EP0398390A2 - Projectile tubulaire - Google Patents

Projectile tubulaire Download PDF

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Publication number
EP0398390A2
EP0398390A2 EP90112207A EP90112207A EP0398390A2 EP 0398390 A2 EP0398390 A2 EP 0398390A2 EP 90112207 A EP90112207 A EP 90112207A EP 90112207 A EP90112207 A EP 90112207A EP 0398390 A2 EP0398390 A2 EP 0398390A2
Authority
EP
European Patent Office
Prior art keywords
projectile
recess
base member
tracer material
rear end
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.)
Withdrawn
Application number
EP90112207A
Other languages
German (de)
English (en)
Other versions
EP0398390A3 (fr
Inventor
James Edward Baxter
Robert Duncan Poole
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.)
BAE Systems Global Combat Systems Munitions Ltd
Original Assignee
Royal Ordnance PLC
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 Royal Ordnance PLC filed Critical Royal Ordnance PLC
Priority to EP19900112207 priority Critical patent/EP0398390A3/fr
Publication of EP0398390A2 publication Critical patent/EP0398390A2/fr
Publication of EP0398390A3 publication Critical patent/EP0398390A3/fr
Withdrawn legal-status Critical Current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
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/34—Tubular projectiles
    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B27/00—Compositions containing a metal, boron, silicon, selenium or tellurium or mixtures, intercompounds or hydrides thereof, and hydrocarbons or halogenated hydrocarbons
    • 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
    • F42B12/38—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 of tracer type
    • F42B12/382—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 of tracer type emitting an electromagnetic radiation, e.g. laser beam or infrared emission

