CN101970973A - Support member for supporting shell into breech-loading weapon barrel, and method - Google Patents
Support member for supporting shell into breech-loading weapon barrel, and method Download PDFInfo
- Publication number
- CN101970973A CN101970973A CN2009801036578A CN200980103657A CN101970973A CN 101970973 A CN101970973 A CN 101970973A CN 2009801036578 A CN2009801036578 A CN 2009801036578A CN 200980103657 A CN200980103657 A CN 200980103657A CN 101970973 A CN101970973 A CN 101970973A
- Authority
- CN
- China
- Prior art keywords
- afterbody
- support unit
- flying pig
- pig
- flying
- 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.)
- Pending
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Classifications
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- 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
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- 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
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- 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
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- 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
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Toys (AREA)
- Lining And Supports For Tunnels (AREA)
- On-Site Construction Work That Accompanies The Preparation And Application Of Concrete (AREA)
- Tents Or Canopies (AREA)
Abstract
The invention relates to a support member (6) for supporting a mortar shell (1) into a breech-loading weapon barrel. The support member (6) comprises a support element (8) with an edge flange (7) and a firing mechanism for firing the actual primer of the mortar shell (1) and further comprising connecting means (10) for attaching the support element (8) to a tail (4) of the mortar shell (1). The connecting means (10) for attaching the support element (8) to the tail (4) of the mortar shell (1) comprise at least one flexible part (13, 20, 30) arranged to be attached to the tail (4) of the mortar shell (1) by means of spring force.
Description
Technical field
The present invention relates to support unit according to the preamble of claim 1, particularly relate to a kind of support unit that is used for flying pig is bearing in the gun barrel of breech loading formula weapon, this support unit comprises supporting member, this supporting member has rim lip and being used for to pull the trigger the firing lock (ignition mechanism) of the true fire in a stove before fuel is added of mortar projectile, and support unit also comprises and is used for support component is installed in jockey on the flying pig afterbody.The invention still further relates to the method according to the preamble of claim 10, be used for support unit is installed in mortar projectile, this method comprises: arrange support unit in the afterbody of flying pig, this support unit comprises supporting member; And support unit is installed on the afterbody of flying pig.
Background technology
Mortar can be arranged in movably on the pedestal, panzer for example, thus make mortar to move to another place from a place easily, on the other hand, make mortar promptly to move to safety place from the emplacement.When planning to open fire with artillery vertically or downwards with mortar, problem is that mortar projectile does not rest in the appropriate location in the smoothbore tube of mortar, but may be to front slide in gun barrel, so that it no longer can be opened fire with artillery.United States Patent (USP) 5503080 discloses a kind of support unit, and this support unit can be installed on the guiding wing in the mortar projectile afterbody by friction.The problem of the scheme of the disclosure teach literature is that the afterbody and the support unit self of projectile all needs split hair size, so that it is worked with gratifying at least reliable fashion.
Summary of the invention
The purpose of this invention is to provide a kind of support unit and a kind of being used for is installed in method on the flying pig with support unit.Purpose of the present invention realizes by the support unit according to the characteristic of claim 1, it is characterised in that: be used for the jockey that supporting member is installed on the afterbody of flying pig is comprised at least one compliant member, this compliant member is arranged through spring force and is installed on the afterbody of flying pig.Purpose of the present invention also realizes by the method according to claim 10, it is characterised in that: support unit is installed on the afterbody of flying pig by one or more compliant members, and/or be installed on one or more guide tabs of a part that forms the flying pig afterbody, and/or be installed on the corresponding component that is arranged in the flying pig afterbody, when receiving the afterbody of flying pig with box lunch, compliant member acts on spring force on the periphery of flying pig afterbody and/or forms on one or more guide tabs of a part of Minnie shell afterbody and/or be arranged on the corresponding component in the flying pig afterbody.
The preferred embodiments of the present invention are disclosed in the dependent claims.
