US3388666A - Rifle grenade - Google Patents

Rifle grenade Download PDF

Info

Publication number
US3388666A
US3388666A US623303A US62330367A US3388666A US 3388666 A US3388666 A US 3388666A US 623303 A US623303 A US 623303A US 62330367 A US62330367 A US 62330367A US 3388666 A US3388666 A US 3388666A
Authority
US
United States
Prior art keywords
grenade
tail sleeve
head portion
propulsive
combustion chamber
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.)
Expired - Lifetime
Application number
US623303A
Other languages
English (en)
Inventor
Walther Willi
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.)
KUKA AG
Original Assignee
Industrie Werke Karlsruhe Ausburg AG
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 Industrie Werke Karlsruhe Ausburg AG filed Critical Industrie Werke Karlsruhe Ausburg AG
Application granted granted Critical
Publication of US3388666A publication Critical patent/US3388666A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • 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
    • 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
    • F42B10/26—Stabilising arrangements using spin
    • F42B10/28—Stabilising arrangements using spin induced by gas action
    • F42B10/30—Stabilising arrangements using spin induced by gas action using rocket motor nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B30/00—Projectiles or missiles, not otherwise provided for, characterised by the ammunition class or type, e.g. by the launching apparatus or weapon used
    • F42B30/04—Rifle grenades
    • 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
    • F42B5/10—Cartridges, i.e. cases with charge and missile with self-propelled bullet
    • F42B5/105—Cartridges, i.e. cases with charge and missile with self-propelled bullet propelled by two propulsive charges, the rearwardly situated one being separated from the rest of the projectile during flight or in the barrel; Projectiles with self-ejecting cartridge cases

