CN101970970A - Arrangement and method for supporting shell into breech-loading weapon barrell - Google Patents
Arrangement and method for supporting shell into breech-loading weapon barrell Download PDFInfo
- Publication number
- CN101970970A CN101970970A CN2009801036597A CN200980103659A CN101970970A CN 101970970 A CN101970970 A CN 101970970A CN 2009801036597 A CN2009801036597 A CN 2009801036597A CN 200980103659 A CN200980103659 A CN 200980103659A CN 101970970 A CN101970970 A CN 101970970A
- Authority
- CN
- China
- Prior art keywords
- support component
- shell
- propulsive charge
- charge element
- afterbody
- 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
- 238000000034 method Methods 0.000 title claims abstract description 9
- 230000001141 propulsive effect Effects 0.000 claims description 84
- 239000000446 fuel Substances 0.000 claims description 11
- 230000000694 effects Effects 0.000 claims description 4
- 230000000295 complement effect Effects 0.000 claims description 3
- 230000003014 reinforcing effect Effects 0.000 description 7
- 239000003721 gunpowder Substances 0.000 description 5
- 239000004570 mortar (masonry) Substances 0.000 description 5
- 239000000463 material Substances 0.000 description 3
- 238000004458 analytical method Methods 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 238000004513 sizing Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
- F41A9/00—Feeding or loading of ammunition; Magazines; Guiding means for the extracting of cartridges
- F41A9/54—Cartridge guides, stops or positioners, e.g. for cartridge extraction
- F41A9/58—Cartridge stops; Cartridge positioners
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F1/00—Launching apparatus for projecting projectiles or missiles from barrels, e.g. cannons; Harpoon guns
- F41F1/06—Mortars
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/052—Means for securing the rocket in the launching apparatus
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B30/00—Projectiles or missiles, not otherwise provided for, characterised by the ammunition class or type, e.g. by the launching apparatus or weapon used
- F42B30/08—Ordnance projectiles or missiles, e.g. shells
- F42B30/10—Mortar projectiles
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Toys (AREA)
- Elimination Of Static Electricity (AREA)
Abstract
The invention relates to an arrangement for supporting a shell (1) into a barrel (2) of a breech-loading weapon, the arrangement comprising a rim-flanged support element (6) attachable to a shell tail (4). The arrangement is characterized in that the arrangement comprises a propelling charge element (12) comprising a propelling charge (14) and a primer (13), the element having a threading (15a) suited for the shell tail allowing the support element (6) to be fastened to the shell tail by threading the propelling charge element (6) into the tail of the shell (1) through the support element (6). The invention further relates to a method of supporting a shell into a barrel of a breech-loading weapon.
Description
Technical field
The present invention relates to a kind of being used for shell is supported device in the launching tube enter breech load mode weapon, this device comprises that the support component that is used for the band edge flange is fastened to the device on the shell afterbody.
The invention still further relates to a kind of being used for support component is fastened to method on the shell, in the method, comprise that the support component of edge flange is secured on the shell afterbody.
Background technology
Mortar can be arranged on the movable base, for example is arranged on the armored vehicle, allows mortar to move to another place from a place easily, and on the other hand, allows it to move to safe place rapidly from the emplacement.If plan mortar is used for level or emission downwards, then problem is, shell can not be held in place in the no rifling launching tube of mortar, to such an extent as to but in launching tube forward slippage it no longer can be launched.United States Patent (USP) 5,503,080 discloses a kind of support component, and this support component can be attached on the control fin in the shell afterbody by means of friction.Yet, can not realize the enough reliably fastening of support component by the frictional connection that this publication is lectured.In addition, the size of support component and control fin always shows some deviation in the mill, and this deviation causes the variation of fastening force numerical value.
Summary of the invention
The objective of the invention is, provide a kind of by using support component to be used for shell is supported new device in the launching tube that enters breech load mode weapon and a kind of method of fastening such support component.
Device of the present invention is characterised in that, being used for the device of fastening support component comprises the propulsive charge element, this propulsive charge element comprises the propulsive charge and the fire in a stove before fuel is added, element has the screw thread that is suitable for the shell afterbody, rotate the propulsive charge element by passing support component for the shell afterbody, allow support component to be fastened on the shell afterbody.At this, the central opening that the propulsive charge element passes support component is screwed onto in the thread cavity in the shell afterbody, thereby the support component of edge flange is fastened against the shell afterbody.
