US20040200375A1 - Artillery projectile comprising an interchangeable payload - Google Patents

Artillery projectile comprising an interchangeable payload Download PDF

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Publication number
US20040200375A1
US20040200375A1 US10/481,201 US48120103A US2004200375A1 US 20040200375 A1 US20040200375 A1 US 20040200375A1 US 48120103 A US48120103 A US 48120103A US 2004200375 A1 US2004200375 A1 US 2004200375A1
Authority
US
United States
Prior art keywords
projectile
section
tail
projectile according
annular wall
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.)
Abandoned
Application number
US10/481,201
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English (en)
Inventor
Karl Kautzsch
Klaus Bar
Jurgen Bohl
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.)
Diehl BGT Defence GmbH and Co KG
Original Assignee
Diehl Munitionssysteme GmbH and Co KG
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 Diehl Munitionssysteme GmbH and Co KG filed Critical Diehl Munitionssysteme GmbH and Co KG
Assigned to DIEHL MUNITIONSSYSTEME GMBH & CO. KG reassignment DIEHL MUNITIONSSYSTEME GMBH & CO. KG ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BOHL, JURGEN, BAR, KLAUS, KAUTZSCH, KARL
Publication of US20040200375A1 publication Critical patent/US20040200375A1/en
Abandoned 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
    • F42B10/02—Stabilising arrangements
    • F42B10/04—Stabilising arrangements using fixed fins
    • F42B10/06—Tail fins
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B14/00—Projectiles or missiles characterised by arrangements for guiding or sealing them inside barrels, or for lubricating or cleaning barrels
    • F42B14/02—Driving bands; Rotating bands
    • 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
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • F42B10/16—Wrap-around fins
    • 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
    • F42B10/60—Steering arrangements
    • F42B10/62—Steering by movement of flight surfaces
    • F42B10/64—Steering by movement of flight surfaces of fins
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
    • F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles
    • F42B12/62—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected parallel to the longitudinal axis of the projectile

