EP0738869A1 - Entsichern eines militärischen Explosivkörpers mittels unterschiedlicher Ausdehnungskoeffizienten - Google Patents

Entsichern eines militärischen Explosivkörpers mittels unterschiedlicher Ausdehnungskoeffizienten Download PDF

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Publication number
EP0738869A1
EP0738869A1 EP96400830A EP96400830A EP0738869A1 EP 0738869 A1 EP0738869 A1 EP 0738869A1 EP 96400830 A EP96400830 A EP 96400830A EP 96400830 A EP96400830 A EP 96400830A EP 0738869 A1 EP0738869 A1 EP 0738869A1
Authority
EP
European Patent Office
Prior art keywords
envelope
expansion
face
housing
expansion body
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.)
Withdrawn
Application number
EP96400830A
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English (en)
French (fr)
Inventor
Jacky Lolive
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Protac
Original Assignee
Protac
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Protac filed Critical Protac
Publication of EP0738869A1 publication Critical patent/EP0738869A1/de
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B39/00—Packaging or storage of ammunition or explosive charges; Safety features thereof; Cartridge belts or bags
    • F42B39/20—Packages or ammunition having valves for pressure-equalising; Packages or ammunition having plugs for pressure release, e.g. meltable ; Blow-out panels; Venting arrangements

