EP1286128B2 - Roquette d'artillerie controllée par satellite avec correction par poussée latérale - Google Patents

Roquette d'artillerie controllée par satellite avec correction par poussée latérale Download PDF

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Publication number
EP1286128B2
EP1286128B2 EP02018702A EP02018702A EP1286128B2 EP 1286128 B2 EP1286128 B2 EP 1286128B2 EP 02018702 A EP02018702 A EP 02018702A EP 02018702 A EP02018702 A EP 02018702A EP 1286128 B2 EP1286128 B2 EP 1286128B2
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EP
European Patent Office
Prior art keywords
rocket
ogive
former
artillery
separating plane
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 - Fee Related
Application number
EP02018702A
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German (de)
English (en)
Other versions
EP1286128B1 (fr
EP1286128A1 (fr
Inventor
Bernhard Trosky
Harald Wich
Lutz Lehmann
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
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Diehl BGT Defence GmbH and Co KG
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Application filed by Diehl BGT Defence GmbH and Co KG filed Critical Diehl BGT Defence GmbH and Co KG
Publication of EP1286128A1 publication Critical patent/EP1286128A1/fr
Publication of EP1286128B1 publication Critical patent/EP1286128B1/fr
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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
    • F42B10/60—Steering arrangements
    • F42B10/66—Steering by varying intensity or direction of thrust
    • F42B10/661—Steering by varying intensity or direction of thrust using several transversally acting rocket motors, each motor containing an individual propellant charge, e.g. solid charge
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/34—Direction control systems for self-propelled missiles based on predetermined target position data

