EP0872704A1 - 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
EP0872704A1
EP0872704A1 EP98400906A EP98400906A EP0872704A1 EP 0872704 A1 EP0872704 A1 EP 0872704A1 EP 98400906 A EP98400906 A EP 98400906A EP 98400906 A EP98400906 A EP 98400906A EP 0872704 A1 EP0872704 A1 EP 0872704A1
Authority
EP
European Patent Office
Prior art keywords
warhead
bosses
bars
trajectory
piezoelectric
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
EP98400906A
Other languages
English (en)
French (fr)
Other versions
EP0872704B1 (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
Original Assignee
TDA Armements SAS
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 TDA Armements SAS filed Critical TDA Armements SAS
Publication of EP0872704A1 publication Critical patent/EP0872704A1/de
Application granted granted Critical
Publication of EP0872704B1 publication Critical patent/EP0872704B1/de
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

Definitions

  • the present invention relates to a skin device smart for corrected trajectory of ammunition stabilized by rotation.
  • 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.
  • the precision error corresponds to random dispersions inherent in weapon systems. This error which can not be compensated by the pointing of the weapon intervenes mainly on range deviations.
  • the accuracy error corresponds at identical deviations during a short time interval it is due to atmospheric disturbances and pointing errors. This error which can be corrected by a change in aiming of the weapon, is characterized by both lateral and span deviations. However, a correction by simple depointing of the weapon is not generally not sufficient to compensate for the effects of disturbances encountered by the shell.
  • the skirt system deployable allows to control the trajectory of the shell by increase of the train, by opening the petals at an opportune moment of the path.
  • the major drawback of this system is that it allows correction only on the range error, the lateral deviations due to winds and pointing errors are not corrected.
  • the duck-based system has the advantage over the precedent of correct range and lateral deviations by creating force in a fixed shot 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, characterized in what it includes bosses in 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.
  • 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.

Landscapes

  • 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)
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
FR9704603A FR2762080B1 (fr) 1997-04-15 1997-04-15 Dispositif de microgouverne pour la correction de trajectoire de munition stabilisee par rotation
FR9704603 1997-04-15

Publications (2)

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1366339A2 (de) * 2001-02-01 2003-12-03 United Defense, L.P. Zweidimensionale geschossflugbahnkorrekturvorrichtung

Citations (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
US3287019A (en) * 1964-04-20 1966-11-22 Arthur Norman Robert Maneuverable target for anti-missile systems
US4142696A (en) * 1962-02-27 1979-03-06 Novatronics, Inc. Guidance devices
FR2554577A1 (fr) * 1983-11-05 1985-05-10 Diehl Gmbh & Co Systeme de commande pour munition guidee se propageant dans l'air a une vitesse supersonique
GB1605396A (en) * 1965-01-04 1995-04-26 Short Brothers & Harland Ltd Improvements relating to control systems for missiles

Patent Citations (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
FR2554577A1 (fr) * 1983-11-05 1985-05-10 Diehl Gmbh & Co Systeme de commande pour munition guidee se propageant dans l'air a une vitesse supersonique

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
A.R. KRIEBEL: "Missile nose slat", NAVY TECHNICAL DISCLOSURE BULLETIN, vol. 5, no. 12, December 1980 (1980-12-01), CAT. NO. 4164, NAVY CASE NO. 64310, pages 33 - 35, XP002055886 *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1366339A2 (de) * 2001-02-01 2003-12-03 United Defense, L.P. Zweidimensionale geschossflugbahnkorrekturvorrichtung
EP1366339A4 (de) * 2001-02-01 2006-07-19 United Defense Lp Zweidimensionale geschossflugbahnkorrekturvorrichtung

Also Published As

Publication number Publication date
FR2762080B1 (fr) 1999-07-02
EP0872704B1 (de) 2002-12-11
FR2762080A1 (fr) 1998-10-16
DE69809996T2 (de) 2003-08-21
DE69809996D1 (de) 2003-01-23

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