EP1321737A2 - Projectiles à empennage sur-calibré lancés à partir d'un canon - Google Patents

Projectiles à empennage sur-calibré lancés à partir d'un canon Download PDF

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Publication number
EP1321737A2
EP1321737A2 EP20020027993 EP02027993A EP1321737A2 EP 1321737 A2 EP1321737 A2 EP 1321737A2 EP 20020027993 EP20020027993 EP 20020027993 EP 02027993 A EP02027993 A EP 02027993A EP 1321737 A2 EP1321737 A2 EP 1321737A2
Authority
EP
European Patent Office
Prior art keywords
pot
missile
pressure
tail
stern
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Withdrawn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
EP20020027993
Other languages
German (de)
English (en)
Other versions
EP1321737A3 (fr
Inventor
Klaus Bär
Jürgen Bohl
Thomas Leidenberger
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
Publication of EP1321737A2 publication Critical patent/EP1321737A2/fr
Publication of EP1321737A3 publication Critical patent/EP1321737A3/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Withdrawn legal-status Critical Current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
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • F42B10/20—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel deployed by combustion gas pressure, or by pneumatic or hydraulic forces
    • 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
    • F42B10/18—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel using a longitudinally slidable support member

Definitions

  • the invention relates to a mortar-like missile to be fired from a pipe, which according to the preamble of claim 1 with an over-caliber Function position swing-out tail is equipped, which is Sliding wing or in particular around the rudder or stabilizing fins on the rear can act.
  • DE 35 07 677 A1 discloses a missile with an empennage in the form of the rear structure articulated pivotally held transversely to the missile longitudinal axis Rudder blades, with a caliber-containing position until it is fired from the tube the rudder blades is ensured, which can then be released in a defined manner when fired.
  • there are positive locking means by means of sliding locking pins between each rudder end face and the lateral surface of the rear structure intended. Due to the launch acceleration, each locking pin shifted towards its holder, causing the pivoting movement of the respective rudder blade is released in its over-calibrated functional position.
  • a similar missile with an over-caliber tail, the rudder blades for the Storage, transport and launch folded into the missile structure and in this position are locked at the end until they are dependent on starting acceleration by a safety device to be opened for unfolding is from DE 37 21 512 C1 known.
  • a safety device to be opened for unfolding is from DE 37 21 512 C1 known.
  • a missile should be spin-stabilized and therefore made of a train-equipped one Pipe are shot, so are due to the extreme passage Acceleration forces occurring in the pipe Damage caused by cutting the trains in the tail surfaces sliding along it cannot be avoided. This can then improve the functionality of the missile during free flight e.g. because of deteriorate directional stability significantly.
  • the invention is based on the knowledge of these circumstances, the task Missile, in particular one to be placed in the manner of a swirl mortar projectile Missile, to be provided at the rear, parallel or parallel to the axis Tail surfaces can be swiveled transversely to the longitudinal direction of the projectile using simple constructive measures reliably and safely in their caliber-bearing position are fixed and just as reliable for issuing after leaving the tube be released in their over-calibrated functional position.
  • the invention with a safety pot for holding tail surfaces Missiles equipped in a sub-caliber position have the advantage that the caliber-like safety pot inside the rear of the missile provided wing in the folded storage position reliably and safely sets.
  • the fuse box also has handling requirements optimal protection function in a magazine. This protective function not only refers to the said tail surfaces, but also to further ballistic located on the rear side towards the propellant gas space in the tube and sensory structures of the missile.
  • Another very significant advantage of the missile equipped according to the invention is that the safety pot without the use of external energy after the missile emerges the tube is reliably dropped from the missile in order to issue to release the rudder or similar tail surfaces.
  • the wall of the pot is pressure-tight sealed against the tail of the missile.
  • at least one sealing ring can be behind the tail unit pressure-tight sealing of the inside of the pot against the rear of the missile be provided.
  • the tail of the missile at least one sealing ring in front of the tail unit for pressure-tight sealing has opposite the pot wall.
  • the pot casing can be temporarily attached to the rear of the missile using shear pins be fixed.
  • the shear pins provide both a transport lock as well as an in-pipe fuse.
  • the shear pins are dimensioned in such a way i.e. trained with predetermined breaking points that due to the large pressure in Pressure space between the rear face of the missile and the bottom of the pot the fuse pot relative to the atmospheric pressure of the external environment, as he after the missile emerges from the tube is reliable Separation of the fuse box from the tail of the missile is effected.
  • pens are not sufficiently resilient to take the spin on the missile to transfer the pipe run from the trains to the wall of the Fuse pot is exercised.
  • the propellant gas inlet into the interior of the pot is advantageously with a directional function and therefore designed as a nozzle.
  • the nozzle can have an externally threaded section have with which they are provided in a threaded through hole provided in the bottom of the pot is screwed in.
  • the nozzle can have a central longitudinal hole have, which is connected to cross holes.
