EP0485897A1 - Projectile à correction de trajectoire - Google Patents

Projectile à correction de trajectoire Download PDF

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Publication number
EP0485897A1
EP0485897A1 EP91119035A EP91119035A EP0485897A1 EP 0485897 A1 EP0485897 A1 EP 0485897A1 EP 91119035 A EP91119035 A EP 91119035A EP 91119035 A EP91119035 A EP 91119035A EP 0485897 A1 EP0485897 A1 EP 0485897A1
Authority
EP
European Patent Office
Prior art keywords
projectile
cover
projectile according
envelope element
envelope
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
EP91119035A
Other languages
German (de)
English (en)
Other versions
EP0485897B1 (fr
Inventor
Jürgen Leininger
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
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 GmbH and Co filed Critical Diehl GmbH and Co
Publication of EP0485897A1 publication Critical patent/EP0485897A1/fr
Application granted granted Critical
Publication of EP0485897B1 publication Critical patent/EP0485897B1/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
    • F42B10/66—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
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/30—Command link guidance systems
    • F41G7/301—Details
    • F41G7/305—Details for spin-stabilized missiles

Definitions

  • the invention relates to a projectile according to the preamble of claim 1.
  • Such a projectile is known from DE 22 64 243 C2 as a missile rotating during flight, in which the trajectory can be changed with the aid of at least one pulse which can be triggered during flight and is oriented radially to the missile in order to increase the probability of being hit.
  • the pulse resulting from the ignition of the corresponding pulse charge is composed of two parts, namely the part of the lid mass flying away from the projectile and the part of the gas mass flowing out.
  • the impulse causes the projectile to react with a transverse velocity component perpendicular to the central longitudinal axis of the projectile.
  • the amount of the resulting transverse speed depends on whether the impulse acts radially through the projectile center of gravity or under a lever arm radially to the projectile center of gravity. In one case there is a force control, in the other case there is a torque control.
  • Information about the current path deposit with respect to the target receiving or calculating control device determines in which roll position of the projectile the transverse pulse is triggered, or which of several cross-thrust drive devices arranged and still available distributed around the circumference of the projectile for the necessary path correction has the most suitable spatial orientation and is therefore to be controlled electrically.
  • the invention has for its object to provide a projectile of the type mentioned, in which the manufacturing cost is significantly reduced compared to the generic projectile of the type mentioned.
  • the advantages achieved with the invention are that it is not necessary to produce a separate cover for each transverse thrust drive device and to mount the various covers on the projectile in separate operations. This results not only in a reduction in the manufacturing outlay but also in a reduction in the assembly outlay, ie a production- or production-friendly system for the integration of the covers for the transverse thrust drive devices of the web-correctable projectile.
  • the projectile according to the invention can be, for example, an aerodynamically stabilized or a spin-stabilized projectile. Spin stabilization is not mandatory for orbit correction with impulse charges. To use the impulse charges discretely distributed around the circumference of the projectile for a spatial orbit correction, only a non-zero roll rate is required. The required roll rotation rate depends on the realizable impulse effective time.
  • the projectile can also be aerodynamically stabilized and have a much smaller roll rotation wire than a spin-stabilized projectile. It is possible to provide a separate envelope element for each pulse charge ring, ie for each row of pulse charges that are provided spaced apart along the circumference of the projectile. However, it is also possible to provide an enveloping element for a plurality of impulse charge rings, ie rows of transverse thrust drive devices distributed uniformly along the circumference of the projectile. Another advantage is that the individual pulse charges adhere to the shape of the envelope element surrounding the projectile can be adapted, whereby an increase in the pulse charge volume and consequently an increase in the pulse effect can be achieved.