Definitions

  • the invention concerns an artillery projectile as set forth in the classifying portion of claim 1 .
  • the arrangement the general kind set forth is known as the artillery rocket system MLRS 1/2.
  • the continuous rocket casing thereof can be equipped with canisters from the tail while it is still open, behind the ogive which is fitted with a time fuse.
  • the canisters in turn are equipped with distribution units for the ejection of different armour-piercing active bodies such as for example bomblets or armour mines. Behind that axial stack of canisters the rocket is then equipped with its motor, the housing of which is equipped in the tail region with control rudders which can be deployed and which are curved parallel to the system axis.
  • the flexibility of such a system is limited however because the rocket casing is in one piece from the ogive as far as the separation location for the connection of the discardable rocket motor.
  • the technical object of the present invention is to provide a system which is more open in terms of the interchangeability of the warheads and which is distinguished in particular also by a great range with nonetheless accurately targeted delivery of the payload.
  • the payload space is the entire central section of an artillery projectile which is to be ballistically launched and which after the apogee goes into a controlled gliding flight; wherein that section which accommodates very different payloads is disposed between a standard tail section which remains the same for all payloads and which determines the external ballistics immediately after leaving the barrel, and a standard tip section which also remains the same for all payloads and which in turn is provided with canard or nose-mounted control surfaces for a controllable glide and with navigation devices such as inertial and/or satellite navigation for payload delivery of the utmost possible pinpoint accuracy.
  • the central section which can be interchangeably inserted between those two standard end sections has in its hollow-cylindrical peripheral casing at least one warhead in the manner of target-seeking submunition, a bundle of bomblets to be spread, a high-energy warhead or a post-acceleratable bar penetrator.
  • a suitably produced projectile casing portion of the central section is then flange-mounted to the standard bottom section and the standard tip section, for example being connected together by radial pins or by a kind of bayonet coupling.
  • the projectile has a unitary airframe for very different payloads and for that reason, because of unchanged external ballistics, is to be handled without any problem for firing from the artillery canon, irrespective of the payload which is to be fired at that time.
  • FIGURE of the drawing is a view in axial longitudinal section through a range-enhanced gliding projectile which is to be launched ballistically, with an interchangeable payload section between standard end sections.
  • the diagrammatic view shows in longitudinal section a projectile 11 which is to be fired from an artillery canon, that is to say ballistically, and which is divided into three in the axial direction, namely it has a load section 14 which can be inserted between a tail section 12 and a tip section 13 .
  • the load section 14 is therefore no longer a loadable load space in a continuous projectile casing, but it embodies the completely interchangeable central region of the projectile 11 together with its wall 15 .
  • the payload space 16 within the wall 15 of the central or load section 14 of the projectile 11 can be equipped with different warheads and in particular with warheads for attack on hard-armoured target objects.
  • a suitably produced load section 14 can then be equipped in the completion phase with the tail section 12 and the tip section 13 in order to complete the projectile 11 .
  • the projectile 11 is fitted with stabilisation fins 17 which are oriented rigidly in parallel relationship with the axis and which comprise for example steel sheet and which are applied against the cylindrical external peripheral surface of the tail section 12 , under a spring bias, until launch from the barrel. So that they are held in that slightly sub-calibre launch position, a cup-shaped cover 18 is pushed from the rear over the tail section 12 with those stabilisation fins 17 peripherally surrounding it.
  • the hollow-cylindrical annular wall 19 prevents the stabilisation fins 17 which are applied against the cylindrical surface of the tail section 12 from becoming deployed.
  • a peripherally extending guide band 21 is inserted into a radially shallow, axially wide groove 20 provided in the external peripheral surface of the annular wall 19 .
  • This is designed as a so-called slip-through guide band 21 , that is to say it is not non-rotatably connected to the projectile 11 , in order to reduce the stabilisation spin which is produced when the projectile is fired from the barrel, by the rifling thereof, to about 10% of the natural value, because the projectile 11 is not intended to fly in a spin-stabilised mode, in an external ballistic phase, that is to say after leaving the mouth of the barrel, but is to be aerodynamically stabilised by the fins 17 which are then extended somewhat radially outwardly.
  • annular wall 19 is caused to rotate with respect to the projectile 11 , that is to say with respect to its tail section 12 ; however it is structurally easier for the cover 18 with the annular wall 19 to be fixed non-rotatably on the tail section and for the guide band 21 to be allowed to slip through in its groove 20 .
  • That deployment effect can be implemented about axes which are parallel to the projectile axis, under the effect of centrifugal force; however, as already mentioned, it is more appropriate for the stabilisation fins 17 to be made from spring plates which are each rigidly connected (for example riveted) to the tail section 12 along an edge and which, upon being released, possibly also assisted by a flexural spring, are released from the condition of being held in contact against the tail section 12 by the annular wall 19 into a position of radially projecting in a curved configuration parallel to the longitudinal axis 22 of the projectile.
  • That flight guidance is effected by pivotal movement of the gliding wings 23 out of the neutral position, parallel to the generatrix of the ogive 24 , by means of a steering unit 25 which in turn is actuated by way of a navigation device 26 in order then to transfer from the shallow glide into a steep attack trajectory with the projectile 11 shortly before flying over the predetermined target point.
  • a navigation device 26 is activated by a fuse 27 which acts for example in distance-oriented relationship with respect to the surrounding terrain, in order to separate the tip section 13 from the load section 14 and to empty the payload space 16 by way of that separation location directly into the more closely confined target area.
  • an inexpensive terminal phase-steerable artillery munition of markedly increased range and acquisition accuracy for use which is universal in terms of variable payload under aerodynamic conditions which are always the same by virtue of maintaining the external-ballistic projectile coefficients is afforded if, in an aerodynamically stabilised gliding projectile 11 inserted between a standardised tail section 12 which initially determines the external ballistics and an also standardised tip section 13 which in the terminal phase determines range and precision is a load section 14 which connects the two contours of said sections together and which can be equipped with very different warheads which in particular are optimised against hard targets.
  • the tail section 12 For launch into an aerodynamically stabilisedly ballistic trajectory the tail section 12 is provided with super-calibre stabilisation fins 17 which in the barrel, in the firing position of being applied against the peripheral surface of the tail section 12 , have an annular wall 19 engaging thereover, the annular wall 19 being provided with a slip-through guide band 21 for initial reduction of spin while still in the barrel.
  • nose-mounted gliding wings 23 are extended from the tip section 13 , by means of which wings 23 , by way of a steering unit 25 , a transition is implemented from the descending path of the ballistic trajectory into a shallower gliding path of therefore greater range, from which finally under navigational control there is a steeper descent into a more closely predetermined target area into which the load section 14 delivers its payload.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Pharmaceuticals Containing Other Organic And Inorganic Compounds (AREA)
  • Braking Arrangements (AREA)
  • Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)
US10/481,201 2001-06-23 2002-06-15 Artillery projectile comprising an interchangeable payload Abandoned US20040200375A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE101-30-383.1 2001-06-23
DE10130383A DE10130383A1 (de) 2001-06-23 2001-06-23 Artillerie-Projektil mit austauschbarer Nutzlast
PCT/EP2002/006623 WO2003001141A1 (de) 2001-06-23 2002-06-15 Artillerie-projektil mit austauschbarer nutzlast

