US3754726A - Assembly comprising a self-propelled finned projectile and its case - Google Patents

Assembly comprising a self-propelled finned projectile and its case Download PDF

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Publication number
US3754726A
US3754726A US00157360A US3754726DA US3754726A US 3754726 A US3754726 A US 3754726A US 00157360 A US00157360 A US 00157360A US 3754726D A US3754726D A US 3754726DA US 3754726 A US3754726 A US 3754726A
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United States
Prior art keywords
case
coupling
projectile
rear end
fins
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Expired - Lifetime
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US00157360A
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English (en)
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M Rusbach
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Sarmac SA
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Sarmac SA
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    • 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
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • F42B10/16—Wrap-around fins
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/042—Rocket or torpedo launchers for rockets the launching apparatus being used also as a transport container for the rocket
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/052—Means for securing the rocket in the launching apparatus
    • 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
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel

Definitions

  • This assembly is fitted at its rear end with an insertable member which can be ejected under the effect of the thrust of the propellant gases of the projectile and which locks at least one movable part of a coupling, that is carried by the rear end of the said projectile, to a fixed part of this coupling that is carried by the rear end of the case. All the elements of this fixed coupling part which projects into the interior of the case are ejected under the effect of the thrust of said gases.
  • this retaining means should be capable of readily releasing the projectile at the moment of firing without causing reaction on the launching tube, either as a result of its own mechanical functioning or under the effect of the rush of gases, the free movement of which it might possibly impede.
  • certain retaining means constituted by pins, screws, shear discs etc. are made oversize at the weakest part so as to prevent them from failing prematurely under the effect of vibrations, bending, twisting, impacts etc., so that a greater shear force is thus required at the moment of separation.
  • the object of the invention is to provide an assembly comprising a self-propelled finned projectile and its case, which is used successively as a container and a launching tube, the assembly being characterized in that it is fitted at its rear end with an insertable member which can be ejected under the effect of the thrust of the propellant gases of theprojectile and .whichlocks at least one movable part of a coupling, that is carried by the free end of the latter, to a fixed part of this coupling that is carried by the rear end of the case, all elements of this fixed coupling part projecting into the interior of the case being ejected under the effect of the thrust of said gases.
  • the attached drawing illustrates by way of example one form of construction of the assembly according to the invention and I3 modified forms of this assembly.
  • FIG. 1 of the drawing is a general arrangement view, partly in axial and truncated section, showing the projectile in its case.
  • FIGS. 2 and 3 areaxial sections of part of the arrangement seen in FIG. 1 and illustrating respectively the detachment of the insertable member and the base of the case and the release of the coupling of the projectile from the case after the projectile has been fired.
  • FIGS. 4 to 9, ll, 12, 14 to 17 and 19 are views of parts of modified forms, each of which illustrates in axial section a variant of the coupling of the projectile to the case.
  • FIG. is a cross-section on line XX ofFIG. 9.
  • FIG. 13 is a view of part of the arrangement seen in FIG. 12 and illustrates a fin in elevation.
  • FIG. 18 is a section on line XVIII-XVIII through a detail seen in FIG. 17.
  • FIG. 20 is a cross-section on the line XX-XX through the modified form shown in FIG. 19.
  • the assembly according to the invention comprises a self-propelled finned projectile l and its case 2 which is used successively as a container for storing and transporting the projectile, and as a launching tube for the latter.
  • the case 2 comprises a tubular body 3, a front cover 4 and a rear cover 5.
  • the projectile 1 comprises a forward explosive charge located at 6 and a rear propellant charge located at 7.
  • a venturi 8 enables the propellant gases to escape at the rear of the projectile after the propellant charge 7 has been set off.
  • the fin system comprises fins 9 hinged on a collar 10 and pressed back on the venturi 8 against the action of return springs, not illustrated, while the projectile is contained in the case 2.
  • each of the fins 9 On that of its sides presented to the wall of the tubular body 3 of the case, each of the fins 9 has a projection 11 which engages in a slot 12 cut in the wall of the tubular body 3 of the case opposite said projection 11.
  • Each of the slots 12 is reinforced by a metal part 13 which contains a cavity opposite the slot 12 and is fitted on the outer surface of the tubular body 3 of the case 2,'said metal part on the one hand reinforcing said slot 12 and on the other closing it on one side.
