WO2012160271A1 - Elément de jonction pour un corps en matériau composite d'un projectile militaire de perforation - Google Patents
Elément de jonction pour un corps en matériau composite d'un projectile militaire de perforation Download PDFInfo
- Publication number
- WO2012160271A1 WO2012160271A1 PCT/FR2012/000196 FR2012000196W WO2012160271A1 WO 2012160271 A1 WO2012160271 A1 WO 2012160271A1 FR 2012000196 W FR2012000196 W FR 2012000196W WO 2012160271 A1 WO2012160271 A1 WO 2012160271A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- projectile
- contact
- composite material
- projectile according
- longitudinal extension
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
- F42B12/72—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the material
- F42B12/74—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the material of the core or solid body
- F42B12/745—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the material of the core or solid body the core being made of plastics; Compounds or blends of plastics and other materials, e.g. fillers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
- F42B10/38—Range-increasing arrangements
- F42B10/42—Streamlined projectiles
- F42B10/46—Streamlined nose cones; Windshields; Radomes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
- F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
- F42B10/52—Nose cones
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
- F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
- F42B12/04—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type
- F42B12/08—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type with armour-piercing caps; with armoured cupola
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
- F42B12/72—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the material
- F42B12/76—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the material of the casing
Definitions
- Joining element for a composite material body of a military piercing projectile Joining element for a composite material body of a military piercing projectile.
- the present invention relates to a connecting element for connecting an element (preferably a metal nose) of a military piercing projectile to a cylindrical body of composite material of said projectile, and a metallic nose and a projectile provided with such a junction element.
- an element preferably a metal nose
- the present invention is applicable to one.
- military piercing projectile which can equip a missile, which is provided with a cylindrical body made of composite material, filled with an explosive, and a nose which is arranged in front of said body.
- Such a mixed embodiment which appears very advantageous requires, however, to be completely effective that particular characteristics are present at the junction between the composite material of the body of the projectile and the steel of the nose of said projectile. Indeed, this junction must, first of all, be sufficiently robust to avoid separation of steel parts and composite material during impact. In addition, this junction must also help the composite material to withstand the puncture stresses likely to be encountered. Indeed, especially during the perforation of very thick targets in concrete, the military piercing projectile undergoes very important constraints. It may in particular have to undergo a deceleration of the order of 10000g during an impact.
- the present invention relates to a connecting element for connecting an element (preferably a metal nose) of a military piercing projectile to a body (preferably a cylindrical body) made of composite material of said projectile, whose design makes it possible to remedy to the aforementioned drawbacks and in particular to withstand the constraints indicated above.
- said connecting element is remarkable, according to the invention, in that its rear part, intended to be connected to said body of composite material, comprises at least:
- annular stop centered with respect to its longitudinal axis, which is intended to come into contact with the front edge of said body (preferably cylindrical);
- a longitudinal rearward extension which is defined from said abutment, which comprises a contact face, and which has a shape and a diameter adapted to said body so as to be able, with its contact face, laterally to contact with a peripheral surface of the latter.
- the body of composite material is preferably, but not exclusively, of cylindrical.
- said connecting element which is made of metal, preferably of steel or of any other dense and resilient material (having good resistance to impact), the mechanical strength of the projectile is improved.
- the abutment in combination with the longitudinal extension makes it possible to transmit the axial compression (due to the impact on the target) to the body which is able to support such compression.
- the composite material works almost exclusively in axial compression (that is to say in the field where it is the most efficient), while the joining element compensates for radial stresses (due to movement of the explosive inside the projectile), as well as a large part of the bending efforts of the projectile as a whole during an impact on a target with an impact.
- the composite material thus working substantially under stress where it is most robust, it is possible to optimize its characteristics (thickness, bulk, mass, ...), especially to seek a gain in mass.
- Such mass gain obtained by virtue of the invention can be replaced by additional or more dense explosive.
- the performance of the entire piercing military projectile can be improved by using the joining element according to the invention.