Definitions

  • the invention relates to improvements in a rifle grenade which is provided with a supplementary propulsion unit and is intended to be attached by means of a tail sleeve to the muzzle end of a firearm.
  • the propulsion unit is generally constructed to have a smaller diameter than the caliber of the grenade. This rather small diameter allows for only small propulsive charges even when the unit is considerably lengthened. The result of such construction is that in spite of great length, the thrust created by such propellants can only be low. Moreover, it is customary to ignite the propulsion unit directly by means of the gas pressure created by the propulsive cartridge charge, so that the combustion chamber wall must be made strong enough to withstand the high detonation pressure.
  • the tail sleeve besides serving as means for fastening the grenade to the gun barrel, is also used for carrying the stabilizing tail fins and these as well as the sleeve form dead weight after start and must be accelerated by the propulsion unit.
  • Another drawback of present rifle grenades is the fact that they endanger the rifleman by the rearward blast of exhaust flames. In order to reduce this danger it has been the practice to employ weak propulsion charges with consequently lower energy and shorter length of rearward blast, but also having a limited firing range.
  • Susceptible to improvement in known rifle grenades is also the imparting of spin motion to the grenade for correction of structural and thrust asymmetry to stabilize the trajectory. conventionally this is etfected by an arrangement of holes in the tail sleeve, which holes can be effective only during flight of the grenade so that very little correction is obtained at the instant of firing when the pro jectile leaves the rifle barrel.
  • this invention provides that between the propulsion unit and the tail sleeve of the grenade a piston equipped with a firing pin is inserted.
  • the stem of this piston is provided with a reduced portion having a predetermined breaking point, which upon predetermined stress will break and thereby separate the propulsion unit from the tail sleeve and its head portion.
  • sepaate t rable construction has the advantage that the tail sleeve and its head portion are dropped immediately after firing, whereby the weight of the projectile is reduced and, owingto a more favorable mass propulsion relationship gained thereby, its flight velocity and firing range increased.
  • the principle here employed of disposing elements not further used is similar to the practice with two-stage rockets.
  • the piston with the firing pin is inserted gas tight in a centering piece of the combustion chamber bottom and, after firing, is freely movable therein along the firing direction, while the piston stem is connected with the head portion of the tail sleeve.
  • Another structural feature of this invention is the arrangement of holes in the face area of the tail sleeve head portion and the radial extension of this head portion into an annular face plate provided with radial bores and tangential discharge nozzles.
  • the stabilizing tail fins Swingably and settably secured to the combustion chamber bottom are also the stabilizing tail fins which extend rearward through suitable slots in the annular face plate of the tail head portion.
  • This construction in which the combustion chamber bottom serves as carrier for the stabilizing tail unit is an inventive deviation from prior art constructions in which the tail fins are mounted on the tail sleeve. Mounting on the tail sleeve is impossible here, because the tail sleeve is dropped at the instant of firing and is not carried by the projectile in flight.
  • the head portion of the tail sleeve be arranged on the centering piece of the combustion chamber bottom and that it be in connection therewith only through dowel pins engaging head portion and centering piece.
  • This connection insures transmittal of torsional forces but will disengage upon axial movement.
  • Such axial movement is effected at the instant of firing when the rearward projecting blast flames of the supplementary propulsion unit in the grenade strike against the forward side of the face plate around the head portion of the tail sleeve. The force produced thereby will remove the head portion from the centering piece and disengage the dowel pins.
  • the tail sleeve slipped from the rifle barrel by the propulsive cartridge charge at the muzzle and counteracted by the supplementary propulsion, will drop to the ground and the rifle grenade, released from the tail sleeve, will travel toward its target. From this description, it will be clear that the dowel-pin engagement between the head portion of the tail sleeve and the combustion chamber bottom is necessary for transmitting the spinning motion imparted by the tangential discharge nozzles in the face plate of the tail sleeve to the grenade at the instant of firing and until this connection is subsequently disengaged.
  • the combustion chamber bottom is provided with a socketlike projection into the combustion chamber.
  • This socket is suitable for receiving a shell surrounding an ignition cartridge containing an ignition propellant in additon to a supplementary ignition charge.
  • the addition of an ignition propellant to the supplementary ignition charge insures that the main propulsive charge for accelerating the grenade in its flight is ignited immediately after the ignition of the supplementary ignition charge.
  • the large diameter of the propulsion unit has the advantage that within its more ample combustion chamber, there can be accommodated a larger main propulsive charge of greater diameter but relatively short length; and the large diameter of the face plate and its arrangement behind the exhaust nozzles gives the assurance that the danger of accidental burns inflicted on the rifleman by the rearward projecting exhaust flames is practically eliminated, since the large face plate serves as protective shield in deflecting the blast.
  • FIG. 1 is a broken away diagrammatic side view, partly in section, of a rifle grenade according to the present invention
  • FIG. 2 is a cross-sectional view taken along the line IIII of FIG. 1;
  • FIG. 3 is a diagrammatic side view, on a reduced scale, of the grenade shown in FIG. 1, but without its tail sleeve;
  • FIG. 4 is a reduced-scale side view of the tail sleeve with head portion after separation from the grenade.
  • the rifle grenade comprises generally a propulsive unit 1 with a warhead 2 and tail sleeve 3.
  • a piston 5 equipped with a firing pin 4 and mounted on a stem 6.
  • the stem 6 includes a portion 7 of a reduced cross-sectional area having a predetermined breaking point. This portion 7 is calculated to break and separate the tail sleeve 3 with its head portion 8 from the propulsion unit 1 at the instant of firing.
  • the piston 5 itself is arranged gas tight in a centering piece 9 forming a projection of the combustion chamber bottom 10, while its stem 6 with its rear end is connected with the head portion 8 of the tail sleeve 3.
  • the face area 12 of the head portion 8 is provided with holes 11 which communicate with radial bores 13 extending to the periphery of an annular face plate 15, in which head portion 8 is centered (see FIG. 2).
