US2613605A - Projectile - Google Patents

Projectile Download PDF

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Publication number
US2613605A
US2613605A US760423A US76042347A US2613605A US 2613605 A US2613605 A US 2613605A US 760423 A US760423 A US 760423A US 76042347 A US76042347 A US 76042347A US 2613605 A US2613605 A US 2613605A
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US
United States
Prior art keywords
projectile
hood
charge
explosive
perforating
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
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US760423A
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English (en)
Inventor
Brandt Edgar William
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Anstalt Fuer die Entwicklung von Erfindungen und Gewerblichen Anwendungen ENERGA
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Anstalt Fuer die Entwicklung von Erfindungen und Gewerblichen Anwendungen ENERGA
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Publication of US2613605A publication Critical patent/US2613605A/en
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    • 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
    • F42B12/04—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type
    • F42B12/10—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type with shaped or hollow charge

Definitions

  • PROJECTILE Filed July 11, 1947 '3 Sheets-Sheet 3 7/ 5 I I I as 9 finentor (Ittomegs Patentecl Oct. 1 4, 1952 UNITED STAT-E I PATENTO 2,613,605 FFICUE PRGJECTILE Edgar William Brandt, Geneva, Switzerland, as-
  • This invention relates to projectiles and more particularly to hollow charge perforating projecrangements, as well as experimentation, could give them.
  • An explosive charge acting on a preferably metallic cone or hood having a large surface and persecond, and if this core in formation has to.
  • the increase in perforating power relatively to that obtained in prior designs results from structural dispositions and proportions by which the explosive power determines and develops an essential supplementary effect not hitherto analysed or described, but nevertheles capable of supply-- ing the main result.
  • the hollow-charge anti-tank projectile of the present invention is of the type comprising an explosive charge of a thickness decreasing from the apex of the hood to become almost zero at the base, and is characterized in that said charge is of conical shape externally for about twothirdsof its height and then substantially cylindrical, the height of the conical portion of said charge being comprised between 80% and 120% of the height of the perforating hood.
  • the projectile of the present invention complieswith the required conditions by reason ,of itsconsiderable perforating power relatively to its weight and'calibre, its ease of firing, and its great accuracy. Furthermore, it has the advantage of possessing-a ballistic form ;of least resistance,
  • the perforating hood constitutesinweight, apart from thecxplosive charge, the principal part of the device, I j
  • ternal safety device of the grenadeare disposed, in relation to the base of the hood, symmetrically and at substantially equahdistances from said base.
  • base portion of the projectile comprises an aper-' ture which is hermetically sealed by means of a safety stopper, which can be locked and immobilised by screwing thetail on the projectile.
  • the projectile of the present invention maybe designed:
  • vanes are mountedeither on the charge carrier tail or on the rear of the 3.
  • Fig. 1 illustrates in elevation and partial lon- 1 gitudinal section one embodiment
  • Fig. 2 illustrates diagrammatically the formation of the core under the ,action of the 'deflagration of the explosive charge
  • Fig. 3 is a'plan view of'the phenomenon illustrated in Fig. 2;
  • Fig. 4 illustrates, in elevation and partial 1ongitudinal section a perforating, hollow charge projectileprovided-with a detachable detonator;
  • I Figs. Sand 6 show respectively,v in elevation, embodiments of projectiles intended to befired from smooth bore barrels;
  • Fig. 7 shows, in exterior view, va projectile fitted into a rear tubular case carrying the explosive charge
  • Fig. ,8 illustrates in elevation a projectile provided with a-self-propelling device
  • Fig. 9 is an exterior view, partly in section, of ananti-tank aircraft projectile provided with vanes adapted to deploy over agreater diameter than that of the projectile;
  • the projectile illustrated in Fig. 1 consists of.
  • Thebody I is formed of ajacket 5 housing the explosive, charge formed by two superimposed mas s a d The p er ma s 5 t m in.
  • the propulsive charge or as a projectile charge and. consists of high explosive, which may be either compressedor cast, and the lower mass 1 or relay charge preferably consists of compressed pulverulent explosive.
  • the mass 6 On its front face,. the mass 6 has a deep conical cavity 8 which opens outfrom the rearitowards the front. against the walls of this cavity is applied a metallic hood or cone 9 immobilized in position by a collar or mask l;fixed on the.
  • the explosive charge 6-1 which is thus of decreasing thickness fromthe apex of the hood and becomes almost zero at the base of the latter, is conical externally overabout two-thirds of its height and then substantially cylindrical; the height of the conical portion of said charge beingequal to that of the perforating hood or approximating thereto.
  • the collar or mask 10 has at its base an outer diameter substantially equal to that of the base of the perforating hood 9;. the internal oblique face H of said mask being of a height-at least equal to its width in section I2, it forms with the inner wall of the perforating hood 9 an angle a of at least 90. 1
  • a member l3 caps the mask l,0,forming a support for the crimping of the'jacket 5 on the conical head 2 provided with the fuze Land is extended inside said fuze-carrying head.
  • a detonator I5 is housed preferably in the mass 1 of pulverulentexplosive, whichacts as a relay between said 'detonator I5 and the high ex plosive 6. Fire is transmitted by waves from the fuze I4 tothe detonator l5.
