WO2008096069A1 - Bombe aerienne de penetration munie d'un revetement externe - Google Patents
Bombe aerienne de penetration munie d'un revetement externe Download PDFInfo
- Publication number
- WO2008096069A1 WO2008096069A1 PCT/FR2007/002143 FR2007002143W WO2008096069A1 WO 2008096069 A1 WO2008096069 A1 WO 2008096069A1 FR 2007002143 W FR2007002143 W FR 2007002143W WO 2008096069 A1 WO2008096069 A1 WO 2008096069A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- bomb
- hollow
- penetration body
- penetration
- outer coating
- 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
- F42B12/02—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
-
- 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
- F42B12/06—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 hard or heavy core; Kinetic energy penetrators
-
- 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
- F42B12/20—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B25/00—Fall bombs
Definitions
- the present invention relates to an aerial penetration bomb.
- An object of the present invention is therefore to solve the problems mentioned above with a solution that is simple to implement, reliable and inexpensive.
- the invention proposes to reduce the dimensions of the penetration body while maintaining the characteristics of a qualified general purpose spray. More specifically, the present invention relates to an aerial penetration bomb comprising:
- the bomb according to the present invention may comprise at least one of the following features: the outer coating comprises a plurality of longitudinal elements each fixed directly over the entire length of the hollow penetration body;
- the outer coating comprises three identical thermoformed elements made of a fiber-reinforced plastics material, such as a prepreg (SMC), for example a mixture of polyester and glass fibers loaded with graphite; each longitudinal element has a housing receiving a balancing flange made of a high-density material, for example greater than or equal to that of steel, and contributing to impart to the spray said voluminal, dimensional, mechanical, aerodynamic and inertial; - Each balancing flange is fixed directly to the hollow penetration body with screws provided to be sheared during an impact of the bomb against an obstacle generating a deceleration exceeding a predetermined value;
- SMC prepreg
- each longitudinal element and / or each flange is bonded directly to the hollow penetration body, for example using a polyurethane adhesive
- the outer coating is coated with a thin protective coating surrounding it integrally;
- the protective coating is made of a material capable of withstanding shocks defined by the aeronautical standard Gam EG13, abrasion and fire, this material being for example a polyurethane cast monolayer;
- the bomb may have two suspension ring wells and an accessory well, said wells being fixed directly to the hollow penetration body by means of screws intended to be sheared during an impact of the bomb against an obstacle generating a deceleration exceeding a determined value;
- the bomb may furthermore comprise at least one sleeve providing passage for cables connecting accessories of the accessory well to the detonation means, said sleeve being embedded in the active or inert material and being made of a material resistant to chemical attack by the latter; -
- the outer coating locally has openings delivering to the wells so as to make them accessible from the outside;
- the hollow penetration body comprises a trunk having a front end shaped ogive and a rear end forming a base including the detonation means, the front end being provided with an external thread adapted to cooperate with an internal thread.
- a front sleeve serving as an interface with at least one equipment involved in the operation of the bomb, such as a guidance system.
- FIG. 1 is an exploded perspective view of an aerial penetration bomb according to the present invention
- FIG. 2 is a top view of a penetration body of the bomb
- FIG. 3 is a sectional view along the line III-III of Figure 2;
- - Figure 4 is a sectional view of the bomb once assembled;
- FIG. 5 is a detail view of a sleeve before the bomb.
- FIG. 6 is a sectional view along the line VI-VI of Figure 5.
- Figures 1 to 4 show an aerial penetration bomb 1 according to the present invention. This bomb is intended to be integrated under an aircraft to which it is suspended.
- This bomb 1 comprises a hollow penetration body 10 made for example by forging in a high elastic limit material, high density and high hardness, such as steel.
- the material chosen to make the penetration hollow body also ensures a natural fragmentation thereof during the detonation of the active ingredient after penetration of a hard target.
- the hollow penetration body 10 has a generally cylindrical shape comprising a front portion 11, a central portion 12 and a rear portion 13.
- the front part 11, or nose has two successive warheads 11a and 11b ending in a penetration point Ile.
- the double-warped shape of the front portion 11 facilitates penetration of the penetration body 10 into the hard targets and allows an optimal distribution of the stresses generated during the penetration phase.
