US2944486A - Self-propelled projectile - Google Patents

Self-propelled projectile Download PDF

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Publication number
US2944486A
US2944486A US732470A US73247058A US2944486A US 2944486 A US2944486 A US 2944486A US 732470 A US732470 A US 732470A US 73247058 A US73247058 A US 73247058A US 2944486 A US2944486 A US 2944486A
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US
United States
Prior art keywords
charge
self
launching
projectile
nozzle
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
US732470A
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English (en)
Inventor
Jasse Joseph Raymond
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.)
Hotchkiss Brandt SA
Original Assignee
Hotchkiss Brandt SA
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 Hotchkiss Brandt SA filed Critical Hotchkiss Brandt SA
Application granted granted Critical
Publication of US2944486A publication Critical patent/US2944486A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C19/00—Details of fuzes
    • F42C19/08—Primers; Detonators
    • F42C19/0819—Primers or igniters for the initiation of rocket motors, i.e. pyrotechnical aspects thereof
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/28—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges operated by flow of fluent material, e.g. shot, fluids
    • F42C15/30—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges operated by flow of fluent material, e.g. shot, fluids of propellant gases, i.e. derived from propulsive charge or rocket motor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C19/00—Details of fuzes
    • F42C19/08—Primers; Detonators
    • F42C19/0807—Primers; Detonators characterised by the particular configuration of the transmission channels from the priming energy source to the charge to be ignited, e.g. multiple channels, nozzles, diaphragms or filters
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C19/00—Details of fuzes
    • F42C19/08—Primers; Detonators
    • F42C19/0838—Primers or igniters for the initiation or the explosive charge in a warhead
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C9/00—Time fuzes; Combined time and percussion or pressure-actuated fuzes; Fuzes for timed self-destruction of ammunition
    • F42C9/10—Time fuzes; Combined time and percussion or pressure-actuated fuzes; Fuzes for timed self-destruction of ammunition the timing being caused by combustion