- the longitudinal extension of the junction element provides a large contact surface, which is sufficient to allow bonding between the body of composite material and the connecting element ( made of metal, preferably steel). By using a bonding for the joining of these parts, it is not necessary to perform machining or drilling at the composite material such as for example for a screw fastener.
- the fibers composing the composite material (and ensuring most of the mechanical strength of the composite material) are not damaged or cut.
- the mechanical properties of the composite material are therefore not deteriorated by the fixing.
- the glue used can be chosen according to the environmental conditions of use of the projectile, which improves the attachment.
- said longitudinal rearward extension has a diameter adapted to said cylindrical body so as to be laterally in contact with a radially outer face of the latter.
- the longitudinal extension of the junction element thus surrounds the front portion of the cylindrical body and is bonded by its radially inner face to the radially outer face of the latter.
- the contact face of said longitudinal extension intended to come into contact with the cylindrical body is provided with at least one channel forming a housing, preferably of annular shape, which is capable of receiving glue. .
- This channel is dimensioned so as to receive a sufficient amount of glue to generate a suitable attachment.
- said stop has at least one contact surface, and preferably a plurality of contact surfaces which succeed one another in the radial direction (directly or via a side contact face).
- a contact surface can:
- any possible combination of these different contact surfaces is conceivable. This makes it possible to achieve an advantageous contact between the abutment and the front face of the cylindrical body, in particular for efficiently transmitting to said cylindrical body the forces generating the axial compression.
- said rearward longitudinal extension has a diameter adapted to said cylindrical body so as to be laterally in contact with a radially inner face of the latter.
- the longitudinal extension of the connecting element thus enters the front portion of the cylindrical body and is bonded by its radially outer face on the radially inner face of the latter.
- the junction element further comprises an annular lip connected to the outer edge of the abutment and arranged so as to be able to come laterally into contact with a radially outer face of the front edge of said cylindrical body.
- This annular lip thus retains the composite material during an impact and to prevent delamination at its end, during a crash against a more rigid structure (the steel of the nose).
- this lip is arranged longitudinally opposite to said longitudinal extension so as to form, with said abutment and said extension, a housing for the front part of the body. cylindrical material, allowing a triple contact between the connecting element and said front part.
- said connecting element represents an independent element which is used as an intermediate junction element between the metal nose and the cylindrical body of a projectile.
- said connecting element advantageously comprises, at its front part, connecting means making it possible to connect it, for example by screwing, to a metal nose of a military piercing projectile.
- said joining element corresponds to the rear part of a metal nose of a military piercing projectile.
- the connecting element is therefore an integral part of the metal nose which is intended to be mounted on the cylindrical body of the projectile.
- the joining element according to the invention which thus contributes to the maintenance of the composite material and which plays a preponderant role in the mechanical resistance to impact of the entire projectile, also has the following advantages:
- the composite material part can be made from a simplified geometry, for example in the form of a tube (cylinder).
- the present invention also relates to a military piercing projectile, which can in particular equip a missile, provided in particular with a body (cylindrical) of composite material, which is filled with an explosive or other, and a nose which is arranged in the before said cylindrical body.
- said projectile is remarkable in that it comprises a joining element such as that mentioned above, which is arranged to connect said nose to said cylindrical body of composite material.
- the walls, metal and composite, radially successive of said projectile at the junction are such that their stiffness to pressure is increasing, radially outwardly from the axis, so that each they are plated. laterally against the outer one.
- the connecting element is intended to connect a metal nose to a body of composite material on a projectile.
- the connecting element can also be used to connect another element, for example rear closure means, to the body of composite material.
- Figure 1 is a schematic view of a military perforation projectile provided with a connecting element according to a first embodiment of the invention.
- Figure 2 is an enlarged view of a portion of Figure 1, illustrating the junction.
- Figure 3 is a perspective view of a connecting element according to the first embodiment of the invention.
- Figures 4 and 5 are views similar to that of Figure 2, which respectively illustrate different embodiments of the contact surfaces.