- An internal empty zone or hollow 14 is defined inside the trunk 12. This hollow 14 extends over the entire length of the latter and contains an active material 20.
- the rear portion 13 of the penetration body 10, or base has a tapered conical shape to ensure its continuity with the central portion 12.
- the base 13 provides the interface with the guide systems or is protected in storage by a hood rear guard 15 which is removable.
- a sheath 30 is inserted inside the hollow 14 of the penetration body 10, more precisely inside the active material 20.
- This sheath 30 encloses, for example, detonation initiation means (not shown) and possibly guide means and / or propulsion means.
- An inner sheath 31 also passes through the active material 20.
- the sheath 31 allows in particular the passage of cables (not shown) for cooperating with the detonation means.
- the sheath 31 is connected on the one hand to a sleeve tip 32 fixed to the sheath 30 by means of a tip nut 33, and to an accessory shaft 40. In order to ensure a level of safety sufficient, the fasteners of the sleeve 31 to the accessory well 40 and the sheath 30 are perfectly sealed.
- the sheath 31 is also made of a material resistant on the one hand to the chemical attack of the various elements constituting the active ingredient and on the other hand to the mechanical forces generated during the life of the product (storage, handling, transport, catapulting,
- the sheath 30 is connected on the one hand to the tip nut 33 and on the other hand to a closure plate 34 by means of a sheath nut 35 protected by a removable protective cap 36 for the storage of the bomb. Since the bomb 1 is intended for the penetration of hard targets, the sheath 30 is therefore capable of withstanding the decelerations generated by the penetration and the stresses generated by all the elements with which it is interfaced under all the conditions of use applicable to this type of material. Furthermore, the sheath 30 is designed to best ensure the transmission of shock waves between the detonation means and the active or inert material.
- the accessory shaft 40 is fixed directly on the penetration body 10, more precisely on its trunk 12, by means of screws 42 provided to be sheared during an impact of the bomb 1 against an obstacle generating a deceleration exceeding a determined value, for example of the order of 500 G negative.
- Accessory well 40 meets the military standards of the general skilled use bomb, particularly in terms of its positioning.
- the accessory well 40 allows the assembly of a generator necessary for the operation of the cocking system when it is not directly connected to the aircraft, and is protected by a waterproof and removable protective plug 43 in the part of the storage of the bomb.
- Two suspension ring wells 50 and 51 are fixed on the penetration body 10, at its trunk 12. Each suspension ring well is fixed to the trunk 12 by means of screws 52 provided to be sheared during impact of the bomb 1 against an obstacle generating a deceleration exceeding a determined value, for example of the order of 500 G negative.
- the distance between the center of the suspension ring wells is normalized and is identical to that of a qualified general purpose spray. This makes it possible to hang the bomb 1 of the present invention under many types of aircraft.
- the suspension of the bomb 1 is for example made using NATO standard suspension rings which are the interface with the aircraft.
- the front suspension ring well 50 and the accessory well 40 are made in one piece, the three wells being made of a strong metallic material. Furthermore, the two suspension ring wells 50 and 51 are each closed by a waterproof and removable protective cap 53 for storing the bomb.
- An aerodynamic outer coating 60 is disposed around the penetration body 10.
- the outer coating 60 is integral with the penetration body 10, that is to say that it is not removable once installed and that it can not be removed. to be separated from the penetrating body 10 only after a violent shock capable of destroying it, in particular during the penetration of the bomb into a hard target.
- the outer liner 60 is generally cylindrical in shape. It extends over the entire length of the penetrating hollow body 10.
- the outer coating 60 has an outer profile, a mass and a spatial arrangement around the penetration body 10 determined so as to give the bomb 1, provided with said coating, the same dimensional, volume, mechanical, aerodynamic and inertial characteristics (mass, center of gravity and moments of inertia) as a qualified general purpose bomb, for example an Mk82 model. More specifically, the outer coating 60 comprises three identical longitudinal elements 62 each fixed directly on the entire length of the penetration body 10. In other words, each of these elements 62 extends integrally from one end to the other of the penetration body 10. Each longitudinal element 62 covers one-third of the circumference of the penetration body, that is 120 °.