Definitions

  • the invention relates to an artillery rocket according to the preamble of claim 1.
  • the generic Artillerierakete is from the DE 4325218 C2 known. It is an MLRS1 rocket equipped with canards to increase range; to be able to extend the descending branch of the ballistic trajectory by their buoyancy effect on the ogive of the rocket structure. So that the fault budget does not increase incompatible, the rocket is equipped with a satellite navigation system for correcting the current trajectory with respect to the predetermined target coordinates. The orbital correction takes place dynamically by variable employment of the canards, depending on the current situation in the course of the rolling motion of the rocket in space. Since for a stable trajectory the control of the canards must always be tracked to the constant rotation of the rocket, the control effort, however, is considerable and accordingly function critical. In addition, the space required for the installation of the drive means for constantly changing the Canard employment and the vorge Glaende on board energy requirements for it is quite significant.
  • a version modified from the rocket of the MLRS 1 artillery rocket system is in the DE 37 39 370 A1 described.
  • Such missiles are ejected from a launch tube and accelerated immediately after pipe exit via a short-time active rocket engine into an aerodynamically stabilized, relatively flat ballistic trajectory along which they perform a weak rolling motion to compensate for disturbance due to departure.
  • a pre-launch temperation of a timing fuze in the tip of the rocket giveaway initiates, above the target area, a likewise inflatable gas generator for filling a coaxially along the system axis through the payload space within the missile shell extending inflation tube which increases with the growth of its Diameter axially parallel bar-shaped around it packed submunitions from the inside radially outward presses against the rocket shell and this breaks along predetermined breaking points to deploy the submunition stack side.
  • a projectile in the top of a device for projectile steering is provided in the form of a coaxial about the projectile longitudinal axis rotatable nozzle body.
  • a bulletproof gas reservoir is connected to a concentric bulletproof channel, which merges into a coaxial channel of the rotary body and then opens at right angles to the outside to a rotating transverse thrust nozzle.
  • a rotary drive for the rotating nozzle is housed, by means of which the nozzle can be stopped in any angular direction.
  • a rotating radial nozzle would scarcely make it possible to stably swivel from a spin-stabilized ballistic trajectory into a deviating trajectory.
  • EP 0 418 636 A2 is it from the WO 00/52414 A1 known to influence the trajectory of a projectile by means of a ring of small pulse motors.
  • the WO 99/66418 deals with the design of a neural network for controlling a pulsating rocket motor in the tactical missile system. From this, too, no suggestions can be made with regard to equipment measures for the cost-effective increase in performance of the artillery rockets introduced in the artillery.
  • the present invention is based on the technical problem to be able to subject the need-carrier in the depot MLRS-1 artillery rockets as simple as possible, technologically risk-free interference performance increase in terms of more precise delivery of submunitions.
  • the transverse thrust unit is equipped with an at least single-layer rim of miniaturized pyrotechnic reaction elements which act radially with respect to the rocket longitudinal axis.
  • a navigation device In front of it in the Ogive is a navigation device.
  • the navigation in the sense of tracking the actually flown actual path and at least one course correction for the eventual approach directly to the predetermined delivery coordinates preferably takes place via a winding antenna inserted in the approximately conical outer surface of the ogive for receiving the signals from navigation satellites.
  • the instantaneous roll position in the space which determines the impulse direction for carrying out a given change in direction of the rocket flight by means of a certain of the not yet consumed in previous corrections reaction elements, is particularly reliable within the course correction unit and thereby inexpensive in apparatus known as such by means to detect a rotating with the rocket, the earth's magnetic field responsive magnetic sensor on the periodicity of the time course of the signal amplitude, because the non-brightness-dependent and thus in particular also weather-independent is working.
  • a microprocessor for repeatedly comparing actual and desired positions during the flight and for the directionally selective triggering of shear thrust reaction elements for carrying out identified correction requirements also has the capacity, upon reaching the target position above the target area, to easily deploy the signal for igniting the gas generator to generate the submunition.
  • the outlined in the axial longitudinal section foremost section of an artillery rocket 11 includes the ogive 13, with an igniter 12 in its tip, to the transition into the hollow cylindrical shell 14 of the rocket body.
  • a payload space 15 for axially parallel stacked submunitions extends in itself into the rear region of the ogive 13 into it. Coaxially through the payload space 15 passes through a hose 16 which is connected via a gas pipe 17 to a pyrotechnic gas generator 18 directly behind the igniter 12. The gas generator 18 can be initiated by the igniter 12.
  • the foremost section of the payload space 15 located behind the igniter 12 and gas generator 18 is freed from submunitions in order to accommodate a course correction unit 20 with a transverse thrust unit 23.
  • the ogive 13 is separated immediately before the remaining payload space 15 to her after emptying here, pushed from the parting plane 22 forth in the slightly conically tapered interior of the ogive 18, an additional, axially thick annular bulkhead 21 as a mounting floor for the functional elements for navigation and course influence.
  • This also serves, after installation, to re-assemble the two partial arms 13a, 13b coaxially on both sides of the parting plane 22.
  • the here flush colliding faces on both sides of the dividing plane 22 are then screwed or riveted radially on the frame 21, whereby the original rocket contour is restored.
  • the above-mentioned rear part-ogive 13b is the part of the rocket structure adjoining the hollow-cylindrical shell 14, into which the payload space 15 only now extends after installation of the spider 21.
  • the annular bulkhead 21 carries the course correction unit 20 in front of a frusto-conical shear unit 23 and a wiring board 24. These internals are annularly arranged or formed so that the gas pipe 17 as sketched from the igniter 12 and the gas generator 18 forth may extend concentrically through the bulkhead 21 until the connection of the inflatable tube 16 in the payload space 15.
  • the transverse thrust unit 23 is equipped with a ring of - if necessary, as outlined, distributed to a plurality of mutually adjacent transverse planes - reaction elements 25 on the basis of pyrotechnic reaction. They can be installed as sketched in radial orientation. However, it may be structurally more advantageous to stack the small engines (that is to say the reaction elements 25) axially parallel and to connect to windrow channels which then open in the radial direction through the casing after a deflection in order to trigger the transverse thrust impulse in response.
  • the direction in which a change in course is caused thereby depends on the spatial direction in which the departure direction of the still unused and now to be activated reaction element 25 is currently oriented.
  • This current spatial position is determined by the fact that 27 recorded in the course of the rolling motion of the rocket 11 periodically recurring detection of the earth's magnetic field by means of a board 24 contained, preferably magnetically responsive roll position sensor.
  • This periodicity represents the reciprocal of the duration of one revolution of the rocket 11 about its longitudinal axis 19, so that within this period each rotational angle with respect to a spatial reference direction can be interpolated with sufficient accuracy in time.
  • a signal processor 28 which also contains the navigation data from a satellite receiver 29, which is connected to a winding antenna 30, which is inserted in a flat circumferential recess 31 in the front part of the ogive 13.
  • Such data are obtained via the navigation satellite receiver 29 in order to initiate the path correction in the direction of the predetermined target coordinates, if necessary - with respect to the fixed system orientation of the remaining available reaction elements - just matching spatial position of the rocket 11 at least one of the reaction elements 25.
  • the circuit board 24 is equipped with a power supply 32 (preferably an activatable battery with electronic voltage converter circuit) for the operation of the described additional components.
  • a Zündverteilscrien 33 provides the Initialisierraj from the signal processor 28 to the still functional, currently released to release the reaction elements 25 for a specific course influence.
  • the igniter 12 is no longer timed, but it is triggered via an ignition line 34 from the signal processor 28 when the rocket 11 has reached the predetermined position for the application of the submunitions target position.
  • the MLRS1 artillery rockets 11 stored in the depots of the consumer can thus undergo a technically uncritical increase in performance in terms of significantly improved delivery precision by temporarily cutting off the ogive 13, into it and thus into the foremost, behind the igniter 12 located area of the original payload space 15 surrounding the pyrotechnic ejection system, an annular mounting bulkhead 21 for a transverse thrust unit 23 with circumferentially radially acting small reaction elements 25 in the form of pulse engines (with pyrotechnic repulsion of a mass 26) or rocket engines incorporate, depending on the location individually of a navigation satellite-based course correction unit 20 also mounted there can be triggered.