Method of the present invention is characterised in that, the central opening that passes support component by rotation is set to the propulsive charge element in the shell afterbody, makes the posterior face of support component against at least one control fin.
A basic thought of the present invention is by means of novel propulsive charge element support component to be fastened on the shell afterbody.In the propulsive charge element, the gunpowder element, for example the fire in a stove before fuel is added is arranged in end sections, and propulsive charge, promptly so-called basic gunpowder is arranged in its vertical stem portion.The outer surface of vertical stem portion of propulsive charge element is provided with screw thread.The afterbody of shell partly is provided with corresponding cavity, and this corresponding cavity is used for admitting the propulsive charge element.The inner surface of the cavity of afterbody part is provided with screw thread, and the screw thread of the stem portion of these screw threads and gunpowder element is complementary.The propulsive charge element is passed in the central opening in the support component and is fastened on the shell afterbody, and support component is fastened against the shell afterbody whereby.As seen the end sections of propulsive charge element and the fire in a stove before fuel is added that is positioned at wherein keep on the posterior face of support component.In this case, do not need the middle trigger that sets up, because the striker of weapon can directly clash into the fire in a stove before fuel is added of propulsive charge.
In the present invention, support component adopts mechanical caging to be fastened on the shell afterbody, and this fastening ratio is more firm based on the locking of friction.Another advantage of the present invention is, even under hard situation, support component also can be attached on the shell afterbody easily and promptly by means of the propulsive charge element, because support component can be fastening with the propulsive charge element, and the locking piece that portion need set up.
The basic thought of one embodiment of the present of invention is, determine the size of the length of propulsive charge element by a kind of like this mode, thereby when the propulsive charge element is secured on the shell, leave a segment distance between shell afterbody and support component, this distance is as the fracture snap point under the effect of the power that is produced by the shell emission.
In the solution according to this embodiment, break-off portion is arranged on the stem portion of propulsive charge element, and this part be can't help cartridge container or support component and centered on.
The snap point of propulsive charge also can comprise the weakened part.The wall part that the weakened part can for example keep opening wide by processing is finished, thereby it becomes thinner.By this way, snap point can more accurately pre-determine.Yet, should be noted that by changing the wall material or the wall thickness of propulsive charge element, realizes fastening, this is fastening can tolerate by rotation propulsive charge element or shell and to support component carry out fastening, but when shell is launched, can fracture at the predetermined point place.This provides a kind of simple solution, and wherein, the structure of propulsive charge is by not only being used as it locking piece but also providing snap point to be utilized.
The basic thought of one embodiment of the present of invention is that the propulsive charge element has the screw thread that is applicable to support component and shell afterbody.This screw thread is on the outer surface of propulsive charge element, and on the inner surface in the shell afterbody.
The basic thought of one embodiment of the present of invention is that notch part is arranged on the central opening place in the support component, and the edge flange of propulsive charge element is placed in the notch part of support component.
The basic thought of one embodiment of the present of invention is, the edge flange of propulsive charge element has screw thread, and the notch part of support component has the screw thread that the screw thread with the edge flange of propulsive charge element is complementary.
Description of drawings
To the present invention be described in more detail in the accompanying drawings, in the accompanying drawings
Fig. 1 a schematically represents to be supported to shell in the launching tube of weapon by means of device according to the present invention,
The rearview of the device of Fig. 1 b presentation graphs 1a,
Fig. 2 analyses and observe an embodiment who schematically represents device of the present invention with part,
Fig. 3 a schematically represents an embodiment of the structure of propulsive charge element,
Fig. 3 b schematically represents an embodiment of the structure of propulsive charge element,
Fig. 4 a analyses and observe an embodiment who schematically represents device of the present invention with part,
The rearview of the embodiment of the device of Fig. 4 b presentation graphs 4a.
In the drawings, some embodiments of the present invention are for the sake of clarity represented by simplified way.In the drawings, similar portions is indicated with like reference numerals.