  • the predetermined breaking lines for fixing the individual covers can be formed, for example, on a flat, flat band, after which the actual shaping of the enveloping element takes place as a closed annular sleeve, as an open annular sleeve or as a two-part or multi-part sleeve.
  • the formation of the predetermined breaking lines is relatively easy to implement in a flat, flat band.
  • FIG. 1 shows a path-correctable projectile 10 with transverse thrust drive devices 12, which - as can be clearly seen in FIG. 2 - are evenly spaced apart along the circumference of the projectile 10.
  • Each transverse thrust drive device 12 has a pulse charge 14 and a cover 16.
  • the covers 16 are formed on an envelope element 18 surrounding the projectile 10, each cover 16 being delimited and determined by a predetermined breaking line 20 formed in the envelope element 18, i.e. is set.
  • Each individual pulse charge 14 is provided in an associated receiving space 22 formed in the projectile 10.
  • the individual receiving spaces 22 for each associated pulse charge 14 are tapered in the shape of a truncated cone towards the central longitudinal axis 24 of the projectile.
  • Each pulse charge 14 is provided with a detonator 26 which is connected to an electrical ignition cable 28.
  • the enveloping element 18 is designed as a self-contained, annular sleeve. However, it would also be possible for the enveloping element 18 to be designed as an open annular sleeve. Likewise, it is possible to use two enveloping elements Form halves of the sleeve or by more than two sleeve parts. It can be seen from FIGS. 1, 2 and 3 that the predetermined breaking lines 20 delimiting and defining the individual covers 16 are formed on the inner surface 30 of the enveloping element 18. In this way, there is the advantage that no reworking is necessary in order not to impair the aerodynamic properties of the projectile 10 by the predetermined breaking lines 20.
  • the predetermined breaking line 20 which defines a corresponding cover 16 has a profile which is adapted to the profile of the outer edge 32 of the receiving space 22 for the corresponding pulse charge 14. If the individual receiving spaces 22 are thus tapered in the shape of a truncated cone, the predetermined breaking lines 20 are circular in accordance with the outer edge edges 32 of the receiving spaces 22, as can be seen from FIG. 3.
  • the enveloping element 18 is preferably arranged in a recess 34 which runs around the projectile 10, the cross-sectional contour of the enveloping element 18 being dimensioned such that, for aerodynamic reasons, there is a virtually stepless or offset outer contour of the projectile 10.
  • Fastening elements 36 which are, for example, countersunk screws, are used to fasten the enveloping element 18 to the projectile 10 or in the recess 34 of the projectile 10. With the aid of the fastening elements 36, in particular an open ring-shaped envelope element 18 or an envelope element 18 formed by at least two sleeve parts or halves on the projectile 10 is secured against axial displacement or against displacement in the circumferential direction of the projectile 10.
  • the enveloping element 18 - as can be seen particularly clearly from FIG. 3 - is formed on the edge section 38 with spaced-apart recesses 40 and the projectile is provided with a circumferential shoulder 42 which has a height corresponding to the wall thickness of the enveloping element 18 and the recesses 40 on the edge portion 38 of the Envelope element 18 has corresponding locking members 44.
  • Such a latching also results in a mechanical relief of the fastening elements 36.
  • the reference number 46 in FIG. 3 denotes through holes which have a depression 48 on the outside.
  • the fastening elements 36 are screwed into corresponding threaded holes 50 (see FIG. 1) in the projectile 10 through the through holes 46.
  • the depressions 48 serve to receive the countersunk heads of the fastening elements 36 designed as countersunk screws.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP91119035A 1990-11-14 1991-11-08 Projectile à correction de trajectoire Expired - Lifetime EP0485897B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4036166 1990-11-14
DE4036166A DE4036166A1 (de) 1990-11-14 1990-11-14 Bahnkorrigierbares projektil

Publications (2)

Publication Number Publication Date
EP0485897A1 true EP0485897A1 (fr) 1992-05-20
EP0485897B1 EP0485897B1 (fr) 1995-09-20

Family

ID=6418198

Family Applications (1)

Application Number Title Priority Date Filing Date
EP91119035A Expired - Lifetime EP0485897B1 (fr) 1990-11-14 1991-11-08 Projectile à correction de trajectoire