  • An insertable member constituted by a cap 14 is fitted over the opening in the venturi 8 and when so fitted its edge 15 is inserted between the outer wall of the venturi 8 and the free end of each of the fins 9 forming the fin system of the projectile l. The fins 9 are thus pushed against the wall of the tubular body 3 and their projections 11 are locked in the engaged position in the corresponding slot 12 in the case.
  • projections 11 constitute the movable part of a coupling, the fixed part of which is constituted by the corresponding slots 12 in the case and their metal reinforcement 13.
  • This coupling of the rear end of the projectile 1 to the rear end of the case 2 is locked by the cap 14 when its edge 15 is inserted between the outer wall of the venturi 8 and the free ends of the fins 9.
  • v I r r As illustrated in FIG. 2, when the propellant charge 7 of the projectile 1 is fired, the cap 14 is ejected by the thrust of the propellant gases of the projectile I escaping through the venturi 8, and the rear cover 5 is likewise ejected.
  • the venturi 8 and the cap 14 will each have travelled a certain distance in opposite directions, which distance will obviously be proportional to their inertia.
  • the bearing edge 15 of the cap 14 is tapered. This tapered form enables the fin 9 and the coupling to begin to detach themselves from their locking means as soon as displacement of the cap commences. This disengagement is further facilitated by the tapered form of projections 11 on the fins 9 and of the cavities in the metal reinforcements 13, the sloping portions of which form retention means and at the same time a ramped release means.
  • the angle of slope is carefully selected so as to avoid all reaction particularly in the direction in which disengagement takes place.
  • the cap 14 may be replaced by a plug 16, which is fitted in the end of the venturi 8 and comprises an edge 17 which pushes the fins 9 towards the wall of the tubular body 3 of the case so as to lock the projections 11 on said fins 9 in corresponding slots 12 cut in said wall of the tubular body 3 of the case.
  • the free end of the fins 9 extend beyond the end of the venturi 8 so as to lie against said edge 17 of the plug 16.
  • an annular recess 18 is formed in the inner face of the wall of the venturi 8, and the plug 16 has a peripheral rib 19 which engages in said recess 18 in the venturi 8 to hold it in its operating position until the projectile is fired.
  • the cap 14 and the rear cover of the case are formed as a single piece 20 and the end of the edge 15, engaging on the end of the venturi, has a peripheral thinned portion 21 which engages in a peripheral recess 22 in the outer face of the wall of the venturi 8 so as to be retained therein in the active position until the projectile is fired.
  • the plug 16 (see FIG. 4) and the rear cover of the case are made as a single piece 23.
  • the fins 9 extend beyond the end of the venturi 8 and are held in the position in which their projections 11 engage in the corresponding slots 12 in the wall 3 of the case by an inner, concentric protuberance 24 which constitutes the rear cover 5 of the case.
  • FIG. 8 illustrates a modified form in which said clots 12 are formed in a metal ring 25 fitted on the rear end of the case and forming an extension of its tubular body 3. It will be seen that in this embodiment there are provided fins 9 each of which has at its free end a nose at right-angles to said metal ring 25, this nose forming the projection 11 on each fin and thus contributing to better retention of the projectile in the rearward direction.
  • FIG. 9 illustrates a modified form in which the slots 12 formed in the wall of the tubular body 3 of the case and facing said projections 11 are reinforced by an outer metal clamping ring having complementary swaged lipped portions 27 which engage in said slots 12 (see FIG. 10).
  • FIG. 11 illustrates a modified form in which the fixed part of the coupling in which the projections 11 on the fins 9 are locked is constituted by a circular recess 28 formed opposite said projections 11 in the inner face of the wall of the circular body 3 of the case.
  • the cap fitted on the end of the venturi and its edge 15 inserted between the outer wall of the venturi 8 and the free ends of the fins 9 of the projectile form a single piece 20 with the rear cap of the case.
  • the diameter of the rear end of the case in the zone closed by said cover 20 is greater than the diameter of the body 3 of the case, and the cf fect of this is further to reduce any possible reaction on the body of the case resulting from the thrust of the gases likely to be released in the recess 28 when the shot is fired.
  • the fixed part of the coupling that is carried by the rear end of the case is constituted by a resilient ring 32, which can be ejected under the effect of the thrust of said propellant gases, this ring being lodged in a circular recess 33 formed in the inner face of the tubular body 3 of the case.
  • the movable part of the coupling is constituted, in this embodiment, by a slot 30 in each fin 9 and on that of its sides opposite the wall of the tubular body 3 of the case (see FIG. 13).
  • the slots 30 in the fins 9 bear against the resilient ring 32, the latter however being ejected by the thrust of the propellant gases of the projectile l immediately after the latter has been fired, due to the fact that it is no longer retained in the recess 33 by said fins 9 once the cap 14 of the venturi 8, the edge 15 of which locks the coupling, has itself been ejected by the thrust of the gases.