  • the fuse pot results in a correspondingly large, axially counter pressure force directed at the bottom of the pot, with which the safety pot is sheared off the locking pins after the missile emerges from the tube as a result of mentioned pressure difference from the tail of the missile is separated by about the surfaces articulated at the tail of the missile in their over-caliber flight position to swing out.
  • the missile according to the invention to be fired from a tube is thus with regard to ensuring a position that is still sub-calibrated at the start of its tailplane very simply constructed, whereby the fuse box not only a protective function for the tail unit to be kept folded and the rear side possesses ballistic and sensory structures, but also one Reliable release of the tail unit by dropping it from the tail of the missile guaranteed.
  • Figure 1 and in particular Figure 2 show a portion of the tail 10 from a tube to be fired missile 12, which is in particular one in the manner of a swirl mortar projectile but with over-caliber Tail acts.
  • wings 14 are provided, which are shown in FIG. about axes 16 oriented transversely to the longitudinal axis of the missile 12 Storage position in an extended flight position away from the tail 10 can be set up. The installation can take place due to swirl and for example are supported by means of spring elements (not shown).
  • a safety cup 18 by means of shear pins 20 temporarily fixed against relative axial displacement.
  • Slotted blocks 62 arranged in a circumferentially distributed manner engage axially in depressions one, to avoid tolerance problems as radially oriented grooves 64 inside the pot, in a solid ring surface 30 on the edge of the pot bottom are trained and in the drawn launch tube (not shown) on the Pot 18 exerted swirl transferred to the missile 12 without relative rotation.
  • the safety pot 18 is axially repelled from the rear 10 after leaving the pipe the slot the slot nuts 62 axially disengage from their slots 64.
  • the safety pot 18 has a pot shell 22 and a small wall thickness Pot bottom 24 with a 22 compared to the wall thickness of the pot shell Wall thickness.
  • the rear 10 of the missile 12 has a rear end face on the rear 26, which is formed with an annular contact surface 28.
  • the Pot bottom 24 of the securing pot 18 has an annular abutment surface 30 formed with which the pot bottom 24 on the contact surface 28 of the rear 10 of the missile 12 abuts to between the tail face 26 and the Pot bottom 24 of the fuse pot 18 to keep a pressure chamber 32 free.
  • the Pressure chamber 32 points in the cross-sectional direction between the rear end face 26 and the bottom of the pot 24 large area dimensions by the abutment surface 30 of the pot bottom 24 are defined defined.
  • the axial gap distance between the rear end face 26 and the pot bottom 24 is relatively small.
  • the pot bottom 24 of the fuse pot 18 has at least one propellant gas inlet 34 with preferred flow direction into the pot 18, which is why it as a nozzle 36 is formed, which is further below in connection with FIGS. 3 and 4 will be described in more detail.
  • the propellant gas inlet 34 opens into the pressure chamber 32 between the rear end face 26 and the pot bottom 24.
  • the tail 10 of the missile 12 is in the vicinity of the tail face 26 formed behind the wings 14 with circumferential grooves 38, in which sealing rings 40 are arranged.
  • the sealing rings 40 are used for pressure-resistant Sealing the pot shell 22 of the fuse cup 18 against the rear 10 of the Missile 12, because outside the pot 18 in the launch tube propellant pressure is pending, which should not be able to enter the structure of the missile 12.
  • a further circumferential groove 42 is in front of the wings 14 in the rear of the missile 12 educated.
  • a sealing ring 44 is arranged in the circumferential groove 42, by means of which the pot jacket 22 of the fuse cup 18 additionally against Tail 10 of the missile 12 is sealed.
  • a sealing ring 46 is on the fuse cup 18 fastened by means of screws 48.
  • FIG. 3 and 4 illustrate an embodiment of the nozzle 36 on the bottom of the pot 24 provided propellant gas inlet 34.
  • the nozzle 36 has an externally threaded section 50 and a hexagon section 52.
  • the pot bottom 24 of the fuse box 18 is formed with a threaded through hole 54 (see FIG. 2), into which the nozzle 36 is screwed with its external thread section 50.
  • To the Screwing in the nozzle 36 serves the hexagon section 52 of standardized claw or width across flats.
  • the nozzle 36 has a central longitudinal hole 56, which with Transverse holes 58 is fluidly connected.
  • the cross holes 58 are in Hexagon section 52 slit-like, intersecting, formed. They flow from the back of the fuse box 18.
  • the one associated with the cross holes Longitudinal hole 56 opens into the pressure chamber 32 between the rear end face 26 and the pot bottom 24 of the fuse pot 18.
  • FIG. 5 shows a modification of that according to FIG 2 highly abstracted in the broken longitudinal section and not to scale the tail 10 of a missile 12 enclosed by the protective pot 18 in the launch tube 66 in front of its LPG space 67, without showing the trains in Tube 66 and one between the inner tube wall and the outer pot wall attached slipping guide band to reduce twist when Pipe run.
  • the missile 12 is equipped with wings 14, which are curved around the outer lateral surface of the rear 10 in the form of a shell. They unroll when the relative overpressure in the pot interior 32 is pushed off of the pot 18 has led backwards.
  • hood 70 is put over the lens 68 and by means of elastic supports 72 pressed gas-tight against the rear 10.
  • the hood 70 is made of linen 74 or the like flexibly tied to the pot 18.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)
EP02027993A 2001-12-18 2002-12-14 Projectiles à empennage sur-calibré lancés à partir d'un canon Withdrawn EP1321737A3 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10162136 2001-12-18
DE10162136A DE10162136B4 (de) 2001-12-18 2001-12-18 Aus einem Rohr zu verschießender Flugkörper mit überkalibrigem Leitwerk

