EP2461129A1 - Dispositif de durcissement d'une liaison mecanique de propulseur pour munition de mortier et munition comportant une telle liaison - Google Patents

Dispositif de durcissement d'une liaison mecanique de propulseur pour munition de mortier et munition comportant une telle liaison Download PDF

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Publication number
EP2461129A1
EP2461129A1 EP11191656A EP11191656A EP2461129A1 EP 2461129 A1 EP2461129 A1 EP 2461129A1 EP 11191656 A EP11191656 A EP 11191656A EP 11191656 A EP11191656 A EP 11191656A EP 2461129 A1 EP2461129 A1 EP 2461129A1
Authority
EP
European Patent Office
Prior art keywords
ammunition
thruster
rear body
envelope
longitudinal axis
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Withdrawn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
EP11191656A
Other languages
German (de)
English (en)
French (fr)
Inventor
Patrick Cohe
Bertrand Dubois
Fabien Moreau
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.)
TDA Armements SAS
Original Assignee
TDA Armements SAS
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 TDA Armements SAS filed Critical TDA Armements SAS
Publication of EP2461129A1 publication Critical patent/EP2461129A1/fr
Withdrawn legal-status Critical Current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
    • F42B5/00—Cartridge ammunition, e.g. separately-loaded propellant charges
    • F42B5/02—Cartridges, i.e. cases with charge and missile
    • F42B5/067—Mounting or locking missiles in cartridge cases
    • F42B5/073—Mounting or locking missiles in cartridge cases using an auxiliary locking element
    • 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 propelled type ammunition and in particular a device for self-hardening of a mechanical connection between the ammunition and its propellant.
  • Propelled artillery ammunition is, for example, missiles, rockets, or guided and / or long-range powered munitions.
  • the propellant of the ammunition includes a pyrotechnic propulsion charge that will be active during the use of the ammunition.
  • powered ammunition must meet invulnerability requirements. For this purpose, they must be designed and constructed in such a way as to withstand, or at least minimize, the pyrotechnic reactions due to aggression external to the munition and the thruster such as, the heat caused by a fire, a fuel fire, a fire, slow heating by external or climatic causes, the impact of a bullet, the impact of heavy or light shrapnel from other ammunition, the effect of a hollow charge, a fall of the ammunition from a height of 12 meters; to withstand other constraints or effects that can activate the pyrotechnic loading of the thruster; to ensure no detonation by influence.
  • the invulnerability of the ammunition must be, moreover, maintained throughout the life of the ammunition that is to say from storage until firing of the ammunition.
  • the choice of the propellant pyrotechnic loading compositions in particular in the sensitivity to initiation, the choice of materials, the mechanical characteristics and the geometry such as the thickness of the propellant envelope containing the propellant charge contribute to a great extent to obtaining the invulnerability requirements.
  • the ammunition In propellant ammunition of the state of the art the ammunition is firmly connected to the thruster by rigid links so as to ensure normal operation of the ammunition during firing.
  • the thrusters of these types of ammunition of the state of the art include deconfinement safeties, for example, thinning in certain areas of the thruster wall to release accidental combustion gases from the engine. pyrotechnic loading.
  • the pressure necessary to break the thruster wall for deconfinement must be very important so as not to impair its ability to propel in normal operation, which represents a danger to personnel when handling or storing the propelled munition.
  • the invulnerability of this type of ammunition of the state of the art is not always assured in time.
  • the first mechanical link is in the activated state, the entire pins making the propulsion unit of the munition integral in rotation and in translation.
  • the rear ammunition body comprises on either side of the longitudinal axis ZZ 'two notches and the casing of the propeller two pins, a pin being inserted into a respective notch on either side of said longitudinal axis ZZ 'to make integral in rotation, along the axis ZZ', the ammunition and the thruster.
  • the envelope is delimited, on the side of the munition, by an envelope edge in a plane perpendicular to the longitudinal axis ZZ '.
  • the ammunition body of circular cylindrical shape having the same external diameter D2 as that of the thruster casing, is extended inside said casing by the ammunition rear body in the form of a section cylinder.
  • circular of diameter D1 forming a crown-shaped shoulder in a plane perpendicular to the longitudinal axis ZZ ', the rear ammunition body terminating in the envelope by an end surface in another plane perpendicular to the longitudinal axis ZZ' .
