EP0636852A1 - Roquette d'artillerie comportant des ailettes de guidage du type canard - Google Patents

Roquette d'artillerie comportant des ailettes de guidage du type canard Download PDF

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Publication number
EP0636852A1
EP0636852A1 EP94110495A EP94110495A EP0636852A1 EP 0636852 A1 EP0636852 A1 EP 0636852A1 EP 94110495 A EP94110495 A EP 94110495A EP 94110495 A EP94110495 A EP 94110495A EP 0636852 A1 EP0636852 A1 EP 0636852A1
Authority
EP
European Patent Office
Prior art keywords
rocket
flight controller
missile
missile according
rudder
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.)
Granted
Application number
EP94110495A
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German (de)
English (en)
Other versions
EP0636852B1 (fr
Inventor
Raimer Dipl.-Ing. Steuer
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 Verwaltungs Stiftung
Original Assignee
Diehl GmbH and Co
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Filing date
Publication date
Application filed by Diehl GmbH and Co filed Critical Diehl GmbH and Co
Publication of EP0636852A1 publication Critical patent/EP0636852A1/fr
Application granted granted Critical
Publication of EP0636852B1 publication Critical patent/EP0636852B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F42B10/60—Steering arrangements
    • F42B10/62—Steering by movement of flight surfaces
    • F42B10/64—Steering by movement of flight surfaces of fins