Definitions

  • the present invention relates to projectiles having a self-propelling charge capable of being launched or red in a tube by an auxiliary launching charge of the type in which the nozzle provided at the rearofthe body o f the projectile for the ejection of the propelling gases is provided with an ejectable obturating and igniting device adaptedto avoid a premature firing o f the selfpropelling charge by the launching charge, said device, which is ejected after the firing of the self-propelling charge,V being maintained in position by a shearing ring and being provided with a passageway iilled with a delay charge permitting the automatic tiring of the self-propelling charge -by the launching charge with a suitabledelay.
  • the object of the invention is to provide a projectile of the aforementioned type so improved as to permit, as desired, the tiring of the projectile'with or without self-propulsion.
  • the projectile of the invention is so arranged that the delay charge passagewayof said ejectable device for obturating the nozzle and igniting the self-propelling charge communicates with the rear face ofsaid device through at least one igniting passageway on which is disposed an adjustable movable obturator member which permits, as desired, either opening the igniting passageway for igniting the self-propelling charge through the medium of said delay charge or closing the igniting pas'- 3 sageway for-avoiding saidignition.
  • Fig. 1 is an elevational view, with parts cut away, of a projectile which embodies the invention, has stabilizingflns and forms a rocketi
  • Fig, 2 is a longitudinal sectional". ⁇ view of the rear part of the projectile, this view being on an enlarged scale relative to that of Fig. l;
  • Fig. 3 is a longitudinal sectional view taken along. line 3 3 of Fig. 2 on.a still 'further ⁇ enlarged scale, of the ejectable obturating and igniting device;
  • Fig. 4 is a rear view of the device shown in Fig. 3 and,
  • Fig. 5 is an end view of the forward endvof the rear cartridge carrier on the same scale as Fig. 2."
  • the invention is applied to a rocket adapted to be red in a smooth-bore tube.
  • 'Iliisrocket comprises a substantially conical body 1 having Van attached ogival head 5-1 carrying aV conventional combined fuze-relay sleeve F -with a tiring pin,
  • detonator and, preferably, ⁇ a"'rs t powder charge contained in a sleeve.
  • a tubular propelling charge ⁇ 17 Disposedin the sheath 12, 14 is a tubular propelling charge ⁇ 17 adapted to burn only on its inner face 1S, its outer face'being coated with a varnish 19 which prevents cordbustion of the outer face.
  • ⁇ Disposed forward of the charge 17 is an ignitingpellet or tablet22 against which bears a tube 23 which is disposed in the central bore of the charge 17 and' is adapted to direct to the igniting tablet the flame issuing from the tiring device constituted by the obturating and igniting device P.
  • This tube is iitted in the ring 24 mounted in the nozzle T and bears against the device P.
  • This nozzle T consists of two parts: the graphite nozzle ring 24 and the nozzle body 26 which is divergent and is screwed in the rear screwthreaded end of the body 1. Screwed on the nozzle body 26 is the tubular hub 52 carrying fins 53 and forming with the latter a n arrangement Q.
  • the obturating and igniting device P is disposed in the body 26. It comprises a body 54bearing against the body 26 through the medium of a shoulder 55. It is held in position in the body 26 and sealed by a readily shearable ring 56 composed of lead or like material which is disposed in a recess in the body 26 and between the body 54 and a nut 57 screw-threadedly engaged in the latter. In this way there is obtained perfect fluidtightness and an attachment which requires a substantially constant shear Iforce when the obturating device P is ejected.
  • lFluid tightness is obtained by means of a ilange 62 of the relay 60, which ange is Welded in the cold state to the obturating device body and by a disc 63 also welded in position in the cold state.
  • the delay device 59 constituted by the powder terminates at the rear in an enlarged head 64 having a large ignition area and disposed in a cavity 65 containing a certain amount of black powder -66 which is disposed loosely therein or made to adhere to thewall of the cavity by a varnish or is in the form of aportion of a fuse wick.
  • the cavity 65 communicates With the rear transverse face ⁇ 67 4of the obturating device body through two longitudinal passageways 68 which are symmetrical relative to the longitudinal axis X-X of the projectile (Pig. 3).
  • Each of these passageways 68 which are preferably v tance from the longitudinal axis X--X as the passageways 68, two cylindre-conical apertures 74 which, for a given angular position of this disc, coincide with the passageways y68, arotation-of thedisc through .90 permittin-g closure of'the passageways 68 by the disc.
  • the llatter is provided on its 'rear'outer face with a diametral rib 77 adapted to be actuated by the extensionor tail R.
  • the tail R consists of atube 78 vprovided with apertures 79 and engaged in the bore 80 formed in the Ahub 52 of the fin arrangement Q in which it is held in a central position at 81 and 82.
  • a resilient split ring 83 limits the penetration of the tube 78 which is held in axial position by shearing pins 84 which-extend through the hub 52 and engage a recess 85 formed in theouter face of the tube 78.
  • a plug 86 (Figs. 2 and 5) which is screwthreadedly engaged in the tube at S7.
  • a plug 86 (Figs. 2 and 5) which is screwthreadedly engaged in the tube at S7.
  • Formed in the forward face of the plug is an axial cylindre-conical blind hole 88 and two diametrally opposed apertures S9 permitting introduction of two wrench pins for screwing the plug.
  • recesses 90 for the purpose of keying the rib 77 of the disc70 relative to the tail R and directing the flames emanating from the launching cartridge (not shown in the drawing) toward the apertures '74 of the d'isc 70, there are provided, preferably in planes perpendicular to one another, on the one hand, recesses 90 in both thel forward end of the tube 78 and the plug 86, the bases of these recesses being disposed obliquely and rearwardly diver-ging relative to the axis X-X (Fig. 2) and, on the otherhand, recesses 91 situated in yline with the recesses 90 and formed in the peripheral wall of the plug 86 formed by the hole 89.
  • the diameter of the latter is less than the length of the rib 77 ofthe disc 70 and the width of this rib is very slightly less than the width of therecesses 90 and 91 so that this rib 77 is capable of being engaged in one of two pairs of diametrally opposed recesses '90 and 91 so that the disc 7.0 iskeyed to the tail R.
  • the projectile operates in the following manner:
