US2623465A - Projectile - Google Patents

Projectile Download PDF

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Publication number
US2623465A
US2623465A US143867A US14386750A US2623465A US 2623465 A US2623465 A US 2623465A US 143867 A US143867 A US 143867A US 14386750 A US14386750 A US 14386750A US 2623465 A US2623465 A US 2623465A
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US
United States
Prior art keywords
charge
projectile
powder
cavity
propulsion
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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US143867A
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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.)
NOUVELLE des Ets BRANDT Ste
BRANDT SOC NOUV ETS
Original Assignee
BRANDT SOC NOUV ETS
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Application filed by BRANDT SOC NOUV ETS filed Critical BRANDT SOC NOUV ETS
Application granted granted Critical
Publication of US2623465A publication Critical patent/US2623465A/en
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Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • F42B12/12—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 rotatably mounted with respect to missile housing
    • C—CHEMISTRY; METALLURGY
    • C07—ORGANIC CHEMISTRY
    • C07D—HETEROCYCLIC COMPOUNDS
    • C07D499/00—Heterocyclic compounds containing 4-thia-1-azabicyclo [3.2.0] heptane ring systems, i.e. compounds containing a ring system of the formula:, e.g. penicillins, penems; Such ring systems being further condensed, e.g. 2,3-condensed with an oxygen-, nitrogen- or sulfur-containing hetero ring
    • 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

