US2900873A - Ordnance - Google Patents

Ordnance Download PDF

Info

Publication number
US2900873A
US2900873A US619327A US61932756A US2900873A US 2900873 A US2900873 A US 2900873A US 619327 A US619327 A US 619327A US 61932756 A US61932756 A US 61932756A US 2900873 A US2900873 A US 2900873A
Authority
US
United States
Prior art keywords
missile
tube
grooves
supplemental
gun
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US619327A
Other languages
English (en)
Inventor
Wust Hans
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.)
Manufacture de Machines du Haut Rhin SA MANURHIN
Original Assignee
Manufacture de Machines du Haut Rhin SA MANURHIN
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 Manufacture de Machines du Haut Rhin SA MANURHIN filed Critical Manufacture de Machines du Haut Rhin SA MANURHIN
Application granted granted Critical
Publication of US2900873A publication Critical patent/US2900873A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A21/00—Barrels; Gun tubes; Muzzle attachments; Barrel mounting means
    • F41A21/16—Barrels or gun tubes characterised by the shape of the bore
    • F41A21/18—Grooves-Rifling
    • 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

Definitions

  • the effect of a missile is by no means jeopardized by such a rotation; however there is one case at least in which such a rotation of the missile is objectionable; this case is that of missiles containing a hollow or shaped charge.
  • Missiles with shaped charges are used to a wide extent nowadays by reason of their considerable disruptive effect, chiefly in the case of action against armoured cars.
  • the power of penetration of a shaped charge is at a maximum when the missile does not revolve round its axis and it is all the more reduced when the missile revolves at a higher rate.
  • the power of penetration begins decreasing substantially already for a speed of revolution of about 1,000 rpm. and for 15,000 rpm, it may sink down to 50 or 40% of its peak value.
  • missiles with shaped charges have been frequently used as rockets, but the accuracy is then considerably decreased.
  • firing with rifled pieces of ordnance it is possible to obtain a higher accuracy, but this is reached I at the expense of the power of penetration of the shell.
  • roller bearings should be sufiiciently sturdy so that they may resist the shocks to which they are subjected at the moment of the firing. For instance, assuming that the inner section of the missile weighs 2.5 kg. and that the acceleration at the start is equal at the maximum to 20,000 g, (g or acceleration of gravity being equal to 9.81 meters per second), the stress to be transmitted by the roller bearings to the inner section of the shell is of the magnitude of about 50 tons.
  • the present invention brings a remedy to this prior condition through the agency of an inner ordnance tube provided, in addition to its normal twisted grooves with one or more supplemental grooves extending in parallelism with the axis of the tube or having a slight twist in a direction opposed to that of the twist of the conventional grooves, said inner ordnance tube being associated with a corresponding missile including two sections adapted to revolve with reference to each other While the inner section of the missile carries guiding members adapted to slide in the supplemental grooves so as to prevent the said inner section from being driven into rotation or to impart thereto a slight rotation in a direction opposed to that of the rotation of the outer section.
  • These guiding means should be designed so as to be sufficiently resistant from a mechanical standpoint.
  • the speed of rotation of the inner section of the missile when it is urged out of the muzzle is exactly defined and it is for instance equal to zero or to any other selected value.
  • the supplemental grooves should be slightly twisted towards the left so that the rotation towards the left hand side assumed by the inner section of the missile when the latter is passing out of the muzzle may be reduced to zero at a distance of about 600 meters and be transformed at a distance of 1,200 meters into a slight right-handed rotation.
  • the missile When the missile has left the inner tube, it is possible to make the inner section of the missile slide to a small extent, say by a few tenths of a millimeter forwardly with reference to the outer section, for instance through the agency of a spring, the power of which may be slightly above the resistance opposed by the atmospheric air. This provides for a separation between the surfaces serving for the transmission of the stresses at the moment of the firing while the friction between the inner and the outer sections is thus reduced. To provide for the relative rotation between the two sections after the missile has left the inner tube, it is sufiicient to resort to small and light roller bearings and even in certain cases to mere slideways.
  • the guiding members are preferably fitted over the cap of the missile. They may assume the shape of blades and in this case they may constitute fins, the angle of lead of which is selected so as to absorb at least approximately the rotary torque produced by friction and consequently to oppose any transmission of the rotary movement between the outer and the inner section of the missile. Obviously, it is also possible to separate the guiding and the torque-absorbing parts and to provide, independently of the guiding members constituted for instance by sliding bars, separate fins on the cap of the missile.
  • Fig. l is an axial cross-section of the improved missile.
  • Fig. 2 is a diagrammatic developed showing of a part of the inner surface'of the inner tube firing such amissile.