  • the radial bores 13 are closed at the periphery by plugs 13a or the like and are provided near their outer plugged-up end with discharge nozzles 14 pointing at right angles to the bores 13 in substantially tangential direction with respect to the face plate 15.
  • Swingably and settably secured to suitable projections of the combustion chamber bottom 10 are flight-stabilizing tail fins 17 which extend rearward through suitable radial slots 16 in the face plate 15.
  • a socket-like projection 19 extends from the combustion chamber bottom 10 into the combustion chamber 18.
  • This socket 19 is suitable to receive a shell 20 which surrounds an ignition cartridge 21 containing a primer or detonator 22, a small ignition propulsive charge 24 and a supplementary charge 23.
  • the shell 20 is surrounded by a main propulsive charge 25 engaging the outer combustion chamber wall 26.
  • the combustion chamber bottom 10 which is provided with rearwardly directed exhaust nozzles 27 arranged in somewhat slanting and tangentially inclined direction, has also holes for receiving pins 23 which also engage the head portion 8 of the tail sleeve 3 and serve to transmit torsional force from the tail portion to the grenade.
  • the operation of the several elements at the instant of firing of the grenade is as follows: At the instant of firing, the ignition of a propulsive charge cartridge (not shown) creates a pressure at the rifle muzzle and ignites indirectly the propulsion unit 1 of the grenade in the following manner: The pressure from the propulsive charge cartridge enters the holes 11 in the face area 12 of the head portion 8 of the tail sleeve 3 and enters the interior of centering piece 9 of combustion chamber bottom 10 wherein piston 5 is freely movably inserted and gas tight. The pressure exerted against the piston 5 results in a tensile stress in the stem 6 which exceeds the breaking limit of the lowbreaking portion 7.
  • the piston 5 After disruption of stem 6 at 7 the piston 5 is free to move and will be moved forward in the firing direction by the gas pressure. Such movement of the piston 5 causes the firing pin 4 to strike the detouator 22 of the ignition cartridge 21 which ignites the supplementary ignition charge 23 and the ignition propulsive charge 24, whereby, in turn, the main propulsion charge 25 is ignited.
  • the tail sleeve will be pushed off the rifle barrel by the explosion of the propulsive cartridge charge and when the impact of this charge explosion dies out, the tail sleeve will be free to drop to the ground, whereas the grenade will be accelerated by its propulsion unit on its flight toward its target. Since, as above mentioned, the exhaust blast flames, issuing immediately after firing, impinge upon the face plate 15 at the head portion 8 of the tail sleeve 3, it will be understood that these flames by so impinging are deflected by the face plate which thus serves also as a protective shield for the rifleman so that the danger of burn injuries is elfectively prevented.
  • a rifle grenade for attachment to the muzzle end of the barrel of a firearm including a supplementary propulsive charge comprising a propulsive unit for accelerating said grenade in flight after firing and having a front face and a rear structure, a warhead mounted on said front face, a tail sleeve having a head portion, and connecting means between said rear structure and said head portion including destructible means adapted to be destroyed by the gas pressure created by the propulsive charge at the instant of firing to completely detach said tail sleeve from said propulsive unit.
  • said propulsive unit includes a combustion chamber having a bottom
  • said connecting means is arranged between said bottom and said tail portion and includes a centering piece projecting from said bottom, a piston movably inserted in said centering piece and having a rearwardly extending stem, a firing pin projecting from the front face of said piston, said stem at its rearward end being fixedly connected to said head portion and having a section of a predetermined breaking point, and means for directing the gas pressure created by the explosion of said propulsive charge to become effective upon said piston to disrupt said stem at its breaking point and thereby separate said tail sleeve from said propulsive unit.
  • a rifle grenade according to claim 2, wherein said means for directing the gas pressure against said piston consists of a face area in said head portion, provided with holes leading from said tail sleeve into said centering piece.
  • said propulsive unit includes a combustion chamber having a bottom and a circumferential wall, a centering piece extending axially from said bottom into the combustion chamber, the head portion of said tail sleeve being seated on said centering piece, a piston inserted for slidable movement in said centering piece and carrying on one of its ends a firing pin projecting into said combustion chamber, said piston being secured to a stern extending to said head portion and being secured thereto with its other end, a portion having a predetermined low breaking point in said stem, said piston being prevented from slidable movement in said centering piece as long as said stem is in one piece but being free to slide forward after said low-breaking point portion is disrupted, and means for directing the gas pressure resulting from explosion of said propulsive charge into said centering piece to push against said piston so as to disrupt said stem and move said piston forward.
  • a riflle grenade according to claim 5 including pins inserted between said centering piece projecting from said combustion chamber bottom and said head portion of said tail sleeve, said pins serving for the transmission of the torsional force on said tail sleeve to said propulsive unit for imparting a spinning motion to the grenade.
  • a rifle grenade according to claim 5 including flight stabilizing tail fins swingably and settably secured to said combustion chamber bottom and extending rearwardly and engaging slots in said face plate of said tail sleeve.
  • a rifle grenade including a main propulsive charge in said propulsive unit, means forming a combustion chamber in said unit, a socket projecting from the bottom of said chamber into the latter, a shell (20) inserted in said socket and surrounding an ignition cartridge (21) containing a detonator (22), a supplementary ignition charge (23, 24), and a main propulsion charge (25), said combustion chamber bottom carrying an outwardly projecting centering piece and be ing provided with exhaust nozzles, said head portion being adapted to be seated on said centering piece and being provided with a face area having holes therein lead ing into said centering piece, a piston axially movably inserted gas tight in said centering piece and carrying a firing pin (4) extending into said socket and being provided with a stem extending rearwardly to be fixedly secured to said head portion and forming the only unitsustaining connection between said tail sleeve and said propulsive unit, a low-breaking-point portion in said stem, said piston being