  • the fixed part of the coupling may take the form of small rivets which project into the interior of the case opposite slots 30 in the fins of the projectile. Such rivets, fitted in the wall of the tubular body 3 of the case, offer only minimum resistance to the thrust of the gases and this is converted only into a negligible reaction on the case.
  • the movable parts of said coupling are constituted by elements 34 which are hinged by their front ends on hinge-pins on the fins 9 mounted on the collar 10, said elements 34 being arranged along the venturi 8 and each having a projection 35 on that of its sides presented to the tubular wall of the body of the case 3, each projection 35 being located near the free end of the element 34 and opposite a corresponding slot 12 in the body of the case 3, and each slot being provided with a metal reinforcement 13.
  • the abovede scribed coupling is locked by inserting the edge 15 of a removable cap 14 between the outer wall of the venturi 8 and the free ends of said elements 34, the cap 14 closing the free end of the venturi 8.
  • spring blades 36 curved to form a portion 37 which projects laterally towards slots 12 in the wall of the case are secured by their forward ends to the venturi 8 of the projectile.
  • the locking of the coupling is achieved by inserting, between the outer wall of the venturi 8 and the free ends of said spring blades 36, the edge 15 of a removable cap 14 which closes the free end of the venturi 8.
  • the slots 12 in the wall of the tubular body 3 are reinforced by a metallic part 13 containing a cavity facing each of the slots and said metallic part being fitted on the outer face of said tubular body 3 of the case 2.
  • a spring blade 38, curved to form a portion 39 projecting laterally towards a slot 12 opposite the wall of the case may also be detachably hinged by one of its curved ends to engage in a slot contained in each of the fins 9 of a fin system folded over against the venturi 8 towards the rear of the projectile.
  • each of said spring blades may be pressed against the wall of the case by an internal concentric protuberance 41 forming part of the rear cover 5 of the case, so that said lateral projection 39 on each blade 38 will be located in the locking position in the corresponding slot 12 in the wall of the case.
  • the advantage of this latter arrangement resides in the fact that when the projectile l is fired and it leaves the case 2, the spring blades 38 become detached from the fins 9 while the latter are spreading out.
  • FIGS. 17 and 18 Another modified form, employing a detachable intermediate retaining element 42 in the case of a fixed fin system, is illustrated in FIGS. 17 and 18.
  • This element 42 is constituted by a blade which is folded over on to itself and the ends of which, remote from the zone of the fold, are connected by being held a certain distance apart by a rivet 43 adapted to engage in a slot 44 formed for the purpose in each of the fins 9 of said fixed fin system.
  • a lateral projection 45 forming part of said element 42 occupies a position opposite a slot 12 in the wall of the tubular body 3 when said element 42 is suspended by its rivet 43 from a fin 9 and when the projectile l is placed in the required position inside the case 2.
  • each of the slots 12 is closed on one side by a metal part 13 fitted on the outer face of the tubular body 3 of the case and containing a cavity presented to said slot 12.
  • the elements 42 become detached under the effect of the gyration of the projectile or as a result of air friction.
  • the modified form illustrated in FIGS. 19 and relates to a projectile, fins 9 of which when folded are turned over laterally against the venturi 8 about a spindle 46 parallel with the axis of the venturi.
  • Each of the fins 9 has at the rear portion of its free edge opposite the wall of the tubular body of the. case a projection 11 adapted to engage in a'slot 12in the wall of the case, which wall is reinforced by a metal part 13 containing a cavity presented to said wall.
  • This coupling is locked by the edge 48 of the plug 47 of the venturi 8. It will be seen that in this form of construction, the plug 47 contains a large axial opening 49 which does not however prevent it from being ejected by the propellant gases of the projectile.
  • the case for the assembly described is used successively as a container for storing and transporting the projectile and as a tube for launching the projectile.
  • the means for retaining the projectile in its case, as described, enables safety to be ensured if the assembly is dropped, and it opposes all loads and stressed tending to cause the projectile to move out of the case or to displace it longitudinally in the case, until the shot is fired, at which moment it releases the projectile without causing any reaction on the launching tube. It does not comprise any screw, pin or shear disc etc., nor any protuberance on, or reduction of cross-section in the launching tube that could interfere with the rush or flow of the gases.
  • the essential locking element is constituted by an insertable member which totally or partially closes only the tube, or only the venturi, or the two together. In all cases, this insertable member, whatever its shape or position, comprises a conical or cylindrical portion forming a stop for movable elements for retaining the projectile, which elements are solidly associated with the container tube as a result of the presence of this stop.
  • These movable elements may be constituted either by the spreadable fins themselves or by intermediate parts fitted on said fins, or hinged to the venturi or any other rear portion of the projectile.