  • The'm'issile' includes an" inner sleeve 1' enclosingthe shaped charge 2 with its'cover 3.
  • Over the end of the sleeve 1 is fitted the conical point or cap 4' of the missile, said cap carrying a number of blades or fins 5 the outer edges of which are'pa'r'allel with the axis of the missile and are'located' on' a cylindrical surface the diameter of which is slightly larger than the gun calibre.
  • the cap 4' carries an electrically igni'table fuse' 6' connected on the onehand through the" mass constituted by thecap 4' of the missile; the sleeve ll,- etc. and on the other hand through the insulated wire 7 with-the igniting system 8' which controls the relay 9 so as to produce the defiag'ration of the explosive charge 2.
  • an electric fuse it is also possible touse' a fuse of any other type such as a percussion fuse either at the tip of the missile cap or at the rear, inside the bottom of the shell to' act as an' inertia fuse, etc.
  • the inner sleeve 1 is revolubly mounted inside an outer sleeve or sheath 11 with the interposition of the'needle bearing 12;
  • the outer sleeve or sheath 11' is provided with at least one driving band 13.
  • the bot tom 15 of the sheath 11 contains other arrangements suchas'the spring 16 the force exerted by which is' higher than" the resistance opposed by the air and which-urgessligh'tlyforward the-inner sleeve 1 through the agency of the piston 17 when the missile has passed" out ofthe muzzle-of the piece of ordnance;
  • the missile may in the conventional manner form part of a cartridge through engagement in a case containing the propelling charge.
  • the inner tube 2 of the piece of ordnance illustrated in Fig. 2 shows on the one hand the normal inner structure of a conventional gun with the twisted grooves 18 and thepartitions or lands 19 between the latter. These grooves extend along a spiral path forming a selected suitable angl e'with the axis of the gun so as to impart to the outer section 11 of the'missile the desired rotation through cooperation with the driving bands 13 and14l
  • the inner tube isprovided according to the invention with a number of' supplemental grooves 20' which in the example selected are parallel with the axis of the tube, although they may be given a slight pitch'in' a directionopposedto'that' of the" pitch of the conventional grooves, said slight pitch being say of the order of about 1, while the pitch of the con-' ventional grooves is' generally equal to about'7 at least and in fact be substantially higher as will be disclosed hereinafter.
  • supplemental grooves the' number of which, say between 3' and 6, is equal to that of the blades or bars 5 on the periphery of the missile guide said blades or bars at the moment of the firing.
  • the depth of these supplemental grooves 20 is preferably equal to that of the conventional grooves 18 or slightly smaller.
  • the partitions or lands 19 are at different points intersected by said supplemental grooves ZG'and accordingly the supplemental grooves are formed from aligned discontinuities in the lands.
  • the inner sleeve 1 may be made'longer or the enter sleeve ll' lighter or' shorter and if his sired-however in such a case to retain or even-improve the'stahility'of them'issile duringits' flight together with a highaccuracy in-the firing," it is necessary to increase the speed of rotation of the outer sleeve 1 1',i.e. the angle- 6f twist of the conventionalgroovesi This increase is easy matter even up to 'values' above those generally c sidered hitherto as necessary andusual, for instance uir to angles of-lS and above.
  • A' further application of the principle underlying invention consists in making use of the relative to movement'ofthe inner sleeve section 1 of the missile W1 reference to the outer section 11 thereof for the actua tion' of any desired mechanism, for instance for releasing the" safety system associated with the' ig nition'means at af predetermined-point of the path of the missile, say at meters beyond the muzzle of the gun.
  • This leads'to applications” which are of still further interest. It'is possibleto give'the'inner sleeve l any desiredlength'an'd to stabilize it through the agency of fins Which,'upon the missile passing out of the inner tube, are urged'outwardly in'a predetermined uniform manner.
  • the outer rotary section should be very short and thechief partsplayed by the latter consist in this case in providing forfluidtightness, in protecting the stabilizing fins against theaction of thegases formed by the gunpowder and in 'con'trollingthe desired predetermined and uniforni expansionjof said stabilizing fins.
  • ordnance system a pns'ing a gun massin "tube provided with circumferentially spaced lands forming conventional spiral rifling grooves between them, the lands having di scontinuities aligned to tom-supplemental rifiingi' comprising at least one supplemental groove, said" supplemental groove forming with the longitudinal of the tube an angle the value of which is selected be; tween' zero so that the groove is substantially parallel to thejaxis and a small value thereby to form a spiral opposite to that of the conventional rifling grooves of said tube and having a depthno greater than the depth oft'ne length to maintain a portion thereof constantly engaging portions of the lands that are continuous and uninterrupted, and at least one guiding radial vane carried by the outer surface of the inner portion of the missile for slidably engaging the supplemental groove of the gun tube.