- the longitudinal members 62 are thermoformed and made of a fiber-reinforced plastics material, such as a Sheet Molding Compound (SMC), for example a polyester and graphite filled fiberglass blend. More specifically, according to a particular embodiment, the longitudinal elements 62 consist of a polyester resin in a proportion by weight ranging from 50% to 100%, glass fibers in a proportion by weight included in the present invention. range from 0% to 30%, for example 10%, the remainder (at most 20%) consisting of graphite and additives ensuring the lightness of the material (density of 0.74 to 0.86 g / dm 3 ) and its electrical conductivity.
- SMC Sheet Molding Compound
- Each longitudinal element 62 has a housing 64 receiving a balancing flange 70 made of a high density material, for example greater than or equal to that of steel, and contributing to impart to the bomb 1 said volumetric, dimensional, mechanical characteristics , aerodynamic and inertial identical to those of a general purpose bomb. More precisely, these flanges 70 make it possible to move the mass of inertia around the periphery of the bomb for a better distribution of the masses with respect to its main axes of inertia.
- a balancing flange 70 made of a high density material, for example greater than or equal to that of steel, and contributing to impart to the bomb 1 said volumetric, dimensional, mechanical characteristics , aerodynamic and inertial identical to those of a general purpose bomb. More precisely, these flanges 70 make it possible to move the mass of inertia around the periphery of the bomb for a better distribution of the masses with respect to its main axes of inertia.
- Each balancing flange 70 is fixed directly to the hollow penetration body 10 by means of screws 72 intended to be sheared during an impact of the bomb 1 against an obstacle generating a deceleration exceeding a determined value, for example of the order of 500 G negative.
- One of the flanges 70 has three orifices 75 for the passage of the two suspension ring wells 50 and 51 and the accessory well 40.
- Each longitudinal element 62 is bonded directly to the penetrating hollow body 10, for example to the using a glue polyurethane. Once stuck, they can not be separated unless they are destroyed.
- each flange 70 is locally bonded to an area of the corresponding longitudinal element 62 with the same polyurethane glue.
- the outer coating 60 further comprises a thin protective coating 80 surrounding it integrally.
- the protective coating 80 is made of a material capable of withstanding shocks defined by the aeronautical standard Gam EG13, in particular handling or transport shocks, or in the event of a fall when the bomb is suspended on the aircraft.
- the protective coating 80 also resists abrasion.
- the material chosen is, for example, a monolayer elastomeric polyurethane which is cast directly around the longitudinal elements 62 and flanges 70, over a thickness of a few millimeters, for example 3 millimeters, so that the profile of the bomb 1, once coated by the protective coating 80, is identical to that of the general purpose spray.
- the protective coating 80 also has three orifices 85 facing the three orifices 75 of one of the flanges 70 so that the accessory well 40 and the suspension ring wells 50 and 51 are accessible from the outside the bomb 1 and flush with said protective coating 80.
- the bomb 1 comprises a hollow front sleeve 90 intended to enclose equipment participating in its operation, for example laser guiding means, a gyroscope or an accelerometer.
- the hollow sleeve 90 is attached directly to the penetrating hollow body 10, more precisely to the front part 11 of the latter.
- the front sleeve 90 has a rear internal thread 91 intended to cooperate with an external thread Hd located between the zones Ha and Hb of the front portion 11 of the penetrating hollow body 10.
- the front sleeve 90 also has an internal thread. before 92 which interfaces with the guidance systems and is protected, for the storage of the bomb, by a removable protective cap 95. Because the coating provides the bomb 1 with the same dimensional, volume, mechanical, aerodynamic and inertial characteristics as a general purpose bomb, for example of the Mk82 type, it is not necessary to make it pass through. full qualification tests that are long and costly.
- thermoformed elements and flanges around the penetration body there may be more or less than three thermoformed elements and flanges around the penetration body.
- plastics used are given for information only and may be replaced by other materials with identical or similar characteristics, including mechanical and resistance to chemical attack or fire.
