EP2095060B1 - Projectile guide muni d'un manchon pour le montage d'un systeme de guidage - Google Patents
Projectile guide muni d'un manchon pour le montage d'un systeme de guidage Download PDFInfo
- Publication number
- EP2095060B1 EP2095060B1 EP07872426A EP07872426A EP2095060B1 EP 2095060 B1 EP2095060 B1 EP 2095060B1 EP 07872426 A EP07872426 A EP 07872426A EP 07872426 A EP07872426 A EP 07872426A EP 2095060 B1 EP2095060 B1 EP 2095060B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- nose
- sleeve
- cylindrical
- guided missile
- projectile
- 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.)
- Not-in-force
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
Definitions
- the present invention relates to a guided projectile whose nose is provided with a sleeve serving as a mounting interface for a guidance system.
- An object of the present invention is therefore to solve the problems mentioned above with the aid of a simple solution to implement, reliable and inexpensive.
- the Figures 1 and 2 schematically represent a guided military projectile 1, such as an aerial penetration bomb.
- the guided projectile 1 comprises in particular a cylindrical tubular body 10 terminating at the front by a nose 20 having a generally ogival shape.
- the nose 20 comprises a front nose 21 having a first profile and ending with a penetration point 22, and a rear nose 23 having a second profile different from the profile of the nose before 21.
- the double-pointed form of the nose nose 20 thus facilitates the penetration of the guided projectile 1 (progressive penetration) in hard targets and allows an optimal distribution of the stresses generated during the penetration phase.
- An intermediate connecting zone 25 is situated between the front nose 21 and the rear nose 23 and connects them in a continuous manner.
- the intermediate zone of connection 25 is constituted by a cylindrical part provided with an external thread 26.
- Guided projectile 1 also includes a cylindrical sleeve 30 serving as a mounting interface for a NATO standard qualified guidance system (not shown), such as a laser guidance equipment cooperating with a global satellite positioning system.
- a NATO standard qualified guidance system such as a laser guidance equipment cooperating with a global satellite positioning system.
- the cylindrical mounting sleeve 30 is removably attached to the nose 20 of the guided projectile 1. More specifically, the cylindrical sleeve 30 has a rear portion 31 provided with an internal thread 32 for cooperating with the external thread 26 of the part cylindrical connecting 25 of the nose 20.
- the cylindrical mounting sleeve 30 also has a flange-shaped front portion 33 extending continuously outwardly.
- the front portion 33 of the cylindrical sleeve 30 is flared so as to oppose the maximum surface area to the impact and to concentrate the stresses in specific zones. The concentration of stresses within the cylindrical mounting sleeve 30 thus causes the destruction thereof and facilitates the subsequent penetration of the guided projectile 1.
- the front flange 33 has an internal thread 34 intended for fixing the NATO standard guidance system in the conditions of use of the projectile 1 (for example when it is integrated with a military vehicle such as an airplane, a boat, a tank or a submarine), or a protective cap (not shown) when the projectile 1 is stored before integration.
- a military vehicle such as an airplane, a boat, a tank or a submarine
- a protective cap not shown
- the cylindrical mounting sleeve 30 is made of a low-resilience material, for example a brittle steel, so as to reduce the energy dissipation during its destruction.
- the body 10 of the projectile 1 according to the present invention is made by forging in a high-elastic, high-density and high-hardness material, for example a low-alloy steel having has undergone a suitable hardening treatment, such as quenching or carburizing.
- the cylindrical sleeve 30 assures its function as a mounting interface for the guiding systems by keeping them close to the nose 20 of the projectile 1.
- the cylindrical mounting sleeve 30 breaks into pieces because of the fragility of the material constituting it.
- the destruction of the guidance system also occurs at this time, without affecting the penetration or guidance of the guided projectile 1.
- the nose 20 is made of a rigid material and a part of absorbed stresses causes the destruction of the cylindrical sleeve 30, the guided projectile 1 can penetrate deeper into the target.
- the present invention thus proposes a guided projectile 1 equipped with a removable cylindrical sleeve 30 which makes it possible both to easily mount a guidance system on its body 10 and to reduce the dissipation of energy during an impact against a hard target. .
- the removable attachment of the cylindrical mounting sleeve 30 on the nose 20 of the projectile 1 can be made in another way than described, for example by axial clipping force or using a bayonet system.
- the invention applies to any type of guided military projectile, such as a missile, a bomb, a penetrating charge, etc.
- the guided projectile 1 according to the present invention can be launched from the ground (tank, artillery battery), from the sea (cruiser, submarine) or in the air (bomber, fighter), and the target can to be on land, at sea or in the air.
- the profile of the rear warhead 33 may be identical to the profile of the nose before 31, that is to say that the two warheads can follow the same curvature being an extension of one another.