The specific embodiment
In Fig. 1 a, shell 1 is arranged in the launching tube 2 of breech load mode weapon.This weapon can be a mortar, and wherein the inner surface of launching tube 2 is smooth substantially.The end sections of shell 1 comprises tail pipe 3 and control fin.Afterbody 4 comprises one or typically a plurality of control fin, and these control fins are used for influencing the track of shell 1.The details of the structure of shell 1 can be different with the structure that illustrates in the drawings.For the sake of clarity, the lock bolt of weapon and its other details do not illustrate.Support component 6 according to the present invention is fastened on the afterbody 4, so that shell 1 is held in place in launching tube 2, is launched up to it.When launching tube 2 horizontal orientations or even launching tube 2 when directed downwards, the edge flange 7 in support component 6 prevents that shell 1 from moving forward in launching tube 2.In addition, the rear surface of weapon launching tube can be provided with groove or recess, and when the shell 1 that has support component 6 was loaded in the launching tube, the edge flange 7 that belongs to support component 6 can be placed in this groove or the recess.The size of support component is configured to tolerate the load that the quality by shell 1 causes, and can tolerate any power that is caused by vibration and acceleration.
Fig. 1 b represents the rearview of support component, and this support component is arranged in the launching tube according to the weapon of Fig. 1 a.End sections 11 and its fire in a stove before fuel is added 13 of propulsive charge element are visible at the opening of the central authorities that are arranged in support component 6.
The structure of device of the present invention is described with reference to Fig. 2 to 4b hereinafter.
Fig. 2 schematically represents one embodiment of the present of invention, and wherein, support component 6 is secured on the afterbody of shell 1 by means of propulsive charge element 12.
In addition, the central axial line of support component 6 is provided with cover tubular reinforcing section 65, and the inner periphery of this cover tubular reinforcing section 65 is provided with the screw thread that is used for receiving propulsive charge element 12.Propulsive charge element 12 passes on the tail pipe 3 that reinforcing section 65 is fastened to shell 1.Because propulsive charge element 12 is screwed onto in the tail pipe,, support component is fixed on the shell afterbody so also moving.When fastened, the surface 32 of shell afterbody 4 is against the surface 64 of support component and settle.In this position, the distance of reserving between the upper face 61 of the reinforcing section 65 of the posterior face 31 of cartridge container 3 and support component (representing with Reference numeral 120 in Fig. 3) is as snap point.
Distance between the upper face 61 of the reinforcing section 65 of the posterior face 31 of cartridge container 3 and support component can be preferably 0.1 to 10mm, more preferably 0.5 to 5mm, most preferably 1 to 3mm.
Fig. 3 a schematically represents the principle of the structure of propulsive charge element 12, and wherein, screw thread 15a is arranged on the outer surface of vertical stem portion 15 of propulsive charge element, and this screw thread is corresponding with the screw thread in the cavity of shell afterbody part.The fire in a stove before fuel is added 13 is in the end sections 11 of propulsive charge element.In this embodiment, the end sections of propulsive charge element 12 does not have screw thread.At this, edge flange propulsive charge element, for example by compression and is fastened on the support component by means of interference fit.Preferably, the propulsive charge element is arranged in the support component by a kind of mode, and this mode allows end sections to break away from from support component in shell emission back, and allows new propulsive charge arrangements of elements in described support component.
Fig. 3 b schematically represents the principle of the structure of propulsive charge element, and wherein, the outer surface of vertical stem portion 15 of propulsive charge element is provided with screw thread 15a, and this screw thread 15a is corresponding with screw thread in the cavity of shell afterbody part and in support component.Here, screw thread also extends in the whole end sections 11, but is clear that, comprises that the element according to the edge flange fire in a stove before fuel is added of Fig. 2 also can be secured on the end sections.
The length of propulsive charge element is set so that and leaves distance 120 that when the propulsive charge element is fastened on the shell this distance is as the snap point that ruptures between the support component of cartridge container under the effect of the power that is produced by the shell emission.Snap point is arranged on the stem portion of propulsive charge element, and this stem portion be can't help cartridge container or support component and centered on.In a single day the structure of propulsive charge element 12 is configured to tolerate the fastening force of requirement, but then, can fracture under the effect of predetermined force, thereby launch, just allow shell 1 to break away from from support component 6.The stem portion 15 of propulsive charge element 12 can be with sheet metal by cutting and crooked making.Selectively, it can be by injection-molded and by for example plastic material manufacturing, perhaps it can be a composite construction.