Definitions

  • the desired result i. e. a practically complete immobilization of the hollow charge, is obtained by using a balldiameter of about 10 mm.
  • the gyration of the body I may be obtained: either by firing said body in a ried gun, the body I being in this case provided with a usual riling band and it being possible for the rear compartment to contain another explosive, incendiary, smoke-producing, or like charge, or merely a self-propulsive charge with or Without gyratory action, or guiding devices, or the like; or by using the ejection through suitably inclined nozzles of pressure gases produced by the combustion of a charge of powder contained in the rear compartment, said charge automatically producing Iboth the propulsion and the gyration.
  • the rear compartment of the projectile therefore contains the self-propulsion and self-gyration charge.
  • This charge is formed by a number of concentric coaxial cylindrical cakes of powder 24, 25, 26, Z'I (Figs. 1 to 3)
  • the peripheral cylinder 24 is directly housed in the body I of the projectile, between a front shoulder 28 of said body and a rear nozzle-supporting member 29 screwed at 30 in the tapped rear end of said body.
  • Said cylinder 24 of powder is slit at 3I (Fig. 2) along its entire length, so as to enable it to follow exactly the deformations of said body for the reasons which will be analysed hereinafter and also in order to facilitate its insertion.
  • a coat 32 of a varnish for example a thermoplastic resin, which adheres perfectly both to the metal and the powder, while allowing for small deformations which are different for the metal and for the powder.
  • cakes 25, 26, 2 which are coaxial with the axis X-X, they are mounted in the projectile so as to ybe free from the rotation of body I, since they are held between: on the one hand a star-shaped front grating 33, for example with three arms, provided with projections 34 between which said cakes are engaged; and on the other hand a rear grating comprising radial bars 35 provided on their front face with projections 36 for separating the cakes.
  • the front grating 33 is adapted to bear, by means of a ball 31, against the bottom of a cup 38 provided in the rear wall of the web 2 of the body I. Said cup is surrounded by a cylindrical baffle 38a which is supported by the grating and is stuffed with grease.
  • the rear grating 35 it is supported, by means of a ball 39 housed in a cavity iii provided at the centre of said grating, by an intermediate element 4I which in turn bears against an adjusting screw 42 screwed in a tapped hole 43 provided at the centre of the rear member 29 that supports the ejection nozzles for the propulsion gases produced by the combustion ci the cakes of powder 24 to 2l.
  • a cylindrical baffle 43a which is carried by the member 29 and is lled with grease surrounds the cavity 5%.
  • the propulsion and the gyration are effected by means of a series of peripheral nozzles 45 which are merely tted into holes provided with a shoulderd in the member 25; said nozzles are held in position merely by the thrust exerted on them, from the front' towards the rear, by the aforesaid gases.
  • the longitudinal axes Y-Y of said nozzles 45 are inclined with respect to the plane of Fig. l in such a-manner that the gases which issue from the nozzles cause the body I to rotate about its longitudinal axis X-X.
  • the inclination may for example be between l5 and 20 for a distance between the axes Y-Sf and X-X 0f about 35 mm. for a projectile of a calibre of mm.
  • an additional axial nozzle 4l which is normally closed by a disc 4B, for example of copper or aluminium, which is intended to blow out if, for any reason. and in particular in the event of the temperature of the block of powder ⁇ at the instant when the mounting the exception .of the outer cake '24,1the ,cakes 25,
  • the pressure lof the gases Yinside the compartment 4 exceeds a given Ymaximum value that correspends tothe pressure for which the strength of the body has been calculated (for example -web .2, the electric .conductors ⁇ for firing, not
  • the projectile V operates as follows:
  • the cake '24 owl-fig to the fact that it only :burns with its .inner surface 5d, protects the 'body i from a rise of temperature and vmoreover facilitates .the lighting of the powder by preventing a .powder surface to be lighted being placed opposite .the cold .wall of the metal body.
  • the .gases produced by the combustion of the powder are .ejected through the nozzles ⁇ l and simultaneously .effect .the propulsion -cf lthe projectile .and .the .gyratien of the body 'l about the axis ,X--X without .the gyration .of the hollow charge for .the reasons hereinbefore explained.
  • This result can be obtained for example: either by the combined use of a highly exothermic powder and nozzles capable of undergoing a rapid and controlled erosion bythe action of the gases; thus, it is possible to use balistite as the powder and make the nozzles of a low-carbon steel, for exampleabout '1 per cent, or, as known, by suitably-choosing the shape of 'the cakes of powder, so as 'to provide a combustion surface such that it -decreases as a function .of the time.
  • lFig. -4 shows, in order to give a more Vdefinite idea, the variations of p1 (curve A), of p2 (curve B') and of Papi-+132 -(curve C) as a function of ⁇ the time t or, what uamounts ⁇ to the same thing, the I'positions of the projectile along .its 'trajectory.
  • the absc'issa .t1 correspond to the Yend of the combustion of the ypropulsive charge.
  • Figs. 5 and 6 show modications in the manner of constructing the nozzles 5I, which are directly formed "in the .member fixed to the end of the body I.
  • said member 52 is merely adapted to bear by means of a shoulder ⁇ 53 against the inner face of an inwardly projecting ange 54 provided lat the rear end of the body l, whereas in the example of Fig. 6, ⁇ the member 55 is screwed at 56, as in the example of Fig. 1, in the tapped end of the body l.