  • the ends of these elements are provided with projections or slots enabling them to engage in cavities or with ejectable protuberances retained temporarily by the wall of the launching tube (seethe various modified forms), thus ensuring that they are immobilized in the longitudinal direction and also in some cases immobilized against rotation. It is obvious that all the modified forms of the insertable member may be combined with all the various forms of the retaining arrangement, so that a large number of combinations is provided.
  • the primary purpose of the insertable member is to ensure that the projectile is released when said member is ejected by the rush of gas.
  • the rear base is opened automatically when the shot is fired, without any reaction on the weapon assembly and its case.
  • An assembly comprising a self-propelled finned projectile and its case that is successively used as a container and as a launching tube characterized in that it is fitted at its rear end with an insertable member which can be ejected under the effect of the thrust of the propellant gases of the projectile and which locks at least one movable part of a coupling, that is carried by the rear end of the projectile, to a fixed part of this coupling that is carried by the rear end of the case, all the elements of this fixed coupling part projecting into the interior of the case being capable of ejection under the effect of the thrust of said gases, said movable part of said coupling being carried by fins of the projectile, said fins being pivotally mounted on the case and folded over toward the rear, said insertable member pushing the free ends of the fins against the wall of the case.
  • An assembly comprising a self-propelled finned projectile and its case that is successively used as a container and as a launching tube characterized in that it is fitted at its rear end with an insertable member which can be ejected under the effect of the thrust of the propellant gases of the projectile and which locks at least one movable part of a coupling, that is carried by the rear end of the projectile, to a fixed part of this coupling that is carried by the rear end of the case, all the elements of this fixed coupling part projecting into the interior of the case being capable of ejection under the effect of the thrust of said gases, said fixed part of the coupling being a circular recess in the inner face of the wall of the case opposite said movable part of the coupling and said movable part of the coupling being constituted by a projection.
  • An assembly comprising a self-propelled finned projectile and its case that is successively used as a container and as a launching tube characterized in that it is fitted at its rear end with an insertable member which can be ejected under the effect of the thrust of the propellant gases of the projectile and which locks at least one movable part of a coupling, that is carried by the rear end of the projectile, to a fixed part of this coupling that is carried by the rear end of the case, all the elements of this fixed coupling part projecting into the interior of the case being capable of ejection under the effect of the thrust of said gases, said fixed part of the coupling being a notch formed in the wall of the case opposite said movable part of the coupling and said movable part of the coupling being constituted by a projection, said notch being reinforced by an outer metallic ring.
  • An assembly comprising a self-propelled finned projectile and its case that is successively used as a container and as a launching tube characterized in that it is fitted at its rear end with an insertable member which can be ejected under the effect of the thrust of the propellant gases of the projectile and which locks at least one movable part of a coupling, that is carried by the rear end of the projectile, to a fixed part of this coupling that is carried by the rear end of the case, all the elements of this fixed coupling part projecting into the interior of the case being capable of ejection under the effect of the thrust of said gases, said fixed part of the coupling being a notch formed in the wall of the case opposite said movable part of the coupling and said movable part of the coupling being constituted by a projection, said notch being reinforced by an outer metallic part in which is formed a corresponding housing and which closes said notch on one side.
  • An assembly comprising a self-propelled finned projectile and its case that is successively used as a container and as a launching tube characterized in that it is fitted at its rear end with an insertable member which can be ejected under the effect of the thrust of the propellant gases of the projectile and which locks at least one movable pan of a coupling, that is carried by fins of the projectile, to a fixed part of this coupling that is carried by the rear end of the case, all the elements of this fixed coupling part projecting into the interior of the case being capable of ejection under the effect of the thrust of said gases, said projectile having a venturi and said insertable ejectable member being constituted by a cap fitted on the end of the venturi, the edge of said cap being inserted between the outer wall of the venturi and fins on the projectile which are folded toward the venturi.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Containers And Packaging Bodies Having A Special Means To Remove Contents (AREA)
  • Nozzles (AREA)
  • Toys (AREA)
US00157360A 1970-07-10 1971-06-28 Assembly comprising a self-propelled finned projectile and its case Expired - Lifetime US3754726A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH1046470A CH527405A (fr) 1970-07-10 1970-07-10 Ensemble comprenant un projectile autopropulsé empenné et son étui

