that the bonnet appearance of finally making has smooth surface, and has certain mechanical strength, inner side to be convenient to the follow-up groove of offering.
The Kong Kuanwei 5-10mm in the vertical bar hole of the T font cylindrical void in described the 3rd step, the Kong Kuanwei 4-7mm of top rail cylindrical void.
The diameter of the pre-preg glass fabric disk in described the 3rd step is 15-30cm.
In described the 4th step, one section of pressure in die press technology for forming is 5-7MPa, and one section of temperature rises to 125-135 ℃ from normal temperature; Two sections of pressure are 6-9MPa, and two sections of temperature are 125-135 ℃, insulation 10-20min; Three sections of pressure are 14-17MPa, and three sections of temperature are 150-170 ℃, insulation 70-90min; Four sections of pressure are 14-17MPa, cooling 10-30min.
It is triangular in shape that in the final processing of described the 5th step, machining is offered the cross section of groove 4, and triangle height is 2-5mm, and base width is 2-5mm.
The above-mentioned scope that provides and limit indices is that model, specification and the specification requirement according to launching tube selected therein, can reach comparatively ideal effect.
The bonnet of being made by the present invention is not only used on armament systems launching tube, applicable equally on land, is subject to equally restriction of the present invention and protection.
Beneficial effect of the present invention,
1, it is under 2.5-3.0 atmospheric pressure that the frangible bonnet of armament systems launching tube that the present invention makes covers pressure in punching, bonnet is cracked, but shatter root is all tethered on flange ring, none drops in launch site, both guaranteed normal transmission, keep again ground, launch site clean and tidy, clean, guaranteed normally carrying out of subsequent transmission work.
2, the present invention selects to adopt the mechanical characteristic of the glass-cloth board that glass fabric processes good, chemical stability is high, heat-resisting quantity good, and has again certain toughness, and difficult pulverizing is dropped.The pre-preg glass fabric that the present invention has stacked some layers of different size in inner side and the outside of retainer, and adopt die press technology for forming, make smooth surface, high temperature resistant and have a bonnet of certain mechanical strength, in fiber cloth, offer in advance T font cylindrical void, and the vestige along T brief note hole carries out machining inside the bonnet of finished product, offer groove, make bonnet cover and under pressure, just can be rushed brokenly in very little rushing, do not split away off again.
3, the present invention adopts pre-preg glass fabric, in the surperficial pre-preg of glass fabric novolac epoxy resin, in compression molding process, novolac epoxy resin melting is also filled in the full T font cylindrical void of offering in advance, after solidifying, crosslink density is high, the heat resistance and the sealing property that have improved bonnet, processing technology of the present invention is good.
4, retainer of the present invention adopts at the some mooring sheets of the circle spacing of flange ring uniform welding, and described mooring sheet is the structure that metallic plate is scoop shape.Before transmitting, the retainer that mooring sheet forms, as covering on launching tube rear end as cap, can be formed with the closed container of certain mechanical strength.During transmitting, in the inner side of composite material sealing layer, offer radial T word groove and can under the pressure of transmitting, along groove, pulverize easily.Mooring sheet is welded on flange ring with the version of scoop handle, guarantee to pulverize rear mooring sheet and can be tethered on flange ring together with composite material sealing layer, and handle arrangement does not also affect and hinders the easy pulverizing requirement of composite material sealing layer.