Abstract
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
BRPI0720586-4A2A BRPI0720586A2 (pt) | 2006-12-21 | 2007-12-20 | Bomba aérea de penetração equipada com um revestimento externo |
AT07872427T ATE470835T1 (de) | 2006-12-21 | 2007-12-20 | Ummantelte penetrationsfliegerbombe |
KR1020097014836A KR20090113827A (ko) | 2006-12-21 | 2007-12-20 | 덮개로 덮어진 관통 투하 폭탄 |
DE602007007118T DE602007007118D1 (de) | 2006-12-21 | 2007-12-20 | Ummantelte penetrationsfliegerbombe |
EP07872427A EP2095059B1 (fr) | 2006-12-21 | 2007-12-20 | Bombe aerienne de penetration munie d'un revetement externe |
CN200780047308XA CN101578492B (zh) | 2006-12-21 | 2007-12-20 | 带外罩的穿透型航空炸弹 |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0655788A FR2910612B1 (fr) | 2006-12-21 | 2006-12-21 | Bombe aerienne de penetration munie d'un revetement externe. |
FR0655788 | 2006-12-21 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2008096069A1 true WO2008096069A1 (fr) | 2008-08-14 |
Family
ID=38288543
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2007/002143 WO2008096069A1 (fr) | 2006-12-21 | 2007-12-20 | Bombe aerienne de penetration munie d'un revetement externe |
Country Status (10)
Country | Link |
---|---|
EP (1) | EP2095059B1 (fr) |
KR (1) | KR20090113827A (fr) |
CN (1) | CN101578492B (fr) |
AT (1) | ATE470835T1 (fr) |
BR (1) | BRPI0720586A2 (fr) |
DE (1) | DE602007007118D1 (fr) |
ES (1) | ES2346817T3 (fr) |
FR (1) | FR2910612B1 (fr) |
WO (1) | WO2008096069A1 (fr) |
ZA (1) | ZA200905070B (fr) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2011054361A1 (fr) * | 2009-11-04 | 2011-05-12 | Diehl Bgt Defence Gmbh & Co. Kg | Bombe aérienne |
US20160377396A1 (en) * | 2014-02-11 | 2016-12-29 | Raytheon Company | Munition with multiple fragment layers |
US10228223B1 (en) * | 2016-12-15 | 2019-03-12 | The United States Of America As Represented By The Secretary Of The Navy | Cook-off mitigation systems |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9810513B2 (en) | 2014-08-04 | 2017-11-07 | Raytheon Company | Munition modification kit and method of modifying munition |
US9739583B2 (en) | 2014-08-07 | 2017-08-22 | Raytheon Company | Fragmentation munition with limited explosive force |
US9909848B2 (en) | 2015-11-16 | 2018-03-06 | Raytheon Company | Munition having penetrator casing with fuel-oxidizer mixture therein |
WO2019048914A1 (fr) * | 2017-09-09 | 2019-03-14 | Ruag Ammotec Ag | Projectile de sécurité blindé conçu en particulier pour des applications polyvalentes |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2968244A (en) * | 1948-05-07 | 1961-01-17 | Jr Leo Maas | Jet accelerated missile |
FR2155008A5 (fr) * | 1971-10-04 | 1973-05-18 | Mulleman Michel | |
FR2688304A1 (fr) * | 1992-03-05 | 1993-09-10 | Mulleman Michel | Corps de bombe perfectionne, procede de fabrication de tels corps de bombe, et bombes de divers types equipees d'un tel corps. |
US6227096B1 (en) * | 1999-06-22 | 2001-05-08 | The Boeing Company | Universal warhead adapter, and missile and method incorporating same |
US7261042B1 (en) * | 2004-07-08 | 2007-08-28 | Lockheed Martins Corporation | Insensitive munition design for shrouded penetrators |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB168837A (en) * | 1917-01-08 | 1921-09-12 | Vicente Almonacid | Improvements in or relating to projectiles particularly for use on aircraft |