Definitions

  • the invention relates to the field of envelopes intended to receive a pyrotechnic composition, for example a propellant or an explosive.
  • envelopes are now constructed to allow deconfinement of the pyrotechnic material in the event of a temperature rise due to an accidental cause such as for example a fire.
  • the deconfinement allows the non-explosive combustion of the pyrotechnic material.
  • Deconfinement is obtained by rupture or opening of the envelope in the event of a temperature rise.
  • the opening of the envelope can be obtained in a known manner, for example by means of holes made in the envelope and plugged with materials melting at relatively low temperature such as bismuth alloys. It can also be obtained by locks made from shape memory materials. These locks unlock a part of the envelope when, as a result of a rise in temperature, they recover an earlier shape.
  • An example of such an embodiment is known from patent application No. FR 2,686,410 in the name of the French State for example.
  • the opening can also be obtained by the shearing, in the event of overpressure, of pins holding a piece of the envelope as described for example in patent US 4,423,683 taken in the name of the Secretary of State for the Navy.
  • a housing intended to confine an expansion body.
  • This expansion body completely fills the housing. It has a coefficient of expansion ⁇ 2 .
  • this thrust In case of overheating this confined body exerts on the walls of the housing a thrust. It is this thrust that is used to exert stress on at least one part to be broken. The stress can be exerted directly or indirectly on the part to be broken.
  • the invention relates to a sealed envelope intended to contain a pyrotechnic material and capable of opening by rupture of at least one part, having a coefficient of expansion ⁇ 1 , to break the along a fracture surface when the envelope is subjected to an outside temperature above a predetermined value characterized in that the envelope comprises at least one housing having two bearing faces, a first and a second substantially parallel to the minus one of the fracture surfaces, each housing confining an expansion body with expansion coefficient ⁇ 2 greater than ⁇ 1 , each body having two bearing faces, a first and a second, the expansion of each expansion body transmitting , in a direction substantially perpendicular to each of the fracture surfaces, forces to at least one part to be broken.
  • each part to be broken is broken by the tensile stress which is exerted at the level of the weakest part of this part.
  • this weakening is achieved by means of a rupture initiator constituted by a groove.
  • the bearing faces of the housing and of the expansion body are said to be substantially parallel to the fracture surface, and not simply parallel because it may be necessary for the overall architecture or to ensure better confinement of the expansion body d '' slightly tilt the support faces.
  • the bearing faces are located perpendicular to an axial direction of the expansion body perpendicular to the fracture surface.
  • FIG 1 shows the preferred embodiment.
  • This is the rear part of a propellant 20.
  • This propellant comprises, in a known manner, an envelope 30 made up of several parts and in particular of a lateral ferrule 1 of revolution about an axis XX 'onto which is screwed a rear bottom 2, which bottom comprises a nozzle 3 closed in a known manner by a nozzle cover 4 shown diagrammatically.
  • the interior of the casing 30 comprises a propellant 5.
  • a front part of the bottom 2 comprises a housing annular 8.
  • This housing has the shape of a torus generated by the rotation of a rectangle around the axis XX 'of the propellant.
  • the accommodation is open to the front. It has two lateral faces of revolution around XX ′, an internal lateral face 10 and an external lateral face 11. It finally has a face 12 which constitutes the bottom of the housing.
  • the casing 2 is made of steel with an expansion coefficient ⁇ 1 .
  • the ring 13 is in this embodiment, zinc. It has four faces, an internal revolution face 14, this face is in contact with the internal revolution face 10 of the housing 8, an external revolution face 15, this face is in contact with the external revolution face 11 of the housing, a rear face 16, this rear face is in contact with the bottom 12 of the housing.
  • the ring 13 finally has a front face 17. When the rear bottom 2 is screwed onto the ferrule 1, a rear part 18 of the ferrule 1 fills the part of the housing 8 which is not filled by the ring 13.
  • FIG. 2 This figure represents the detail A of FIG. 1.
  • l represents the dimension of the ring 13 which is parallel to the axis XX '.
  • L represents a length which is taken into account for the calculation of the relative elongations. It is a length where the thickness of material on which the ring 13 will exert a stress is greater than the thickness between the bottom of the groove 21 and the external face 11 of the housing 8 but less than the parts located on either side of a hollow 22 having precisely this length L.
  • S 1 denotes the surface of a circular crown comprised between two circles, a first circle having the diameter of the diameter of the cylindrical surface constituting the bottom 23 of the groove and a second circle having the diameter of the diameter of the cylindrical surface 24 from from which the bottom of the groove 21 is hollowed out.
  • the stress ⁇ 1 in the weakest section is therefore ⁇ 1 l ⁇ ( ⁇ 2 - ⁇ 1 ) E e + S 1 S 2 (( The )
  • the preferred embodiment relates to a 150 mm caliber propellant.
  • the ferrule 1 and the bottom 2 are made of steel, the ring 13 is made of zinc.
  • the tensile strength of the steel should be reached between 140 and 180 ° C.
  • the rupture should take place between 180 and 230 ° C.
  • FIG. 4 illustrates a second embodiment of the invention.
  • This figure represents a longitudinal section of part of an envelope of a military charge, in which the invention is incorporated.
  • This envelope 40 comprises a cylindrical ferrule 31 of revolution about an axis XX '.
  • This ferrule is closed on its rear part, the only one shown in FIG. 4, by a flange 29 by means of studs 28, for example eight studs distributed regularly on the flange 29.
  • This stud has a head 27 and a rod 26 terminated by a threaded part 25.
  • the rod has a weakened part 32 by digging a groove 33 shown excessively deep in FIG. 4. This groove is hollowed out from the external surface 35 of the rod 26.
  • Each stud 28 contributes to maintaining the flange 29.
  • Each stud 28 is screwed into a filter 34 of the shell.
  • This thread is located at the bottom of a blind hole 35 of axis YY 'of the ferrule.
  • This blind hole is hollowed out from the contact surface 36 between the ferrule 31 and the flange 29.
  • the end of the blind hole 35 located on the side of the surface 36 therefore opposite the bottom has a part 37 whose diameter is greater than diameter of the bottom of the blind hole comprising the threaded part 34.
  • This part 37 has a cylindrical lateral surface 38 and a bottom 12 constituted by a circular annular crown having as axis the axis YY 'of the blind hole.
  • the small circle of this crown has the diameter of the clearance near the diameter of the rod 26.
  • the volume delimited by the surfaces 38, 12 and a cylinder centered on the axis YY 'of the blind hole and having the diameter of the rod diameter 26 constitutes a housing 8.
  • This housing 8 is filled by an expansion body in the shape of an O-ring 13 made of a material with a coefficient of expansion ⁇ 2 greater than the coefficient ⁇ 1 of the material constituting the ferrule 31 or the rod 26.
  • This material has a face 16 in contact with the face 12 of the housing 8.
  • the opposite face 17 of this ring is in tight contact with the flange 29.
  • the housings 8 are annular and situated around the stud rods. It could for example be blind holes not threaded filled by the bodies 13 and closed by the establishment of the flange. It suffices that the flange is rigid enough at the temperatures envisaged to transmit the force to the studs or to weakened parts of the flange.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Connection Of Plates (AREA)
  • Gasket Seals (AREA)
EP96400830A 1995-04-18 1996-04-18 Entsichern eines militärischen Explosivkörpers mittels unterschiedlicher Ausdehnungskoeffizienten Withdrawn EP0738869A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9504594 1995-04-18
FR9504594A FR2733316A1 (fr) 1995-04-18 1995-04-18 Muratisation par dilatation differentielle

Publications (1)

Publication Number Publication Date
EP0738869A1 true EP0738869A1 (de) 1996-10-23

Family

ID=9478190

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96400830A Withdrawn EP0738869A1 (de) 1995-04-18 1996-04-18 Entsichern eines militärischen Explosivkörpers mittels unterschiedlicher Ausdehnungskoeffizienten

Country Status (2)

