EP0872704B1 - Mikroleitwerkeinrichtung zur Veränderung der Flugrichtung eines rotationsstabilisierten Geschosses - Google Patents

Mikroleitwerkeinrichtung zur Veränderung der Flugrichtung eines rotationsstabilisierten Geschosses Download PDF

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Publication number
EP0872704B1
EP0872704B1 EP19980400906 EP98400906A EP0872704B1 EP 0872704 B1 EP0872704 B1 EP 0872704B1 EP 19980400906 EP19980400906 EP 19980400906 EP 98400906 A EP98400906 A EP 98400906A EP 0872704 B1 EP0872704 B1 EP 0872704B1
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EP
European Patent Office
Prior art keywords
ogive
piezo
bosses
trajectory
warhead
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 - Lifetime
Application number
EP19980400906
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English (en)
French (fr)
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EP0872704A1 (de
Inventor
Jean-Pierre Frehaut
Jean-Paul Labroche
Pascal Tarayre
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.)
TDA Armements SAS
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TDA Armements SAS
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Publication date
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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

Definitions

  • the present invention relates to a smart skin device for correction of trajectory of ammunition stabilized by rotation.
  • US-A-3,287,019 describes a micropilot device for ammunition trajectory correction.
  • the deviations between the point of impact of a shell and its target are usually defined in terms of precision errors and accuracy measured in the longitudinal displacement directions and cross-section of the shell.
  • Accuracy error corresponds to dispersions random inherent in weapon systems. This error which cannot be compensated by the pointing of the weapon intervenes mainly on the range deviations.
  • the accuracy error corresponds to identical deviations for a short time it is due to disturbances atmospheric and pointing errors. This error which can be corrected by a change in aiming of the weapon, is characterized at the times by lateral and span gaps. However, a correction by simple depointing of the weapon is generally not sufficient to compensate for the effects of disturbances encountered by the shell.
  • the deployable skirt system allows to control the trajectory shell by increasing the drag, opening the petals to a convenient moment of the trajectory.
  • the major drawback of this system lies in the fact that it only allows correction on the error range, lateral deviations due to winds and pointing errors do not are not corrected.
  • the duck-based system has the advantage over precedent to correct the range and lateral deviations by creating a force in a fixed plane by fins deflected at the front of the shell and which are decoupled in rotation.
  • the object of the invention is to overcome the aforementioned drawbacks.
  • the invention relates to a device for microswitch for the correction of the trajectory of stabilized ammunition by rotation of the type comprising a proximity rocket having a warhead movable in rotation relative to the body of the ammunition, comprising bosses made of deployable flexible materials arranged on the warhead to allow fixed stabilization of the warhead by compared to fixed benchmarks of space and to create a force transverse aerodynamics when the bosses are deployed on the warhead characterized in that the bosses are deployed by means of piezoelectric bars swiveling around an axis located on the surface of the warhead.
  • the main advantage of the invention is that it allows to improve both the precision and the accuracy of the shots by a control of drag and lift by modifying the obliquity of balance. For increase the range, just place the control surface formed by the bosses in a position such that the skew is balanced upwards which increases the lift coefficient. She also has the advantage that it can be implemented in a rocket interchangeable with the shell while remaining compatible with ammunition loading systems in the barrels since the outer geometry of the rocket remains unchanged, allowing the mount on statically unstable shells, i.e. shells without tail. Finally, as the bars are made of a material piezoelectric, their actuation is very simple, relative to known actuation systems for control surfaces by electric motor.
  • the example of rocket architecture according to the invention which is shown in Figure 3 includes a conical warhead 1 movable in rotation about its axis of symmetry XX 'at the end 2 an axis 3 of which the other threaded end 4 is engaged at the conical front a shell 5.