  • Fig. 2 illustrates the operation and effect obtained with the novel arrangement of Fig. l.
  • the explosive charge deflagrating "from the rear towards the front outside the hood 9,.which is made. of, a material of suflicient density (such as mildsteel) and having a high coefficient of elongation and therefore. great malleability, appliesto the whole of the surface of said hood a thrustv which effects the concentration and projection of the material constituting said hood:
  • the plan view (Fig. 3). shows that the material .is projectedin converging. manner to?- i wards the centre .(longitudinal'axis of the hood); Now the meeting of said matter takes place from the rear towards the front on this centre, and V the high speed at which it takes'place, as well as the irresistible. pressure developed, cause the projection of ajetahead of the central portionhof the closedihood, thespeedof said jet accelerating to reach the value W which is considerably higherstill.
  • the arrangements and proportions of the projectile of the present invention ensure. this jet of optimum formation and remarkable.
  • the speed of' said jet is in fact liable to exceed to a marked degree that ofthe explosive deflagration proper, which itself attains a speed of 7000 to 8000 metres per second;
  • the distance be of the fuze head M are equal and inferior ree; spectively to twice the length and diameterof the transmitter cap IS.
  • the total weight givon' by the assembly of. parts constituting said fuze-ls thus reduced to less than four [6.
  • the fuze carrier has less resist-J ance to the shock of impact.
  • the apex of the hood 9 is situated towards the centre of the total length of the projectile .(Fig. 1)
  • the base portion, I8, placed inrear ofthe explosive charge covers peripherally, over its enand , tire height, the small cake of explosive 1 (Fig.
  • the vaning 4 is composed of a series of thin times the weight theinternal safety; .device I! of the grenade (Fig. 1) are, in relation 2 andthle when, are combined in such manner that, incomet m the examm aeraeosr I vanes S21 bedded in the thickness of theiwall' 22 b zgt ;mubularilguiding tail,-..these vanes pro-t jecti'ng to the rearl of. said. .tail and; forming a vaningwfanheight .substantially less than its diameter. i I
  • Theip'roiectile illustrated in Fig. 4 is similar: to that'zillustrated in Fig. .1,but comprises a detachable-netonatorhoused in a small .cake of llustrated'in Fig; '1 of a propossible with; the .minimum aerodynamic ree.
  • vaning 26 which, on release from the aircraft, is adapted to unfold in-accordance with 26', for example, over a greater diameter than that of 'theprojectile itself, and. thus ensures great stability of the latter; it may also cause the. gyrationof: the projectile and, in cone sequence, the arming of the :internal safety de- WhatI claim is: v 1.. A hollow charge perforating projectile, said vice of the latter at'a desired distance.
  • projectile comprising: a shell, a. highexplosive charge in said. shell, said highexplosive charge being formed withla front cavity, a hood applied against the wallsof said cavity. and" adapted to be transformed by the detonation intoa core,
  • a base portion on said shell a vaned tubular guiding tail mounted at the rear of said base portion, said base portion being formed with' an compressed explosive 21, in which isprovided a cavity 28' corresponding to the .external shape of the detonator 1.5.7:
  • a cylindrically shaped cavu ity-28 ismoreoven'provided in the lower mass of compressed pulverulent explosive'l, the diameter ofisaidiz cavity corresponding. exactly to that of the"cake:2 1. 1';
  • the 1 safety device may' either, be integral 'withthe detachable detonator, or be independent and "be. permanently mounted in the housing 39' annular inside groove at its rearinside'end, said shell and said base portion engaging mutuallyover the height of the base portion, and a washer:
  • projectile comprising: a shell, a high explosive charge in said shell, said high explosive charge being formed with a front cavity, a hood applied against the walls of said cavity and adapted'to be transformed by the detonation. into a' core, a base portion on said shell, a vaned tubular guiding tail mounted at the rear of said basepor-tion;
  • said base portion being formed withan annular inside groove'at its rear inside end, said shell provided'qforvthatpurpose'in the upper mass gh re'xplosive: 6.
  • the aperture 3! is provided with a safety stopper 32, which is locked an'dimmobilised by screwing on to the basethe tail.3.
  • the vanes 2 I are fashioned in sets of twoficut from the'sainesheetof metal, and have between them apor'tion in' th'e shape of av cylindrical segment 36,"whic'h engages inthe circular countersunk portion 33, after which theflange'35' is fitted over thevanes, which"'are thus immobilised on the tube 22.”
  • 1 1 v 1 The'projecti'les illustrated in Figs. and-6 are intended-to'rb'e' fired from a smooth bore. barrel; they 'c'omp'r-ise at the rear a cartridge 23 containi'ng the pi opulsiv'e charge.
  • Vaning- 4 is mounted either -j-on the charge carrier tail 3 (Fig; 6) or on'the rear'of-thefprojectile"(Figi 5). g The;projectilefillustratd in Fig. '7 -is fitted into a rear tube 24" c'arryin'g the propulsive charge 23.
  • The-projectile may also be provided with a varied self propulsion; device 25 for firing without recoil 51a the event of the'projectilefof the invention from an appropriate launching tube and said base portion" engaging mutually over theheight of the base portion,:an'd a washer en'-, gaging the back part of said shell andf-being adapted'to be forced during mountingflintosaid groove to set together the shell with the'base portion, in order to ensure the tightness between them, said high-explosive charge comprising a large cake 'and a small cake of explosive, said small cake being placed at the rear of the large cake, said base portion covering peripherally said small cakeof high ex'plosiv'e' for its entire height.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
US760423A 1946-11-09 1947-07-11 Projectile Expired - Lifetime US2613605A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH625333X 1946-11-09