  • the envelope contains a pyrotechnic chamber containing a pyrotechnic propulsion charge, the pyrotechnic chamber having thermal protection walls of the pyrotechnic charge, a tube-shaped thermal protection wall, in contact with the inner surface of the pyrotechnic charge. 'envelope, closed on the side of the munition, by another thermal protection wall perpendicular to the longitudinal axis ZZ'.
  • the envelope of the thruster comprises, on the side of the other thermal protection wall of the pyrotechnic chamber, a circular cylindrical movable bottom of the same diameter D1 as the inner surface of the envelope, of axis of revolution. coincident with the longitudinal axis ZZ 'having two faces in planes perpendicular to the axis ZZ', a face in contact with a heat shield wall and another face on the rear body side of the munition having a circular recess for holding in the longitudinal axis ZZ 'of a helically shaped spring, the spring being inserted between said movable bottom and the ammunition rear body end surface to ensure a distance L1 forming a clearance J1 between the other side of the bottom mobile and ammunition rear body.
  • the thruster shell has holes near the shell edge in a plane perpendicular to the axis ZZ ', the rear ammunition body having other respective holes in the same plane perpendicular to the ZZ 'axis vis-a-vis the holes of the thruster casing for the insertion of force pins, the positions of the holes near the edge of the envelope and those of the other holes in the rear body of ammunition being such when the pins are inserted into the respective holes of the shell and the ammunition rear body, the shoulder the ammunition body and the envelope edge are separated by a distance L2 to form a game J2.
  • the clearance J2 is smaller than the clearance J1 so that after shearing the pins during firing, the envelope edge and the shoulder coming into contact, there is still a space between the end surface. ammunition rear body and the other side of the movable bottom.
  • the shear strength of the second mechanical bond is greater than the shear strength of the first mechanical bond.
  • shear pins and the snap ring are secured to the munition by means of a thruster bottom, itself secured to the thruster.
  • the thruster bottom is in the form of a ring closed by a bottom wall in a plane perpendicular to the longitudinal axis ZZ ', the circular cylindrical outer surface of the bottom comprises the shoulder, the holes for the pins, the groove having the snap ring and the groove having the body seal, the side of the bottom wall of the thruster side having the same function as the end surface.
  • a circular cylindrical inner portion of the thruster bottom has a thread for fixing by screwing the ammunition rear body which also comprises a thread screwing on the thread of the thruster bottom.
  • the propelled munition is equipped during its storage phase, transport and maintenance, a locking belt in the activated state of the first mechanical link.
  • the blocking belt in the form of a tube of outside diameter D5 greater than the diameter D2 of the surface external of the thruster, partially surrounding the ammunition body and the envelope, has an inner ring-shaped portion inserted between the envelope and the ammunition body to prohibit their approximation.
  • a main purpose of the propelled munition according to the invention is to obtain a deconfinement of the propellant of the ammunition with a low pressure of the gases due to an accidental combustion of the pyrotechnic charge of the propellant.
  • Another object of the invention is to obtain a reliable deconfinement over time of an ammunition propellant.
  • Another object of the invention is to provide a hardenable mechanical connection between the thruster and the ammunition, automatically, by the thrust generated on the ammunition during firing.
  • the figure 1a is a partial view in axial section of a mortar projectile, according to the invention, comprising a self-hardenable mechanical connection.
  • the figure 1b a detailed view of the figure 1 at.
  • the mortar projectile comprises, along a longitudinal axis ZZ ', a munition 10 having an ammunition body 12, a thruster 20 of said ammunition 10, a first and a second mechanical link 24 between the ammunition and the thruster.
  • a munition 10 having an ammunition body 12, a thruster 20 of said ammunition 10, a first and a second mechanical link 24 between the ammunition and the thruster.
  • Each may take an activated state rendering the ammunition thruster 20 or a deactivated state integral, releasing the thruster 20 from the ammunition 10.
  • the figure 1b shows the zone of the mortar projectile comprising the mechanical links, the first mechanical link essentially comprises shear pins.
  • the second mechanical connection is a self-curing device, described below, of the mechanical connection between the munition 10 and the propellant 20.
  • the thruster comprises a tube-shaped envelope 30 of circular section having an internal surface 31 of internal diameter D1 and an external surface of external diameter D2.
  • the envelope 30 is delimited, on the side of the munition, by an envelope edge 32 in a plane perpendicular to the longitudinal axis ZZ '.
  • the casing 30 encloses a pyrotechnic chamber 33 containing a pyrotechnic propellant charge 34.