- FIGS. 6 to 8 are views similar to those of FIGS. 1 to 3, respectively, of a military piercing projectile equipped with a joining element according to a second embodiment of the invention.
- the joining element 1 serves to connect a metal nose 2. from a military piercing projectile 3 to a body 4 of composite material of said projectile 3.
- the body 4 has a preferred (but not exclusive) cylindrical shape.
- this military piercing projectile 3 which can in particular equip a missile, is provided in the usual manner, in addition in particular to said cylindrical body 4 and said nose 2 which is arranged in front of said body.
- Said junction element 1 has a longitudinal axis 10 which, in the assembled position (shown for example in Figures 2 and 7), coincides with the longitudinal axis 1 1 of the cylindrical body 4 (and therefore of the projectile 3 ).
- the rear portion 12 of said connecting element 1, intended to be bonded to the front 5 of said cylindrical body 4 of composite material comprises at least:
- annular abutment 13, 23 which is centered with respect to the longitudinal axis 10, and which is intended to come into contact with the front edge 14, 24 of said cylindrical body 4.
- annular shape means a closed curve, preferably circular, but not exclusively;
- this longitudinal extension 15, 25 which is extended towards the rear of the joining element 1, which is defined from said abutment 13, 23 which comprises a contact face 16, 26 and which has a shape cylindrical, and a diameter adapted to the diameter of said cylindrical body 4 so as to come with its contact face 16, 26 laterally in contact with a peripheral surface 1 7, 27 of the latter.
- this longitudinal extension 15, 25 has a length that depends on the level of pressure exerted by the explosive and the level of bending expected at impact.
- the stop 13, 23 (in combination with the maintenance generated by the longitudinal extension 15, 25) makes it possible to transmit the axial compression due to impact on the target 20, to said cylindrical body 4 which, by its own characteristics, is capable of to support such compression.
- said connecting element 1 which is made of metal, preferably steel or any other material dense and resilient (with good resistance to impact), improve the mechanical strength of the projectile 3.
- the composite material of the body 4 works almost exclusively in axial compression (that is to say in the field where it is the most efficient), while the connecting element 1 and the nose 2 compensate the radial stresses (due to the movement of the explosive 6 inside the projectile 3), as well as a large part of the bending forces of the projectile 3 as a whole during an impact on a target 20 with an impact a.
- the composite material thus working substantially under stress where it is most robust, it is possible to optimize its characteristics (thickness, bulk, mass, ...), especially to seek a gain in mass.
- Such a gain in mass obtained by virtue of the invention can in particular be used for additional or more dense explosive.
- the performance of the military piercing projectile 3 as a whole can be improved by using the joining element 1 according to the invention.
- the longitudinal extension 1 5, 25 of the junction element 1 provides a contact surface 1 6, 26 large surface area, which is sufficient to allow bonding between the body 4 of composite material and the joining element 1 (metal, preferably steel).
- the joining element 1 metal, preferably steel.
- said longitudinal extension 15 towards the rear has a suitable internal diameter (that is to say very slightly greater) than the external diameter of the cylindrical body 4. so as to be able to receive the front part of the latter, while coming laterally to the contact (via the contact face 1 6) of a radially external face 1 7 of the latter, as shown in Figure 2 which shows an enlarged manner a part P1 of Figure 1.
- the longitudinal extension 1 5 of the junction element 1 thus surrounds in the front portion 5 of the cylindrical body 4 and is bonded by its radially inner face 1 6 on the face 1 7 radially external thereof.
- This face 1 6 may be longitudinal ( Figures 1 to 3 and 5) or slightly conical ( Figure 4).
- said contact face 1 6 of said longitudinal extension 1 5, intended to come into contact with the cylindrical body 4 is provided with at least one channel 21 forming a housing, preferably of annular shape, which is likely to receive glue.
- This channel 21 shown in particular in Figures 1 and 2 is dimensioned so as to receive a sufficient amount of glue to generate a suitable attachment.
- said abutment 1 3 has at least one contact surface 1 3A, 1 3B, and preferably a plurality of contact surfaces which succeed in the radial direction (directly or via the face 1 6).