Fig. 4 a and 4b schematically represent an embodiment of device of the present invention.Here, propulsive charge element 12 is provided with threaded portion 65a and edge flange 17, and this threaded portion 65a is corresponding with the screw thread 15a of propulsive charge element, and this edge flange 17 has screw thread 65b.By this way, the end sections 11 of propulsive charge element is strengthened with the fastening of support component 6.If it is fastening by rotating shell enforcement, then the end sections of propulsive charge element 12 also is provided with two recesses 40, proper implements can be placed in these two recesses 40, this proper implements is used for the propulsive charge element is screwed in the shell afterbody, perhaps is used for propulsive charge element 12 is held in place.Be noted that at the recess shown in Fig. 4 b and also can be provided with shown in figure 2 in the device.
Fig. 2 and 4a illustrate, and the end sections 11 of propulsive charge element 12 extends to the upper face 61 of the reinforcing section 65 of support component at least from the end surface 62 of support component 6.At this, the emission of shell does not cause the distortion of the reinforcing section 65 of support component 6, allows support component 6 to be reused after the end sections 11 of propulsive charge element breaks away from.
When shell 1 was launched, gunpowder destroyed the wall of stem portion, and this stem portion keeps opening wide, and the material that does not belong to support component 6 substantially therewith leaves (track that this can damage the launching tube of weapon or influence shell).
It will be apparent to those skilled in the art that along with technological progress basic thought of the present invention can be implemented by variety of way.Therefore, the present invention and embodiment are not limited to above example, but can change in the scope of claims.
Claims (9)
1. one kind is used for shell (1) is supported device in the launching tube (2) enter breech load mode weapon, described device comprises the support component (6) that will be secured to the band edge flange on the shell afterbody (4), it is characterized in that, described device comprises propulsive charge element (12), this propulsive charge element (12) comprises the propulsive charge (14) and the fire in a stove before fuel is added (13), described element has the screw thread (15a) that is suitable for described shell afterbody, thereby relative to each other rotate by passing described propulsive charge element (12) and the described shell (1) that described support component (6) is provided with, axial location between them changes, thereby described support component (6) can move to the described afterbody of described shell (1).
2. device according to claim 1 is characterized in that, described propulsive charge element (12) comprises the screw thread (15a) of the afterbody that is suitable for described support component (6) and described shell (1).
3. device according to claim 1 is characterized in that, described propulsive charge element (12) is secured on the central opening of described support component (6) by interference fit.
4. each the described device in requiring according to aforesaid right is characterized in that, described screw thread (15a) is arranged on the outer surface of described propulsive charge element (12) and on the inner surface of the tail pipe (3) of described shell (1).
5. each the described device in requiring according to aforesaid right is characterized in that described propulsive charge element (12) is provided with the edge flange of settling against described support component (6) (17).
6. device according to claim 5 is characterized in that, the excircle of the described edge flange (17) of described propulsive charge element is provided with screw thread, and described support component (6) comprises the threaded portion (65b) that is complementary.
7. each the described device in requiring according to aforesaid right, it is characterized in that, the length of described propulsive charge element is set so that when described propulsive charge element is secured on the described shell, between described cartridge container (3) and described support component (6), reserve a segment distance (120), the break-off portion that ruptures under the effect of described distance as the power that produces in emission by described shell.
8. device according to claim 7 is characterized in that, the break-off portion of the stem portion (15) of described propulsive charge (12) comprises the weakened part.
9. one kind is used for shell is supported method in the launching tube (2) enter breech load mode weapon, in the method, the support component (6) that is provided with edge flange (7) is secured on the afterbody (4) of described shell (1), it is characterized in that, screw in the afterbody of described shell by passing the propulsive charge element that described support component (6) is provided with, and described support component (6) is fastened on the afterbody of described shell (1).