The present invention is based on flying pig and be installed on the support unit by jockey, this jockey makes spring force act on the afterbody of flying pig.In other words, jockey comprises compliant member, and the afterbody of flying pig is installed on the support unit by this compliant member.According to the present invention, compliant member can receive the afterbody of flying pig like this, it makes spring force act on the periphery of afterbody of flying pig, perhaps act on one or more guide tabs of a part that forms the flying pig afterbody, perhaps act on the periphery of flying pig afterbody and on one or more guide tabs.Also can select, the afterbody of flying pig can provide corresponding component, and compliant member is installed on this corresponding component by spring force.
In the present invention, support unit is installed on the afterbody of flying pig based on spring force, and therefore, this is installed than more reliable based on the breech of friction.And, can not resemble big or small and being held in place in support unit that crucially influences installing force in the friction breech scheme owing to the manufacturing of flying pig change in size that cause, possible.In according to the solution of the present invention, relatively easily control installing force.And, even advantage of the present invention be support unit also can be easily under different situations and be installed in apace on the afterbody of flying pig.
According to embodiments of the invention, support unit provides ring spring, and this ring spring is arranged to receive the afterbody of flying pig.When receiving the afterbody of flying pig, the ring spring surrender makes spring force act on the afterbody of flying pig simultaneously.Ring spring can be arranged to like this, makes spring force act on the periphery of afterbody of flying pig.Also can select, ring spring can comprise one or more slits, be used to receive the guide tabs of a part that forms the flying pig afterbody, like this, the guide tabs in the slit of will packing into makes the ring spring surrender, therefore, slit makes spring force act on the guide tabs, so that flying pig is installed on the support unit.
In another embodiment of the present invention, support unit provides the lamination ring, and this lamination is periphery and is set to the afterbody that receives flying pig.Lamination is periphery and is set to like this, and it makes spring force act on the periphery of flying pig afterbody.In other words, the afterbody of flying pig is arranged to pack in the space that is produced by the lamination ring, like this, and the local yielding at least when receiving the flying pig afterbody of lamination ring, and make spring force act on the afterbody of flying pig.Also can select, lamination is periphery and is set to the one or more guide tabs that receive a part that forms the flying pig afterbody, like this, the local yielding at least when receiving one or more guide tabs of lamination ring, and make spring force act on the guide tabs of reception.
In an also embodiment of the present invention, support unit provides flexible attachment components, and this flexible attachment components is arranged to receive the corresponding component that is arranged in the flying pig afterbody.Flexible attachment components for example can be flexible boot tubular attaching parts, it be arranged to when receiving corresponding component along with its direction surrender of axis normal, and make spring force act on the corresponding component, so that flying pig is installed on the support unit.
Description of drawings
Come in conjunction with the preferred embodiments below with reference to the accompanying drawings to introduce the present invention in more detail, in the accompanying drawing:
Fig. 1 has schematically illustrated the flying pig in the gun barrel that support unit by the embodiment of the invention is bearing in weapon;
Fig. 2 has schematically illustrated one embodiment of the present of invention, is used for by ring spring support unit being installed in flying pig;
Fig. 3 has schematically illustrated the second embodiment of the present invention, is used for by ring spring support unit being installed in flying pig;
Fig. 4 has schematically illustrated the cutaway view of one embodiment of the present of invention, is used for by the lamination ring support unit being installed in flying pig;
Fig. 5 has schematically illustrated the lamination ring of Fig. 4;
Fig. 6 has schematically illustrated one embodiment of the present of invention, is used for being arranged in the corresponding component of flying pig support unit being installed in flying pig by compliant member; And
Fig. 7 has represented embodiment when support unit is installed on the flying pig by compliant member, Fig. 6.
The specific embodiment
Fig. 1 has schematically illustrated the flying pig 1 in the gun barrel 2 that support unit 6 by the embodiment of the invention is bearing in weapon.