- a contact surface can: - Or be located in a plane which is radial with respect to said longitudinal axis 1 0, as for the contact surfaces 1 3A shown in Figure 4;
- any possible combination of these different contact surfaces 1 3A, 1 3B, and 1 6 is possible.
- This makes it possible to achieve an advantageous contact between the stop 1 3 and the front face 14 of the cylindrical body 4, in particular to efficiently transmit to said cylindrical body 4 the forces generating the axial compression.
- the introduction of successive walls is carried out gradually using conical parts.
- the longitudinal extension 25 towards the rear of the joining element 1 has a suitable external diameter (that is to say very slightly less ) to the internal diameter of the cylindrical body 4 so as to be inserted into the latter, while coming laterally to the contact (via an outer contact face 26) of a radially inner face 27 of the latter, as shown in Figure 7 which shows in an enlarged manner a portion P2 of FIG. 6.
- the longitudinal extension 25 of the joining element 1 thus enters the front portion 5 of the cylindrical body 4 and is bonded by its radially outer face 26 on the radially inner face 27 of the latter.
- the longitudinal extension 25 further comprises an annular lip 22 connected to the outer edge of the abutment 23 and arranged so as to come laterally in contact with a radially outer face 28 of the front side 5 of the cylindrical body 4.
- This annular lip 22 has a length which is of the same order of magnitude as the 4 composite body thickness. This annular lip 22 thus makes it possible to retain the composite material during an impact and to prevent delamination at its end 5, due to a crushing against a more rigid structure (the steel of the nose).
- the lip 22 is arranged longitudinally opposite to said longitudinal extension 25 so as to form with said abutment 23 and said extension 25 a housing 29 for the front portion 5 of the body 4 made of composite material, allowing a triple contact between the joining element 1 and said front part 5.
- said lip 22 has a tapered shape tapered rearwardly, as shown in particular in FIG. 7.
- said joining element 1 represents an independent element which is used as an intermediate element for joining a nose 2 and a cylindrical body 4 of a projectile 3.
- said connecting element 1 comprises, at its front portion, conventional connecting means for connecting it, for example by screwing, to a metal nose of a military piercing projectile.
- Such a metal / metal connection is easy to perform and has good mechanical strength.
- the connecting element according to this first embodiment has, in particular, the advantage of being easily manufactured.
- said joining element 1 corresponds to the rear part of a metal nose 2 of a military piercing projectile. 3, as shown in the figures (even if nose 2 is only partially shown).
- the joining element 1 is therefore an integral part of the metal nose 2 which is intended to be mounted directly on the cylindrical body 4 of the projectile 3. By this integration, no connecting means is therefore necessary. between the nose 2 and the connecting element 1.
- the joining element 1 according to the invention which therefore contributes to the maintenance of the composite material and which plays a preponderant role in the mechanical resistance to impact of the entire projectile 3, also has the following advantages:
- the part of the projectile 3 composite material can for example be made in the form of a cylinder or tube (or some other simple geometric form), instead of a more complex geometry.
- said composite material of the cylindrical body 4 comprises unbalanced fiber weaves, that is to say with a proportion of axial fibers different (and greater) than the proportion of radial fibers.
- a proportion of axial fibers different (and greater) than the proportion of radial fibers is to say with a proportion of axial fibers different (and greater) than the proportion of radial fibers.
- the connecting element 1 is intended to connect a metal nose 2 to a body 4 of composite material on a projectile.
- the connecting element can also be used to connect another element, in particular rear closure means such as the aforementioned means 8, to the body of composite material.
- the forces are less important at the rear than at the front of the projectile 3.