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US3754726A true US3754726A (en) 1973-08-28

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US (1) US3754726A (nl)
JP (1) JPS5432279B1 (nl)
AT (1) AT318440B (nl)
BE (1) BE769744A (nl)
CA (1) CA957885A (nl)
CH (1) CH527405A (nl)
FI (1) FI54743C (nl)
FR (1) FR2100377A5 (nl)
GB (1) GB1329489A (nl)
IL (1) IL37208A (nl)
NL (1) NL164128C (nl)
SE (1) SE389190B (nl)
ZA (1) ZA714281B (nl)

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US3946639A (en) * 1974-09-06 1976-03-30 Emerson Electric Co. Fin and spin stabilized rocket
US4047466A (en) * 1976-07-29 1977-09-13 The United States Of America As Represented By The Secretary Of The Army Projectile fall-back prevention means
US4080868A (en) * 1977-02-25 1978-03-28 Lockheed Corporation Support and retention mechanism for missiles in launchers
US4191087A (en) * 1978-08-14 1980-03-04 The United States Of America As Represented By The Secretary Of The Army Rocket detent and release mechanism
US4304170A (en) * 1979-04-16 1981-12-08 The Boeing Company Locking assembly for a rocket and launch tube
US4376405A (en) * 1981-03-05 1983-03-15 The United States Of America As Represented By The Secretary Of The Army Automatic hard-soft rocket detent system
US4384691A (en) * 1980-12-22 1983-05-24 The United States Of America As Represented By The Secretary Of The Army Rocket fin hold down spring
US4550640A (en) * 1983-09-16 1985-11-05 Werkzeugmaschinenfabrik Oerlikon-Buehrle Ag Missile canister restraint device
US5074187A (en) * 1991-03-08 1991-12-24 The United States Of America As Represented By The Secretary Of The Navy Rocket nozzle shield
US5125318A (en) * 1991-12-18 1992-06-30 United States Government As Represented By The Secretary Of The Navy Inflatable device for excluding sea water from a rocket motor
US5174236A (en) * 1992-06-29 1992-12-29 The United States Of America As Represented By The Secretary Of The Navy Submarine torpedo tube motion weapon restrainer
US5239909A (en) * 1989-09-15 1993-08-31 Short Brothers Plc Missile weapon system
US20050109873A1 (en) * 2003-11-24 2005-05-26 Byrne James P. Method and apparatus for stowing and deploying control surfaces of a guided air vehicle
WO2009070076A1 (en) * 2007-11-30 2009-06-04 Bae Systems Bofors Ab Shell designed for securing in a mortar and mortar designed for such a shell
US20100154624A1 (en) * 2007-07-04 2010-06-24 Bae Systems Plc Charge mount
US20100288150A1 (en) * 2008-01-31 2010-11-18 Patria Land & Armament Oy Arrangement for supporting shell into breech-loading weapon barrel
WO2011003511A1 (de) * 2009-07-07 2011-01-13 Rheinmetall Waffe Munition Gmbh Waffensystem
US7984676B1 (en) 2007-06-29 2011-07-26 Taser International, Inc. Systems and methods for a rear anchored projectile
US8104407B1 (en) 2007-06-29 2012-01-31 Taser International, Inc. Systems and methods for deploying an electrode using torsion
US20120097144A1 (en) * 2008-06-02 2012-04-26 Causwave, Inc. Explosive decompression propulsion system
US8584569B1 (en) * 2011-12-06 2013-11-19 The United States Of America As Represented By The Secretary Of The Navy Plume exhaust management for VLS
US20190170475A1 (en) * 2017-02-01 2019-06-06 X Products Llc Projectile launcher
RU2695470C1 (ru) * 2018-08-03 2019-07-23 Акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" Носовой обтекатель летательного аппарата в транспортно-пусковом контейнере