Flying pig 1 is arranged in the gun barrel 2 of breech loading formula weapon.Weapon can be a mortar, and in this mortar, the inner surface of gun barrel 2 is level and smooth substantially.The rear portion of flying pig 1 comprises afterbody pipe 3 and afterbody 4.Afterbody 4 comprises one or be generally a plurality of guide tabs 5, is used to influence the trajectory of flying pig 1.The detailed structure of flying pig 1 can be different from the structure shown in the figure.For clear, the breech of weapon and other details are not shown.
Support unit 6 of the present invention is installed on the afterbody 4, is used for mortar projectile 1 remained in the appropriate location of gun barrel 2 being launched up to it.Shell 12 in the supporting member 8 of a part that forms support unit 6 is sized to make at least a portion of afterbody 4 of flying pig 1 can be arranged in its inside.When gun barrel 2 horizontal sights or even during gun barrel 2 directed downwards, the rim lip 7 in the support unit 6 can prevent that mortar projectile 1 from moving forward in gun barrel 2.Support unit 6 is sized to bear the load that the quality by mortar projectile 1 causes, and any power that can bear by vibration and quicken to cause.Supporting member 8 also comprises jockey 10, and flying pig 1 is installed on the support unit 6 by this jockey.
Jockey 10 can be for example be installed on the supporting member 8 by nipple or other mechanical splice (this mechanical splice preferably selectively open and close).Also can select, jockey 10 can be installed on the supporting member 8 with fixed form.
Fig. 2 has schematically illustrated embodiments of the invention, and wherein, the jockey 10 that is arranged in the supporting member 8 comprises ring spring 13, and this ring spring forms the afterbody 4 that can receive flying pig.According to Fig. 2, ring spring 13 form it can receive especially afterbody 4 afterbody pipe 3, away from the end of flying pig 1.Like this, ring spring 13 forms opening, and the end of afterbody pipe 3 can be arranged in this opening.The aperture arrangement of ring spring 13 becomes like this, when afterbody pipe 3 was arranged in this opening, ring spring 13 was surrendered and is subjected to stress, thereby spring force is acted on the periphery or outer surface 14 of afterbody pipe 3, be the flying pig afterbody, spring force is attached on the support unit 6 flying pig 1.In other words, ring spring 13 is as the flexible member on the afterbody 4 that spring force is acted on flying pig 1, so that flying pig 1 is installed on the support unit 6.
In the optional embodiment of ring spring 13, as shown in Figure 3, slit can be arranged such that their surrenders when receiving guide tabs 5, thereby they are subjected to stress, and spring force is acted on the guide tabs 5.In other words, when receiving guide tabs 5, slit is opened, thus with spring force act on guide tabs 5, along on the surface of the longitudinal axis direction of flying pig 1.Still in this case, spring members 18 can form like this, and the afterbody 4 of flying pig can be easy to be arranged in the ring spring 13, but because the spring force that produces, taking out flying pig 1 from ring spring 13 needs much bigger power.Therefore, the slit of ring spring 13 relatively easily receives guide tabs 5, and simultaneously, ring spring 13 acts on spring force on the guide tabs 5, and therefore, taking out flying pig 1 from ring spring 13 needs much bigger power.
In going back an embodiment, ring spring 13 can be provided as the combination of previous embodiment, in this case, afterbody pipe 3 is arranged in the spring force on the outer surface 14 that in the opening of ring spring 13 generation is acted on afterbody 4, simultaneously, guide tabs 5 is arranged in the slit 16 spring force that generation is acted on the guide tabs 5.As mentioned above, should be known in that ring spring 13 can be the ring of any type, it can produce the spring force on the afterbody 4 that acts on flying pig 1 when at least a portion of the afterbody 4 that receives flying pig 1.