  • the pyrotechnic chamber 33 comprises thermal protection walls of the pyrotechnic charge, a heat-shielding wall 40 in the form of a tube, contact with the inner surface 31 of the casing 30, closed on the side of the munition, by another thermal protection wall 44 perpendicular to the longitudinal axis ZZ '.
  • the munition body 12, of circular cylindrical shape having the same external diameter D2 of the casing 30 of the propellant, is extended inside said casing 30 by a rear body 50 of cylindrical ammunition of circular section similarly diameter D1 than that of the inner surface of the casing 30 forming a shoulder 51 in the shape of a ring in a plane perpendicular to the longitudinal axis ZZ '.
  • the ammunition rear body 50 terminates in the envelope 30 by an end surface 54 in another plane perpendicular to the longitudinal axis ZZ '.
  • the rear body 50 of the ammunition can slide inside the casing 30 along the longitudinal axis ZZ 'and has on its surface a ring groove 56 for the insertion of a snap ring 58.
  • the pyrotechnic chamber 33 comprises, on the side of the other thermal protection wall 44, a circular cylindrical movable base 60 of the same diameter D1 as the inner surface of the envelope, of axis of revolution coinciding with the longitudinal axis ZZ ' having two faces in planes perpendicular to the axis ZZ, one face 61 in contact with the thermal protection wall 44 and another face 62 on the side of the body of the munition having a circular recess 63 for holding in the longitudinal axis ZZ a spring 64 of helical shape.
  • the spring 64 is inserted between said movable base 60 and the ammunition rear body end surface 54 to provide a distance L1 forming a clearance J1 between the other face 62 of the movable base 60 and the rear body 50 of the munition.
  • the mortar projectile further comprises the first mechanical link having a series of shear pins 70 inserted into the shell and the munition body regularly distributed about the longitudinal axis ZZ 'in a plane Pg perpendicular to the longitudinal axis ZZ 'making the ammunition and the thruster integral during a storage or manipulation phase before firing.
  • the activated state of this first mechanical connection corresponds to whole pins 70 not broken by shear forces, the deactivated state corresponds to the shearing of the pins.
  • the figure 2a shows an external view of the connection area between the ammunition and the propellant of the mortar projectile of the figure 1a .
  • the figure 2b a perspective view of the connection area of the figure 2b .
  • the projectile is subjected to rotational forces during its ejection of the barrel, in which case the ammunition 10 and the thruster 20 must remain rotationally fixed around the barrel.
  • 'longitudinal axis ZZ' when the shear pins are cut, or in the deactivated state, when fired.
  • the rear body 50 of ammunition comprises on either side of the longitudinal axis ZZ 'two notches 72, 74 and the envelope 30 of the propeller two pins 76, 78, a pin being inserted into a respective notch on both sides of the longitudinal axis ZZ '.
  • the envelope 30 of the thruster comprises holes 80 near its edge 32 in a plane perpendicular to the axis ZZ '.
  • the rear body 50 of ammunition other holes 82 respectively, in the same plane Pg perpendicular to the axis ZZ ', vis-à-vis the holes 80 of the envelope 30 of the thruster for the insertion of force pins 70 in the envelope 30 and in the rear body 50 of ammunition.
  • the position, along the longitudinal axis ZZ ', of the holes 80 near the edge 32 of the envelope 30 and the position of the other holes 82 in the rear body 50 of the ammunition are such that, when the pins 70 are inserted into the holes 80 of the envelope 30 and in the holes 82 of the ammunition rear body 50, the shoulder 51 of the ammunition body and the envelope edge 32 are separated by a distance L2 to form a game J2 (see FIG. Figure 1 (b) whose function is explained later.
  • the clearance J2 must be smaller than the clearance J1 so that after the shearing of the pins 70 during the firing phase, the envelope edge 32 and the shoulder 51 coming into contact there still remains a space (or one clearance) between the end surface 54 of the ammunition rear body 50 and the other face 62 of the movable floor.
  • the snap ring 58 in the form of a split ring, of axis of revolution coinciding with the longitudinal axis ZZ ', of width E, inserted in the groove of the ring 56 of the surface the rear body 50 of ammunition, is maintained in force to the diameter D1 of the envelope, by said envelope 30 covering it.
  • the uncompressed snap ring 58 before its assembly between the casing 30 and the rear body 50 of the munition has a diameter D3 greater than the internal diameter D1 of the casing 30, or even greater than the diameter D4.
  • the snap ring 58 is, for example, in the form of an elastic ring of diameter D3 having edges separated by a distance sufficient so that, when the snap ring is compressed radially, it can take the diameter D1 of the inner surface 31 of the casing 30 of the propellant.