  • the non-rotary hollow charge is only taken lby way of example of an embodiment and may be replaced by any other device that has to be shielded from .the action of the centrifugal force, such as a rself-guiding device, lifting surfaces, .or the like.
  • the casing .5 .of the hollow charge could be provided with projections which would make it possible, by .ring the projectile from a riifled tube, to impart .to Vsaid .charge an .initial rotation .in the opposite .direction to that of the body I so that, when the impact occurs, the rotation of the hollow charge is substantially eliminated by the frictional forces which tend to rotate it in the direction Yof said body l.
  • pivoting means coaxial to said axis and interposed between said container and said transverse partition, a first ball bearing mounted between the lateral wall of said cavity and said container in the region of its largest cross-section, and a second ball bearing between said wall and said container near said pivoting means,
  • a gyroscopically stabilized self-propelled projectile comprising in combination: an outer body which is a body of revolution about a longitudinal axis and which is provided with a front cavity and a rear cavity separated by a transverse partition, an explosive charge of powder which is placed in said front cavity, a transverse support xed to said body in the rear end of Said rear cavity, a set of nozzles carried by said support and through which said rear cavity opens into the atmosphere, a charge of self-propulsion powder housed in said rear cavity for producing propulsion gases which are ejected through said nozzles, at least one portion of said charge being mounted freely in said rear cavity about said longitudinal axis and being free from the rotation of said body, a front grating with radial bars which is arranged parallel to said transverse partition and against which said freely mounted portion of the propulsion charge is adapted to bear from the rear towards the front, a front pivot between said transverse partition and said front grating, a rear grating with radial bars against which the rear
  • said central pivot device for pivoting the rear grating on the nozzle support comprises a ball engaged in a central cavity of said grating, a screw screwed in an axial central hole of said support and an intermediate element between said ball and screw, whereby an axial adjustment of the rotary portion of said self-propulsion charge can be effected.
  • said means comprise the combination of a highly exothermic powder that forms said self-propulsion charge, with nozzles which are made of a material capable of undergoing corrosion by the action of the propulsion gases.
  • said self-propulsion charge is formed by balistite which is a highly exothermic powder
  • said nozzles are made of steel capable of corrosion that contains about 1 of carbon, whereby, owing to the heat of the propulsion gases, the nozzles corrode and produce a drop in the pressure exerted by said gases on the wall of said body, which is substantially the reverse of the variation 8 of the action of the centrifugal force on said body, in such a manner that said body is subjected to a substantially constant strain by the combined action of said centrifugal force and said pressure due to said gases.
  • Projectile according to claim 2 further comprising, for attenuating the variations of eciency due to the temperature, a central nozzle located axially in said support, a disc placed in said support behind said central nozzle for normally closing same, said disc being adapted to be driven out automatically if the pressure in said body exceeds a predetermined value, and behind said disc a grating for retaining same and preventing it being converted into a projectile.
  • a gyroscopically stabilized self-propelled projectile comprising in combination: an outer body which is a body of revolution about a longitudinal axis and which is provided with a front cavity and a rear cavity separated by a transverse partition, a hollow charge housed in said front cavity and formed by a hollow container of generally bi-conical shape coaxial to said body, by a substantially conical wall housed in said container in such a manner that its apex is turned towards the rear of said container in which it forms a front chamber and a rear chamber with a concave front face and by an explosive charge placed in said rear chamber, pivot means coaxial to said axis and interposed between said container and said transverse partition, a first ball bearing mounted between the lateral wall of said front cavity and said container in the region of its largest cross-section, and a second ball bearing between said wall and said container near the pivot means, a transverse support xed to said body in the rear end of said rear cavity, a set of nozzles carried by said support and through which said
  • a hollow charge mounted in said cavity to be free of the rotation of said body, said hollow charge being formed by a hollow container of generally bi-com'cal shape coaxial to said body, by a substantially conical Wall housed in said container in such a manner that its apex is turned towards the rear of said container in which it forms a front chamber and a rear chamber with a concave front face and by an explosive charge located in said rear chamber, a thrust and centering device of very small diameter carried by the rear of said container and adapted to bear against the rear bottom of said cavity, and guiding means interposed between the lateral wall of said cavity and said container to center the latter.
  • a self-propulsion charge in said body comprising a peripheral cylindrical cake of powder which is on the one hand externally coated with an inhibiting substance and on the other hand slit longitudinally so as to be pressed resiliently against the inner face of said body.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Organic Chemistry (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
US143867A 1949-02-15 1950-02-13 Projectile Expired - Lifetime US2623465A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR985015T 1949-02-15