Fig. 4 has represented another embodiment of the present invention, and wherein, jockey comprises one or more lamination rings 20.In the embodiment of Fig. 4, the jockey of support unit 8 comprises installing sleeve 21 and the flexibility 23 that is connected with it.Installing sleeve 21 can for example be installed on the support unit 8 by screw thread or with fixed form or with other mechanical system.In Fig. 4, two lamination rings 20 can be arranged in flexibility 23 volume inside.One or more support plates or substrate (not shown) can be arranged between the lamination ring or in the front side and/or rear side.The diameter in the hole of flexibility 23 is to make flexibility 23 can receive the afterbody pipe 3 of flying pig 1 or the head piece 25 of afterbody pipe.An embodiment who has represented lamination ring 20 among Fig. 5.At least be slightly less than the external diameter of afterbody pipe 3 of flying pig 1 or the external diameter of head piece 25 at the diameter of the opening 24 of the lamination ring 20 of flexibility 23 inside.Therefore, in flying pig 1 pushes support unit 8 and when being in correct position, lamination ring 20 and 22 surrenders of (particularly) its thin slice, and spring force is acted on the afterbody pipe 3 of flying pig 1 or on the head piece 25, this spring force makes flying pig 1 be installed on the support unit 8.The diameter of the opening of support plate and substrate equals the external diameter of afterbody pipe 3 of flying pig 1 or the external diameter of head piece 25 substantially, thus they not with any drag effect on flying pig.
As mentioned above, according to desirable spring force the size or according to being used to install the required power of flying pig, jockey 10 preferably includes one or more lamination rings 20.According to Fig. 5, lamination ring 20 be divided into adjacent thin slice 22 interior week, this thin slice 22 can be surrendered.The number of thin slice 22 and (therefore) can change as required along the length of the radial direction of peripheral direction and edge periphery, thereby can produce suitable spring force.Lamination ring 20 can be made by steel plate by cutting or with other corresponding manner, is perhaps made by other respective material.
Fig. 6 has schematically illustrated embodiments of the invention, and wherein, the jockey 10 of supporting member 8 comprises compliant member 30.And corresponding component 32 is arranged in the end place of afterbody pipe 3 of the afterbody 4 of flying pig 1.Compliant member 30 is arranged to receive this corresponding component 32, like this, compliant member 30 surrenders, thus spring force is acted on the corresponding component of reception, be used for flying pig 1 is installed in support unit 6.In the example of Fig. 6, compliant member is cover tubular attaching parts 30, makes it along the direction surrender vertical with its longitudinal axis when receiving corresponding component 32.Corresponding component 32 is arranged in afterbody 4 places of flying pig, particularly locates (according to Fig. 6) in the end of afterbody pipe 3.In this embodiment, attaching parts 30 comprise a plurality of flexible claw-like parts, and these claw-like arrangements of components are on circular arc, so that cover tubular attaching parts are provided.
In the embodiment of Fig. 7, cover tubular attaching parts 30 receive the inside of corresponding component 32 to it.Corresponding component 32 comprises the tapered opening of leaving flying pig afterbody 4.This taper helps flying pig 1 is correctly placed support unit 6.And when corresponding component 32 placed attaching parts 30 inside, the cone of corresponding component 32 was pressed against on the inwall of cover tubular attaching parts 30.When pushing and surrender, attaching parts 30 will be subjected to stress, spring force be acted on the outer surface of the corresponding component 32 that is arranged in its inside simultaneously, so that flying pig is installed on this support unit 6.For this reason, corresponding component 32 is sized to make its external diameter less times greater than the internal diameter of attaching parts 30, thereby will force this attaching parts 30 surrenders in corresponding component 32 places attaching parts 30 time.In a preferred embodiment, corresponding component 32 is pushed the inside of attaching parts 30, up to the upper surface of attaching parts 30 cone by corresponding component 32.Like this, corresponding component 32 is arranged in the inside of cover tubular attaching parts 30 securely, and can deviate from.The conical in shape of corresponding component 32 makes that also this corresponding component blocks in attaching parts 30 in place, and as shown in Figure 7, therefore, flying pig is not easy to separate with support unit 8.
Corresponding component 32 can be arranged in the end of afterbody pipe 3 of the afterbody 4 of flying pig, and in this case, it is the extension of afterbody pipe 3 or the part of afterbody pipe 3.In optional embodiment, corresponding component 32 can only be the end of afterbody pipe 3 simply, makes it hollow, thereby forms corresponding component 32.