  • the launching chargegases issue from the apertures 79 in the tube 78 and from the .apertures u93 -and the recess 92 of the hub 52 ofthe iin arrangement Q and reach, by passing through the recesses 90, the apertures 74 of the disc 70 and in passing through these aperftures ignite the powder 66 which fills orlinesfthe passageways 68 and the cavity 65 of the obturating and ,igniting device .1. .In consequence, the large end-.tof the 4 head 64 of the delay charge 59 is ignited and, through the medium of this charge, the combustion is propagated with the desired delay to the igniting charge 61.
  • the arnes produced ll the axial tube Z3 and ignite the pellet 22 which ignites the self-propelling charge 17.
  • the self-propelling charge 117 cannot ignite vand the trajectory of the projectile depends ,solely on the force initially imparted thereto by the auxiliary launching charge S when launchmg.
  • a projectile provided with a self-propelling charge .and capable of being launched by an auxiliary launching charge: .a rear .nozzle for ejecting the gases produced by combustion of theself-propelling charge and an eject- Aable device .disposed in the nozzle for obturating ythe Anozzle vin thecourse of the launching of the projectile by the launching charge .and Yfor igniting the self-propelling vcharge by means ofthe launching charge, said device comprisinga body, a shearing member fixing the .body in the nozzle, said body having a longitudinal igniting passageway and a transverse rear face, a delay charge viilling said passageway and permitting automatic ignition, with a predetermined delay, of the self-propelling lcharge by the launchingcharge, said passageway communicating With'said rear lface of the body through at least one ignition aperture, and a movable and adjustable obturator member against said rear face and :permitting selective
  • ⁇ a .projectile provided with a self-propelling charge and .capable of beinglaunched by an auxiliary launching charge: a rear nozzle for ejecting the gases produced .by rcombustion of the self-propelling charge and an ejectable device disposedinthe, nozzle for obturating the nozzle in the course of :the launching ⁇ of the projectile by the launching charge andfor igniting.
  • said device compris- .in g a body, a shearing member fixing the body in the nozzle, said bodyhaving a longitudinal igniting passageway and a transverse rear face, a delay charge filling said passageway andpermitting automatic ignition, with a .predetermined delay, .of .the self-propelling charge by the launching charge, said passageway communicating with said rearxface of the body through at -least one member which is positioned against .said ,rear faoeand permits selectively closing said aperture for launching said projectile without self-propulsion and uncovering said aperture for ignition of the self-propelling charge, said obturator member consisting of a disc which is rotatable around an axis and having as many apertures as said body comprises ignition apertures, the apertures of the body and of the disc being located at the same distance from said axis of rotation of the disc and a nut threadedly engaged on the body
  • a rear nozzle for ejecting the gases produced by combustion of the self-propelling charge; an ejectable device disposed in the nozzle for obturating the nozzle in the course of the launching of the projectile by the launching charge and for igniting the self-propelling charge by means of the launching charge, said device comprising a body, a shearing member fixing the body in the nozzle, said body having a longitudinal igniting passageway and a transverse rear face, a delay charge iilling said passageway and permitting automatic ignition, with a predetermined delay, of the self-propelling charge by the launching charge, said passageway communicating with said rear face of the body through at least one ignition aperture, and a movable and adjustable obturator member which is positioned against said rearV face and permits selectively closing said aperture forV launching said projectile without self-propulsion and uncovering said aperture
  • a rear nozzle for ejecting the gases produced by combustion of the self-propelling charge, -and an ejectable device disposed in the nozzle for obturating the nozzle in the course of the launching of the pro- I jectile by the launching charge and for ignitingV the selfpropelling charge by means of the launching charge, said device comprising a body, a shearing memberrixing the body in the nozzle, said body having a rear'transverse face and including a delay charge carrier composed of plastic material provided with a longitudinal ignition passageway which communicates with said rear face of the body through at least one ignition aperture, a charge of black powder tilling said passageway and forming an ignition delay between the launching charge and the self-propelling charge, the coeliicient of expansion of the plastic material being substantially equal to that of said black powder so as to avoid creation of any escape path capable of causing an
  • a projectile provided with a self-propelling charge and capable of being launched by an auxiliary launching charge: a rear nozzle for ejecting the gases produced by combustion of the self-propelling charge, and an ejectable device disposed in the nozzle for obturating the nozzle in the courseV of the launching ⁇ of the projectile by the launching charge and for igniting the selfpropelling charge by means ofthe launching charge,
  • said device comprising a body, a shearing member fixing the body in the nozzle, said body having a rear transverse faceVa forward ignition passageway and a rear cavity with which said passageway communicates, said cavity communicating with said rear face of the bodyv through at least one ignition aperture, a delay powder charge filling said passageway and powder iilling at least partly said cavity and said ignition aperture, and a movable and adjustable obturator member against said rear face for selectively closing said aperture for launching said projectile without self-propulsion and uncovering said aperture for ignition of the self-propelling charge powder lining the wall of said cavity and said ignition aperture, and the delay powder charge terminating in said cavity in the form of an enlarged head which increases the ignition area.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Ignition Installations For Internal Combustion Engines (AREA)
  • Powder Metallurgy (AREA)
  • Toys (AREA)
  • Fire-Extinguishing By Fire Departments, And Fire-Extinguishing Equipment And Control Thereof (AREA)
  • Portable Nailing Machines And Staplers (AREA)
US732470A 1954-01-21 1958-05-02 Self-propelled projectile Expired - Lifetime US2944486A (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR768295X 1954-01-21
FR83403 1958-02-03
FR737687A FR81001E (fr) 1954-01-21 1958-02-03 Projectile auto-propulsé