Publications (1)

Publication Number Publication Date
US2623465A true US2623465A (en) 1952-12-30

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Family Applications (1)

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US143867A Expired - Lifetime US2623465A (en) 1949-02-15 1950-02-13 Projectile

Country Status (6)

Country Link
US (1) US2623465A (fr)
BE (1) BE493685A (fr)
CH (1) CH283465A (fr)
FR (1) FR985015A (fr)
GB (1) GB683484A (fr)
NL (1) NL90798C (fr)

Cited By (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2787958A (en) * 1952-09-15 1957-04-09 Belge De Mecanique Et D Armeme Projectile
US2865168A (en) * 1952-07-09 1958-12-23 Alex Deutsch Fuel burning reaction motor powered hydraulic and electric power unit
US2877504A (en) * 1954-08-02 1959-03-17 Phillips Petroleum Co Method of bonding propellant grain to metal case
US2900873A (en) * 1955-11-10 1959-08-25 Haut Rhin Manufacture Machines Ordnance
US2911912A (en) * 1957-06-27 1959-11-10 United Aircraft Corp Roll control means
US2923126A (en) * 1955-02-17 1960-02-02 Soc Tech De Rech Ind Propulsion system
US2939275A (en) * 1954-02-24 1960-06-07 Unexcelled Chemical Corp Solid-fuel rocket type motor assemblies
US2956400A (en) * 1957-06-05 1960-10-18 Curtiss Wright Corp Internal-ribbed exhaust nozzle for jet propulsion devices
US2981188A (en) * 1955-10-10 1961-04-25 Henry S Lipinski Spin-stabilized projectile with nonrotating shaped charge
US3000306A (en) * 1958-01-09 1961-09-19 Gen Dynamics Corp Solid propellant propulsion system
US3008379A (en) * 1958-11-07 1961-11-14 Curtiss Wright Corp Low dispersion missile and launching structure
US3029734A (en) * 1958-10-02 1962-04-17 Phillips Petroleum Co Separation of stages in a staged rocket
US3067681A (en) * 1960-01-04 1962-12-11 Telecomputing Corp Guided missile
US3072055A (en) * 1959-08-03 1963-01-08 Ross Sidney Gun launched, terminal guided projectile
US3093074A (en) * 1960-01-08 1963-06-11 Foras Joseph De Means for protecting flight vehicles from injury attributable to heat of air friction
US3095163A (en) * 1959-10-13 1963-06-25 Petroleum Res Corp Ionized boundary layer fluid pumping system
US3157124A (en) * 1961-01-05 1964-11-17 Rheinmetall Gmbh Spin stabilized hollow charge projectile
US3180086A (en) * 1962-03-20 1965-04-27 Snecma Multi-nozzle jet propulsion units
US3191379A (en) * 1961-03-08 1965-06-29 Ralph M Pierce Propellant grain for rocket motors
US3225694A (en) * 1964-01-20 1965-12-28 Gunnar P Michelson Missile
US3251301A (en) * 1962-09-12 1966-05-17 Lockheed Aircraft Corp Missile and launcher system
US3274772A (en) * 1963-07-16 1966-09-27 Gen Motors Corp Continuously staged rocket construction
US3361385A (en) * 1965-04-02 1968-01-02 Bert B. Gould Miniature ballistic rocket
US3372548A (en) * 1965-06-17 1968-03-12 Thiokol Chemical Corp Rocket nozzle
US3724216A (en) * 1957-06-13 1973-04-03 Us Navy Combined rocket-ram-jet aircraft
US3724781A (en) * 1970-02-27 1973-04-03 Oerlikon Buehrle Ag Spin-stabilised rocket projectile
US3802345A (en) * 1962-05-02 1974-04-09 Aai Corp Multiple projectile sabot assembly for use in rifled barrel
US4063512A (en) * 1966-10-05 1977-12-20 The United States Of America As Represented By The Secretary Of The Air Force Armor penetrating projectile
US4690350A (en) * 1985-12-19 1987-09-01 Raytheon Company Despinning mechanism
US4796534A (en) * 1988-01-22 1989-01-10 The United States Of America As Represented By The Secretary Of The Army Spinning ramjet vehicle with a non-spinning combustor

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1142536B (de) * 1952-08-12 1963-01-17 Charlotte Vogt Geb Petersen Rotationssymmetrische Hohlsprengladung
DE1005874B (de) * 1953-05-19 1957-04-04 Bofors Ab Raketentriebwerk, vorzugsweise fuer Raketengeschosse
DE1012540B (de) * 1953-09-28 1957-07-18 Ludwig Bucklisch Hohlladungsgeschoss
DE977712C (de) * 1957-03-03 1968-08-08 Franz Rudolf Dipl-Ing Thomanek Mit einer ausgekleideten Hohlladung ausgeruesteter Flugkoerper mit Raketentriebwerk
DE1111066B (de) * 1958-02-10 1961-07-13 Rheinmetall Gmbh Drallstabilisiertes Hohlladungsgeschoss
GB2162927B (en) * 1977-10-27 1986-07-30 Bayern Chemie Gmbh Flugchemie A solid rocket propulsion system

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US422636A (en) * 1890-03-04 Shell for high explosives
US1102653A (en) * 1913-10-01 1914-07-07 Robert H Goddard Rocket apparatus.
US1305216A (en) * 1917-12-11 1919-05-27 Clarence Janes Projectile.
US1307607A (en) * 1918-06-13 1919-06-24 Willie A Wilkins Projectile.
FR502560A (fr) * 1916-08-21 1920-05-19 Procedes Westinghouse Leblanc Torpille aérienne
FR530223A (fr) * 1921-01-27 1921-12-17 Perfectionnements apportés aux projectiles, en vue d'augmenter la longueur de leur trajectoire
GB543739A (en) * 1940-06-07 1942-03-11 Casimir Stanislas Piestrak Improvements in or relating to projectiles
US2441388A (en) * 1942-08-19 1948-05-11 George W Blackinton Projectile
US2519878A (en) * 1946-07-31 1950-08-22 Carold F Bjork Rocket projectile