By being installed in the one or more spring element (not shown) in the attaching parts, can further increasing by attaching parts 30 and act on spring force on the corresponding component 32.Spring element can be each spring that is arranged on the outer surface of attaching parts 30, perhaps also can select, and spring can be arranged around the periphery of attaching parts 30.Also can select, corresponding component 32 can form and make it arrange that around attaching parts 30 therefore, the spring force of flexible attachment components 30 acts on the inner surface of corresponding component 32.Corresponding component 32 can be the head part 25 of the afterbody 4 of flying pig 1.
As mentioned above, should be known in the ring spring of a part that receives flying pig afterbody or this afterbody in inside and can form in many ways and change around the flexible attachment components that its receives the corresponding component that is arranged in afterbody.In other words, essence of the present invention is that flying pig can be installed on the support unit by spring force.Spring force produces by the compliant member that is arranged in the supporting member and surrender when flying pig is installed on the support unit.And, should be known in that in some cases flying pig can be installed on the support unit 8 by above-mentioned two or more embodiment.
Obviously, it will be appreciated by those skilled in the art that basic thought of the present invention can be implemented in many ways along with technological progress.Therefore, the present invention is not limited to above-mentioned example, but can change within the scope of the claims.
Claims (10)
1. support unit (6) that is used for flying pig (1) is bearing in the gun barrel of breech loading formula weapon, this support unit (6) comprises supporting member (8), this supporting member has rim lip (7) and is used for pulling the trigger the firing lock of the true fire in a stove before fuel is added of mortar projectile (1), support unit also comprises and is used for support component (8) is installed in jockey (10) on the afterbody (4) of flying pig (1), it is characterized in that: be used for the jockey (10) that supporting member (8) is installed on the afterbody (4) of flying pig (1) is comprised at least one compliant member (13,20,30), this compliant member is arranged through spring force and is installed on the afterbody (4) of flying pig (1).
2. support unit according to claim 1 (6) is characterized in that: compliant member (13,20,30) is arranged such that spring force acts on the periphery of the afterbody of flying pig (1) (4) (14).
3. support unit according to claim 2 (6), it is characterized in that: compliant member comprises ring spring (13), this ring spring is arranged to receive the afterbody (4) of flying pig (1), and like this, it makes spring force act on the periphery of the afterbody of flying pig (1) (4) (14).
4. support unit according to claim 2 (6), it is characterized in that: it comprises one or more lamination rings (20), this lamination ring is included in two or more contiguous sliceses (22) on its periphery, and be arranged to receive the afterbody (4) of flying pig (1), like this, one or more thin slices (22) of lamination ring (20) make spring force act on the periphery of the afterbody of flying pig (1) (4) (14).
5. support unit according to claim 1 (6) is characterized in that: compliant member (13,20,30) is arranged such that spring force acts on one or more guide tabs (5) of a part that forms flying pig (1) afterbody (4).
6. according to claim 3 or 5 described support units (6), it is characterized in that: compliant member comprises ring spring (13), this ring spring has slit, this slit is arranged to receive one or more guide tabs (5) of a part that forms flying pig (1) afterbody (4), like this, it makes spring force act on one or more guide tabs (5) of a part that forms flying pig (1) afterbody (4).
7. support unit according to claim 1 (6), it is characterized in that: compliant member (30) is arranged to be received in corresponding component (32) or the head piece that the afterbody (4) of Minnie shell (1) is located, like this, compliant member (30) makes spring force act on corresponding component (32) or the head piece.
8. support unit according to claim 7 (6) is characterized in that: compliant member comprises cover tubular attaching parts (30), and these cover tubular attaching parts are arranged to along the direction surrender vertical with its longitudinal axis.
9. support unit according to claim 8 (6), it is characterized in that: cover tubular attaching parts (30) are arranged to be received in the corresponding component (32) that the afterbody (4) of flying pig (1) is located, like this, this corresponding component (32) places the inside of attaching parts (30).