  • the rotation of the warhead 1 on the axis 3 is ensured by a bearing bearing 6.
  • the warhead 1, contains a positioning system by satellite 7, still known by the English abbreviation GPS of "Global positioning system”, possibly associated with an indicator of vertical or horizontal 8 composed for example by a central inertial and a guidance system 9 with calculator to calculate and correct trajectory errors.
  • a receiver and / or transmitter unit radio is incorporated into the guidance system 9 for ensure the transfer of flight data during the firing between the flight system guidance 9 and a ground station.
  • the shell of the warhead 1 is made of a material transparent to electromagnetic waves.
  • the angular position of the rocket relative to the marks terrestrial is controlled by two bars 10 and 11 which are arranged on either side of the fuselage of the warhead 1 and each composed of a flexible piezo-ceramic bimetal strip. These rotate in opposite directions from each other from a folded position at the warhead 1 surface to a deployed position respectively around fixed deployment axes 12 and 13 oriented in one direction perpendicular to the axis of symmetry XX '. Deployment axes 12 and 13 are located on the fuselage of the warhead 1 at different distances relatively to the front of the warhead 1.
  • a canvas referenced respectively 14 and 15 hermetically surrounds each bar 10, 11 in order to ensure a continuous geometry of the external surface of the warhead 1 and a stop to the movement of the bars when they are deployed. Because of offset axes 12 and 13, bosses 14 and 15 have also rounded edges 14a and 15a offset one with respect to the other relatively to the front of the warhead 1 which create forces of the lift forces in opposite directions in the transverse direction of the warhead 1. These forces are modulated according to the electric voltage applied to the piezoelectric bars to adjust the center of thrust of the munition relative to its center of gravity.
  • bars 10 and 11 and their fabrics enveloping 14 and 15 are pressed against the body of the warhead 1 and are deployed during the flight when a trajectory correction is to be carry out. In the deployed position, these form with the fabrics 14 and 15 two bosses on the body of the warhead 1 as shown according to the plan of section aa of FIG. 4.
  • a system for twisting bars 10 and 11, shown in Figure 5, allows by deformation of the fabrics enveloping to control the roll position of the bosses.
  • This system is realized by means of two bimetallic strips with deployment axes perpendicular, a first bimetallic strip being articulated around an axis of deployment 12 or 13, the second being articulated around an axis 16 fixed perpendicularly on a sheet of the first allows to perform a twisting of bimetallic strips 10 and 11.
  • These bimetallic strips are formed in known by two sheets 17, 18 of PZT-54 piezo-ceramic bonded from on either side of a bronze sheet 19, as shown in Figure 6.
  • This stack of bimetallic strips allows movements of deformation of the bosses according to the electric voltage applied to each bimetallic strip with an amplitude of these movements being able to be relatively large.
  • An electric current generator in the form of a alternator constituted by a stator 20 fixed to the warhead 1 and a rotor 21 fixed to the end of axis 3 allows to supply electricity to the assembly electrical circuits of the warhead 1.
  • the operating principle of the system consists, starting from of a target whose position known a priori is transmitted by radio to the guidance system 9, to be detected via the navigation system by satellite 7 or the inertial unit 8 trajectory errors early enough to have time to integrate small forces amplitudes.
  • the computer of the guidance system 9 or of the station at ground gives the instant of triggering of the correction system and the plan correction.
  • the duration of the correction represents the parameter which modulates the amplitude of the correction.
  • a pyrotechnic decoupler not shown, unlocks bars 10 and 11 which deploy by centrifugal effect. The amplitude of the movement of these is limited by the canvas covering them.
  • the governance system which is thus constituted generates a roll damping torque which uncouples roll the warhead 1 of the shell 5 by braking the rotation of the warhead 1 and stabilizes the warhead 1 in a fixed position relative to marks land space. This allows on the one hand, to eliminate the forces centrifugal damaging internal mechanisms to the warhead and secondly, allows to control the direction of the transverse correction force obtained in relation to terrestrial landmarks.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Claims (5)