  • An ordnance system comprising a gun including a tube provided with circumferentially spaced lands forming conventional spiral rifling grooves between them, the lands having discontinuities aligned to form supplemental rifling comprising at least one supplemental groove, said supplemental groove forming with the longitudinal axis of the tube an angle the value of which is selected between zero so that the groove is substantially parallel to the axis and a small value thereby to form a spiral opposite to that of the conventional rifling grooves of said tube and having a depth no greater than *the depth of the conventional grooves, a missile to be fired from the gun including a first outer portion and an inner portion coaxial therewith for carrying a charge and revolubly carried inside the outer portion and extending outwardly at one end thereof, a plurality of driving bands on the outside periphery of the outer portion of the missile for engaging the conventional rifling grooves of the tube of the gun, the driving bands being disposed axially on said outer portion in a predetermined axial spacing
  • An ordnance system comprising a gun including a tube provided with circumferentially spaced lands forming conventional spiral rifling grooves between them, the lands having discontinuities aligned to form supplemental rifling comprising at least one supplemental groove, said supplemental groove forming with the longitudinal axis of the tube an angle the value of which is selected between zero so that the groove is parallel to the axis and a small value thereby to form a spiral opposite to that of the conventional rifling grooves of said tube and having a depth no greater than the depth of the conventional grooves, a missile to be fired from the gun including an outer portion and an inner portion coaxial therewith for carrying a charge and revolubly carried inside the outer portion, the inner portion having a cap rigid therewith extending outwardly of the inner portion at one end thereof, a plurality of driving bands disposed peripherally of the outer portion of the missile for engagement by the conventional rifling grooves of the tube of the gun, the driving bands being disposed axially on said outer portion
  • An ordnance system comprising a gun including a tube provided with circumferentially spaced lands forming conventional spiral rifling grooves between them, the lands having discontinuities aligned to form supplemental rifling comprising at least one supplemental groove, said supplemental groove forming with the longitudinal axis of the tube an angle the value of which is selected between zero so that the supplemental groove is substantially parallel to said axis and a small value thereby to form a spiral opposite to that of the conventional rifling grooves of said tube and having a depth no greater than the depth of the conventional grooves, a missile for firing from said tube, the missile comprising an outer portion and an inner portion coaxial therewith for carrying a charge and revolubly carried inside the outer portion, the inner portion having an end portion extending outwardly of the outer portion at one end thereof, a plurality of driving bands on the outside periphery of the outer portion of the missile for engaging the conventional rifling grooves of the tube of the gun, the driving bands being disposed axial
  • At least one guiding member carried on an outer surface of the outwardly extending end portion of said inner portion of the missile for slidably engaging a corresponding supplemental groove in the tube.
  • An ordnance system comprising a gun including a tube provided with circumferentially spaced lands forming conventional spiral rifling grooves between them, the lands having discontinuities aligned to form supplemental rifling consisting of at least one supplemental groove, said supplemental groove forming with the longitudinal axis of the tube an angle the value of which is selected between zero so that the supplemental groove is substantially parallel to said axis and a small value thereby to form a spiral opposite to that of the conventional rifling grooves of said tube and having a depth no greater than the depth of the conventional grooves, a missile for firing from said tube including an outer portion and an inner portion coaxial therewith for carrying a charge and revolubly carried inside the outer portion, the inner portion having an end thereof extending forwardly of the outer portion, at least one driving band on the outside periphery of the outer portion of the missile for engaging the conventional rifling grooves of the tube of the gun, at least one radially extending guiding member carried by the outer surface of the
  • An ordnance system comprising a gun including a tube provided with circumferentially spaced lands forming conventional spiral rifling grooves between them, the lands having discontinuities aligned to form supplemental rifling consisting of at least one supplemental groove, said supplemental groove forming with the longitudinal axis of the tube an angle the value of which is selected between zero so that the supplemental groove is substantially parallel to the axis and a small value thereby to form a spiral opposite to that of the conventional rifling grooves of said tube and having a depth no greater than the conventional grooves, a missile for firing from said tube including an outer portion and an inner portion for carrying a charge and revolubly carried inside the outer portion and coaxial therewith, at least two driving bands on the outer portion of the missile for engaging the conventional rifling grooves, the driving bands being disposed axially on said outer portion in a predetermined axial spacing so that at least one of the driving bands engages portions of the lands which are free of discontinuities when another band is moving through