Publications (2)

Publication Number Publication Date
EP1321737A2 true EP1321737A2 (fr) 2003-06-25
EP1321737A3 EP1321737A3 (fr) 2004-05-12

Family

ID=7709650

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02027993A Withdrawn EP1321737A3 (fr) 2001-12-18 2002-12-14 Projectiles à empennage sur-calibré lancés à partir d'un canon

Country Status (3)

Country Link
US (1) US6769643B2 (fr)
EP (1) EP1321737A3 (fr)
DE (1) DE10162136B4 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009051866A1 (fr) * 2007-10-19 2009-04-23 Hr Textron Inc. Techniques pour contrôler l'accès à travers une fente sur un projectile
US8097838B2 (en) * 2005-11-15 2012-01-17 Bae Systems Bofors Ab Method of increasing the range of a subcalibre shell and subcalibre shells with a long range

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8378277B2 (en) 2009-11-30 2013-02-19 Physical Optics Corporation Optical impact control system

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3432614A1 (de) 1984-09-05 1986-03-13 Rheinmetall GmbH, 4000 Düsseldorf Flugkoerper
DE3507677A1 (de) 1985-03-05 1986-09-11 Diehl GmbH & Co, 8500 Nürnberg Flugkoerper mit ueberkalibrigem leitwerk
DE3721512C1 (de) 1987-06-30 1989-03-30 Diehl Gmbh & Co Flugkoerper mit ueberkalibrigem Leitwerk

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2603756A1 (de) * 1976-01-31 1977-08-04 Rheinmetall Gmbh Unterkalibergeschoss mit stabilisierungsfluegeln
DE2623582C2 (de) * 1976-05-26 1985-06-13 Rheinmetall GmbH, 4000 Düsseldorf Raketengeschoß mit Ausklappleitwerk und Treibspiegel
SE432670B (sv) * 1979-09-27 1984-04-09 Kurt Andersson Sett att stabilisera en artilleriprojektil och i slutfasen korrigera dess bana och artilleriprojektil for genomforande av settet
GB2077399A (en) * 1980-05-20 1981-12-16 British Aerospace Missile accuracy improvement
DE8627818U1 (fr) * 1986-10-18 1987-02-19 Messerschmitt-Boelkow-Blohm Gmbh, 8012 Ottobrunn, De
JPH06101998A (ja) * 1992-09-17 1994-04-12 Nissan Motor Co Ltd 飛翔体の展開翼保持具およびノズルクロージャ
SE508857C2 (sv) * 1997-03-25 1998-11-09 Bofors Ab Fenstabiliserad base-bleedgranat
DE19944379B4 (de) * 1999-09-16 2007-05-16 Rheinmetall Waffe Munition Patrone
SE518665C2 (sv) * 2000-03-21 2002-11-05 Bofors Weapon Sys Ab Fenstabiliserad artillerigranat
US6435097B1 (en) * 2001-04-09 2002-08-20 The United States Of America As Represented By The Secretary Of The Army Protective device for deployable fins of artillery projectiles

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3432614A1 (de) 1984-09-05 1986-03-13 Rheinmetall GmbH, 4000 Düsseldorf Flugkoerper
DE3507677A1 (de) 1985-03-05 1986-09-11 Diehl GmbH & Co, 8500 Nürnberg Flugkoerper mit ueberkalibrigem leitwerk
DE3721512C1 (de) 1987-06-30 1989-03-30 Diehl Gmbh & Co Flugkoerper mit ueberkalibrigem Leitwerk

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8097838B2 (en) * 2005-11-15 2012-01-17 Bae Systems Bofors Ab Method of increasing the range of a subcalibre shell and subcalibre shells with a long range
WO2009051866A1 (fr) * 2007-10-19 2009-04-23 Hr Textron Inc. Techniques pour contrôler l'accès à travers une fente sur un projectile
US7829830B1 (en) 2007-10-19 2010-11-09 Woodward Hrt, Inc. Techniques for controlling access through a slot on a projectile
CN101903739A (zh) * 2007-10-19 2010-12-01 伍德沃德Hrt公司 用于控制通过导弹上的狭缝的通道的技术

Also Published As

Publication number Publication date
US20040004156A1 (en) 2004-01-08
US6769643B2 (en) 2004-08-03
DE10162136A1 (de) 2003-07-10
EP1321737A3 (fr) 2004-05-12
DE10162136B4 (de) 2004-10-14

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