Publications (1)

Publication Number Publication Date
US2613605A true US2613605A (en) 1952-10-14

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US760423A Expired - Lifetime US2613605A (en) 1946-11-09 1947-07-11 Projectile

Country Status (6)

Country Link
US (1) US2613605A (fr)
BE (1) BE475671A (fr)
CH (1) CH269535A (fr)
DE (1) DE840066C (fr)
FR (1) FR953913A (fr)
GB (1) GB625333A (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2801587A (en) * 1953-02-06 1957-08-06 Albert S Gould Folding fins for rockets and missiles
US2821924A (en) * 1954-07-09 1958-02-04 Lawrence J Hansen Fin stabilized projectile
US3234878A (en) * 1962-10-05 1966-02-15 Soc Tech De Rech Ind Powder-fuelled rocket
US3302567A (en) * 1964-03-09 1967-02-07 Dresser Ind Shaped-charge booster
US4334657A (en) * 1977-02-09 1982-06-15 Aktiebolaget Bofors Device for fin-stabilized shell or the like
US4405100A (en) * 1981-02-20 1983-09-20 The United States Of America As Represented By The Secretary Of The Navy Turbulence generator for maximizing configuration tolerances of free flight ordnance
US5773751A (en) * 1994-05-10 1998-06-30 Bofors Liab Ab Shell for gun with smooth-bore barrel

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL175102B (nl) * 1952-01-25 Berg Kg Plaatradiator voorzien van twee platen en een daarmee door lassen verbonden koppelstuk.
NL105034C (fr) * 1956-09-12 Energa
IT1137049B (it) * 1981-06-11 1986-09-03 Bovone Elettromecc Perfezionamenti nelle o relativi alle macchine bisellatrici,particolarmente per lastre di vetro
CA1264123A (fr) * 1981-12-08 1990-01-02 John Stuart Mcveagh Charge creuse sous enveloppe

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR491114A (fr) * 1915-02-12 1919-05-22 Charles Leopold Mayer Obus biogivaux à ailettes planes ou hélicoidales
GB516818A (en) * 1937-06-28 1940-01-12 Sageb Sa Improvements in or relating to projectiles comprising a reaction propulsion device
US2419414A (en) * 1941-10-03 1947-04-22 Sageb Sa Projectile
US2427989A (en) * 1942-08-19 1947-09-23 George W Blackinton Projectile

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR491114A (fr) * 1915-02-12 1919-05-22 Charles Leopold Mayer Obus biogivaux à ailettes planes ou hélicoidales
GB516818A (en) * 1937-06-28 1940-01-12 Sageb Sa Improvements in or relating to projectiles comprising a reaction propulsion device
US2419414A (en) * 1941-10-03 1947-04-22 Sageb Sa Projectile
US2427989A (en) * 1942-08-19 1947-09-23 George W Blackinton Projectile

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2801587A (en) * 1953-02-06 1957-08-06 Albert S Gould Folding fins for rockets and missiles
US2821924A (en) * 1954-07-09 1958-02-04 Lawrence J Hansen Fin stabilized projectile
US3234878A (en) * 1962-10-05 1966-02-15 Soc Tech De Rech Ind Powder-fuelled rocket
US3302567A (en) * 1964-03-09 1967-02-07 Dresser Ind Shaped-charge booster
US4334657A (en) * 1977-02-09 1982-06-15 Aktiebolaget Bofors Device for fin-stabilized shell or the like
US4405100A (en) * 1981-02-20 1983-09-20 The United States Of America As Represented By The Secretary Of The Navy Turbulence generator for maximizing configuration tolerances of free flight ordnance
US5773751A (en) * 1994-05-10 1998-06-30 Bofors Liab Ab Shell for gun with smooth-bore barrel

Also Published As

Publication number Publication date
GB625333A (en) 1949-06-27
FR953913A (fr) 1949-12-15
CH269535A (fr) 1950-07-15
BE475671A (fr)
DE840066C (de) 1952-05-26

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