Definitions

  • the invention relates to an artillery rocket according to the preamble of claim 1.
  • Such a missile is introduced in the western world as the MLRS base missile for ballistic deployment of submunition warheads over a predetermined target area.
  • the azimuth and elevation of the rocket's stowage and launch container determine the direction and distance to the target area during its ejection, which is followed by a short boost phase to accelerate into a ballistic trajectory, over which a time-liner programmed for a flight path determines a gas generator for ejecting the submunition warhead fires from the launch vehicle.
  • the invention is therefore based on the object of increasing the precision of a rocket of the generic type while maintaining the system components introduced.
  • the rocket is equipped with a flight controller, the technical complexity of which can be kept comparatively low because it is supported by a precise radio navigation system that not only provides a reference for the current orbit coordinates, but in particular also for the location and time of the payload delivery .
  • the flight controller works on an actuating system that is located in front of the warhead in the front area of the ogive, without the usable one Noticeably restrict the volume of the warhead.
  • the design of the rocket in the area of their rocket motor remains completely unaffected by the fact that the rudders on which the flight controller works are designed as comparatively strongly extended canards in the longitudinal direction of the rocket. Their small span enables them to be accommodated in the rocket's stowage and launch container without resorting to complex folding mechanisms to have to.
  • the basic missile 11 of the MLRS artillery system (also as the medium one) which was introduced in the western world Artillery Missile System called MARS) (which does not appear visually as a result of the interrupted representation of FIG. 1) is a very slim, that is to say very long in relation to its diameter.
  • the rocket 11 By means of its solid rocket motor 12, which extends approximately over the rear half of the missile length, the rocket 11 is accelerated in the order of magnitude of two seconds immediately after it has been ejected from the storage and launching container, in order then to be without drive on the ballistic path over the predetermined one
  • the missile 11 is equipped according to the invention with an active inertial trajectory control system 13, to which a target trajectory is predefined in the target coordinates at the start and which can thereby correct influences of errors when approaching the target area, in particular on departure disorders and on disturbing wind influences decrease, which lead to an offset of the ballistic trajectory 14 (FIG. 3) in the case of an uncorrected flight.
  • the active flight path control system 13 enables the position to be kept and the position controlled during the entire flight mission, with the detection of any deviations from the desired flight path and the correction of errors that have occurred by means of the flight controller 15, which, with the information about the control deviation 16 (FIG. 2), compensates for this on a control system 17 acts on the missile 11.
  • the rocket 11 is also equipped with a roll position sensor 18 for acting on the flight controller 15.
  • An initialization computer 19 transmits the specified target values with regard to the flight path and delivery point and the current actual values with respect to the flight controller 15 immediately before the launch of the rocket 11 Operating variables such as start coordinates and start elevation as well as current disturbance variables such as manufacturing-related misdirection when starting from the container and current cross wind strength.
  • a radio-based navigation system such as ibs. of a global positioning system (GPS) receiver 20 in the function of the flight path control system 13 with the inertial flight controller 15 allows the ignition point for the initiation of the gas generator 21 for the lateral ejection of the payload with regard to the time period from the start of the rocket 11 and / or to determine very precisely with regard to the location coordinates of the target area reached by the flight path 14 and thus to achieve high precision in the defined payload delivery that would not be achievable with an autonomous runtime control from the rocket launch.
  • GPS global positioning system
  • the entire trajectory control system 13, including electrical energy supply 22 and actuating system 17, is integrated into the front section of the ogive of the missile 11 between the warhead and the gas generator 21 in the space immediately behind the front frame 23 and takes up only a minimal payload space there in comparison to the conventional equipment of the MLRS Basic rocket 11.
  • the front main frame 23, which connects the gas generator section to the warhead shell, is thus retained in its form and function completely, but is incorporated as an integral part in the structural implementation of the additionally installed trajectory control system 13, especially with regard to the Storage of the control system 17 (see below).
  • the flight controller 15 including the inertial package (consisting of pitch and yaw rate gyros, roll position sensor 18, navigation receiver 20, and data processing) and the energy supply 22 in the conically widening section of the ogive.
  • the implementation effort for the inertial flight controller 15 can be kept comparatively low despite increased demands on the delivery accuracy, since it is updated with precise actual position coordinates from the GPS receiver 20 during the flight of the rocket 11 and the current flight speed is also always very high can be determined exactly from the GPS information (change in position over the system time difference).
  • the stabilizing fins 24 emerging at the tail of the rocket 11 after leaving the start canister are not readily available for retrofitting to control the flight path because the articulation area of the rocket motor 12 intervenes in this area should be.
  • the mechanically highly stressable area behind the front main frame 23 in the ogive of the missile 11 is selected for the positioning system storage, as a result of which the control rudders 25 are realized as canards.
  • the rear stabilizing flaps 24, which are spring-loaded only after the start, are mounted without employment.
  • the canard rudders 25 also have no position when the start is as swirl-free as possible in order to first fly through the undisturbed ballistic path 14 (left in FIG. 3) during and after the boost phase.
  • the height h of the railway apogee 34 which depends on the elevation e, this would lead to a range R which can only be varied to a limited extent and, if the start is too steep, even reduced.
  • the rudders 25 are turned on by the flight path control system 13 after apogee 34 has been reached in order to intervene correctively in the path, then the originally ballistic flight path 14 is left because the lifting effect of the now turned rudders 25 leads to an elongated path 14 'and thus to one Increasing the distance d leads to approximately twice the range 2R (FIG. 3). Because of the aerodynamic buoyancy of the canard rudders 25, the rocket 11 then flies along the latter with an almost constant glide angle precisely over the target area specified in terms of coordinates.
  • the radial dimensions of the canard oars 25 in the conically tapering ogive area in front of the warhead do not require expensive folding wings, because the clear width of the storage and launch container is sufficient to accommodate sufficiently protruding canard wings.
  • the control system 17 is not yet active during the boost phase. Then the rocket 11 is accelerated to multiple speeds of sound, but this is not a problem for the canard rudders 25 because they do not have to be unfolded first, but are held in their functional position without play.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Radar Systems Or Details Thereof (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP94110495A 1993-07-28 1994-07-06 Roquette d'artillerie comportant des ailettes de guidage du type canard Expired - Lifetime EP0636852B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4325218 1993-07-28
DE4325218A DE4325218C2 (de) 1993-07-28 1993-07-28 Artillerie-Rakete und Verfahren zur Leistungssteigerung einer Artillerie-Rakete

Publications (2)

Publication Number Publication Date
EP0636852A1 true EP0636852A1 (fr) 1995-02-01
EP0636852B1 EP0636852B1 (fr) 1996-10-02

