US3686999A - Munition - Google Patents

Munition Download PDF

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Publication number
US3686999A
US3686999A US16302A US3686999DA US3686999A US 3686999 A US3686999 A US 3686999A US 16302 A US16302 A US 16302A US 3686999D A US3686999D A US 3686999DA US 3686999 A US3686999 A US 3686999A
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United States
Prior art keywords
missile
tube
locking means
firing
munition
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Expired - Lifetime
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US16302A
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English (en)
Inventor
Marcel Francois
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ARMY FRANCE
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ARMY FRANCE
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Publication date
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Publication of US3686999A publication Critical patent/US3686999A/en
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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
    • F42B5/03—Cartridges, i.e. cases with charge and missile containing more than one missile
    • F42B5/035—Cartridges, i.e. cases with charge and missile containing more than one missile the cartridge or barrel assembly having a plurality of axially stacked projectiles each having a separate propellant charge
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
    • F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles

Definitions

  • the present invention provides an improved munition comprising a series of missiles disposed one behind the other and means for firing them in succession one by one.
  • Such a munition has many advantages over munitions having a single missilev and in particular the following: increased rate of fire due to avoidance of the reloading operation, reduction in the transverse size of the arms or groups of arms adapted to fire a large number of missiles, improved ratio between the fired mass (missiles) .and the immobile mass (arm) for a given rate of fire.
  • the number of missiles that is is possible to fire by means of this rnulti-missile munition is in fact merely limited by the permissible overall length which depends on the column or stack of missiles. It will be understood that the structure and shape of the missile should be such that the latter is unaffected by the effects of the powder gases, namely the pressure, thrust and temperature.
  • the multi-missile munition comprises a metal tube which is open at one end and provided with an end wall at the other, and in which the missiles are disposed, the missile which was the first introduced in the tube bearing against said end wall, the other missiles bearing against one another and forming, at the rear of each missile, an annular chamber, firing means fixed on the tube and comprising as many missile-propelling gas-producing means as there are missiles, each gas-producing means comprising a powder charge and an igniting device and communicating with one of the annular chambers, the firing devices comprising therebetween a safety actuating means which corresponds to a pyrotechnic logic and is soarranged that the powder charges are ignited in succession one after the other, the powder charge of a given missile being ignited only after the missile immediately preceding it has been launched.
  • the tube constitutes both a case and firing chamber, that is to say, it is capable of withstanding the pressure of the launching gases with no need for support afforded by the wall of the chamber of an arm.
  • the end wall of the tube Before firing, the end wall of the tube is applied against the breech of the arm so that the successive thrusts produced by firing the missiles are transmitted to this breech through the column of missiles and this end wall of the tube.
  • the length of the tube containing the missiles is:
  • the munition performs the functions of a case and an arm.
  • the igniting devices which are actuated one after the other, are electric and supplied irrespective of the number of the missiles of the munition, through a single conductor connected to a firing station.
  • FIG. 1 is a diagrammatic elevational view, with a part cut away, of a munition according'to the invention
  • FIG. 2 is a half axial sectional view and half elevational view of the two end portions of this munition and shows the first missile, the corresponding firing means, the repetition of the missile and associated firing means, the required number of timesconstituting the desired multi-missile munition, and the tail end of the last missile bearing against the end wall;
  • FIG. 3 is a corresponding plan view partly in section taken along line 3-3 of FIG. .2;
  • FIG. 4 is an end elevational view, with the transparent cover removed, of the igniting device of a missile, this device being on a scale larger than that of FIGS. 2 and 3;
  • FIG. 5 is a sectional view taken along line 5-5 of FIG. 4, and
  • FIGS. 6-8 are diagrammatic views, on a reduced scale, of this igniting device in three successive positions.
  • FIG. 1 is an assembly view of the munition.
  • the munition comprises the combination of a tube A, n number of missiles B B B" disposed one behind the other in the tube A and n number of firing devices C C C'.', which produce propelling gases, are electrically ignited and fixed to the outside of the tube A for firing the missiles one by one, starting with the missile B- and ending with missile B", merely by the supply of electric ignition current through a single conductor D which is, at one end, connected to a firing station (not shown) and, at the other end, connected to the first device C, the other devices being connected in series by conductor sections D D D".
  • the tube A comprises (FIGS. 2 and 3) a tube proper 1, open at its forward end 2 and closed at its rear end by a transverse end wall 3 secured to the tube by a screwthread 4.
  • the tube 1 is surrounded locally by binding collars 5 which are fixed by adhesion, welding or other means and include plane faces 6 which constitute supports for the exterior firing devices C C".
  • Each missile B, B" is of any known type, depending on its function.