Publications (1)

Publication Number Publication Date
US20040200375A1 true US20040200375A1 (en) 2004-10-14

Family

ID=7689238

Family Applications (1)

Application Number Title Priority Date Filing Date
US10/481,201 Abandoned US20040200375A1 (en) 2001-06-23 2002-06-15 Artillery projectile comprising an interchangeable payload

Country Status (7)

Country Link
US (1) US20040200375A1 (de)
EP (1) EP1399706B1 (de)
KR (1) KR100796706B1 (de)
AT (1) ATE305128T1 (de)
DE (2) DE10130383A1 (de)
IL (1) IL159502A0 (de)
WO (1) WO2003001141A1 (de)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6978967B1 (en) * 2003-04-25 2005-12-27 The United States Of America As Represented By The Secretary Of The Army Space saving fin deployment system for munitions and missiles
US20070205320A1 (en) * 2005-02-07 2007-09-06 Zemany Paul D Optically Guided Munition
WO2008089078A3 (en) * 2007-01-12 2008-10-16 Raytheon Co Methods and apparatus for weapon fuze
US7506587B1 (en) 2007-02-20 2009-03-24 The United States Of Americas As Represented By The Secretary Of The Navy Modular projectile system
WO2011019424A3 (en) * 2009-05-19 2011-05-05 Raytheon Company Guided missile
US8671839B2 (en) 2011-11-04 2014-03-18 Joseph M. Bunczk Projectile and munition including projectile
US9194677B1 (en) * 2013-03-26 2015-11-24 Raytheon Company Projectile with aft obturating device
EP2972063A4 (de) * 2013-03-14 2017-01-04 BAE Systems Land & Armaments L.P. Einsatzsystem
US20200025542A1 (en) * 2017-03-15 2020-01-23 Rheinmetall Waffe Munition Gmbh Munition and logistics concept for, in particular, artillery projectiles
US10953976B2 (en) 2009-09-09 2021-03-23 Aerovironment, Inc. Air vehicle system having deployable airfoils and rudder
US11319087B2 (en) 2009-09-09 2022-05-03 Aerovironment, Inc. Systems and devices for remotely operated unmanned aerial vehicle report-suppressing launcher with portable RF transparent launch tube
JP2022099357A (ja) * 2020-12-23 2022-07-05 三菱電機株式会社 飛しょう体用レドーム、飛しょう体用レドームの製造方法
US11555672B2 (en) 2009-02-02 2023-01-17 Aerovironment, Inc. Multimode unmanned aerial vehicle

Families Citing this family (5)