Publications (1)

Publication Number Publication Date
US2944486A true US2944486A (en) 1960-07-12

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ID=31981950

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Application Number Title Priority Date Filing Date
US732470A Expired - Lifetime US2944486A (en) 1954-01-21 1958-05-02 Self-propelled projectile
US790711A Expired - Lifetime US3008414A (en) 1954-01-21 1959-02-02 Self-propelled projectile

Family Applications After (1)

Application Number Title Priority Date Filing Date
US790711A Expired - Lifetime US3008414A (en) 1954-01-21 1959-02-02 Self-propelled projectile

Country Status (6)

Country Link
US (2) US2944486A (fr)
BE (1) BE567169A (fr)
CH (2) CH346135A (fr)
FR (3) FR1098633A (fr)
GB (3) GB768295A (fr)
NL (1) NL106017C (fr)

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3064381A (en) * 1959-10-28 1962-11-20 A V R Achat Ventes Representat Combination firearm and grenade
US3119303A (en) * 1960-09-23 1964-01-28 Hotchkiss Brandt Gyratory self-propelled projectile
US3120151A (en) * 1961-07-03 1964-02-04 Hotchkiss Brandt Ejectable tail unit for the propelling launching charge of a projectile which is loaded through the muzzle of the firing means
US3143073A (en) * 1961-03-10 1964-08-04 Hotchkiss Brandt Fluid pressure actuated time delay fuze
DE1200172B (de) * 1960-09-23 1965-09-02 Hotchkiss Brandt Raketengeschoss mit abwerfbarer Verzoegerungsvorrichtung
US3236317A (en) * 1962-07-02 1966-02-22 Dresser Ind Projectile propelling apparatus for use in high temperature environment
DE1258765B (de) * 1963-04-30 1968-01-11 Tech De Rech S Ind & Mecanique Aus einem Rohr mit Hilfe einer Abschusshilfsladung abschiessbares Geschoss mit einem Raketentreibsatz
US3421410A (en) * 1967-08-25 1969-01-14 George Kayaian Missile and hand held launcher
US3505958A (en) * 1967-06-27 1970-04-14 Contigea Sa Devices and weapons using delayed priming
US3505924A (en) * 1967-04-18 1970-04-14 Allied Res Ass Inc Silent mortar
US3886841A (en) * 1973-05-29 1975-06-03 Matthew S Smith Rocket powered round
US3981225A (en) * 1973-05-29 1976-09-21 Smith Matthew S Launcher arrangement for rocket powered round
US3982467A (en) * 1973-05-29 1976-09-28 Smith Matthew S Launch cartridge arrangement
EP0120215A1 (fr) * 1983-02-09 1984-10-03 Affärsverket FFV Munition pour mortier
US5390605A (en) * 1992-08-11 1995-02-21 Societe Nationale Des Poudres Et Explosifs Stabilized and propelled decoy, emitting in the infra-red
WO2013059841A1 (fr) * 2011-10-17 2013-04-25 Ael Mining Services Limited Élément pyrotechnique à retardement

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL268986A (fr) * 1960-09-15
US3176615A (en) * 1962-12-31 1965-04-06 Avco Corp Gun-propelled rocket-boosted missile
US3352242A (en) * 1963-11-29 1967-11-14 Charles E Mcfann Thermally initiated pyrotechnic delay time fuze
US3521564A (en) * 1965-10-22 1970-07-21 Mb Assoc Miniature rocket
US3626852A (en) * 1968-08-16 1971-12-14 Us Navy Warhead initiation transfer link
US3915091A (en) * 1973-05-29 1975-10-28 Matthew S Smith Rocket powered round
FR2353040A1 (fr) * 1976-05-25 1977-12-23 Europ Propulsion Allumeur pour bloc de poudres propulsives
US4432512A (en) * 1978-08-31 1984-02-21 British Aerospace Public Limited Company Jet propulsion efflux outlets
FR2448706A1 (fr) * 1979-02-09 1980-09-05 Luchaire Sa Perfectionnements apportes aux munitions, notamment antichars, lancees par une arme a tir tendu
DE3246540A1 (de) * 1982-12-16 1984-06-20 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Schubduesenanordnung zum verstellen des schubduesenquerschnitts von rueckstosstriebwerken fuer flugkoerper
US6561101B1 (en) 2001-03-28 2003-05-13 Alliant Techsystems Inc. Explosive delay assembly
DE102009060658B4 (de) * 2009-12-22 2012-11-15 Diehl Bgt Defence Gmbh & Co. Kg Granate und Granatabschussvorrichtung
EP2423352A1 (fr) 2010-08-24 2012-02-29 Centesil S.L. Bouclier thermique pour les réacteurs de production de silicium
US9664142B1 (en) * 2016-05-11 2017-05-30 Jian-Lin Huang Rocket structure
US11346640B2 (en) * 2020-08-11 2022-05-31 Jian-Lin Huang Two-stage propulsion system