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Telescopes (AREA)
  • Toys (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
US623303A 1966-03-22 1967-03-15 Rifle grenade Expired - Lifetime US3388666A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DEJ0030404 1966-03-22

Publications (1)

Publication Number Publication Date
US3388666A true US3388666A (en) 1968-06-18

Family

ID=7203875

Family Applications (1)

Application Number Title Priority Date Filing Date
US623303A Expired - Lifetime US3388666A (en) 1966-03-22 1967-03-15 Rifle grenade

Country Status (8)

Country Link
US (1) US3388666A (de)
BE (1) BE695268A (de)
CH (1) CH472018A (de)
ES (1) ES336633A1 (de)
FR (1) FR1508558A (de)
GB (1) GB1165802A (de)
NL (2) NL6700671A (de)
SE (1) SE333527B (de)

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3724781A (en) * 1970-02-27 1973-04-03 Oerlikon Buehrle Ag Spin-stabilised rocket projectile
US3750581A (en) * 1971-09-20 1973-08-07 Us Army Missile motor igniter assembly
US3880044A (en) * 1973-07-05 1975-04-29 Us Army Muzzle attachment for accelerating a projectle
US3949676A (en) * 1974-06-10 1976-04-13 The United States Of America As Represented By The Secretary Of The Navy Load actuated electro-ignition circuit switch
US3952664A (en) * 1974-06-10 1976-04-27 The United States Of America As Represented By The Secretary Of The Navy Rocket nozzle multi function
US3960084A (en) * 1973-08-08 1976-06-01 Fabrique Nationale Herstal S.A. En Abrege Fn Fuse for rifle-grenade
US3981225A (en) * 1973-05-29 1976-09-21 Smith Matthew S Launcher arrangement for rocket powered round
US4023499A (en) * 1975-01-07 1977-05-17 Fabrique Nationale Herstal S.A. Fuse for rifle-grenade
US4099465A (en) * 1976-12-17 1978-07-11 The United States Of America As Represented By The Secretary Of The Navy Ignition device for missile motors
FR2398998A1 (en) * 1977-07-26 1979-02-23 Serat Firearm-launched self-propelled missile - has additional propellant charge with nozzle axes converging on its own
FR2448706A1 (fr) * 1979-02-09 1980-09-05 Luchaire Sa Perfectionnements apportes aux munitions, notamment antichars, lancees par une arme a tir tendu
US4886223A (en) * 1988-05-31 1989-12-12 Honeywell Inc. Projectile with spin chambers
US9664142B1 (en) * 2016-05-11 2017-05-30 Jian-Lin Huang Rocket structure
RU2631515C1 (ru) * 2014-08-26 2017-09-25 Ренат Абдульберович Юсупов Калиберный снаряд с жёстким креплением к корпусу стабилизирующего оперения, пластины которого имеют продолжение на корпус, центрируя снаряд по стволу
US11306997B2 (en) * 2020-08-11 2022-04-19 Jian-Lin Huang Throwing device with two-stage propulsion system
US11346640B2 (en) * 2020-08-11 2022-05-31 Jian-Lin Huang Two-stage propulsion system