  • the last missile B" bears against the end wall 3, whereas each of the other missiles bears against the missile located immediately behind.
  • Each of them is provided with rings or flanges 7 for guiding the missile in the tube 1 and these flanges define annul chambers 8 between adjacentmissiles.
  • Each device C C" comprises three .units or blocks 9, l0 and 11 interconnected as by screws 12 (FIG. 3) and a screwthread 13.
  • the unit 9 constitutes a control unit and is connected to the elongated unit 10 defining a chamber 14 which is capable of withstanding high pressure and communicates with an orifice 15 which constitutes a nozzle formed in the unit 11 and communicates with the interior of the tube 1 in the region of the tail end of the corresponding missile (B for example) and in front of the following missile (B in the annular chamber 8, by way of an aperture 16 formed in the tube 1.
  • an igniting relay 17 Located in a chamber 14 of the unit is an igniting relay 17 followed by the powder charge element or elements 18 known per se, whose combustion at relatively high pressure affords, after expansion by way of the nozzle 15, all or a part of the gases for expelling the corresponding missile (if desired, an additional or complementary charge can in fact be provided in the chamber 8).
  • the powder element or elements 18 can be held stationary before and during combustion by any known means (not shown).
  • a locking means 19 for maintaining the corresponding missile (for example missile B) at rest.
  • This locking means extends through an aperture 20 in the tube 1 into a recess 21 or blind hole formed in the body of the missile. It is held in this position by means affording a limited force of reaction, for example a resiliently yieldable split ring 22.
  • the locking means has a head 23 which is slidable in a fluid tight manner in a cylindrical cavity 24 and constitutes a piston and closing element. At rest, this head closes an aperture 25 which connects the cylinder 24 to the relay 17.
  • An electrically ignited primer detonator of fuze 26 is disposed in the unit 9.
  • the gases it produces are admitted by way of an aperture 27 below the head 23 of the locking means 19 and causes the latter to overcome the retaining action exerted by the resiliently yieldable split ring 22 and move a distance which corresponds to the release of the missile and to the unmasking of the aperture 25 leading to the relay 17 and powder charge 18.
  • an electric connecting box Secured in the front part of the unit 9 by screws 28 (FIGS. 4 and 5) or other means, is an electric connecting box, preferably of moulded insulating material. It comprises a plate 29 and a preferably transparent hollow cover 30.
  • valve element 32 Located in a closed bore 31 (FIG. 3) in the unit 9 is a valve element 32 which is biased by a calibrated spring 33 and retained in the illustrated position by a ball 34 which bears against the lateral face of the head 23 of the locking means 19.
  • the ball 34 is movable through a transverse aperture 35 having a diameter slightly greater than that of the ball.
  • the valve element 32 terminates in an insulated stem 32 which extends into the electric connecting box (29,30) which it completely closes.
  • a piston 37 Movable in another parallel bore 36 in the unit or block 9 and located on the other side of the locking means (19-23) is a piston 37 which is maintained in the illustrated position by a shearable pin 38.
  • An insulated stem 37 of this piston extends into the box (29, which it also completely closes.
  • An aperture 39 (FIGS. 3,4 and 6 to 8), formed in the tube 1 and in the body of the unit 9, communicates with the bore 36 and allows the gases expelling the corresponding missile to arrive behind the head of the piston 37 and shift it to the right from the position shown in FIG. 3, provided of course that the pressure of the gases is equal to or higher than the pressure required for shearing the pin 38.
  • Each electric connecting box comprises a terminal 40 (FIGS. 2,4,6] and 8) to which is connected, in respect of the gas producer C the conductor D (FIGS. 1,2 and 3) and, in respect of the other gasproducing devices, the corresponding conductor section D, D D.
  • a spring 41 is centered on a stud 41 carried by the plate 29, and one of its ends is connected to the fixed terminal 40 whereas a branch ab (FIG. 4) at its other end tends, owing to the effect of resilience, to move from left to right (as viewed in FIG. 4) but is prevented from doing so by the fact that it bears against the insulated stem 32 of the valve element 32, this stem completely closing the box 30.
  • the branch ab of the spring therefore cannot move so long as the valve element 32 is in its position of rest shown in FIG. 2.
  • This branch ab of the spring is then in contact with a trigger guard plate 42 which is electrically associated with the stud of the electric primer of detonator 26 the body of which is earthed.
  • Another spring 43 also centered-on a stud 44 of the plate 29, has one end secured at 45.
  • One of the conductors D D D is connected to this end and to the terminal 40 of the following device C C C".
  • the free branch cd at the other end of the spring tends, owing to the effect of resilience, to move from right to left (as viewed in FIG. 4) but is prevented from doing so by the fact that it bears against the uninsulated stem 37 of the piston 37 (FIG. 4).
  • This piston stern completely closes the box 30 and the branch cd of the spring is prevented from moving so long as the piston 37 is in its position of rest (FIG. 3).
  • a metal connecting member 46 which is fixed to the plate 29 and adapted to receive the ends of the two springs when they have been released, as shown in FIG. 8. At rest, there are therefore two breaks or interruptions in series in the supply circuit between the portions D, D or D, D of the conductor: an upper break (ab,46) depending on the position of the spring 41 and a lower break (46, cd) depending on the position of the spring 43.
  • each housing comprises two contactors 42, ab, 46; 46, cd, 37, whose positions (ab, 42 or ab,46 and cd, 46 or cd, 37) are governed by the positions of the respective moving elements, namely the valve element 32 and the piston 37, these contactors being, for example, in series in the position ab, 46, cd.