Definitions

  • the present invention relates to tubular projectiles.
  • UK Patent No. 1,571,010 assigned to the present applicant Company describes a supersonic tubular projectile invented by Abraham Flatau and Joseph Huerta, which may be used in (but not exclusively in) training ammunition rounds.
  • the projectile may be incorporated as a sub-calibre component in discarding sabot training rounds fired from the 30mm RARDEN (Registered Trade Mark) gun of the present applicant Company.
  • the present invention provides a novel tubular projectile which may optionally comprise a beneficially modified form of the projectile described in UK Patent No. 1,571,010.
  • Tubular projectiles of this kind do not readily lend themselves to the inclusion of a tracer facility, on account of the narrow cross-section available in the rear end of the tube wall for the accommodation of tracer material.
  • US-A-3726495 discloses a projectile having a longitudinal bore which is deliberately constricted. Embodiments thereof include tracer material in annular form contained within the rear end of the projectile. Projectiles of this kind, are not properly described as "tubular" because of their relatively thick wail and extremely narrow bore. In this prior art design, the annular cross-section available for tracer material is quite substantial. The disclosure of US-A-3726495 does not include any special characteristic for the tracer composition, such as might render it suitable for us in mass production of tubular projectile in which only a narrow annulus is available for the accommodation of tracer material.
  • a tubular projectile comprising a hollow tube having a recess formed in the rear end of the tubular wall thereof, said recess containing a tracer material, characterised in that said tracer material comprises a flexible polymer bonded pyrotechnic composition.
  • the recess is of annular cross-section and said tracer material is in the form of a cylindrical sleeve.
  • tracer material any material which may be incorporated in a projectile for the purpose of tracing or tracking the trajectory of the projectile.
  • the rear surface desirably comprises a flat annulus or a frustro-conical surface.
  • the rear surface may extend and taper inwardly from the trailing edge of the projectile, i.e. forming a mouth at the rear end of the hollow portion of the projectile tube.
  • the frustro-conical surface may be on the outer surface of the projectile tube tapering toward the axis of the projectile at a point behind the projectile.
  • the inner and outer lateral extremities of the recess are contained in an intermediate region between the inner and outer diameters of the rear surface annulus, although the tracer-embedded recess could comprise substantially the entire rear surface of the projectile.
  • the recess may comprise a recess of annular cross-section, the recess annulus preferably being substantially coaxial with the portion of the projectile in which it is formed.
  • the recess may comprise one or a plurality of discrete holes extending into the rear projectile wall in its rear portion in a direction parallel to the projectile axis.
  • the hole or holes may comprise one or more holes of circular or other suitable cross-section, e.g. an arcuate shape such as a bent rectangular or bent oval (e.g. sausage) shape.
  • the holes preferably are arranged in cross-section in a circular formation.
  • the present invention provides a highly convenient and advantageous technique for incorporating a tracer material, e.g. a tracer composition, in a round incorporating a tubular projectile without substantially affecting the aerodynamic properties of the projectile.
  • a tracer material e.g. a tracer composition
  • the tracer material incorporated in the projectile according to the present invention permits the trajectory of the projectile to be tracked.
  • the tracer composition may be a composition which strongly emits visible light when ignited. It could, however, be a composition which is a strong smoke emitter or an infra-red radiation emitter (which may, for example, be tracked by an infra-red detector) or a material which strongly reflects radio or microwave frequencies, e.g. for tracking by radar.
  • the tracer material comprises an emitter of visible light it may comprise a pyrotechnic or chemiluminescent material.
  • a pyrotechnic or chemiluminescent material may comprise a metallic fuel such as powdered magnesium, aluminium, titanium, or zirconium and an energetic oxidiser such as an inorganic nitrate or perchlorate, e. g. of ammonium, barium, or strontium optionally together with a polymeric binder, e.g. a polyester or polyurethane.
  • Suitable specific examples of pyrotechnic tracer compositions include the compositions commercially supplied by the present applicants under the designations SR889 and SR390B.
  • the flexible sleeve comprises a powdered metallic fuel and one or more fluoroelastomers as an oxidiser and flexible binder.
  • the material of the sleeve comprises magnesium 30 to per cent by weight, polytetrafluorethylene 35 to 50 per cent by weight and a rubbery binder 5 to 25 per cent by weight.
  • the rubbery binder may be a copolymer of vinylidene fluoride and hexafluoropropylene.
  • the material of the flexible sleeve comprises magnesium 48 per cent by weight, polyetrafluorethylene 35 per cent by weight, and a copolymer of vinylidene fluoride and hexafluoropropylene 17 per cent by weight.
  • the flexible sleeve may be produced by mixing the ingredients together as powders or particulate solids in the presence of a solvent such as acetone or ethyl acetate to form a soft processible dough-like mass. This is then cast, pressed or extruded into sheets. The solvent is allowed to evaporate from the sheets by drying in a warm atmosphere. After drying the resulting sheets which are pliant are cut to size and then rolled around a cylindrical former to produce the required sleeve as a pre-form for insertion into a projectile.
  • a solvent such as acetone or ethyl acetate
  • the sleeve may be formed by direct extrusion of a tubular shape from an extruder. It may for instance be convenient to extrude elongate tubes and then to cut these to size to form sleeves prior to drying.
  • a sleeve formed in one of the ways described above may be incorporated in the recess in a tubular projectile by insertion using a suitable guidance tool followed by consolidation using a plate driven by hydraulic press.
  • a sleeve produced by extrusion may be extruded directly into the recess.