- the cylindrical body may be solid or hollow so as to enclose an active or inert material.
- the sleeve may be made of a composite material or a metal alloy having the same mechanical characteristics as those of the steel described.
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Forklifts And Lifting Vehicles (AREA)
- Chair Legs, Seat Parts, And Backrests (AREA)
- Mutual Connection Of Rods And Tubes (AREA)
- Toys (AREA)
- Steering Devices For Bicycles And Motorcycles (AREA)
- Vibration Dampers (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0655787A FR2910613B1 (fr) | 2006-12-21 | 2006-12-21 | Projectile guide muni d'un manchon pour le montage d'un systeme de guidage |
PCT/FR2007/002142 WO2008102069A2 (fr) | 2006-12-21 | 2007-12-20 | Projectile guide muni d' un manchon pour le montage d'un systeme de guidage |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2095060A2 EP2095060A2 (fr) | 2009-09-02 |
EP2095060B1 true EP2095060B1 (fr) | 2011-06-08 |
Family
ID=38476853
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP07872426A Not-in-force EP2095060B1 (fr) | 2006-12-21 | 2007-12-20 | Projectile guide muni d'un manchon pour le montage d'un systeme de guidage |
Country Status (8)
Country | Link |
---|---|
EP (1) | EP2095060B1 (xx) |
KR (1) | KR20090112653A (xx) |
CN (1) | CN101578493B (xx) |
AT (1) | ATE512347T1 (xx) |
BR (1) | BRPI0720585A2 (xx) |
FR (1) | FR2910613B1 (xx) |
WO (1) | WO2008102069A2 (xx) |
ZA (1) | ZA200905069B (xx) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2009020697A2 (en) * | 2007-06-08 | 2009-02-12 | Raytheon Company | Methods and apparatus for attachment adapter for a projectile |
US8291827B2 (en) * | 2009-09-28 | 2012-10-23 | Raytheon Company | Rocket guidance adapter |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6254031B1 (en) * | 1994-08-24 | 2001-07-03 | Lockhead Martin Corporation | Precision guidance system for aircraft launched bombs |
KR100549487B1 (ko) * | 1997-12-11 | 2006-02-08 | 록히드 마틴 코포레이션 | 장갑형 투하 폭탄 |
US6276277B1 (en) * | 1999-04-22 | 2001-08-21 | Lockheed Martin Corporation | Rocket-boosted guided hard target penetrator |
AUPQ776300A0 (en) * | 2000-05-25 | 2000-08-10 | Metal Storm Limited | Missile control |
FR2845763B1 (fr) * | 2002-10-11 | 2006-12-01 | Tda Armements Sas | Systeme autonome de guidage pour munition d'artillerie et munition d'artillerie guidee |
CN2656930Y (zh) * | 2003-12-04 | 2004-11-17 | 罗林桂 | 78式无座力炮内膛炮及其模拟弹 |
DE102005039902A1 (de) * | 2005-02-04 | 2006-08-10 | Rheinmetall Waffe Munition Gmbh | Einrichtung zur Steigerung der Präzision heckflügelstabilisierter Munition |
-
2006
- 2006-12-21 FR FR0655787A patent/FR2910613B1/fr not_active Expired - Fee Related
-
2007
- 2007-12-20 WO PCT/FR2007/002142 patent/WO2008102069A2/fr active Application Filing
- 2007-12-20 AT AT07872426T patent/ATE512347T1/de not_active IP Right Cessation
- 2007-12-20 CN CN2007800472388A patent/CN101578493B/zh not_active Expired - Fee Related
- 2007-12-20 BR BRPI0720585-6A2A patent/BRPI0720585A2/pt not_active IP Right Cessation
- 2007-12-20 KR KR1020097014835A patent/KR20090112653A/ko not_active Application Discontinuation
- 2007-12-20 EP EP07872426A patent/EP2095060B1/fr not_active Not-in-force
-
2009
- 2009-07-10 ZA ZA200905069A patent/ZA200905069B/xx unknown
Also Published As
Publication number | Publication date |
---|---|
BRPI0720585A2 (pt) | 2014-10-07 |
CN101578493A (zh) | 2009-11-11 |
CN101578493B (zh) | 2012-08-29 |
WO2008102069A2 (fr) | 2008-08-28 |
WO2008102069A8 (fr) | 2009-07-30 |
ZA200905069B (en) | 2010-07-28 |
ATE512347T1 (de) | 2011-06-15 |
KR20090112653A (ko) | 2009-10-28 |
FR2910613A1 (fr) | 2008-06-27 |
EP2095060A2 (fr) | 2009-09-02 |
FR2910613B1 (fr) | 2009-10-02 |
WO2008102069A3 (fr) | 2008-10-30 |
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