Accompanying drawing explanation
Fig. 1 is the flow process chart of the manufacture method of a kind of armament systems launching tube of the present invention bonnet;
Fig. 2 is the flange ring front view that an embodiment of the present invention is produced;
Fig. 3 is that the master that retainer that an embodiment of the present invention is produced is fixed on flange ring looks cutaway view;
Fig. 4 is the top view of Fig. 3;
Fig. 5 is that the armament systems launching tube bonnet finished product master that an embodiment of the present invention is produced looks cutaway view;
Fig. 6 is the non-sectioned front view of Fig. 5;
Fig. 7 is the top view of Fig. 6, and composite material sealing layer inside broken section;
Fig. 8 is the Type B composite material sealing sheet that an embodiment of the present invention is produced;
Fig. 9 is the A type composite material sealing sheet that an embodiment of the present invention is produced;
Figure 10 is the armament systems launching tube bonnet that an embodiment of the present invention is produced, impact and to split along T word groove being subject to impulsive force, and the schematic diagram outwards strutting, captive plate with split after composite material sealing layer be all tethered on flange ring;
Figure 11 is the groove sectional view that composite material sealing layer inner side that an embodiment of the present invention is produced offered;
Figure 12 is that the captive plate that an embodiment of the present invention is produced is launched view;
Figure 13 is the partial enlarged drawing of Fig. 5;
Figure 14 is an embodiment of the present invention's the 4th step compression molding, the pressurization punch front view of making and using;
Figure 15 is the structure of fixed retainer on the flange ring produced of an embodiment of the present invention, wherein on retainer mooring sheet, not yet offers the schematic perspective view of circular hole.
In figure:
The 1st, flange ring, 1a is that external screw thread, 1b are jacks, the 2nd, composite material sealing layer, 2a is that A type composite material sealing sheet, 2b are Type B composite material sealing sheets, the 3rd, retainer, 3a is that mooring sheet, 3a1 are that hypotenuse, 3a2 are that back, 3a3 are handles, the 4th, groove.
The specific embodiment
Below in conjunction with the specific embodiment, the present invention is further described.
Together referring to Fig. 1-15, the manufacture method of the frangible bonnet of a kind of armament systems launching tube, its step comprises:
The first step, flange ring is made:
By the flange ring 1 of one section of annular of machining mode processing, the height of this flange ring is 2-8cm, and diameter is 14-19cm; External screw thread 1a is installed in the outside processing of flange ring 1 one end; The some jack 1b for inserting wrenching bar of outside processing of flange ring 1, are convenient to flange to be fastened on launching tube.Described in this, on flange ring 1, also offer rubber seal mounting groove.
Second step, retainer is made:
Circumference at the other end of flange ring 1, welds some mooring sheet 3a evenly and at intervals, and described mooring sheet 3a is that metallic plate is scoop shape, and preferred, this mooring sheet 3a scoop shape is triangle or fan-shaped.On mooring sheet 3a, offer 4-10 circular hole, be conducive to mooring sheet and under less punching press, just can be rushed broken.The tip of mooring sheet 3a scoop is for the center of flange ring 1, the handle 3a3 of scoop is welded on flange ring 1 one weeks after being downward circular arc bending, the handle 3a3 of scoop with flange ring 1 weld than all the other position wider width, be circular-arc, at the periphery of flange ring 1, fix 3-8, stop forming the retainer 3 of approximate " skull cap " shape;
The 3rd step, stacks composite material sealing sheet;
Pre-preg glass fabric is made into A type and Type B composite material sealing sheet,
Described A type composite material sealing sheet 2a is the pre-preg glass fabric disk that diameter is greater than flange ring 1 external diameter; Described Type B composite material sealing sheet 2b is that diameter is at the pre-preg glass fabric disk of 15-30mm, on disk, offer some radial T font cylindrical void symmetrical centered by the center of circle, the vertical bar vent needle of this T font hole bar is to the center of circle, be positioned at the gap location of the scoop hypotenuse 3a1 of two adjacent mooring sheet 3a, the Kong Kuanwei 5-10mm in this vertical bar hole; The top rail cylindrical void of T font hole bar linearly or circular arc, is radially positioned at the outside of described mooring sheet 3a scoop back 3a2, circumferentially by the handle 3a3 of each mooring sheet 3a scoop, is separated the Kong Kuanwei 4-7mm of this top rail cylindrical void;
The 4th step, compression molding;
The retainer 3 that has stacked composite material sealing sheet is placed in mould, adopts die press technology for forming, heating, cure under pressure moulding; One section of pressure in die press technology for forming is 6MPa, and one section of temperature rises to 130 ℃ from normal temperature; Two sections of pressure are 6MPa, and two sections of temperature are 125-135 ℃, insulation 10-20min; Three sections of pressure are 15MPa, and three sections of temperature are 160 ℃, insulation 70-90min; Four sections of pressure are 15MPa, cooling 10-30min.