  • the envelope 30 comprises, on its inner surface 31, a groove 90 having a diameter D4 greater than the diameter D1 of the inner surface 31 of the envelope 30, of width equal to the width E of the snap ring 58 to at least partially contain the snap ring 58 expanding by its elasticity to the diameter D4, when the snap ring 58 is released in said other snap ring groove 90.
  • the ring groove 56, the snap ring 58 and the other ring groove 90 form the second mechanical connection forming the self-hardening device of the mechanical connection between the ammunition and the thruster.
  • This second mechanical connection is in the deactivated state when the snap ring, during the storage phase of the munition, is compressed to the diameter D1 between the inner surface of the envelope and the rear ammunition body and in the state activated during the expansion of the retaining ring (58) in the other ring groove (90) facing the ring groove (56) during a sliding of the envelope (30) on the rear body (50) of ammunition.
  • This second mechanical link will only be activated when firing the ammunition.
  • the distance between the edges of the same side of one 56 and the other 90 locking rod grooves is equal to the clearance J2 between the casing edge 32 and the shoulder 51 of the ammunition body 12 of so that, during the hardening of the propellant / ammunition mechanical connection, the snap ring 58 comes opposite the other ring groove 90 and expand into this other ring groove 90.
  • the rear body 50 has a body groove 94 containing a body seal 96 for sealing between the rear ammunition body 50 and the surrounding environment.
  • the movable bottom 60 has a bottom groove 98 having a bottom seal 100 to seal the pyrotechnic chamber.
  • the figure 1c represents a detailed view of an alternative embodiment of the mortar projectile according to the invention.
  • This variant embodiment of the figure 1 c avoids damaging the body seal 96 when mounting the rear body 50 in the casing 30 of the propellant. Indeed, when the rear body 50 is outside the casing 30, the uncompressed body seal 96 expands and its diameter becomes larger than the diameter D1 of the inner surface 31 of the casing 30.
  • the inner surface 31 of the envelope of diameter D1 extends towards the edge of envelope 32 by another surface 310 of diameter D30 greater than the diameter D1, the rear body 50 having, on the side of the end surface 54, a circular surface of the same diameter D1 extending towards the shoulder 51 by another surface of greater diameter equal to the diameter D30.
  • the diameter D30 should be at least, if not larger, than the outside diameter of the uncompressed body seal 96.
  • the deterioration of the body seal 96 can be avoided by producing, on the surface side 31, chamfers, on the envelope edge 32, on the edge of the hole 80 of the pin 70 and on the edges of the the other groove 90.
  • the figures 1a , 1b , 2a and 2b show the mortar projectile during the storage or handling phase by personnel before firing without aggression of the pyrotechnic charge that could activate it.
  • FIGS. 3a and 3b show two respective stages of operation of the mortar projectile of the figure 1a during a pressure increase in the thruster before firing.
  • the pressure generated in the pyrotechnic chamber 33 tends to move the movable base 60 towards the surface 54 of the rear body 50 of ammunition by compressing the spring 64.
  • the sealing of the pyrotechnic chamber 33 is still ensured by the seal bottom 100 mounted on the periphery of the movable bottom 60.
  • the movable bottom 60 abuts against the rear surface 54 of the rear body 50 of ammunition thus canceling the game J1.
  • An additional increase of the pressure in the pyrotechnic chamber results in the application of the forces F by the movable member 60 on the rear body 50 of ammunition and by stressing the shear pins 70.
  • the shear pins 70 are calibrated to withstand low forces Fg compared to the pressure that may occur in the pyrotechnic chamber. These forces Fg exceeded, the pins 70 break authorizing the release of the envelope 30 of the thruster which moves away from the ammunition. The first mechanical link is then in the deactivated state.
  • the remoteness of the casing of the munition body releases into the environment the pyrotechnic charge 34 with its thermal protection walls 40, 44 and the hot gases Gc produced by the pyrotechnic combustion.
  • the figure 4a represents the mortar projectile of the figure 1 has in a shooting phase.
  • the figure 4b shows an external view of the connection area between the ammunition and the propellant of the mortar projectile of the figure 4a .
  • the mortar projectile is equipped at the end of the thruster with a propulsive tail (not shown in the figures) ensuring the ejection of the mortar projectile from the mortar tube.
  • This ejection phase of the mortar is called internal ballistic phase.
  • the thrust of ejection by the propulsive tail generates a force which, because of the inertia of the ammunition, pushes the thruster 20 against the body 12 of ammunition.
  • Instantly all the pins 70 are sheared passing the first mechanical link from the activated state to the deactivated state.
  • the edge 32 of the envelope 30 of the thruster abuts with the shoulder 51 of the ammunition body thus canceling the clearance J2.