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2246429A (en) * 1936-03-30 1941-06-17 Sageb Sa Projectile
US2383053A (en) * 1942-04-18 1945-08-21 Martin C Mogensen Mounting device for projectiles
US2462135A (en) * 1944-04-06 1949-02-22 Leslie A Skinner Rocket primer

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US200223A (en) * 1878-02-12 Improvement in combination shell-fuses
US1513411A (en) * 1924-01-09 1924-10-28 Alten S Miller Art of controlling time powder trains
US1949841A (en) * 1931-08-01 1934-03-06 Hercules Powder Co Ltd Fuse for shells
US2724237A (en) * 1946-03-05 1955-11-22 Clarence N Hickman Rocket projectile having discrete flight initiating and sustaining chambers
US2773448A (en) * 1954-01-21 1956-12-11 Brandt Soc Nouv Ets Rocket projectile
US2913983A (en) * 1954-11-29 1959-11-24 Ardell L Lytle Rocket motor

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2246429A (en) * 1936-03-30 1941-06-17 Sageb Sa Projectile
US2383053A (en) * 1942-04-18 1945-08-21 Martin C Mogensen Mounting device for projectiles
US2462135A (en) * 1944-04-06 1949-02-22 Leslie A Skinner Rocket primer

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3064381A (en) * 1959-10-28 1962-11-20 A V R Achat Ventes Representat Combination firearm and grenade
US3119303A (en) * 1960-09-23 1964-01-28 Hotchkiss Brandt Gyratory self-propelled projectile
DE1200172B (de) * 1960-09-23 1965-09-02 Hotchkiss Brandt Raketengeschoss mit abwerfbarer Verzoegerungsvorrichtung
US3143073A (en) * 1961-03-10 1964-08-04 Hotchkiss Brandt Fluid pressure actuated time delay fuze
US3120151A (en) * 1961-07-03 1964-02-04 Hotchkiss Brandt Ejectable tail unit for the propelling launching charge of a projectile which is loaded through the muzzle of the firing means
DE1176026B (de) * 1961-07-03 1964-08-13 Hotchkiss Brandt Fa Auswerfbarer Kartuschentraeger fuer einen Vorderlader
US3236317A (en) * 1962-07-02 1966-02-22 Dresser Ind Projectile propelling apparatus for use in high temperature environment
DE1258765B (de) * 1963-04-30 1968-01-11 Tech De Rech S Ind & Mecanique Aus einem Rohr mit Hilfe einer Abschusshilfsladung abschiessbares Geschoss mit einem Raketentreibsatz
US3505924A (en) * 1967-04-18 1970-04-14 Allied Res Ass Inc Silent mortar
US3505958A (en) * 1967-06-27 1970-04-14 Contigea Sa Devices and weapons using delayed priming
US3421410A (en) * 1967-08-25 1969-01-14 George Kayaian Missile and hand held launcher
US3886841A (en) * 1973-05-29 1975-06-03 Matthew S Smith Rocket powered round
US3981225A (en) * 1973-05-29 1976-09-21 Smith Matthew S Launcher arrangement for rocket powered round
US3982467A (en) * 1973-05-29 1976-09-28 Smith Matthew S Launch cartridge arrangement
EP0120215A1 (fr) * 1983-02-09 1984-10-03 Affärsverket FFV Munition pour mortier
US4611540A (en) * 1983-02-09 1986-09-16 Affarsverket Ffv Mortar ammunition
US5390605A (en) * 1992-08-11 1995-02-21 Societe Nationale Des Poudres Et Explosifs Stabilized and propelled decoy, emitting in the infra-red
WO2013059841A1 (fr) * 2011-10-17 2013-04-25 Ael Mining Services Limited Élément pyrotechnique à retardement
US20140245917A1 (en) * 2011-10-17 2014-09-04 Ael Mining Services Limited Pyrotechnic time delay element

Also Published As

Publication number Publication date
FR1098633A (fr) 1955-08-16
US3008414A (en) 1961-11-14
GB834969A (en) 1960-05-18
FR81001E (fr) 1963-07-19
CH348080A (fr) 1960-07-31
CH346135A (fr) 1960-04-30
NL106017C (fr) 1963-09-16
BE567169A (fr) 1960-08-12
GB853789A (en) 1960-11-09
GB768295A (en) 1957-02-13
FR83403E (fr) 1964-08-07

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