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Fluid Mechanics (AREA)
- Thermal Sciences (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Vibration Dampers (AREA)
- Laminated Bodies (AREA)
- Earth Drilling (AREA)
Abstract
Description
Claims
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US14/119,012 US9347752B2 (en) | 2011-05-24 | 2012-05-15 | Connecting element for a body made of composite material of a piercing projectile |
AU2012260708A AU2012260708B2 (en) | 2011-05-24 | 2012-05-15 | Connecting element for a body made of composite material of a piercing military projectile |
BR112013029928-2A BR112013029928B1 (pt) | 2011-05-24 | 2012-05-15 | Projétil militar penetrante |
IL229279A IL229279A (en) | 2011-05-24 | 2013-11-06 | Component for a body made of penetrating military missile |
ZA2013/08986A ZA201308986B (en) | 2011-05-24 | 2013-11-28 | Connecting element for a body made of composite material of a piercing military projectile |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1101605 | 2011-05-24 | ||
FR1101605A FR2975770B1 (fr) | 2011-05-24 | 2011-05-24 | Element de jonction pour un corps en materiau composite d'un projectile militaire de perforation |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2012160271A1 true WO2012160271A1 (fr) | 2012-11-29 |
Family
ID=46125344
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2012/000196 WO2012160271A1 (fr) | 2011-05-24 | 2012-05-15 | Elément de jonction pour un corps en matériau composite d'un projectile militaire de perforation |
Country Status (9)
Country | Link |
---|---|
US (1) | US9347752B2 (fr) |
EP (1) | EP2527781B1 (fr) |
AU (1) | AU2012260708B2 (fr) |
BR (1) | BR112013029928B1 (fr) |
ES (1) | ES2452544T3 (fr) |
FR (1) | FR2975770B1 (fr) |
IL (1) | IL229279A (fr) |
WO (1) | WO2012160271A1 (fr) |
ZA (1) | ZA201308986B (fr) |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10036619B2 (en) * | 2016-01-11 | 2018-07-31 | Lehigh Defense, LLC | Armor-piercing cavitation projectile |
CA3018754A1 (fr) | 2016-03-25 | 2017-10-05 | Vista Outdoor Operations Llc | Systeme msr a energie reduite |
US11118851B2 (en) | 2016-03-25 | 2021-09-14 | Vista Outdoor Operations Llc | Reduced energy MSR system |
IT201800003525A1 (it) * | 2018-03-14 | 2019-09-14 | Imz S R L | Elemento balistico |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR1292383A (fr) * | 1961-03-24 | 1962-05-04 | Soc Tech De Rech Ind | Perfectionnements aux projectiles, en particulier aux projectiles perforants |
JPS59159414A (ja) * | 1983-02-28 | 1984-09-10 | Yokohama Rubber Co Ltd:The | 樹脂製駆動軸 |
FR2691571A1 (fr) * | 1992-05-16 | 1993-11-26 | Bodenseewerk Geraetetech | Joint de raccord étanche. |
US5567908A (en) * | 1980-04-25 | 1996-10-22 | The United Of America As Represented By The Secretary Of The Navy | Advanced anti ship penetrator warhead |
US20040082394A1 (en) * | 2002-10-23 | 2004-04-29 | Lee Dai Gil | Hybrid propeller shaft made of metal and composite material and method of manufacturing the same |
Family Cites Families (14)
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US3641936A (en) * | 1970-05-27 | 1972-02-15 | Us Army | Composite shell with ceramic base |
US4147107A (en) * | 1976-02-17 | 1979-04-03 | Kupag Kunststoff-Patent-Verwaltungs Ag | Ammunition cartridge |
US5311820A (en) * | 1991-01-17 | 1994-05-17 | Thiokol Corporation | Method and apparatus for providing an insensitive munition |