US1557082A (en) * | 1921-09-01 | 1925-10-13 | Newton Henry | Shell and bomb |
CN1731073A (zh) * | 2005-08-29 | 2006-02-08 | 陈嘉农 | 一种可以调节损伤毁坏威力的航空炸弹 |
-
2006
- 2006-12-21 FR FR0655788A patent/FR2910612B1/fr not_active Expired - Fee Related
-
2007
- 2007-12-20 AT AT07872427T patent/ATE470835T1/de not_active IP Right Cessation
- 2007-12-20 ES ES07872427T patent/ES2346817T3/es active Active
- 2007-12-20 KR KR1020097014836A patent/KR20090113827A/ko not_active Application Discontinuation
- 2007-12-20 DE DE602007007118T patent/DE602007007118D1/de active Active
- 2007-12-20 WO PCT/FR2007/002143 patent/WO2008096069A1/fr active Application Filing
- 2007-12-20 CN CN200780047308XA patent/CN101578492B/zh not_active Expired - Fee Related
- 2007-12-20 BR BRPI0720586-4A2A patent/BRPI0720586A2/pt not_active IP Right Cessation
- 2007-12-20 EP EP07872427A patent/EP2095059B1/fr not_active Not-in-force
-
2009
- 2009-07-10 ZA ZA200905070A patent/ZA200905070B/xx unknown
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2968244A (en) * | 1948-05-07 | 1961-01-17 | Jr Leo Maas | Jet accelerated missile |
FR2155008A5 (fr) * | 1971-10-04 | 1973-05-18 | Mulleman Michel | |
FR2688304A1 (fr) * | 1992-03-05 | 1993-09-10 | Mulleman Michel | Corps de bombe perfectionne, procede de fabrication de tels corps de bombe, et bombes de divers types equipees d'un tel corps. |
US6227096B1 (en) * | 1999-06-22 | 2001-05-08 | The Boeing Company | Universal warhead adapter, and missile and method incorporating same |
US7261042B1 (en) * | 2004-07-08 | 2007-08-28 | Lockheed Martins Corporation | Insensitive munition design for shrouded penetrators |
Non-Patent Citations (1)
Title |
---|
BIASS E H: "SCIENTIA POTESTAS EST TRUE OF RUAG", ARMADA INTERNATIONAL, ARMADA INTERNATIONAL, ZURICH, CH, vol. 26, no. 4, August 2002 (2002-08-01), pages 41 - 42, XP001170519, ISSN: 0252-9793 * |
Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2011054361A1 (fr) * | 2009-11-04 | 2011-05-12 | Diehl Bgt Defence Gmbh & Co. Kg | Bombe aérienne |
US8689694B2 (en) | 2009-11-04 | 2014-04-08 | Diehl Bgt Defence Gmbh & Co. Kg | Flying bomb |
US20160377396A1 (en) * | 2014-02-11 | 2016-12-29 | Raytheon Company | Munition with multiple fragment layers |
US9816793B2 (en) | 2014-02-11 | 2017-11-14 | Raytheon Company | Shock-resistant fuzewell for munition |
US10184763B2 (en) | 2014-02-11 | 2019-01-22 | Raytheon Company | Munition with nose kit connecting to aft casing connector |
US10267607B2 (en) | 2014-02-11 | 2019-04-23 | Raytheon Company | Munition with outer enclosure |
US10401135B2 (en) | 2014-02-11 | 2019-09-03 | Raytheon Company | Penetrator munition with enhanced fragmentation |
US10520289B2 (en) | 2014-02-11 | 2019-12-31 | Raytheon Company | Munition with multiple fragment layers |
US10228223B1 (en) * | 2016-12-15 | 2019-03-12 | The United States Of America As Represented By The Secretary Of The Navy | Cook-off mitigation systems |
Also Published As
Publication number | Publication date |
---|---|
BRPI0720586A2 (pt) | 2014-03-18 |
EP2095059B1 (fr) | 2010-06-09 |
FR2910612B1 (fr) | 2009-10-02 |
ATE470835T1 (de) | 2010-06-15 |
ZA200905070B (en) | 2010-07-28 |
ES2346817T3 (es) | 2010-10-20 |
EP2095059A1 (fr) | 2009-09-02 |
FR2910612A1 (fr) | 2008-06-27 |
CN101578492B (zh) | 2012-12-05 |
CN101578492A (zh) | 2009-11-11 |
KR20090113827A (ko) | 2009-11-02 |
DE602007007118D1 (de) | 2010-07-22 |
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