  • the clearance J1 between the end surface 54 of the rear body 50 of the ammunition and the other side 62 of the moving bottom is reduced but still existing, this game J1 being as previously described superior to the game J2 (see FIG. figure 4a ).
  • the other groove 90 on the inner surface 31 of the casing 30 is now opposite the groove 56 on the surface of the rear body 50 of ammunition which allows the ring 58 , which was mounted under stress in the groove of ring 56, to expand in the other ring groove 90 to make again, integral in translation the thruster 20 and the ammunition body 12 more rigidly than that made by the pins 70.
  • the second mechanical link goes from the deactivated state to the activated state.
  • the two pins 76, 78 remain nested and fit without play in the notches 72, 74 respectively still immobilizing in rotation, despite the shearing of the pins 70, the envelope 30 of the thruster with the ammunition body 12 (see figure 4b ).
  • the figure 5a represents the mortar projectile of the figure 1 has in a phase of firing of its thruster.
  • the figure 5b a detailed view of the figure 5a .
  • the fired thruster 20 generates a pressure in the pyrotechnic chamber 33 which tends to compress the spring 64 and move the movable bottom 60 towards the end surface 54 of the rear body 50 of the munition.
  • the sealing of the movable bottom 60 in displacement in the casing 30 of the propellant is provided by the bottom seal 100.
  • the snap ring 58 is in turn subjected to shear stress between the casing 30 and the rear body 50 of ammunition. This snap ring 58 is sized to withstand this effort.
  • the operation of the thruster in this phase is called nominal.
  • the figure 6 shows an alternative embodiment of the hardenable mechanical connection according to the invention of the mortar projectile of the figure 1 at.
  • the shear pins 70 and the snap ring 58 are integral with the munition via a bottom 110 of propellant, itself secured to the propellant.
  • the thruster 20 comprises the thruster bottom 110 of ring-shaped circular cylindrical shape closed by a bottom wall 112 in a plane perpendicular to the axis ZZ '.
  • the circular cylindrical outer surface of the bottom 110 has the shoulder 51, the holes 82 for the pins 70, the groove 56 having the snap ring 58 and the groove 94 having the seal 96.
  • the face of the bottom wall 112 on the thruster side having the same role as the end surface 54 of the previous embodiment.
  • a circular cylindrical internal portion 120 of the thruster bottom 110 comprises a thread 121 for screw fastening the rear body 50 of the munition which also comprises a thread 122 which is screwed onto the thread 121 of the thruster bottom 110.
  • the ammunition is secured to the thruster by the threads 121, 122, the self-hardening device of the ammunition / propellant mechanical link being completely integrated with the thruster.
  • the propeller in this variant of the figure 6 is always equipped with the deconfinement function whether or not it is linked to the ammunition body 12.
  • the mortar projectile can be equipped during its phase of storage, transport and maintenance, a belt 130 for blocking the breaking of the first mechanical link.
  • the figure 7 represents a partial view in axial section of the mortar projectile of the figure 1a having a mechanical connection breaking blocking belt.
  • the belt 130 in the form of a tube of outside diameter D5 greater than the diameter D2 of the external surface of the thruster and the ammunition, partially surrounding the ammunition body 12 and the envelope 30, comprises an inner portion 140 in the form of ring inserted in the game J2 so as to prohibit the approach of the edge of the envelope 32 of the shoulder 51 thus effectively protecting the shear pins 70 during a possible fall of the mortar projectile while retaining the possibility of deconfinement of the thruster 20 in case of fire type aggression.
  • the mortar munition is intended to be introduced into a launch tube having an internal diameter equal (or slightly larger) to the diameter D2 of the munition equipped with its propellant.
  • the mortar ammunition can not be introduced into the launch tube until the belt 130 is removed, because of the diameter of the belt D5 larger than the internal diameter D2 of the launch tube. This is an additional security that prevents the launching of the ammunition without having first removed the belt 130 for blocking the rupture of the first mechanical link.
  • the pins 76, 78 and the notches 72, 74 may be made differently such as a pin or a key in a groove, a splined shaft in a splined hub, or other means making the propellant ammunition rotational but in rotation. allowing translation along the longitudinal axis ZZ '.
  • the shear strength of the second self-hardening mechanical connection formed by the snap ring 58 when inserted into the other groove 90 is much greater than that of the first mechanical connection made by the shear pins 70, thus the deconfinement of the thruster 20 is carried out with a low gas pressure in the pyrotechnic chamber much lower than that required in the deconfining devices of the state of the art propellants .