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GR68779B (de) * 1981-11-16 1982-02-18 Karampateas Eustratios
DE3510446A1 (de) * 1985-03-22 1986-09-25 Nico-Pyrotechnik Hanns-Jürgen Diederichs GmbH & Co KG, 2077 Trittau Treibsatz zur bodensogreduzierung
US5431106A (en) * 1985-06-05 1995-07-11 Shorts Missile Systems Limited Release of daughter missiles
DE4210113C1 (de) * 1992-03-27 1998-11-05 Athanassios Dr Ing Zacharias Verfahren zum Leiten eines Flugkörpers und Flugkörper
SE501082C2 (sv) * 1993-03-30 1994-11-07 Bofors Ab Sätt och anordning för att ge en luftburen stridsdel ett önskat rörelsemönster

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1900790A (en) * 1930-07-25 1933-03-07 Brandt Edgar William Grenade
US2415803A (en) * 1944-12-23 1947-02-18 Abell Royal Allen Cartridge
US3007271A (en) * 1958-03-28 1961-11-07 Energa Device for throwing grenades by means of firearms
US3071073A (en) * 1959-05-21 1963-01-01 Brevets Aero Mecaniques Projectiles to be launched by means of a firearm and including an auxiliary propulsion motor
US3098447A (en) * 1960-05-05 1963-07-23 Brevets Aero Mecaniques Projectiles to be slidably fitted on the end of a gun barrel
US3140660A (en) * 1961-12-07 1964-07-14 Brevets Aero Mecaniques Grenades comprising a booster and similar devices to be launched by a firearm
US3204559A (en) * 1962-12-31 1965-09-07 Avco Corp Rocket propellant charge igniter

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1900790A (en) * 1930-07-25 1933-03-07 Brandt Edgar William Grenade
US2415803A (en) * 1944-12-23 1947-02-18 Abell Royal Allen Cartridge
US3007271A (en) * 1958-03-28 1961-11-07 Energa Device for throwing grenades by means of firearms
US3071073A (en) * 1959-05-21 1963-01-01 Brevets Aero Mecaniques Projectiles to be launched by means of a firearm and including an auxiliary propulsion motor
US3098447A (en) * 1960-05-05 1963-07-23 Brevets Aero Mecaniques Projectiles to be slidably fitted on the end of a gun barrel
US3140660A (en) * 1961-12-07 1964-07-14 Brevets Aero Mecaniques Grenades comprising a booster and similar devices to be launched by a firearm
US3204559A (en) * 1962-12-31 1965-09-07 Avco Corp Rocket propellant charge igniter