10. one kind is used for support unit is installed in method on the mortar projectile, and this method comprises:
Arrange support unit in the afterbody of flying pig, this support unit comprises supporting member; And
Support unit is installed on the afterbody of flying pig, it is characterized in that: support unit is installed on the afterbody of flying pig by one or more compliant members, and/or be installed on one or more guide tabs of a part that forms the flying pig afterbody, and/or be installed on the corresponding component that is arranged in the flying pig afterbody, like this, when receiving the afterbody of flying pig, compliant member acts on spring force on the periphery of flying pig afterbody and/or forms on one or more guide tabs of a part of flying pig afterbody and/or be arranged on the corresponding component in the flying pig afterbody.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FI20085081A FI121553B (en) | 2008-01-31 | 2008-01-31 | The support means for supporting a grenade in a weapon pipe and the method of attaching a support member to a grenade |
| FI20085081 | 2008-01-31 | ||
| PCT/FI2009/050075 WO2009095537A1 (en) | 2008-01-31 | 2009-01-30 | Support member for supporting shell into breech-loading weapon barrel, and method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101970973A true CN101970973A (en) | 2011-02-09 |
Family
ID=39004381
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009801036578A Pending CN101970973A (en) | 2008-01-31 | 2009-01-30 | Support member for supporting shell into breech-loading weapon barrel, and method |
Country Status (11)
| Country | Link |
|---|---|
| US (1) | US20100288112A1 (en) |
| EP (1) | EP2242982A4 (en) |
| JP (1) | JP2011511249A (en) |
| CN (1) | CN101970973A (en) |
| AU (1) | AU2009208917B2 (en) |
| CA (1) | CA2711756A1 (en) |
| FI (1) | FI121553B (en) |
| IL (1) | IL206871A (en) |
| RU (1) | RU2482424C2 (en) |
| WO (1) | WO2009095537A1 (en) |
| ZA (1) | ZA201004945B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2537068C1 (en) * | 2013-09-02 | 2014-12-27 | Открытое акционерное общество "Завод им. В.А. Дегтярева" | Launching facility |
| CN104266545A (en) * | 2014-09-23 | 2015-01-07 | 中国运载火箭技术研究院 | Underwater horizontal hot launching device |
| CN109668479A (en) * | 2019-01-30 | 2019-04-23 | 黄仕 | A kind of fort |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| 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 |
| DE102013005378B3 (en) * | 2013-03-28 | 2014-10-02 | Rheinmetall Waffe Munition Gmbh | Launcher for firing cartridged ammunition |
| US10247511B2 (en) * | 2017-02-01 | 2019-04-02 | X Products Llc | Projectile launcher |
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| US1311006A (en) * | 1919-07-22 | Planoqraph co | ||
| US2368064A (en) * | 1942-05-25 | 1945-01-23 | Herman J Fanger | Hand grenade gun adapter |
| US2409945A (en) * | 1943-06-25 | 1946-10-22 | Harris Trust And Savings Bank | Ammunition |
| US2447971A (en) * | 1945-07-25 | 1948-08-24 | Fed Lab Inc | Tree suspension grenade device |
| US2712270A (en) * | 1950-03-14 | 1955-07-05 | Samuel G Green | Ammunition retainer for rocket launchers |
| US2996880A (en) * | 1958-10-14 | 1961-08-22 | Texaco Experiment Inc | Reaction propulsion system and rocket |
| BE670537A (en) * | 1965-10-06 | 1966-02-16 | ||
| FR1515243A (en) * | 1967-01-20 | 1968-03-01 | Retaining base, removable, for mortar projectiles | |