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US422636A (en) * 1890-03-04 Shell for high explosives
US1102653A (en) * 1913-10-01 1914-07-07 Robert H Goddard Rocket apparatus.
FR502560A (fr) * 1916-08-21 1920-05-19 Procedes Westinghouse Leblanc Torpille aérienne
US1305216A (en) * 1917-12-11 1919-05-27 Clarence Janes Projectile.
US1307607A (en) * 1918-06-13 1919-06-24 Willie A Wilkins Projectile.
FR530223A (fr) * 1921-01-27 1921-12-17 Perfectionnements apportés aux projectiles, en vue d'augmenter la longueur de leur trajectoire
GB543739A (en) * 1940-06-07 1942-03-11 Casimir Stanislas Piestrak Improvements in or relating to projectiles
US2441388A (en) * 1942-08-19 1948-05-11 George W Blackinton Projectile
US2519878A (en) * 1946-07-31 1950-08-22 Carold F Bjork Rocket projectile

Cited By (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2865168A (en) * 1952-07-09 1958-12-23 Alex Deutsch Fuel burning reaction motor powered hydraulic and electric power unit
US2787958A (en) * 1952-09-15 1957-04-09 Belge De Mecanique Et D Armeme Projectile
US2939275A (en) * 1954-02-24 1960-06-07 Unexcelled Chemical Corp Solid-fuel rocket type motor assemblies
US2877504A (en) * 1954-08-02 1959-03-17 Phillips Petroleum Co Method of bonding propellant grain to metal case
US2923126A (en) * 1955-02-17 1960-02-02 Soc Tech De Rech Ind Propulsion system
US2981188A (en) * 1955-10-10 1961-04-25 Henry S Lipinski Spin-stabilized projectile with nonrotating shaped charge
US2900873A (en) * 1955-11-10 1959-08-25 Haut Rhin Manufacture Machines Ordnance
US2956400A (en) * 1957-06-05 1960-10-18 Curtiss Wright Corp Internal-ribbed exhaust nozzle for jet propulsion devices
US3724216A (en) * 1957-06-13 1973-04-03 Us Navy Combined rocket-ram-jet aircraft
US2911912A (en) * 1957-06-27 1959-11-10 United Aircraft Corp Roll control means
US3000306A (en) * 1958-01-09 1961-09-19 Gen Dynamics Corp Solid propellant propulsion system
US3029734A (en) * 1958-10-02 1962-04-17 Phillips Petroleum Co Separation of stages in a staged rocket
US3008379A (en) * 1958-11-07 1961-11-14 Curtiss Wright Corp Low dispersion missile and launching structure
US3072055A (en) * 1959-08-03 1963-01-08 Ross Sidney Gun launched, terminal guided projectile
US3095163A (en) * 1959-10-13 1963-06-25 Petroleum Res Corp Ionized boundary layer fluid pumping system
US3067681A (en) * 1960-01-04 1962-12-11 Telecomputing Corp Guided missile
US3093074A (en) * 1960-01-08 1963-06-11 Foras Joseph De Means for protecting flight vehicles from injury attributable to heat of air friction
US3157124A (en) * 1961-01-05 1964-11-17 Rheinmetall Gmbh Spin stabilized hollow charge projectile
US3191379A (en) * 1961-03-08 1965-06-29 Ralph M Pierce Propellant grain for rocket motors
US3180086A (en) * 1962-03-20 1965-04-27 Snecma Multi-nozzle jet propulsion units
US3802345A (en) * 1962-05-02 1974-04-09 Aai Corp Multiple projectile sabot assembly for use in rifled barrel
US3251301A (en) * 1962-09-12 1966-05-17 Lockheed Aircraft Corp Missile and launcher system
US3274772A (en) * 1963-07-16 1966-09-27 Gen Motors Corp Continuously staged rocket construction
US3225694A (en) * 1964-01-20 1965-12-28 Gunnar P Michelson Missile
US3361385A (en) * 1965-04-02 1968-01-02 Bert B. Gould Miniature ballistic rocket
US3372548A (en) * 1965-06-17 1968-03-12 Thiokol Chemical Corp Rocket nozzle
US4063512A (en) * 1966-10-05 1977-12-20 The United States Of America As Represented By The Secretary Of The Air Force Armor penetrating projectile
US3724781A (en) * 1970-02-27 1973-04-03 Oerlikon Buehrle Ag Spin-stabilised rocket projectile
US4690350A (en) * 1985-12-19 1987-09-01 Raytheon Company Despinning mechanism
US4796534A (en) * 1988-01-22 1989-01-10 The United States Of America As Represented By The Secretary Of The Army Spinning ramjet vehicle with a non-spinning combustor

Also Published As

Publication number Publication date
FR985015A (fr) 1951-07-13
CH283465A (fr) 1952-06-15
GB683484A (en) 1952-11-26
NL90798C (fr)
BE493685A (fr)

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