The 5th step, the demoulding and finally processing;
After the demoulding, in the inner side of composite material sealing layer 2, the vestige of going up radial T brief note hole along Type B composite material sealing sheet 2b carries out machining, offers groove 4, and the cross section of this groove 4 is triangular in shape, and triangle height is 2-5mm, and base width is 2-5mm.
Test result: to cover pressure be under 2.5-3.0 atmospheric pressure to the frangible bonnet of armament systems launching tube that manufacture of the present invention obtains in punching, and bonnet percentage of damage is 100%, and shatter root is all tethered on flange ring, and none drops in launch site.
Claims (9)
1. a manufacture method for the frangible bonnet of armament systems launching tube, its step comprises:
The first step, flange ring is made:
By the flange ring (1) of one section of annular of machining mode processing, external screw thread (1a) is installed in the outside processing of flange ring (1) one end;
Second step, retainer is made:
Circumference at the other end of flange ring (1), weld evenly and at intervals some mooring sheets (3a), described mooring sheet (3a) is scoop shape for metallic plate, the tip of mooring sheet (3a) scoop is for the center of flange ring (1), the handle of scoop (3a3) is welded on flange ring (1) one week after being downward circular arc bending, forms the retainer (3) of approximate " skull cap " shape;
The 3rd step, stacks composite material sealing sheet;
Or, in mooring sheet (3a) inner side or outside, stack circular composite material sealing sheet;
Or, pre-preg glass fabric is made into A type and Type B composite material sealing sheet,
Described A type composite material sealing sheet (2a) is greater than the pre-preg glass fabric disk of flange ring (1) external diameter for diameter; The pre-preg glass fabric disk that described Type B composite material sealing sheet (2b) is different-diameter, on disk, offer some radial T font cylindrical void symmetrical centered by the center of circle, the vertical bar vent needle of this T font hole bar is to the center of circle, be positioned at the gap location of the scoop hypotenuse (3a1) of two adjacent mooring sheets (3a), the top rail cylindrical void of T font hole bar linearly or circular arc, radially be positioned at the outside of described mooring sheet (3a) scoop back (3a2), circumferentially by the handle (3a3) of each mooring sheet (3a) scoop, separated;
In the inner side of described retainer (3), place some Type B composite material sealing sheets, in the outside of retainer, place some Type B composite material sealing sheets (2b), then in outside, place again some A type composite material sealing sheets (2a);
The 4th step, compression molding;
The retainer (3) that has stacked composite material sealing sheet is placed in mould, adopts die press technology for forming, heating, cure under pressure moulding form composite material sealing layer (2);
The 5th step, the demoulding and finally processing;
After the demoulding, in the inner side of composite material sealing layer (2), the vestige of going up radial T brief note hole along Type B composite material sealing sheet (2b) carries out machining, offers groove (4).
2. the manufacture method of the frangible bonnet of armament systems launching tube according to claim 1, is characterized in that, during described first step flange ring is made, by machining mode, in flange ring (1) outside, processes some jacks (1b) for inserting wrenching bar.
3. the manufacture method of the frangible bonnet of armament systems launching tube according to claim 1, it is characterized in that described first step flange ring make in the flange ring (1) of processing be highly 3-8cm, diameter is 14-19cm.