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SE0502509L (sv) 2005-11-15 2007-01-09 Bae Systems Bofors Ab Underkalibrerad granat med lång räckvidd
FR2910122B1 (fr) * 2006-12-15 2009-03-06 Thales Sa Dispositif d'empennage porteur deployable pour obus
KR101098114B1 (ko) * 2009-07-06 2011-12-26 주식회사 풍산 이중 탄두형 폭발탄
FR3080912B1 (fr) 2018-05-02 2020-04-03 Nexter Munitions Projectile propulse par statoreacteur
KR102081885B1 (ko) 2018-06-19 2020-02-26 주식회사 풍산 접이식 날개전개장치

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US5760330A (en) * 1996-03-08 1998-06-02 Diehl Gmbh & Co. Method and apparatus for conveying a large-calibre payload over an operational terrain
US6126109A (en) * 1997-04-11 2000-10-03 Raytheon Company Unlocking tail fin assembly for guided projectiles
US6135387A (en) * 1997-09-17 2000-10-24 Rheinmetall W&M Gmbh Method for autonomous guidance of a spin-stabilized artillery projectile and autonomously guided artillery projectile for realizing this method
US6408762B1 (en) * 1997-12-11 2002-06-25 Lockheed Martin Corporation Clamp assembly for shrouded aerial bomb
US6666402B2 (en) * 2001-02-01 2003-12-23 United Defense, L.P. 2-D projectile trajectory corrector
US20040021034A1 (en) * 2000-08-15 2004-02-05 Ulf Hellman Guided artillery missile with extremely long range
US20040094661A1 (en) * 2000-07-03 2004-05-20 Stig Johnsson Method and arrangement for artillery missiles
US6779754B2 (en) * 2000-03-21 2004-08-24 Bofors Defence Ab Fin-stabilized artillery shell
US6886775B2 (en) * 2000-07-03 2005-05-03 Bofors Defence Ab Fin-stabilized shell
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DE3334023A1 (de) * 1983-09-21 1985-04-04 Mauser-Werke Oberndorf Gmbh, 7238 Oberndorf Geschosskoerper mit kunststoffuehrungsband
FR2654822B1 (fr) * 1987-03-17 1993-04-23 Thomson Brandt Armements Dispenseur de sous-projectiles.
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US6227119B1 (en) * 1998-10-30 2001-05-08 Lockheed Martin Corporation Lightweight warhead assembly
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US5439188A (en) * 1964-09-04 1995-08-08 Hughes Missile Systems Company Control system
US6910421B1 (en) * 1992-12-08 2005-06-28 Bae Systems Plc General purpose bombs
US5760330A (en) * 1996-03-08 1998-06-02 Diehl Gmbh & Co. Method and apparatus for conveying a large-calibre payload over an operational terrain
US6126109A (en) * 1997-04-11 2000-10-03 Raytheon Company Unlocking tail fin assembly for guided projectiles
US6135387A (en) * 1997-09-17 2000-10-24 Rheinmetall W&M Gmbh Method for autonomous guidance of a spin-stabilized artillery projectile and autonomously guided artillery projectile for realizing this method
US6408762B1 (en) * 1997-12-11 2002-06-25 Lockheed Martin Corporation Clamp assembly for shrouded aerial bomb
US6779754B2 (en) * 2000-03-21 2004-08-24 Bofors Defence Ab Fin-stabilized artillery shell
US20040094661A1 (en) * 2000-07-03 2004-05-20 Stig Johnsson Method and arrangement for artillery missiles
US6886775B2 (en) * 2000-07-03 2005-05-03 Bofors Defence Ab Fin-stabilized shell
US20040021034A1 (en) * 2000-08-15 2004-02-05 Ulf Hellman Guided artillery missile with extremely long range
US6666402B2 (en) * 2001-02-01 2003-12-23 United Defense, L.P. 2-D projectile trajectory corrector