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FI20085083A FI20085083L (en) | 2008-01-31 | 2008-01-31 | Arrangement and method of supporting a shell in a barrel of a breech-loading weapon |
| FI20085083 | 2008-01-31 | ||
| PCT/FI2009/050072 WO2009095535A1 (en) | 2008-01-31 | 2009-01-30 | Arrangement and method for supporting shell into breech-loading weapon barrell |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101970970A true CN101970970A (en) | 2011-02-09 |
| CN101970970B CN101970970B (en) | 2014-05-14 |
Family
ID=39004383
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200980103659.7A Expired - Fee Related CN101970970B (en) | 2008-01-31 | 2009-01-30 | Arrangement and method for supporting shell into breech-loading weapon barrell |
Country Status (11)
| Country | Link |
|---|---|
| US (1) | US20100294159A1 (en) |
| EP (1) | EP2242980A4 (en) |
| JP (1) | JP5405493B2 (en) |
| CN (1) | CN101970970B (en) |
| AU (1) | AU2009208915B2 (en) |
| CA (1) | CA2712105A1 (en) |
| FI (1) | FI20085083L (en) |
| IL (1) | IL206870A (en) |
| RU (1) | RU2483268C2 (en) |
| WO (1) | WO2009095535A1 (en) |
| ZA (1) | ZA201004947B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112985165A (en) * | 2021-03-30 | 2021-06-18 | 北京新风航天装备有限公司 | Portable modularized emergency cartridge loading device |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104034208B (en) * | 2014-05-21 | 2016-01-13 | 北京航天发射技术研究所 | A kind of method for designing preventing the launching tube of missile loading rolling |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SE83405C1 (en) * | ||||
| GB1037743A (en) * | 1962-05-09 | 1966-08-03 | Dynamit Nobel Ag | Improvements in or relating to cartridges for firing projectiles and the like |
| US4762068A (en) * | 1985-03-05 | 1988-08-09 | Nico-Pyrotechnik Hanns-Jurgen Diederichs Gmbh & Co Kg | Cartridge-type ammunition |
| US4803927A (en) * | 1986-02-03 | 1989-02-14 | Aerojet-General Corporation | Ammunition round and method of manufacture thereof |
| US4938146A (en) * | 1988-09-22 | 1990-07-03 | Rheinmetall Gmbh | Grenade-type projectile |
| WO1998033018A1 (en) * | 1997-01-24 | 1998-07-30 | Patria Vammas Oy | Arrangement for supporting mortar shell into barrel |
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| US3182595A (en) * | 1962-07-20 | 1965-05-11 | Harry F Hassmann | Igniter assembly containing strands of benite |
| DE2648137C2 (en) * | 1976-10-23 | 1984-04-12 | Dynamit Nobel Ag, 5210 Troisdorf | Propellant charge lighter for ammunition |
| DE3009342A1 (en) * | 1980-03-12 | 1986-06-26 | Rheinmetall GmbH, 4000 Düsseldorf | CARTRIDGED AMMUNITION WITH AT LEAST PARTLY COMBUSTIBLE DRIVE CHARGE |
| SE9200562L (en) * | 1992-02-26 | 1993-08-27 | Karl Axel Roheim | Garnet |
| FR2697327B1 (en) * | 1992-10-22 | 1994-12-30 | Luchaire Defense Sa | Box for propellant charge. |
| GB9322392D0 (en) * | 1993-10-29 | 1993-12-22 | Royal Ordnance Plc | Bomb retaining device |
| DE19527621A1 (en) * | 1995-07-28 | 1997-01-30 | Nico Pyrotechnik | Cartridge ammunition |
| FI112700B (en) * | 2002-06-27 | 2003-12-31 | Patria Vammas Oy | Arrangement to support a crane in a weapon's fire pipe |
| SE532244C2 (en) * | 2007-11-30 | 2009-11-24 | Bae Systems Bofors Ab | Motor-driven automatic grenade launcher and grenade for such a cannon |
| FI121554B (en) * | 2008-01-31 | 2010-12-31 | Patria Weapon Systems Oy | Arrangement for supporting a grenade in the barrel of a rear loading weapon and a method for attaching a support to the grenade |