  • a further alternative process for filling a projectile recess with a sleeve of tracer material is to provide the projectile in a form in which the outer collar shaped ring of the projectile surrounding the recess is flared whereby the recess has a greater cross-sectional area at its outer end.
  • An annulus of tracer material formed in one of the ways described above may be inserted into the recess and, after evaporating of the solvent, this may be consolidated by swaging down the flared outer surface of the projectile, eg by pushing the projectile through a die or using rollers or any other well known swaging technique, whereby the required final shape of the projectile outer profile is obtained with the tracer material embedded in the recess therein.
  • the tubular projectile preferably has in cross-section in a plane containing the projectile axis a front portion having an inner surface conically converging in a direction facing toward the rear end of the projectile, an intermediate portion having an inner surface of substantially constant diameter and a rear portion having an inner surface conically diverging in a direction facing toward the rear end of the projectile.
  • the material of which the body of the tubular projectile according to the present invention is made is not critical although high strength metallic materials are preferred. The material may for example be aluminium alloy, steel or in armour piercing applications, denser metal such as tungsten alloy.
  • the overall shape of the projectile according to the present invention is desirably the same as that which is described and claimed in UK Patent No. 1,571,010 except that the sharp boattail rear end of the projectile is preferably replaced by a flat or frustro-conical annular surface as specified hereinbefore.
  • the tubular projectile according to the present invention may be a sub-component of a discarding sabot round, e.g. as described in UK Patent No. 1,571,010.
  • the sabot may be made of a plastic material or a light metal, e.g. aluminium alloy.
  • a driving band imparting spin from the rifling groove of a gnn barrel to stabilise the projectile in flight may be provided, for example, on the sabot outer surface.
  • the projectile according to the present invention may be a full calibre projectile and may for example be provided with a driving band on its outer surface.
  • a base member e.g. a pusher or pusher/obturator may be provided to impart the main launch forces upon the rear end of the projectile and its sabot if included.
  • the base member may for example be made of a high strength plastics material such as polycarbonate material.
  • the tracer material incorporated in the projectile comprises a composition which is ignited to emit visible light during flight of the projectile
  • the tracer composition may be ignited in a direct or an indirect manner when the propellant charge provided to launch the projectile is initiated.
  • a base member e.g. used as a pusher in conjunction with the projectile has a groove, e.g. an annular groove, facing the recess in the projectile incorporating the tracer material to facilitate such ignition.
  • the groove is sealed by the rear surface of the rear end of the projectile in which the said recess is incorporated. Such a groove permits ignition of the tracer composition without venting of the propellant gas by the main hollow aperture of the projectile.
  • an igniter device may be located behind the projectile, e.g. housed in the base member substantially on the axis of the projectile, may be of a known kind which is arranged to be initiated by the set-back force or spin of the projectile, e.g. by the action of pressure or a striker on a suitable composition, for example, an impact sensitive composition comprising lead azide.
  • This device may be conveniently arranged to deliver when ignited hot gas to the tracer composition.
  • the igniter device may be located in a cavity in a base member which has one or more bleed channels extending from the cavity to a surface of the base member, e.g.
  • the pusher in this form of the invention has an annular groove facing the recess incorporating the tracer composition the hot gas emerges at this recess to ignite the tracer composition
  • hot gas obtained from the ignition of the main propellant charge may be bled through a narrow bleed hole or channel in the base member to the groove in the base member facing the recess in which the tracer composition is incorporated.
  • the tracer composition may be ignited whilst restricting the build-up of gas pressure behind whilst restricting the build-up of gas pressure behind the projectile.
  • a septum or burster disc or annulus may be provided in the path of the gas to delay the flow of hot gas to the tracer composition, thereby delaying the undesirable build-up of gas pressure upon the rear of the projectile.
  • the recess in the rear end of the tubular wall may be formed by machining. However, more conveniently, the said recess is formed as a gap between an insert and a portion of a wall of the projectile body at its rear end.
  • the said insert preferably has an inner or outer surface substantially continuous with the inner or outer surface of the body of the projectile forward of the insert.
  • a tubular projectile comprises a front portion 1, a middle or body portion 3 and a rear portion 5.
  • the internal diameter converges conically in a direction facing toward the rear portion 5.
  • the middle portion 3 the internal diameter is constant.
  • the internal diameter diverges conically in a direction facing away from the front portion 1.
  • the rear portion 5 has a flat annular rear surface 7.
  • the outer surface of the front portion 1 has a converging section 8 which meets the inner surface at a sharp annular leading edge 9.
  • the outer surface is of constant diameter in the middle portion 3 and rear portion 5 behind the converging section 8.
  • a recess 11 of annular cross-section is formed in the rear portion 5. This extends from the rear surface 7 inward to occupy part of the middle portion 3 in a direction parallel to the axis of the projectile.
  • the recess 11, which may be formed by machining, is filled with a tracer composition in one of the ways described above.
  • the recess 11 is replaced by individual holes 11a which may be formed e.g. by machining and filled with tracer material.
  • the annular recess 11 again extends from the rear surface 7 through the rear portion 3 in a direction parallel to the projectile axis.
  • the recess 11 is formed between an insert 17 and the inner wall of the body, indicated by reference numeral 18, forming the remainder of the tubular projectile.
  • the insert could have axial grooves to provide the required recess rather than by forming this as a gap between the insert and the body of an inner wall of the body.