4. the manufacture method of the frangible bonnet of armament systems launching tube according to claim 1, in it is characterized in that described second step retainer is made, described mooring sheet (3a) scoop shape is triangle or fan-shaped, the handle of scoop (3a3) with flange ring (1) weld than all the other position wider width, be circular-arc, periphery at flange ring (1) is fixed 3-8, upper distribution of mooring sheet (3a), offers several circular holes.
5. the manufacture method of the frangible bonnet of armament systems launching tube according to claim 1, it is characterized in that described the 3rd step stacks in composite material sealing sheet, 5-13 sheet Type B composite material sealing sheet (2b) is placed in inner side at described retainer (3), 5-10 sheet Type B composite material sealing sheet (2b) is placed in outside at retainer, then in outside, places 3-6 sheet A type composite material sealing sheet (2a) again.
6. the manufacture method of the frangible bonnet of armament systems launching tube according to claim 1, is characterized in that the Kong Kuanwei 5-10mm in the vertical bar hole of the T font cylindrical void in described the 3rd step, the Kong Kuanwei 4-7mm of top rail cylindrical void.
7. the manufacture method of armament systems launching tube bonnet according to claim 1, is characterized in that the diameter of the pre-preg glass fabric disk in described the 3rd step is 15-30cm.
8. the manufacture method of the frangible bonnet of armament systems launching tube according to claim 1, is characterized in that, in described the 4th step, one section of pressure in die press technology for forming is 5-7MPa, and one section of temperature rises to 125-135 ℃ from normal temperature; Two sections of pressure are 6-9MPa, and two sections of temperature are 125-135 ℃, insulation 10-20min; Three sections of pressure are 14-17MPa, and three sections of temperature are 150-170 ℃, insulation 70-90min; Four sections of pressure are 14-17MPa, cooling 10-30min.
9. the manufacture method of the frangible bonnet of armament systems launching tube according to claim 1, is characterized in that machining in the final processing of described the 5th step is offered the cross section of groove (4) triangular in shape, and triangle height is 2-5mm, and base width is 2-5mm.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310539615.7A CN103542769B (en) | 2013-11-04 | 2013-11-04 | A kind of manufacture method of breakable launcher back cover of weapon system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310539615.7A CN103542769B (en) | 2013-11-04 | 2013-11-04 | A kind of manufacture method of breakable launcher back cover of weapon system |
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| CN103542769A true CN103542769A (en) | 2014-01-29 |
| CN103542769B CN103542769B (en) | 2015-09-30 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105354774A (en) * | 2015-10-08 | 2016-02-24 | 常州信息职业技术学院 | Dormitory security management system based on RFID and ZigBee technology |
| 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 |
| CN110806151A (en) * | 2019-09-25 | 2020-02-18 | 北京玻钢院复合材料有限公司 | Fragile front cover of missile 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 |
| CN115014125A (en) * | 2022-06-17 | 2022-09-06 | 北京新风航天装备有限公司 | Breakable thin film cover made of carbon fiber composite material and broken according to preset path |
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| 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 | Barrel type weapon sealing cover |
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| 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 |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105354774A (en) * | 2015-10-08 | 2016-02-24 | 常州信息职业技术学院 | Dormitory security management system based on RFID and ZigBee technology |
| CN110806151A (en) * | 2019-09-25 | 2020-02-18 | 北京玻钢院复合材料有限公司 | Fragile front cover of missile and preparation method thereof |
| CN110806151B (en) * | 2019-09-25 | 2021-02-12 | 北京玻钢院复合材料有限公司 | Fragile front cover of missile and preparation method thereof |
| 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 |
| 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 |
| CN115014125A (en) * | 2022-06-17 | 2022-09-06 | 北京新风航天装备有限公司 | Breakable thin film cover made of carbon fiber composite material and broken according to preset path |
| CN115014125B (en) * | 2022-06-17 | 2023-07-04 | 北京新风航天装备有限公司 | Broken carbon fiber composite fragile film cover according to preset path |
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|---|---|
| CN103542769B (en) | 2015-09-30 |
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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 |
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