Country Link
EP (1) EP0738869A1 (de)
FR (1) FR2733316A1 (de)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2004015360A1 (en) * 2002-08-12 2004-02-19 Qinetiq Limited Temperature responsive safety devices for munitions
WO2009013456A1 (en) * 2007-07-25 2009-01-29 Qinetiq Limited Rupturing devices
FR2922638A1 (fr) * 2007-10-23 2009-04-24 Tda Armements Sas Soc Par Acti Chargement energetique a deconfinement controle et munition equipee d'un tel chargement
EP2335010A1 (de) * 2008-10-10 2011-06-22 Saab AB Patronenhülse und solch eine patronenhülse umfassende munition
US8082846B2 (en) 2002-08-12 2011-12-27 Qinetiq Limited Temperature responsive safety devices for munitions

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3887991A (en) * 1974-05-17 1975-06-10 Us Navy Method of assembling a safety device for rockets
US3992997A (en) * 1975-03-31 1976-11-23 The United States Of America As Represented By The Secretary Of The Navy Warhead casing
US4084512A (en) * 1976-10-18 1978-04-18 The United States Of America As Represented By The Secretary Of The Navy Pressure relief construction for controlled combustion of ordnance items
US4423683A (en) * 1981-12-28 1984-01-03 The United States Of America As Represented By The Secretary Of The Navy Enclosure for a warhead case
US4458482A (en) * 1982-05-17 1984-07-10 The United States Of America As Represented By The Secretary Of The Navy Rocket motor
FR2656085A1 (fr) * 1987-10-13 1991-06-21 Thomson Brandt Armements Munition explosive protegee contre l'elevation de temperature.
US5044154A (en) * 1989-11-27 1991-09-03 Thiokol Corporation Safety mechanism for rendering a rocket motor non-propulsive
FR2686410A1 (fr) * 1992-01-22 1993-07-23 France Etat Armement Dispositif assurant le deconfinement d'une charge contenant un explosif par mise en óoeuvre d'un element deformable en materiau a memoire de forme.
US5361703A (en) * 1992-05-26 1994-11-08 The United States Of America As Represented By The Secretary Of The Navy Inert thermally activated burster

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3887991A (en) * 1974-05-17 1975-06-10 Us Navy Method of assembling a safety device for rockets
US3992997A (en) * 1975-03-31 1976-11-23 The United States Of America As Represented By The Secretary Of The Navy Warhead casing
US4084512A (en) * 1976-10-18 1978-04-18 The United States Of America As Represented By The Secretary Of The Navy Pressure relief construction for controlled combustion of ordnance items
US4423683A (en) * 1981-12-28 1984-01-03 The United States Of America As Represented By The Secretary Of The Navy Enclosure for a warhead case
US4458482A (en) * 1982-05-17 1984-07-10 The United States Of America As Represented By The Secretary Of The Navy Rocket motor
FR2656085A1 (fr) * 1987-10-13 1991-06-21 Thomson Brandt Armements Munition explosive protegee contre l'elevation de temperature.
US5044154A (en) * 1989-11-27 1991-09-03 Thiokol Corporation Safety mechanism for rendering a rocket motor non-propulsive
FR2686410A1 (fr) * 1992-01-22 1993-07-23 France Etat Armement Dispositif assurant le deconfinement d'une charge contenant un explosif par mise en óoeuvre d'un element deformable en materiau a memoire de forme.
US5361703A (en) * 1992-05-26 1994-11-08 The United States Of America As Represented By The Secretary Of The Navy Inert thermally activated burster

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2004015360A1 (en) * 2002-08-12 2004-02-19 Qinetiq Limited Temperature responsive safety devices for munitions
US7549375B2 (en) 2002-08-12 2009-06-23 Qinetiq Limited Temperature responsive safety devices for munitions
US8082846B2 (en) 2002-08-12 2011-12-27 Qinetiq Limited Temperature responsive safety devices for munitions
WO2009013456A1 (en) * 2007-07-25 2009-01-29 Qinetiq Limited Rupturing devices
US8616131B2 (en) 2007-07-25 2013-12-31 Qinetiq Limited Rupturing devices
FR2922638A1 (fr) * 2007-10-23 2009-04-24 Tda Armements Sas Soc Par Acti Chargement energetique a deconfinement controle et munition equipee d'un tel chargement
EP2053344A1 (de) * 2007-10-23 2009-04-29 Tda Armements S.A.S. Energetische Ladung mit kontrollierter Entsicherung und Munition, die mit einer solchen Ladung ausgerüstet ist
EP2335010A1 (de) * 2008-10-10 2011-06-22 Saab AB Patronenhülse und solch eine patronenhülse umfassende munition
EP2335010A4 (de) * 2008-10-10 2013-03-27 Saab Ab Patronenhülse und solch eine patronenhülse umfassende munition

Also Published As

Publication number Publication date
FR2733316A1 (fr) 1996-10-25

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