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)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
  • Carbon And Carbon Compounds (AREA)
  • Powder Metallurgy (AREA)
  • Toys (AREA)

Claims (4)

  1. Roquette d'artillerie (11) divisée le long d'un plan de séparation (22), le plan de séparation (22) se trouvant entre l'ogive (13) et l'espace de charge utile restant (15) de la roquette (11), lequel est ensuite de nouveau assemblé dans le sens coaxial au moyen d'une membrure (21) annulaire épaisse dans le sens axial, la membrure (21) entourant un tube à gaz (17) qui s'étend d'un générateur de gaz (18) dans l'ogive (13) vers un tuyau gonflant (16) dans l'espace de la charge utile (15), et la membrure (21) étant introduite depuis le plan de séparation (22) dans l'intérieur de l'ogive (13) légèrement conique et se rétrécissant et ainsi dans la zone précédemment avant de l'espace de la charge utile (15), où cette membrure (21) sert de fond de montage pour une unité de changement de cap et une unité de poussée transversale (23) de forme annulaire qui présente une couronne d'éléments de réaction pyrotechniques (25) qui s'ouvrent dans le sens radial.
  2. Roquette d'artillerie selon la revendication 1, caractérisée en ce que la membrure de forme annulaire (21) est insérée sur une partie de son épaisseur axiale depuis le plan de séparation (22) dans l'ogive partielle avant (13a) et sert également à la liaison de verrouillage des deux ogives partielles (13a - 13b).
  3. Roquette d'artillerie selon l'une des revendications précédentes, caractérisée en ce que l'unité de poussée transversale (23) présente une couronne composée d'au moins une couche d'éléments de réaction (25) activables individuellement en fonction de la position.
  4. Roquette d'artillerie selon l'une des revendications précédentes, caractérisée en ce que son détonateur (18) peut être commandé pour initier le générateur de gaz (18) auquel est raccordé le tuyau gonflant (16) pour faire sortir latéralement des sous-munitions dans le sens coaxial à travers la membrure (21) avec son unité de poussée transversale (23).
EP02018702A 2001-08-22 2002-08-21 Roquette d'artillerie controllée par satellite avec correction par poussée latérale Expired - Fee Related EP1286128B2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10141169 2001-08-22
DE10141169A DE10141169A1 (de) 2001-08-22 2001-08-22 Artillerierakete

Publications (3)

Publication Number Publication Date
EP1286128A1 EP1286128A1 (fr) 2003-02-26
EP1286128B1 EP1286128B1 (fr) 2006-06-28
EP1286128B2 true EP1286128B2 (fr) 2009-07-29

Family

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EP02018702A Expired - Fee Related EP1286128B2 (fr) 2001-08-22 2002-08-21 Roquette d'artillerie controllée par satellite avec correction par poussée latérale

Country Status (4)