Country Status (2)

Country Link
EP (1) EP0485897B1 (fr)
DE (2) DE4036166A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2287439A (en) * 1994-03-10 1995-09-20 Rheinmetall Ind Gmbh Rocket thruster arrangement for guiding missile
EP1533589A1 (fr) * 2003-11-19 2005-05-25 Rheinmetall Waffe Munition GmbH Système de contrôle utilisant un jet transversal

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4321392A1 (de) * 1993-06-26 1995-01-05 Bayern Chemie Gmbh Flugchemie Verfahren zur Flugbahnkorrektur eines Flugkörpers
DE102005052474B3 (de) * 2005-11-03 2007-07-12 Junghans Feinwerktechnik Gmbh & Co. Kg Drallstbilisiertes Artillerieprojektil
DE102011010902A1 (de) 2011-02-10 2012-08-16 Diehl Bgt Defence Gmbh & Co. Kg Schutzsystem
DE102014014950A1 (de) * 2014-10-08 2016-04-28 Mbda Deutschland Gmbh Flugkörper
DE102014014952B4 (de) * 2014-10-08 2016-05-25 Mbda Deutschland Gmbh Flugkörper

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3860199A (en) * 1972-01-03 1975-01-14 Ship Systems Inc Laser-guided projectile system
FR2346673A1 (fr) * 1976-04-02 1977-10-28 Bofors Ab Dispositif de correction de la trajectoire d'un projectile
WO1983003894A1 (fr) * 1982-04-21 1983-11-10 Hughes Aircraft Company Systeme de guidage de projectiles en fin de trajectoire
EP0229541A1 (fr) * 1985-11-29 1987-07-22 ETAT-FRANCAIS représenté par le DELEGUE GENERAL POUR L'ARMEMENT (DPAG) Dispositif de basculement de projectile sur trajectoire
EP0365886A1 (fr) * 1988-10-27 1990-05-02 Werkzeugmaschinenfabrik Oerlikon-Bührle AG Procédé de fabrication d'une enceinte destinée à la fragmentation
EP0418636A2 (fr) * 1989-09-19 1991-03-27 DIEHL GMBH & CO. Projectile à trajectoire corrigé

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3860199A (en) * 1972-01-03 1975-01-14 Ship Systems Inc Laser-guided projectile system
FR2346673A1 (fr) * 1976-04-02 1977-10-28 Bofors Ab Dispositif de correction de la trajectoire d'un projectile
WO1983003894A1 (fr) * 1982-04-21 1983-11-10 Hughes Aircraft Company Systeme de guidage de projectiles en fin de trajectoire
EP0229541A1 (fr) * 1985-11-29 1987-07-22 ETAT-FRANCAIS représenté par le DELEGUE GENERAL POUR L'ARMEMENT (DPAG) Dispositif de basculement de projectile sur trajectoire
EP0365886A1 (fr) * 1988-10-27 1990-05-02 Werkzeugmaschinenfabrik Oerlikon-Bührle AG Procédé de fabrication d'une enceinte destinée à la fragmentation
EP0418636A2 (fr) * 1989-09-19 1991-03-27 DIEHL GMBH & CO. Projectile à trajectoire corrigé

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2287439A (en) * 1994-03-10 1995-09-20 Rheinmetall Ind Gmbh Rocket thruster arrangement for guiding missile
GB2287439B (en) * 1994-03-10 1998-03-04 Rheinmetall Ind Gmbh Guiding missiles
EP1533589A1 (fr) * 2003-11-19 2005-05-25 Rheinmetall Waffe Munition GmbH Système de contrôle utilisant un jet transversal
US7118065B1 (en) 2003-11-19 2006-10-10 Rheinmetall Waffe Munition Gmbh Lateral thrust control

Also Published As

Publication number Publication date
DE59106528D1 (de) 1995-10-26
EP0485897B1 (fr) 1995-09-20
DE4036166A1 (de) 1992-05-21

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