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Toys (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
US619327A 1955-11-10 1956-10-30 Ordnance Expired - Lifetime US2900873A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1043152X 1955-11-10

Publications (1)

Publication Number Publication Date
US2900873A true US2900873A (en) 1959-08-25

Family

ID=9590375

Family Applications (1)

Application Number Title Priority Date Filing Date
US619327A Expired - Lifetime US2900873A (en) 1955-11-10 1956-10-30 Ordnance

Country Status (7)

Country Link
US (1) US2900873A (enrdf_load_html_response)
BE (1) BE552464A (enrdf_load_html_response)
CH (1) CH336726A (enrdf_load_html_response)
DE (1) DE1043152B (enrdf_load_html_response)
FR (2) FR1135587A (enrdf_load_html_response)
GB (1) GB808032A (enrdf_load_html_response)
NL (2) NL112531C (enrdf_load_html_response)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2961928A (en) * 1958-11-03 1960-11-29 Rosenthal Henry Folding wing projectile
US2968996A (en) * 1959-07-13 1961-01-24 Raymond I Strickland Fin-stabilized, center-rotated rocket
US3008379A (en) * 1958-11-07 1961-11-14 Curtiss Wright Corp Low dispersion missile and launching structure
US3137233A (en) * 1962-02-23 1964-06-16 Henry S Lipinski Explosive confinement ring
US3157124A (en) * 1961-01-05 1964-11-17 Rheinmetall Gmbh Spin stabilized hollow charge projectile
US3208345A (en) * 1964-01-29 1965-09-28 Emil W Thompson Anti-spin device
US4232605A (en) * 1971-07-22 1980-11-11 General Dynamics Corporation Pomona Division Warhead orientation device
CN110145975A (zh) * 2019-04-28 2019-08-20 北京理工大学 一种破片加速装置及加速方法

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1170831B (de) 1958-03-31 1964-05-21 Iaa V R Ia Achat Ventes Repres Hohlladungsgeschoss
GB2126319B (en) * 1982-08-31 1986-07-02 Sven Landstrom Device for underwater missiles for use against submerged submarines
GB2244968B (en) * 1982-11-26 1992-05-13 Secr Defence Improvements in missile and other fuselages
DE3826615C2 (de) * 1988-08-05 1995-06-08 Rheinmetall Gmbh Gierwinkelfreies Geschoß