| FI120709B (en) * | 2008-01-31 | 2010-01-29 | Patria Weapon Systems Oy | Support means for supporting a grenade and procedure |
| FI120708B (en) * | 2008-01-31 | 2010-01-29 | Patria Weapon Systems Oy | Arrangement to support the projectile into the barrel of the weapon, support element and method |
| FI121686B (en) * | 2008-01-31 | 2011-02-28 | Patria Weapon Systems Oy | Arrangement to support a grenade in a pipe of a rear-loaded weapon |
| FI120894B (en) * | 2008-01-31 | 2010-04-15 | Patria Weapon Systems Oy | Arrangement for supporting a grenade in the barrel of the weapon and a support member |
| FI121976B (en) * | 2008-01-31 | 2011-06-30 | Patria Weapon Systems Oy | Arrangement to support a grenade in the rear loading weapon barrel |
-
2008
- 2008-01-31 FI FI20085083A patent/FI20085083L/en unknown
-
2009
- 2009-01-30 AU AU2009208915A patent/AU2009208915B2/en not_active Ceased
- 2009-01-30 CA CA2712105A patent/CA2712105A1/en not_active Abandoned
- 2009-01-30 RU RU2010135803/11A patent/RU2483268C2/en not_active IP Right Cessation
- 2009-01-30 CN CN200980103659.7A patent/CN101970970B/en not_active Expired - Fee Related
- 2009-01-30 US US12/863,603 patent/US20100294159A1/en not_active Abandoned
- 2009-01-30 JP JP2010544745A patent/JP5405493B2/en not_active Expired - Fee Related
- 2009-01-30 EP EP09705215.3A patent/EP2242980A4/en not_active Withdrawn
- 2009-01-30 WO PCT/FI2009/050072 patent/WO2009095535A1/en active Application Filing
-
2010
- 2010-07-07 IL IL206870A patent/IL206870A/en not_active IP Right Cessation
- 2010-07-13 ZA ZA2010/04947A patent/ZA201004947B/en unknown
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SE83405C1 (en) * | ||||
| GB1037743A (en) * | 1962-05-09 | 1966-08-03 | Dynamit Nobel Ag | Improvements in or relating to cartridges for firing projectiles and the like |
| US4762068A (en) * | 1985-03-05 | 1988-08-09 | Nico-Pyrotechnik Hanns-Jurgen Diederichs Gmbh & Co Kg | Cartridge-type ammunition |
| US4803927A (en) * | 1986-02-03 | 1989-02-14 | Aerojet-General Corporation | Ammunition round and method of manufacture thereof |
| US4938146A (en) * | 1988-09-22 | 1990-07-03 | Rheinmetall Gmbh | Grenade-type projectile |
| WO1998033018A1 (en) * | 1997-01-24 | 1998-07-30 | Patria Vammas Oy | Arrangement for supporting mortar shell into barrel |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112985165A (en) * | 2021-03-30 | 2021-06-18 | 北京新风航天装备有限公司 | Portable modularized emergency cartridge loading device |
| CN112985165B (en) * | 2021-03-30 | 2022-06-24 | 北京新风航天装备有限公司 | Portable modularized emergency cartridge loading device |
Also Published As
| Publication number | Publication date |
|---|---|
| EP2242980A4 (en) | 2013-09-04 |
| JP5405493B2 (en) | 2014-02-05 |
| FI20085083L (en) | 2009-08-01 |
| RU2010135803A (en) | 2012-03-10 |
| RU2483268C2 (en) | 2013-05-27 |
| WO2009095535A1 (en) | 2009-08-06 |
| AU2009208915A1 (en) | 2009-08-06 |
| IL206870A (en) | 2014-07-31 |
| CA2712105A1 (en) | 2009-08-06 |
| ZA201004947B (en) | 2011-03-30 |
| AU2009208915B2 (en) | 2013-08-22 |
| JP2011511247A (en) | 2011-04-07 |
| FI20085083A0 (en) | 2008-01-31 |
| IL206870A0 (en) | 2010-12-30 |
| CN101970970B (en) | 2014-05-14 |
| EP2242980A1 (en) | 2010-10-27 |
| US20100294159A1 (en) | 2010-11-25 |
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