US20050257711A1 (en) * | 1999-01-15 | 2005-11-24 | Natec, Inc. | A Cartridge Casing Body And An Ammunition Article Having A Cartridge Casing Body Wherein The Cartridge Casing Body Is Plastic, Ceramic, Or A Composite Material |
US6752084B1 (en) * | 1999-01-15 | 2004-06-22 | Amtech, Inc. | Ammunition articles with plastic components and method of making ammunition articles with plastic components |
US7441504B2 (en) * | 1999-01-15 | 2008-10-28 | Development Capital Management Company | Base for a cartridge casing body for an ammunition article, a cartridge casing body and an ammunition article having such base, wherein the base is made from plastic, ceramic, or a composite material |
WO2003036222A1 (fr) * | 2001-10-22 | 2003-05-01 | Armtec Defense Products Co. | Ensemble circulaire a munitions comportant une douille combustible |
DE10354011A1 (de) * | 2003-11-19 | 2005-06-02 | Rheinmetall Waffe Munition Gmbh | Hülsenboden für großkalibrige Munition und Verfahren zu seiner Herstellung |
US7278491B2 (en) * | 2004-08-04 | 2007-10-09 | Bruce David Scott | Perforating gun connector |
US8240252B2 (en) * | 2005-03-07 | 2012-08-14 | Nikica Maljkovic | Ammunition casing |
US8561543B2 (en) * | 2010-11-10 | 2013-10-22 | True Velocity, Inc. | Lightweight polymer ammunition cartridge casings |
EP2908086B1 (fr) * | 2011-01-14 | 2017-08-23 | PCP Tactical, LLC | Douille de cartouche à base de polymère de résistance élevée et son procédé de fabrication |
US9182204B2 (en) * | 2011-07-28 | 2015-11-10 | Mac, Llc | Subsonic ammunition casing |
EP2737275A4 (fr) * | 2011-07-28 | 2014-09-17 | Mac Llc | Géométrie de corps de munition en polymère |
-
2011
- 2011-05-24 FR FR1101605A patent/FR2975770B1/fr active Active
-
2012
- 2012-05-15 BR BR112013029928-2A patent/BR112013029928B1/pt not_active IP Right Cessation
- 2012-05-15 WO PCT/FR2012/000196 patent/WO2012160271A1/fr active Application Filing
- 2012-05-15 US US14/119,012 patent/US9347752B2/en active Active
- 2012-05-15 AU AU2012260708A patent/AU2012260708B2/en active Active
- 2012-05-15 EP EP12290162.2A patent/EP2527781B1/fr active Active
- 2012-05-15 ES ES12290162.2T patent/ES2452544T3/es active Active
-
2013
- 2013-11-06 IL IL229279A patent/IL229279A/en active IP Right Grant
- 2013-11-28 ZA ZA2013/08986A patent/ZA201308986B/en unknown
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR1292383A (fr) * | 1961-03-24 | 1962-05-04 | Soc Tech De Rech Ind | Perfectionnements aux projectiles, en particulier aux projectiles perforants |
US5567908A (en) * | 1980-04-25 | 1996-10-22 | The United Of America As Represented By The Secretary Of The Navy | Advanced anti ship penetrator warhead |
JPS59159414A (ja) * | 1983-02-28 | 1984-09-10 | Yokohama Rubber Co Ltd:The | 樹脂製駆動軸 |
FR2691571A1 (fr) * | 1992-05-16 | 1993-11-26 | Bodenseewerk Geraetetech | Joint de raccord étanche. |
US20040082394A1 (en) * | 2002-10-23 | 2004-04-29 | Lee Dai Gil | Hybrid propeller shaft made of metal and composite material and method of manufacturing the same |
Also Published As
Publication number | Publication date |
---|---|
US20140150682A1 (en) | 2014-06-05 |
IL229279A (en) | 2016-11-30 |
ZA201308986B (en) | 2015-02-25 |
EP2527781B1 (fr) | 2014-02-19 |
ES2452544T3 (es) | 2014-04-01 |
AU2012260708A1 (en) | 2013-11-14 |
US9347752B2 (en) | 2016-05-24 |
FR2975770B1 (fr) | 2018-06-29 |
BR112013029928B1 (pt) | 2020-06-02 |
BR112013029928A2 (pt) | 2018-06-19 |
EP2527781A1 (fr) | 2012-11-28 |
IL229279A0 (en) | 2014-01-30 |
FR2975770A1 (fr) | 2012-11-30 |
AU2012260708B2 (en) | 2016-08-25 |
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