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Lining And Supports For Tunnels (AREA)
EP11191656A 2010-12-03 2011-12-02 Dispositif de durcissement d'une liaison mecanique de propulseur pour munition de mortier et munition comportant une telle liaison Withdrawn EP2461129A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1004718A FR2968392B1 (fr) 2010-12-03 2010-12-03 Dispositif de durcissement d'une liaison mecanique de propulseur pour munition de mortier et munition comportant une telle liaison

Publications (1)

Publication Number Publication Date
EP2461129A1 true EP2461129A1 (fr) 2012-06-06

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EP11191656A Withdrawn EP2461129A1 (fr) 2010-12-03 2011-12-02 Dispositif de durcissement d'une liaison mecanique de propulseur pour munition de mortier et munition comportant une telle liaison

Country Status (4)

Country Link
US (1) US20120137916A1 (ja)
EP (1) EP2461129A1 (ja)
JP (1) JP2012117809A (ja)
FR (1) FR2968392B1 (ja)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3667227A1 (fr) * 2018-12-13 2020-06-17 Thales Dispositif de deconfinement d'un chargement explosif et munition equipee d'un tel dispositif

Citations (3)

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US5337672A (en) * 1991-11-29 1994-08-16 Thomson-Brandt Armements Locking device for a casing containing pyrotechnic materials
US5398498A (en) * 1994-05-06 1995-03-21 Bei Electronics, Inc. Joint construction between components of military projectile and releasable by melting of fusible eutectic helical member
US6321656B1 (en) * 2000-03-22 2001-11-27 The United States Of America As Represented By The Secretary Of The Navy Thermally actuated release mechanism

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US2937595A (en) * 1955-05-18 1960-05-24 Alco Products Inc Rocket boosters
US3741125A (en) * 1960-11-22 1973-06-26 Us Navy Stabilized rocket head
US3329089A (en) * 1964-12-24 1967-07-04 Herbert L Harrison Retention-release mechanism for reaction motors and rocket interstages
US3855932A (en) * 1973-10-23 1974-12-24 Us Navy Expelling charge ignition system
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DE4116191A1 (de) * 1991-05-17 1992-11-19 Rheinmetall Gmbh Submunition fuer ein drallstabilisiertes traegergeschoss
US5394803A (en) * 1994-02-14 1995-03-07 Bel Electronics, Inc. Joint construction between military rocket motor and warhead and releasable by melting of fusible eutectic wedging ring for operating flexible locking fingers
US5792981A (en) * 1996-10-28 1998-08-11 Thiokol Corporation Gun-launched rocket
JP4056786B2 (ja) * 2001-05-08 2008-03-05 アライアント・テクシステムズ・インコーポレーテッド 圧力容器
US8156867B2 (en) * 2006-07-17 2012-04-17 Raytheon Company Methods and apparatus for multiple part missile

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5337672A (en) * 1991-11-29 1994-08-16 Thomson-Brandt Armements Locking device for a casing containing pyrotechnic materials
US5398498A (en) * 1994-05-06 1995-03-21 Bei Electronics, Inc. Joint construction between components of military projectile and releasable by melting of fusible eutectic helical member
US6321656B1 (en) * 2000-03-22 2001-11-27 The United States Of America As Represented By The Secretary Of The Navy Thermally actuated release mechanism

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3667227A1 (fr) * 2018-12-13 2020-06-17 Thales Dispositif de deconfinement d'un chargement explosif et munition equipee d'un tel dispositif
FR3090086A1 (fr) * 2018-12-13 2020-06-19 Thales Dispositif de deconfinement d’un chargement explosif et munition equipee d’un tel dispositif
US11054229B2 (en) 2018-12-13 2021-07-06 Thales Device for venting an explosive charge and munition equipped with such a device

Also Published As

Publication number Publication date
JP2012117809A (ja) 2012-06-21
FR2968392A1 (fr) 2012-06-08
FR2968392B1 (fr) 2013-06-28
US20120137916A1 (en) 2012-06-07

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