  1. Mikro-Steuervorrichtung für die Korrektur der Flugbahn einer eines durch Rotation stabilisierten Geschosses, das einen Näherungszünder mit einem in Drehrichtung bezüglich des Körpers (5) des Geschosses drehbaren Geschoßkopf (1) und mit Höckern (14, 15) aus flexiblen und entfaltbaren Materialien auf dem Geschoßkopf (1), um in der entfalteten Stellung den Geschoßkopf (1) bezüglich fester Raumkoordinaten stabilisieren zu können und eine aerodynamische Kraft in Querrichtung zu erzeugen, dadurch gekennzeichnet, daß die Höcker (14, 15) mit Hilfe von piezoelektrischen Leisten (10, 11) entfaltet werden, die um eine Achse (12, 13) an der Oberfläche des Geschoßkopfes (1>) schwenkbar sind.
  2. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, daß die piezoelektrischen Leisten (10, 11) von zwei Folien (17, 18) aus einem piezokeramischen Material gebildet werden, die von beiden Seiten auf eine Folie (19) aus Bronze aufgeklebt sind.
  3. Vorrichtung nach einem beliebigen der Ansprüche 1 und 2, dadurch gekennzeichnet, daß sie ein System zum Verdrehen der piezoelektrischen Plättchen (10, 11) enthält, um die Lage der Höcker (14, 15) in Rollrichtung zu kontrollieren.
  4. Vorrichtung nach einem beliebigen der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß sie in den Geschoßkopf (1) integriert ein Satelliten-Positioniersystem (7), einen Anzeiger (8) für die vertikale Richtung und ein Lenksystem (9) enthält, das mit einem Rechner zur Berechnung der Fehler der Flugbahn nach dem Abschuß des Geschosses und zur Bestimmung des Zeitpunkts der Entfaltung der Höcker (14, 15) mittels Bewegung der piezoelektrischen Leisten (10, 11) an der Außenfläche des Geschoßkopfes (1) gekoppelt ist.
  5. Vorrichtung nach Anspruch 4, dadurch gekennzeichnet, daß das Lenksystem (9) eine Sende- und/oder Empfangseinheit für Funkwellen enthält, um die Flugdaten zwischen dem Lenksystem und einer Bodenstation zu übermitteln.
EP19980400906 1997-04-15 1998-04-10 Mikroleitwerkeinrichtung zur Veränderung der Flugrichtung eines rotationsstabilisierten Geschosses Expired - Lifetime EP0872704B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9704603 1997-04-15
FR9704603A FR2762080B1 (fr) 1997-04-15 1997-04-15 Dispositif de microgouverne pour la correction de trajectoire de munition stabilisee par rotation

Publications (2)

Publication Number Publication Date
EP0872704A1 EP0872704A1 (de) 1998-10-21
EP0872704B1 true EP0872704B1 (de) 2002-12-11

Family

ID=9505914

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19980400906 Expired - Lifetime EP0872704B1 (de) 1997-04-15 1998-04-10 Mikroleitwerkeinrichtung zur Veränderung der Flugrichtung eines rotationsstabilisierten Geschosses

Country Status (3)

Country Link
EP (1) EP0872704B1 (de)
DE (1) DE69809996T2 (de)
FR (1) FR2762080B1 (de)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1366339B1 (de) * 2001-02-01 2009-07-29 BAE Systems Land & Armaments L.P. Zweidimensionale geschossflugbahnkorrekturvorrichtung

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3145949A (en) * 1957-06-27 1964-08-25 Jr E Quimby Smith Missile guidance system
US4142696A (en) * 1962-02-27 1979-03-06 Novatronics, Inc. Guidance devices
US3287019A (en) * 1964-04-20 1966-11-22 Arthur Norman Robert Maneuverable target for anti-missile systems
GB1605396A (en) * 1965-01-04 1995-04-26 Short Brothers & Harland Ltd Improvements relating to control systems for missiles
DE3340037A1 (de) * 1983-11-05 1985-05-23 Diehl GmbH & Co, 8500 Nürnberg Stellsystem fuer gelenkte, mit ueberschallgeschwindigkeit fliegende flugkoerper

Also Published As

Publication number Publication date
DE69809996D1 (de) 2003-01-23
DE69809996T2 (de) 2003-08-21
FR2762080A1 (fr) 1998-10-16
FR2762080B1 (fr) 1999-07-02
EP0872704A1 (de) 1998-10-21

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