  • the firing safety of the described munition is afforded by mutually actuated current transfer or transmitting devices contained in the boxes 29, 30 and constituting a pyrotechnic logic, a certain sequence of operations (explained hereinafter) being necessary for firing a missile.
  • the correctness of this sequence is checked by the transfer device pertaining to said missile before allowing the firing of the following missile.
  • the single conductor D which supplies current to the munition is, as explained hereinbefore, connected to the means controlling and supervising the first missile B.
  • the electric connection from one device C to the other is in readiness for operation.
  • the transfer Upon the normal firing of each missile, the transfer is established and the connection advances by a device C.
  • the firing current therefore passes in series through the already-operated devices C for supplying current to the following device.
  • This sequence of operations requires a certain period of time.
  • the interval between these pulses must include this period of time. If the firing current is permanent, this period of time in fact determines the rate of tire.
  • the current arrives at the terminal 40 (FIGS. 4 and 6) and supplies the primer 26, through the spring 41 and by way of the plate 42 which is in contact with the branch ab of the spring.
  • the primer is ignited and produces a corresponding gas pressure.
  • valve element 32 remains applied against its seating in its initial position owing to the pressure of the gases of the primer (this pressure is indeed transmitted immediately through the aperture 35 in which the ball 34 is disposed with clearance) and the pressure of the gases of the powder charge 18.
  • the gases of the primer pass through the aperture 25, after having withdrawn the locking means (19-23), and ignite the relay 17 which, in turn, ignites the powder charge. This pressure ensures that the valve element 32 is still maintained in its initial position.
  • the gases of the powder charge enter, by way of the nozzle 15, the tube 1 and create therein the missile-expelling pressure in the region of the chamber 8 behind the missile to be launched.
  • the missile such as missile B
  • missile B which is urged forward by the effect of the gases which bear against the forward part of the following missile, such as missile B starts to move. After having travelled a given distance, it uncovers the aperture 39 and the missile-expelling pressure is transmitted, by way of this aperture, behind the head of the piston 37 (FIG. 3). If the pressure has the required magnitude, this piston, which is biased by the gases, causes the pin 38 to be sheared. This piston moves and its stem is withdrawn from the box 29, 30
  • missile-expelling pressure suddenly drops.
  • the drop in pressure occurs in the unit 9 in the region of the valve element 32 by way of the communication between the tube 1 and the valve element (nozzle 15, chamber 14, aperture 25, aperture 35 containing the ball 34,- etc.
  • the calibrated spring 33 shifts the valve element 32 as soon as the decreasing pressure can no longer maintain the valve element on its seating. The threshold.
  • the current is transmitted or transferred.
  • the following pulse reaching the terminal 40 passes through the box by way of the two springs 41 and 43 which are electrically interconnected by the connecting member 46 and the conductor D and reaches the following device C where the same sequence recommences and so on up to the last device C" of the munition.
  • a current pulse fed into the device C, C C" of the munition can affect only the primer or fuze 26 of this device; the primer or fuze of the following device is earthed owing to the fact that the branch cd of the spring 43 bears against the uninsulated stem 37 of the piston 37 (FIGS. 4 and 6). The same is true of the following devices C.
  • the prirner 26 can only be ignited if the corresponding missile B is correctly locked in position. Indeed, if the locking means (19-23) is accidentally raised or withdrawn, the valve element 32 is no longer retained and, in moving, releases the branch ab of the spring 43 which leaves its contact with the plate 42. The primer can no longer be ignited. The aforementioned lower break (46-cd) prevents the electric pulse from reaching the following primer and the firing of the munition is interrupted. This is an indispensable safety precaution since the missile to be fired might have moved accidentally.
  • the shearable pin 38 guarantees a sufficient magnitude of the expelling pressure for firing the missile.
  • the closing of the lower break or switch (46-cd) therefore cannot occur for an insufficient pressure which would be liable to result in the missile being left in the barrel of the arm. The same is true of the situation when the powder charge 18 does not ignite.
  • the closure of the upper break or switch (ab-46) cuts off the connection between the circuit and the ignited primer. Any short-circuiting of the latter, due to the combustion of the substances it contained, does not adversely affect the ignition of the following primers.
  • a munition comprising a metal tube having an open forward end and a closing wall at the other end. a plurality of missiles disposed in said tube in axially adjoining relationship to one another, whereby the rear end missile bears against said end wall, means defining at the rear end of each missile an annular chamber with said tube, a plurality of firing means each of which is associated respectively with one of said missiles, fixed laterally on said tube and provided with a missile propelling gas produced means, an igniting device and a chamber for receiving a powder charge, said munition further comprising a plurality of openings provided in said tube for putting respectively in communication corresponding ones of said annular chambers with said chambers of said firing means, and automatically withdrawable locking means engageable with each missile for holding the missile stationary in said tube before it is fired and means associated with said locking means for withdrawing said locking means just before firing the missile, said locking means being movable in