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2402718A (en) * 1942-02-19 1946-06-25 Albree George Norman Projectile
US2623465A (en) * 1949-02-15 1952-12-30 Brandt Soc Nouv Ets Projectile
US2670682A (en) * 1950-01-16 1954-03-02 Alfred F Teitscheid Point initiating fuse for shaped charge projectiles
US2787958A (en) * 1952-09-15 1957-04-09 Belge De Mecanique Et D Armeme Projectile

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE60825C (de) * G. R. EL-LIOTT, 73 Warren Street, Boston, County of Suffolk, Mass., V. St. A Geschofs mit mehreren in demselben angeordneten Treibladungen
FR1054322A (fr) * 1952-01-16 1954-02-09 Projectile à charge creuse pour tubes rayés

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2402718A (en) * 1942-02-19 1946-06-25 Albree George Norman Projectile
US2623465A (en) * 1949-02-15 1952-12-30 Brandt Soc Nouv Ets Projectile
US2670682A (en) * 1950-01-16 1954-03-02 Alfred F Teitscheid Point initiating fuse for shaped charge projectiles
US2787958A (en) * 1952-09-15 1957-04-09 Belge De Mecanique Et D Armeme Projectile

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2961928A (en) * 1958-11-03 1960-11-29 Rosenthal Henry Folding wing projectile
US3008379A (en) * 1958-11-07 1961-11-14 Curtiss Wright Corp Low dispersion missile and launching structure
US2968996A (en) * 1959-07-13 1961-01-24 Raymond I Strickland Fin-stabilized, center-rotated rocket
US3157124A (en) * 1961-01-05 1964-11-17 Rheinmetall Gmbh Spin stabilized hollow charge projectile
US3137233A (en) * 1962-02-23 1964-06-16 Henry S Lipinski Explosive confinement ring
US3208345A (en) * 1964-01-29 1965-09-28 Emil W Thompson Anti-spin device
US4232605A (en) * 1971-07-22 1980-11-11 General Dynamics Corporation Pomona Division Warhead orientation device
CN110145975A (zh) * 2019-04-28 2019-08-20 北京理工大学 一种破片加速装置及加速方法

Also Published As

Publication number Publication date
FR69317E (fr) 1958-10-23
BE552464A (enrdf_load_html_response)
DE1043152B (de) 1958-11-06
FR1135587A (fr) 1957-04-30
CH336726A (fr) 1959-02-28
NL211988A (enrdf_load_html_response)
GB808032A (en) 1959-01-28
NL112531C (enrdf_load_html_response)

Similar Documents

Publication Publication Date Title
US2246429A (en) Projectile
US2900873A (en) Ordnance
US4612859A (en) Multiple purpose warhead
US2408252A (en) Ammunition
US4712465A (en) Dual purpose gun barrel for spin stabilized or fin stabilized projectiles and gun launched rockets
US4800816A (en) Delay discarding sabot projectile
US4676136A (en) Apparatus for recoilless firing of projectiles from a lauching tube
US2788744A (en) Projectile for mortar
US3388666A (en) Rifle grenade
US3838644A (en) Nested hollow-charge subsidiary projectiles
US3815503A (en) Self-propelling ballistic projectiles
US2500117A (en) Rocket projectile
US3177809A (en) Semi-fixed artillery round
US5148750A (en) Unitary projectile
GB2141809A (en) Armour piercing projectile
WO2023233080A1 (en) Projectile
US3098447A (en) Projectiles to be slidably fitted on the end of a gun barrel
US4463745A (en) Device for launching a projectile
KR102269204B1 (ko) 램제트 기관을 구비하는 발사체
US2412266A (en) Reaction propelled device
US2091635A (en) Projectile
US4519316A (en) Ammunition, preferably for machine cannons, including a projectile equipped with a tracer, with the lethal range of the projectile being limited if the target is missed
US2545496A (en) Rocket projectile
US3067685A (en) Supersonic barrel-fired projectiles carrying propulsion units
US3610093A (en) Recoilless gun