| GB1182275A (en) * | 1967-04-13 | 1970-02-25 | Dynamit Nobel Ag | Means for Retaining Rockets in Rocket Launchers. |
| CH524802A (en) * | 1970-05-21 | 1972-06-30 | Sarmac Sa | Set including an infantry weapon and its ammunition |
| US3685450A (en) * | 1970-06-03 | 1972-08-22 | Us Army | Floating grenade cup |
| FR2210281A5 (en) * | 1972-12-12 | 1974-07-05 | France Etat | |
| DE2828251C1 (en) * | 1978-06-28 | 1985-10-03 | Rheinmetall GmbH, 4000 Düsseldorf | Bullet ammunition with bullet and flammable or partially flammable sleeve |
| DE2836963A1 (en) * | 1978-08-24 | 1984-03-08 | Rheinmetall GmbH, 4000 Düsseldorf | AMMUNITION UNIT FOR TUBE ARMS |
| GB9121343D0 (en) * | 1991-10-09 | 1992-11-18 | Royal Ordance Plc | Mortar system |
| GB9322392D0 (en) * | 1993-10-29 | 1993-12-22 | Royal Ordnance Plc | Bomb retaining device |
| SE505184C2 (en) * | 1995-04-07 | 1997-07-07 | Roheim Karl Axel | Sealing valve for grenade with pressure plate |
| FI108965B (en) * | 1997-01-24 | 2002-04-30 | Patria Vammas Oy | Arrangement to support a grenade in the barrel of a rear loading weapon |
| GB9809329D0 (en) * | 1998-05-01 | 1998-07-01 | Royal Ordnance Plc | Device for locking a projectile in a barrel |
| FI112700B (en) * | 2002-06-27 | 2003-12-31 | Patria Vammas Oy | Arrangement to support a crane in a weapon's fire pipe |
-
2008
- 2008-01-31 FI FI20085081A patent/FI121553B/en not_active IP Right Cessation
-
2009
- 2009-01-30 AU AU2009208917A patent/AU2009208917B2/en not_active Ceased
- 2009-01-30 US US12/863,756 patent/US20100288112A1/en not_active Abandoned
- 2009-01-30 EP EP09706208.7A patent/EP2242982A4/en not_active Withdrawn
- 2009-01-30 WO PCT/FI2009/050075 patent/WO2009095537A1/en active Application Filing
- 2009-01-30 CA CA2711756A patent/CA2711756A1/en not_active Abandoned
- 2009-01-30 RU RU2010135802/11A patent/RU2482424C2/en not_active IP Right Cessation
- 2009-01-30 CN CN2009801036578A patent/CN101970973A/en active Pending
- 2009-01-30 JP JP2010544747A patent/JP2011511249A/en active Pending
-
2010
- 2010-07-07 IL IL206871A patent/IL206871A/en not_active IP Right Cessation
- 2010-07-13 ZA ZA2010/04945A patent/ZA201004945B/en unknown
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2537068C1 (en) * | 2013-09-02 | 2014-12-27 | Открытое акционерное общество "Завод им. В.А. Дегтярева" | Launching facility |
| CN104266545A (en) * | 2014-09-23 | 2015-01-07 | 中国运载火箭技术研究院 | Underwater horizontal hot launching device |
| CN104266545B (en) * | 2014-09-23 | 2016-02-10 | 中国运载火箭技术研究院 | A kind of submerged level heat emission device |
| CN109668479A (en) * | 2019-01-30 | 2019-04-23 | 黄仕 | A kind of fort |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2011511249A (en) | 2011-04-07 |
| AU2009208917B2 (en) | 2013-04-18 |
| EP2242982A4 (en) | 2013-09-04 |
| US20100288112A1 (en) | 2010-11-18 |
| RU2010135802A (en) | 2012-03-10 |
| AU2009208917A1 (en) | 2009-08-06 |
| RU2482424C2 (en) | 2013-05-20 |
| FI20085081A (en) | 2009-08-01 |
| WO2009095537A1 (en) | 2009-08-06 |
| IL206871A0 (en) | 2010-12-30 |
| FI20085081A0 (en) | 2008-01-31 |
| EP2242982A1 (en) | 2010-10-27 |
| FI121553B (en) | 2010-12-31 |
| IL206871A (en) | 2014-07-31 |
| CA2711756A1 (en) | 2009-08-06 |
| ZA201004945B (en) | 2011-03-30 |
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Application publication date: 20110209 |