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Air Bags (AREA)
  • Automotive Seat Belt Assembly (AREA)
  • Medicinal Preparation (AREA)
US16302A 1969-03-04 1970-03-04 Munition Expired - Lifetime US3686999A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR6905801A FR2036076A5 (fr) 1969-03-04 1969-03-04

Publications (1)

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US3686999A true US3686999A (en) 1972-08-29

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US16302A Expired - Lifetime US3686999A (en) 1969-03-04 1970-03-04 Munition

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US (1) US3686999A (fr)
JP (1) JPS4942400B1 (fr)
BE (1) BE745987A (fr)
CH (1) CH524130A (fr)
DE (1) DE2010154C3 (fr)
ES (1) ES377443A1 (fr)
FR (1) FR2036076A5 (fr)
GB (1) GB1307692A (fr)
IE (1) IE33728B1 (fr)
IL (1) IL33919A (fr)
NO (1) NO130844C (fr)
SE (1) SE373657B (fr)
ZA (1) ZA701131B (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4733597A (en) * 1987-04-06 1988-03-29 Sparton Corporation Sequential launching system
US4969283A (en) * 1989-10-12 1990-11-13 The United States Of America As Represented By The United States Department Of Energy Firearm equipped with live round inhibiting means and method of making same
US6591535B2 (en) 2000-08-24 2003-07-15 Armalite, Inc. Light weight weapon operating system and cartridge feed
US20060124020A1 (en) * 2002-06-20 2006-06-15 Ben Bishop Cartridge assembly for multiple projectiles
US20070011931A1 (en) * 2003-05-08 2007-01-18 Nico-Pyrotechnik Hanns-Jurgen Diederichs Gmbh & Co Rapid-fire weapon
US20150241157A1 (en) * 2009-02-06 2015-08-27 Metal Storm Limited Stacked projectile launcher and associated methods

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3041149C2 (de) * 1980-10-31 1986-10-02 Dynamit Nobel Ag, 5210 Troisdorf Verkabelung von Submunition
US6643897B2 (en) 2001-10-23 2003-11-11 Trw Inc. Retractable grab handle and coat hook