Family

ID=6493850

Family Applications (1)

Application Number Title Priority Date Filing Date
EP94110495A Expired - Lifetime EP0636852B1 (fr) 1993-07-28 1994-07-06 Roquette d'artillerie comportant des ailettes de guidage du type canard

Country Status (3)

Country Link
US (1) US5467940A (fr)
EP (1) EP0636852B1 (fr)
DE (2) DE4325218C2 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19624187C1 (de) * 1996-06-18 1998-01-15 Diehl Gmbh & Co Rakete
DE19635847A1 (de) * 1996-09-04 1998-03-12 Daimler Benz Aerospace Ag Lenkflugkörper mit Staustrahlantrieb
US6685134B2 (en) 2001-08-22 2004-02-03 Diehl Munitionssystems Gmbh & Co. Kg Artillery rocket

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DE19500993A1 (de) * 1995-01-14 1996-07-18 Contraves Gmbh Verfahren zum Bestimmen der Rollage eines rollenden Flugobjektes
US5775636A (en) * 1996-09-30 1998-07-07 The United States Of America As Represented By The Secretary Of The Army Guided artillery projectile and method
DE19645496C2 (de) * 1996-11-05 2001-05-17 Diehl Stiftung & Co Um ihre Längsachse rotierende Rakete mit Satelliten-Navigationsempfänger
US6237496B1 (en) * 1997-02-26 2001-05-29 Northrop Grumman Corporation GPS guided munition
US5943009A (en) * 1997-02-27 1999-08-24 Abbott; Anthony Steven GPS guided munition
DE19922693A1 (de) * 1999-05-18 2000-11-23 Diehl Stiftung & Co Stelleinrichtung für Ruder eines Flugkörpers
ITMI20010648A1 (it) * 2001-03-27 2002-09-27 Finmeccanica S P A Alenia Dife Gruppo di controllo per alette direzionali di missili e/o proiettili
GB0111171D0 (en) * 2001-05-08 2001-06-27 Special Cartridge Company Ltd Projictile
DE10134785A1 (de) * 2001-07-17 2003-02-06 Diehl Munitionssysteme Gmbh Verfahren zur Flugbahnkorrektur ballistisch verschossener drallstabilisierter Artilleriemunition
DE10147837A1 (de) * 2001-09-27 2003-04-24 Rheinmetall Landsysteme Gmbh Wurfsystem für einen Gefechtskopf mit einer Richtvorrichtung zur Neutralisierung von Minen
DE10236157A1 (de) 2002-08-07 2004-02-26 Junghans Feinwerktechnik Gmbh & Co. Kg Programmierbarer Artilleriezünder
US6685143B1 (en) * 2003-01-03 2004-02-03 Orbital Research Inc. Aircraft and missile forebody flow control device and method of controlling flow
US7121210B2 (en) * 2003-02-18 2006-10-17 Kdi Precision Products, Inc. Accuracy fuze for airburst cargo delivery projectiles
US7530315B2 (en) 2003-05-08 2009-05-12 Lone Star Ip Holdings, Lp Weapon and weapon system employing the same
WO2005026654A2 (fr) 2003-05-08 2005-03-24 Incucomm, Inc. Arme et systeme d'arme mettant en oeuvre une telle arme
IL162027A (en) * 2004-05-17 2009-05-04 Rafael Advanced Defense Sys Method and system for resetting the flight path of a non-guided bullet, including compensation for deviation from the oscillations of the launcher
US7834300B2 (en) * 2005-02-07 2010-11-16 Bae Systems Information And Electronic Systems Integration Inc. Ballistic guidance control for munitions
WO2006088687A1 (fr) * 2005-02-07 2006-08-24 Bae Systems Information And Electronic Systems Integration Inc. Munitions guidees optiquement
US20080029641A1 (en) * 2005-02-07 2008-02-07 Bae Systems Information And Electronic Systems Three Axis Aerodynamic Control of Guided Munitions
US7503521B2 (en) * 2005-02-07 2009-03-17 Bae Systems Information And Electronic Systems Integration Inc. Radiation homing tag
WO2007089243A2 (fr) * 2005-02-07 2007-08-09 Bae Systems Information And Electronic Systems Integration Inc. Procédé et système de commande de munition à guidage optique
US7690304B2 (en) 2005-09-30 2010-04-06 Lone Star Ip Holdings, Lp Small smart weapon and weapon system employing the same
US7895946B2 (en) * 2005-09-30 2011-03-01 Lone Star Ip Holdings, Lp Small smart weapon and weapon system employing the same
US8541724B2 (en) 2006-09-29 2013-09-24 Lone Star Ip Holdings, Lp Small smart weapon and weapon system employing the same
IL178840A0 (en) * 2006-10-24 2007-09-20 Rafael Advanced Defense Sys System
US8117955B2 (en) * 2006-10-26 2012-02-21 Lone Star Ip Holdings, Lp Weapon interface system and delivery platform employing the same
US7926402B2 (en) * 2006-11-29 2011-04-19 Alliant Techsystems Inc. Method and apparatus for munition timing and munitions incorporating same
US7947938B2 (en) * 2007-03-15 2011-05-24 Raytheon Company Methods and apparatus for projectile guidance
US8546736B2 (en) 2007-03-15 2013-10-01 Raytheon Company Modular guided projectile
US7791007B2 (en) * 2007-06-21 2010-09-07 Woodward Hrt, Inc. Techniques for providing surface control to a guidable projectile
SE534614C2 (sv) * 2010-02-25 2011-10-25 Bae Systems Bofors Ab Granat anordnad med utfällbara vingar och styranordning
US8933383B2 (en) * 2010-09-01 2015-01-13 The United States Of America As Represented By The Secretary Of The Army Method and apparatus for correcting the trajectory of a fin-stabilized, ballistic projectile using canards
US9068803B2 (en) 2011-04-19 2015-06-30 Lone Star Ip Holdings, Lp Weapon and weapon system employing the same
US12050085B2 (en) * 2022-12-13 2024-07-30 Bae Systems Information And Electronic Systems Integration Inc. Ballistic guidance system