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DE3507677A1 (de) * 1985-03-05 1986-09-11 Diehl GmbH & Co, 8500 Nürnberg Flugkoerper mit ueberkalibrigem leitwerk
FR2623898B1 (fr) * 1987-11-26 1990-03-23 France Etat Armement Dispositif de deploiement d'une ailette de projectile
EP0448898A1 (en) * 1990-03-23 1991-10-02 Instalaza S.A. Device for firing a rocket-missile using the container holding the same as launching weapon
GB9121343D0 (en) * 1991-10-09 1992-11-18 Royal Ordance Plc Mortar system
DK2858898T3 (da) * 2012-06-07 2017-11-27 Aerovironment Inc System til at aftageligt koble et førerløst luftfartøj inden i et udskydningsrør

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US2465401A (en) * 1943-09-23 1949-03-29 Leslie A Skinner Rocket fin assembly
US2690124A (en) * 1950-10-19 1954-09-28 Us Army Induction firing means for rockets
FR1405380A (fr) * 1964-05-28 1965-07-09 Soc Tech De Rech Ind Perfectionnements aux empennages déployants pour projectiles
FR1528732A (fr) * 1967-04-20 1968-06-14 Dynamit Nobel Ag Mécanisme servant à retenir jusqu'à leur mise à feu des roquettes dans leur dispositif de lancement
US3494249A (en) * 1968-05-01 1970-02-10 Norris Industries Weapon system including a launcher of the rocket launcher type and a projectile of the rocket type

Cited By (31)