  • inner wall of the body 18 has been machined to form a step 19 to provide the recess 15 with the insert 17 included.
  • the insert 17 abuts against a further step 21 machined in the inner wall of the body 18 and has an inner surface which is substantially continuous with that of the inner wall of the body 18 forward of the insert 17.
  • the recess 15 is filled with a tracer material which is a polymer bonded pyrotechnic composition as described above.
  • an insert replacing the insert 17 may have axial grooves to provide discrete holes (rather than an annulus) in which tracer material is embedded.
  • FIG 6 illustrates a construction for launching a tubular projectile embodying the present invention and for igniting the tracer composition therein by a direct method.
  • the projectile indicated by reference numeral 31 may be of the form shown in Figure 1 or of the form shown in Figure 3.
  • the tracer composition of the projectile 31 is indicated by reference numeral 33.
  • a sabot 35 (which may for example be formed of segments in a known manner) is fitted around the projectile 31.
  • a driving band 37 is attached to the outer surface of the sabot 35.
  • a base pusher 39 carrying an obturator 38 is located behind the rear surface of the projectile 31 and the sabot 35.
  • the pusher 39 has an annular channel 41 extending therethrough in a direction parallel to the axes of the pusher 39 and projectile 31.
  • the channel 41 has three regions, namely an annular recess 41a facing the tracer composition 33, a narrow portion 41b and a wider portion 41c behind the narrow portion 41b.
  • the wider portion 41c houses an annular septum 43.
  • the base pusher 39 is contained inside a gun in a conventional launch cartridge (not shown) in front of a known gun propellant (not shown).
  • a gun propellant not shown
  • the propellant is ignited causing a rapid expansion of gas which is obturated by the obturator 38.
  • the pressure built up causes the projectile 31 and sabot 35 to be driven by the pusher 39 in a forward direction out of the gun.
  • the driving band 37 engages the rifling of the gun (not shown) to impart spin to the projectile to maintain stability of the projectile in flight.
  • the septum 43 bursts allowing the gas to enter the channel 41 and reach the tracer composition 33 which it thereby ignites.
  • the narrow portion 41b allows this to be achieved without a build-up of undesirable high gas pressure behind the projectile 31. It is desirable to prevent such a build-up in order to prevent gas leakage on separation of the projectile 31 from the pusher 39 before acceleration starts.
  • the tracer composition allows the trajectory of the projectile to be tracked in flight.
  • Figure 7 there is shown an alternative base pusher 39.
  • the channel 41 ( Figure 4) is replaced by a channel 42 which has a narrow portion 42b conically diverging laterally from a common cylindrically shaped aperture 44 housing a cylindrical septum 46.
  • the narrow portions 42b open at their front end into an annular recess 42a similar to the recess 41a which is adjacent to the tracer composition 33 ( Figure 3). Operation of the Figure 7 embodiment is similar to that of the Figure 5 embodiment.
  • FIG 8 shows a further alternative base pusher construction which may be used in conjunction with the projectile 31 and sabot 35 shown in Figure 5.
  • an igniter device 51 is housed inside the base pusher indicated by reference numeral 50 behind the projectile 31 ( Figure 3).
  • a cap 53 having a striker pin is arranged in front of the device 51.
  • An aperture 56 behind the device 51 leads into an annular recess 55, similar to the recess 41a shown in Figure 1, via a narrow annular channel portion 57.
  • the cap 53 is set back by the projectile 31 (Figure 3) upon firing the gun, causing its striker pin to initiate the device 51.
  • Hot gas produced by initiation of device 51 flows from the aperture 56 to the recess 55 via the channel portion 57 thereby causing ignition of the tracer composition 33 ( Figure 3) adjacent to the recess 55.
  • the method of ignition of the tracer composition 33 by the base pusher construction shown in Figure 7 is an indirect method.
  • the igniter device 51 and cap 53 may be replaced by a known igniter which is sensitive to and ignited by the spin, rather than the set-back, of the projectile 31.
  • a tubular projectile similar to those shown in Figures 1 or 2 or Figures 3, 4 or 5 may be a full calibre projectile which is launched by a base pusher similar to that shown in Figure 6, 7 or 8 but having a diameter substantially the same as that of the projectile.
  • the driving band is provided on the outer surface of the projectile.
  • Figure 9 shows an example of a projectile as shown in Figure 1 in the course of manufacture. This illustrates a method of filling the projectiles shown in Figure 1 and Figures 3 to 5 with tracer material.
  • the outer ring labelled 5a in Figure 9 of the rear portion 5 surrounding the recess 11 is flared toward its rear surface 7 so that the recess 11, prior to insertion of its tracer material, has a greater cross-sectional area at its rear (outer) end than at its front (inner) end.
  • a flexible sleeve of tracer material (not shown in Figure 8) manufactured in one of the ways described above is inserted into the recess 11 and, after any necessary drying of solvent from the tracer material, the ring 5a is swaged down so that the projectile is obtained in the form shown in Figure 1.
  • Figure 10 shows an alternative to the construction show in Figure 3.
  • the projectile comprises a front portion 1, a middle portion 3 and a rear portion 5 all similar to those of Figure 3 but an insert 81 is provided as a collar fitted in a recess 82 in the rear outer wall of the projectile.
  • the recess 82 has, extending from a step 83 toward the rear end of the projectile, a region 84 of increased spacing in which tracer material 85 is embedded inside the insert 81.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Physics & Mathematics (AREA)
  • General Engineering & Computer Science (AREA)
  • Health & Medical Sciences (AREA)
  • Fluid Mechanics (AREA)
  • Organic Chemistry (AREA)
  • Electromagnetism (AREA)
  • Optics & Photonics (AREA)
  • Toxicology (AREA)
  • Combustion & Propulsion (AREA)
  • Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
  • Portable Nailing Machines And Staplers (AREA)
EP19900112207 1986-11-28 1987-11-27 Projectile tubulaire Withdrawn EP0398390A3 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP19900112207 EP0398390A3 (fr) 1986-11-28 1987-11-27 Projectile tubulaire