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US4438893A (en) * 1973-08-10 1984-03-27 Sanders Associates, Inc. Prime power source and control for a guided projectile
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FR2611886A1 (fr) * 1987-03-06 1988-09-09 Diehl Gmbh & Co Procede et dispositif de determination autonome d'une reference intertielle d'assiette a bord d'un projectile guide
FR2623280A1 (fr) * 1987-11-13 1989-05-19 Diehl Gmbh & Co Projectile d'artillerie guide comportant un regulateur de trajectoire
EP0547637A1 (fr) * 1991-12-19 1993-06-23 Hughes Aircraft Company Guidage d'arme de précision autonome utilisant un radar à ouverture synthétique

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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19624187C1 (de) * 1996-06-18 1998-01-15 Diehl Gmbh & Co Rakete
DE19635847A1 (de) * 1996-09-04 1998-03-12 Daimler Benz Aerospace Ag Lenkflugkörper mit Staustrahlantrieb
DE19635847C2 (de) * 1996-09-04 1998-07-16 Daimler Benz Aerospace Ag Lenkflugkörper mit Staustrahlantrieb
US5904319A (en) * 1996-09-04 1999-05-18 Daimler-Benz Aerospace Ag Guided missile with ram jet drive
EP0838656A3 (fr) * 1996-09-04 2000-01-19 LFK Lenkflugkörpersysteme GmbH Missile guidé à statoréacteur
US6685134B2 (en) 2001-08-22 2004-02-03 Diehl Munitionssystems Gmbh & Co. Kg Artillery rocket

Also Published As

Publication number Publication date
EP0636852B1 (fr) 1996-10-02
DE59400761D1 (de) 1996-11-07
DE4325218C2 (de) 1998-10-22
US5467940A (en) 1995-11-21
DE4325218A1 (de) 1995-02-02

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