* Cited by examiner, † Cited by third party
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US3946639A (en) * 1974-09-06 1976-03-30 Emerson Electric Co. Fin and spin stabilized rocket
US4047466A (en) * 1976-07-29 1977-09-13 The United States Of America As Represented By The Secretary Of The Army Projectile fall-back prevention means
US4080868A (en) * 1977-02-25 1978-03-28 Lockheed Corporation Support and retention mechanism for missiles in launchers
US4191087A (en) * 1978-08-14 1980-03-04 The United States Of America As Represented By The Secretary Of The Army Rocket detent and release mechanism
US4304170A (en) * 1979-04-16 1981-12-08 The Boeing Company Locking assembly for a rocket and launch tube
US4384691A (en) * 1980-12-22 1983-05-24 The United States Of America As Represented By The Secretary Of The Army Rocket fin hold down spring
US4376405A (en) * 1981-03-05 1983-03-15 The United States Of America As Represented By The Secretary Of The Army Automatic hard-soft rocket detent system
US4550640A (en) * 1983-09-16 1985-11-05 Werkzeugmaschinenfabrik Oerlikon-Buehrle Ag Missile canister restraint device
US5239909A (en) * 1989-09-15 1993-08-31 Short Brothers Plc Missile weapon system
US5074187A (en) * 1991-03-08 1991-12-24 The United States Of America As Represented By The Secretary Of The Navy Rocket nozzle shield
US5125318A (en) * 1991-12-18 1992-06-30 United States Government As Represented By The Secretary Of The Navy Inflatable device for excluding sea water from a rocket motor
US5174236A (en) * 1992-06-29 1992-12-29 The United States Of America As Represented By The Secretary Of The Navy Submarine torpedo tube motion weapon restrainer
US20050109873A1 (en) * 2003-11-24 2005-05-26 Byrne James P. Method and apparatus for stowing and deploying control surfaces of a guided air vehicle
US7100865B2 (en) * 2003-11-24 2006-09-05 Simmonds Precision Products, Inc. Method and apparatus for stowing and deploying control surfaces of a guided air vehicle
US7984676B1 (en) 2007-06-29 2011-07-26 Taser International, Inc. Systems and methods for a rear anchored projectile
US8104407B1 (en) 2007-06-29 2012-01-31 Taser International, Inc. Systems and methods for deploying an electrode using torsion
US8127684B2 (en) * 2007-07-04 2012-03-06 Bae Systems Plc Charge mount
US20100154624A1 (en) * 2007-07-04 2010-06-24 Bae Systems Plc Charge mount
WO2009070076A1 (en) * 2007-11-30 2009-06-04 Bae Systems Bofors Ab Shell designed for securing in a mortar and mortar designed for such a shell
US8656824B2 (en) 2007-11-30 2014-02-25 Bae Systems Bofors Ab Shell designed for securing in a mortar and mortar designed for such a shell
US20100300321A1 (en) * 2007-11-30 2010-12-02 Nils Johansson Shell designed for securing in a mortar and mortar designed for such a shell
US8430030B2 (en) * 2008-01-31 2013-04-30 Patria Land Systems Oy Arrangement for supporting shell into breech-loading weapon barrel
US20100288150A1 (en) * 2008-01-31 2010-11-18 Patria Land & Armament Oy Arrangement for supporting shell into breech-loading weapon barrel
US20120097144A1 (en) * 2008-06-02 2012-04-26 Causwave, Inc. Explosive decompression propulsion system
US8181561B2 (en) * 2008-06-02 2012-05-22 Causwave, Inc. Explosive decompression propulsion system
US20120204709A1 (en) * 2008-06-02 2012-08-16 Causwave, Inc. Projectile propulsion system
US8327747B2 (en) * 2008-06-02 2012-12-11 Causwave, Inc. Projectile propulsion system
WO2011003511A1 (de) * 2009-07-07 2011-01-13 Rheinmetall Waffe Munition Gmbh Waffensystem
US8584569B1 (en) * 2011-12-06 2013-11-19 The United States Of America As Represented By The Secretary Of The Navy Plume exhaust management for VLS
US20190170475A1 (en) * 2017-02-01 2019-06-06 X Products Llc Projectile launcher
RU2695470C1 (ru) * 2018-08-03 2019-07-23 Акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" Носовой обтекатель летательного аппарата в транспортно-пусковом контейнере

Also Published As

Publication number Publication date
FR2100377A5 (nl) 1972-03-17
AT318440B (de) 1974-10-25
ZA714281B (en) 1972-04-26
DE2134421A1 (de) 1972-01-20
DE2134421B2 (de) 1976-11-25
FI54743B (fi) 1978-10-31
CA957885A (en) 1974-11-19
NL164128C (nl) 1980-11-17
CH527405A (fr) 1972-08-31
JPS5432279B1 (nl) 1979-10-13
NL7109152A (nl) 1972-01-12
SE389190B (sv) 1976-10-25
FI54743C (fi) 1979-02-12
GB1329489A (en) 1973-09-12
IL37208A (en) 1975-02-10
BE769744A (fr) 1972-01-10
IL37208A0 (en) 1971-11-29
NL164128B (nl) 1980-06-16

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