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3724781A (en) * 1970-02-27 1973-04-03 Oerlikon Buehrle Ag Spin-stabilised rocket projectile
US3750581A (en) * 1971-09-20 1973-08-07 Us Army Missile motor igniter assembly
US3981225A (en) * 1973-05-29 1976-09-21 Smith Matthew S Launcher arrangement for rocket powered round
US3880044A (en) * 1973-07-05 1975-04-29 Us Army Muzzle attachment for accelerating a projectle
US3960084A (en) * 1973-08-08 1976-06-01 Fabrique Nationale Herstal S.A. En Abrege Fn Fuse for rifle-grenade
US3949676A (en) * 1974-06-10 1976-04-13 The United States Of America As Represented By The Secretary Of The Navy Load actuated electro-ignition circuit switch
US3952664A (en) * 1974-06-10 1976-04-27 The United States Of America As Represented By The Secretary Of The Navy Rocket nozzle multi function
US4023499A (en) * 1975-01-07 1977-05-17 Fabrique Nationale Herstal S.A. Fuse for rifle-grenade
US4099465A (en) * 1976-12-17 1978-07-11 The United States Of America As Represented By The Secretary Of The Navy Ignition device for missile motors
FR2398998A1 (en) * 1977-07-26 1979-02-23 Serat Firearm-launched self-propelled missile - has additional propellant charge with nozzle axes converging on its own
FR2448706A1 (fr) * 1979-02-09 1980-09-05 Luchaire Sa Perfectionnements apportes aux munitions, notamment antichars, lancees par une arme a tir tendu
US4886223A (en) * 1988-05-31 1989-12-12 Honeywell Inc. Projectile with spin chambers
RU2631515C1 (ru) * 2014-08-26 2017-09-25 Ренат Абдульберович Юсупов Калиберный снаряд с жёстким креплением к корпусу стабилизирующего оперения, пластины которого имеют продолжение на корпус, центрируя снаряд по стволу
US9664142B1 (en) * 2016-05-11 2017-05-30 Jian-Lin Huang Rocket structure
US11306997B2 (en) * 2020-08-11 2022-04-19 Jian-Lin Huang Throwing device with two-stage propulsion system
US11346640B2 (en) * 2020-08-11 2022-05-31 Jian-Lin Huang Two-stage propulsion system

Also Published As

Publication number Publication date
CH472018A (de) 1969-04-30
ES336633A1 (es) 1968-01-01
GB1165802A (en) 1969-10-01
FR1508558A (fr) 1968-01-05
SE333527B (de) 1971-03-15
NL6700671A (de) 1967-09-25
BE695268A (de) 1967-09-11
NL135093C (de)

Similar Documents

Publication Publication Date Title
US3388666A (en) Rifle grenade
US2724237A (en) Rocket projectile having discrete flight initiating and sustaining chambers
US2426239A (en) Rocket shell
US4574702A (en) Armour-piercing high-explosive projectile with cartridge
US4676136A (en) Apparatus for recoilless firing of projectiles from a lauching tube
US3167016A (en) Rocket propelled missile
GB614320A (en) Armour piercing explosive projectile
US2500117A (en) Rocket projectile
US2697400A (en) Projectile with shaped charge and point initiating fuze
US3576165A (en) Safety projectile percussion primer
US2307369A (en) Projectile
NO158273B (no) Drivsats for et artilleriprosjektil.
US3024729A (en) Ram jet projectile
EP0171534B1 (de) Kugelfang und Kugelabweiser für Gewehrgranate
GB2141809A (en) Armour piercing projectile
US5621185A (en) Warhead
US3638571A (en) Recoilless practice cartridge
US2681619A (en) Rocket projectile
US3968945A (en) Shaped mini charge round
US2672094A (en) Fuze
US3274935A (en) Practice ammunition
US3438303A (en) System including a tubular launching tube and a rocket provided with an outer auxiliary launching charge
US4449456A (en) Safety device for a projectile
US4697524A (en) After-firing safety
EP0084095B1 (de) Abschussvorrichtung für Gewehrgranaten sowie ähnliche Geschosse