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
GB8628514 1986-11-28
GB8628514 1986-11-28
EP19900112207 EP0398390A3 (fr) 1986-11-28 1987-11-27 Projectile tubulaire

Related Parent Applications (2)

Application Number Title Priority Date Filing Date
EP87907785A Division EP0294405A1 (fr) 1986-11-28 1987-11-25 Projectile tubulaire
EP87907785.7 Division 1987-11-25

Publications (2)

Publication Number Publication Date
EP0398390A2 true EP0398390A2 (fr) 1990-11-22
EP0398390A3 EP0398390A3 (fr) 1991-05-02

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ID=26125300

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19900112207 Withdrawn EP0398390A3 (fr) 1986-11-28 1987-11-27 Projectile tubulaire

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EP (1) EP0398390A3 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2678055A1 (fr) * 1991-06-18 1992-12-24 Saint Louis Inst Projectile concu pour etre lance a partir d'un accelerateur a effet stato et accelerateur a effet stato mis au point a cette fin.

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3726495A (en) * 1970-01-20 1973-04-10 Dynamit Nobel Ag Projectile
US4094711A (en) * 1977-09-01 1978-06-13 Ford Aerospace & Communications Corporation Tracer and composition
DE8234827U1 (de) * 1982-12-11 1984-02-23 Diehl GmbH & Co, 8500 Nürnberg Geschoß
US4495870A (en) * 1982-08-02 1985-01-29 Thiokol Corporation External tracer for gun launched projectiles

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3726495A (en) * 1970-01-20 1973-04-10 Dynamit Nobel Ag Projectile
US4094711A (en) * 1977-09-01 1978-06-13 Ford Aerospace & Communications Corporation Tracer and composition
US4495870A (en) * 1982-08-02 1985-01-29 Thiokol Corporation External tracer for gun launched projectiles
DE8234827U1 (de) * 1982-12-11 1984-02-23 Diehl GmbH & Co, 8500 Nürnberg Geschoß

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2678055A1 (fr) * 1991-06-18 1992-12-24 Saint Louis Inst Projectile concu pour etre lance a partir d'un accelerateur a effet stato et accelerateur a effet stato mis au point a cette fin.

Also Published As

Publication number Publication date
EP0398390A3 (fr) 1991-05-02

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