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2845004A (en) * 1954-07-07 1958-07-29 Quinton C Johnson Rocket launching system
US2930288A (en) * 1955-05-09 1960-03-29 Chance Vought Aircraft Inc Tandem rocket launcher and firing system
US2937573A (en) * 1956-06-28 1960-05-24 Martin Co Bombing apparatus
US2968222A (en) * 1957-08-27 1961-01-17 Brevets Aero Mecaniques Rockets carried in clusters by a launching machine and in particular by an aircraft
US3139795A (en) * 1962-05-24 1964-07-07 Altschuler Samuel Tandem loaded firing tubes
US3421244A (en) * 1962-03-02 1969-01-14 Us Army Firing mechanism for a rifle mounted auxiliary firearm
US3451306A (en) * 1967-01-26 1969-06-24 Susquehanna Corp Safe and arm ejection system

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2845004A (en) * 1954-07-07 1958-07-29 Quinton C Johnson Rocket launching system
US2930288A (en) * 1955-05-09 1960-03-29 Chance Vought Aircraft Inc Tandem rocket launcher and firing system
US2937573A (en) * 1956-06-28 1960-05-24 Martin Co Bombing apparatus
US2968222A (en) * 1957-08-27 1961-01-17 Brevets Aero Mecaniques Rockets carried in clusters by a launching machine and in particular by an aircraft
US3421244A (en) * 1962-03-02 1969-01-14 Us Army Firing mechanism for a rifle mounted auxiliary firearm
US3139795A (en) * 1962-05-24 1964-07-07 Altschuler Samuel Tandem loaded firing tubes
US3451306A (en) * 1967-01-26 1969-06-24 Susquehanna Corp Safe and arm ejection system

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4733597A (en) * 1987-04-06 1988-03-29 Sparton Corporation Sequential launching system
US4969283A (en) * 1989-10-12 1990-11-13 The United States Of America As Represented By The United States Department Of Energy Firearm equipped with live round inhibiting means and method of making same
US6591535B2 (en) 2000-08-24 2003-07-15 Armalite, Inc. Light weight weapon operating system and cartridge feed
US20040025393A1 (en) * 2000-08-24 2004-02-12 Reynolds George L. Light weight weapon operating system and cartridge feed
US20060124020A1 (en) * 2002-06-20 2006-06-15 Ben Bishop Cartridge assembly for multiple projectiles
US7464649B2 (en) 2002-06-20 2008-12-16 Metal Storm Limited Cartridge assembly for multiple projectiles
US20090120317A1 (en) * 2002-06-20 2009-05-14 Metal Storm Limited Cartridge assembly for multiple projectiles
US7707941B2 (en) 2002-06-20 2010-05-04 Metal Storm Limited Cartridge assembly for multiple projectiles
US20070011931A1 (en) * 2003-05-08 2007-01-18 Nico-Pyrotechnik Hanns-Jurgen Diederichs Gmbh & Co Rapid-fire weapon
US7373884B2 (en) * 2003-05-08 2008-05-20 Nico-Pyrotechnik Hanna-Juergen Diederichs Gmbh & Co. Kg Rapid-fire weapon
US20150241157A1 (en) * 2009-02-06 2015-08-27 Metal Storm Limited Stacked projectile launcher and associated methods
US9677837B2 (en) * 2009-02-06 2017-06-13 Defendtex Pty, Ltd. Stacked projectile launcher and associated methods

Also Published As

Publication number Publication date
CH524130A (fr) 1972-06-15
GB1307692A (en) 1973-02-21
DE2010154B2 (de) 1973-10-25
DE2010154C3 (de) 1974-05-30
ES377443A1 (es) 1972-07-01
BE745987A (fr) 1970-07-16
SE373657B (sv) 1975-02-10
DE2010154A1 (de) 1970-09-10
ZA701131B (en) 1971-04-28
IE33728B1 (en) 1974-10-16
IL33919A (en) 1974-07-31
IL33919A0 (en) 1970-11-30
FR2036076A5 (fr) 1970-12-24
NO130844B (fr) 1974-11-11
JPS4942400B1 (fr) 1974-11-14
IE33728L (en) 1970-09-04
NO130844C (fr) 1975-02-19

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