Country Link
US (1) US6685134B2 (fr)
EP (1) EP1286128B2 (fr)
DE (2) DE10141169A1 (fr)
NO (1) NO329849B1 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10354098A1 (de) * 2003-11-19 2005-06-23 Rheinmetall Waffe Munition Gmbh Querschub-Steuervorrichtung
IL178840A0 (en) * 2006-10-24 2007-09-20 Rafael Advanced Defense Sys System
US8546736B2 (en) 2007-03-15 2013-10-01 Raytheon Company Modular guided projectile
US7947938B2 (en) * 2007-03-15 2011-05-24 Raytheon Company Methods and apparatus for projectile guidance
DE102007059397A1 (de) * 2007-12-10 2009-06-18 Diehl Bgt Defence Gmbh & Co. Kg Taumelzünder

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3332415C2 (fr) † 1983-09-08 1988-01-28 Messerschmitt-Boelkow-Blohm Gmbh, 8012 Ottobrunn, De
DE3739370A1 (de) † 1987-11-20 1989-06-01 Diehl Gmbh & Co Bomblet-gefechtskopf
EP0418636A2 (fr) † 1989-09-19 1991-03-27 DIEHL GMBH & CO. Projectile à trajectoire corrigé
DE4325218C2 (de) † 1993-07-28 1998-10-22 Diehl Stiftung & Co Artillerie-Rakete und Verfahren zur Leistungssteigerung einer Artillerie-Rakete
EP0898146A2 (fr) † 1997-08-16 1999-02-24 BODENSEEWERK GERÄTETECHNIK GmbH Connexion de deux pièces de coque d'un missile
DE19824288A1 (de) † 1998-05-29 1999-12-02 Rheinmetall W & M Gmbh GPS-gestützes Geschoß

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2140538A (en) * 1983-05-17 1984-11-28 Ferranti Plc Projectile guidance system
US6460801B1 (en) * 1993-11-18 2002-10-08 Lockheed Martin Corp. Precision guidance system for aircraft launched bombs
US5379968A (en) * 1993-12-29 1995-01-10 Raytheon Company Modular aerodynamic gyrodynamic intelligent controlled projectile and method of operating same
DE4401315B4 (de) * 1994-01-19 2006-03-09 Oerlikon Contraves Gmbh Vorrichtung zur Flugbahnkorrektur
US6254031B1 (en) * 1994-08-24 2001-07-03 Lockhead Martin Corporation Precision guidance system for aircraft launched bombs
US6138945A (en) * 1997-01-09 2000-10-31 Biggers; James E. Neural network controller for a pulsed rocket motor tactical missile system
WO2000052414A1 (fr) * 1999-03-03 2000-09-08 Linick James M Moteur a impulsions visant a ameliorer des munitions a trajectoires rectifiables
US6502785B1 (en) * 1999-11-17 2003-01-07 Lockheed Martin Corporation Three axis flap control system

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3332415C2 (fr) † 1983-09-08 1988-01-28 Messerschmitt-Boelkow-Blohm Gmbh, 8012 Ottobrunn, De
DE3739370A1 (de) † 1987-11-20 1989-06-01 Diehl Gmbh & Co Bomblet-gefechtskopf
EP0418636A2 (fr) † 1989-09-19 1991-03-27 DIEHL GMBH & CO. Projectile à trajectoire corrigé
DE4325218C2 (de) † 1993-07-28 1998-10-22 Diehl Stiftung & Co Artillerie-Rakete und Verfahren zur Leistungssteigerung einer Artillerie-Rakete
EP0898146A2 (fr) † 1997-08-16 1999-02-24 BODENSEEWERK GERÄTETECHNIK GmbH Connexion de deux pièces de coque d'un missile
DE19824288A1 (de) † 1998-05-29 1999-12-02 Rheinmetall W & M Gmbh GPS-gestützes Geschoß

Also Published As

Publication number Publication date
EP1286128B1 (fr) 2006-06-28
NO20023970D0 (no) 2002-08-21
US20030038211A1 (en) 2003-02-27
US6685134B2 (en) 2004-02-03
EP1286128A1 (fr) 2003-02-26
NO20023970L (no) 2003-02-24
DE50207367D1 (de) 2006-08-10
NO329849B1 (no) 2011-01-10
DE10141169A1 (de) 2003-03-13

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