Cited By (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6978967B1 (en) * 2003-04-25 2005-12-27 The United States Of America As Represented By The Secretary Of The Army Space saving fin deployment system for munitions and missiles
US20070205320A1 (en) * 2005-02-07 2007-09-06 Zemany Paul D Optically Guided Munition
US7533849B2 (en) * 2005-02-07 2009-05-19 Bae Systems Information And Electronic Systems Integration Inc. Optically guided munition
WO2008089078A3 (en) * 2007-01-12 2008-10-16 Raytheon Co Methods and apparatus for weapon fuze
US7971533B1 (en) 2007-01-12 2011-07-05 Raytheon Company Methods and apparatus for weapon fuze
US7506587B1 (en) 2007-02-20 2009-03-24 The United States Of Americas As Represented By The Secretary Of The Navy Modular projectile system
US11555672B2 (en) 2009-02-02 2023-01-17 Aerovironment, Inc. Multimode unmanned aerial vehicle
US12013212B2 (en) 2009-02-02 2024-06-18 Aerovironment, Inc. Multimode unmanned aerial vehicle
WO2011019424A3 (en) * 2009-05-19 2011-05-05 Raytheon Company Guided missile
US11667373B2 (en) * 2009-09-09 2023-06-06 Aerovironment, Inc. Elevon control system
US11731784B2 (en) 2009-09-09 2023-08-22 Aerovironment, Inc. Systems and devices for remotely operated unmanned aerial vehicle report-suppressing launcher with portable RF transparent launch tube
US12103678B2 (en) * 2009-09-09 2024-10-01 Aerovironment, Inc. Elevon control system
US12043382B2 (en) 2009-09-09 2024-07-23 Aerovironment, Inc. Elevon control system
US10953976B2 (en) 2009-09-09 2021-03-23 Aerovironment, Inc. Air vehicle system having deployable airfoils and rudder
US10960968B2 (en) * 2009-09-09 2021-03-30 Aerovironment, Inc. Elevon control system
US11040766B2 (en) 2009-09-09 2021-06-22 Aerovironment, Inc. Elevon control system
US20210261235A1 (en) * 2009-09-09 2021-08-26 Aerovironment, Inc. Elevon control system
US11319087B2 (en) 2009-09-09 2022-05-03 Aerovironment, Inc. Systems and devices for remotely operated unmanned aerial vehicle report-suppressing launcher with portable RF transparent launch tube
US20230264805A1 (en) * 2009-09-09 2023-08-24 Aerovironment, Inc. Elevon control system
US11577818B2 (en) 2009-09-09 2023-02-14 Aerovironment, Inc. Elevon control system
US8671839B2 (en) 2011-11-04 2014-03-18 Joseph M. Bunczk Projectile and munition including projectile
EP2972063A4 (de) * 2013-03-14 2017-01-04 BAE Systems Land & Armaments L.P. Einsatzsystem
US9593922B2 (en) 2013-03-14 2017-03-14 Bae Systems Land & Armaments L.P. Fin deployment system
US9194677B1 (en) * 2013-03-26 2015-11-24 Raytheon Company Projectile with aft obturating device
US10900761B2 (en) * 2017-03-15 2021-01-26 Rheinmetall Waffe Munition Gmbh Munition and logistics concept for, in particular, artillery projectiles
US20200025542A1 (en) * 2017-03-15 2020-01-23 Rheinmetall Waffe Munition Gmbh Munition and logistics concept for, in particular, artillery projectiles
JP2022099357A (ja) * 2020-12-23 2022-07-05 三菱電機株式会社 飛しょう体用レドーム、飛しょう体用レドームの製造方法
JP7456371B2 (ja) 2020-12-23 2024-03-27 三菱電機株式会社 飛しょう体用レドーム、飛しょう体用レドームの製造方法

Also Published As

Publication number Publication date
EP1399706A1 (de) 2004-03-24
ATE305128T1 (de) 2005-10-15
DE50204329D1 (de) 2006-02-02
KR100796706B1 (ko) 2008-01-21
WO2003001141A1 (de) 2003-01-03
IL159502A0 (en) 2004-06-01
DE10130383A1 (de) 2003-01-09
EP1399706B1 (de) 2005-09-21
KR20040011552A (ko) 2004-02-05

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AS Assignment

Owner name: DIEHL MUNITIONSSYSTEME GMBH & CO. KG, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:KAUTZSCH, KARL;BAR, KLAUS;BOHL, JURGEN;REEL/FRAME:015323/0309;SIGNING DATES FROM 20031209 TO 20031212

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION