EP0884554B1 - Verfahren zum Kontrollieren der seitlichen Streuung von kreiselstabilisierten Geschossen - Google Patents

Verfahren zum Kontrollieren der seitlichen Streuung von kreiselstabilisierten Geschossen Download PDF

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Publication number
EP0884554B1
EP0884554B1 EP19980401348 EP98401348A EP0884554B1 EP 0884554 B1 EP0884554 B1 EP 0884554B1 EP 19980401348 EP19980401348 EP 19980401348 EP 98401348 A EP98401348 A EP 98401348A EP 0884554 B1 EP0884554 B1 EP 0884554B1
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EP
European Patent Office
Prior art keywords
munition
fins
ammunition
fin
centre
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
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EP19980401348
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English (en)
French (fr)
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EP0884554A1 (de
Inventor
Jean-Paul Labroche
Jean-Pierre Frehaut
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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Publication of EP0884554A1 publication Critical patent/EP0884554A1/de
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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
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel

Definitions

  • the present invention relates to a method for controlling the lateral dispersion on the ground of artillery ammunition stabilized by effect gyroscopic as, for example, those described in document WO-A-8100908, as well as a munition applying this method. She applies in particular to improving the effectiveness of artillery ammunition especially in the context of ammunition with increased range.
  • the second process is more complex, but offers the advantage of avoiding adjustment shots, which is doubly interesting from an operational point of view by the effect of surprise obtained which does not allow the target to leave the target area and by the reduction of the time required to take a shot on goal which allows the shooter to leave the shooting position quickly, and greatly decreases the probability of location of the shooter by counter-battery radars.
  • the ammunition trajectory correction is carried out according to two steps :
  • a first step is to correct only the errors by scope. All you need is an action in the vertical plane, which can be performed from relatively simple way, by deliberately aiming beyond the target, and by controlling aerodynamic drag by an air brake system. Curvature of the trajectory is thus modulated. During this action, the control of the range involves purely axial forces, and requires only ammunition location information.
  • the second step consists of correcting also lateral errors by implementing for example actuators developing forces perpendicular to the speed of displacement of the ammunition, that is to say substantially perpendicular to the axis of revolution.
  • actuators developing forces perpendicular to the speed of displacement of the ammunition, that is to say substantially perpendicular to the axis of revolution.
  • knowledge of the angular position actuators with respect to a terrestrial reference, vertical for example, is required.
  • the trajectory correction is in principle in one direction relatively unchanging compared to a terrestrial reference, at the most less as long as the amplitude of the requested correction is sufficient important.
  • the actuators When the ammunition rolls, the actuators must, in case they are linked to the ammunition, switch to a double frequency of the roll frequency in order to achieve a "straightening" of the force generated, to obtain an average value of the non-zero resultant force.
  • the direction of the average force is adjusted by playing on the instants of switching.
  • the first method may be to use organs piezoelectric which allow switching frequencies to be reached high. However, these may not satisfy the amplitudes of deformations required.
  • the second method can consist in using organs of correction decoupled in roll from the rest of the ammunition. But such a process encounters problems in making decoupling bearings which must resist initial acceleration at the time of firing and exhibit low friction.
  • the object of the invention is to overcome the aforementioned drawbacks.
  • the invention relates to a method for the control of lateral dispersion of stabilized gyroscopic ammunition characterized in that it consists in modulating the acceleration of bypass horizontal due to the gyroscopic effect by varying the center of thrust aerodynamics of the ammunition.
  • the subject of the invention is also a munition making application of the above method.
  • the method and the device according to the invention have the advantage that they require a simple arrangement of the ammunition stabilized in rotation by gyroscopic effect requiring no rapid switching actuators, no decoupling of actuators and above all no means of vertical reference measurement.
  • the gyroscopic shunt of shells with high roll speed is a physical phenomenon resulting in a continuous lateral deviation of the trajectory, which can reach several hundred meters at the end of path.
  • the lateral deflection of a 155-millimeter shell range 27 km, depending on the horizontal distance traveled is around 800 m.
  • the skid angle corresponds to a rotation around the axis vertical and therefore lies in a horizontal plane. Lifting force associated is itself horizontal, and produces the trajectory derivation.
  • the gyroscopic bypass phenomenon leads to a horizontal deflection which is the natural response of ammunition to the vertical stress of gravity.
  • the derivation is to the right of the line firing, for a projectile rotating in the positive direction around its spin axis.
  • the speed vector V is as shown in Figure 1 tangent to the path and its direction relative to the horizontal defines the slope of the path.
  • the center of aerodynamic thrust F is located in front of the center of gravity G as shown in Figure 2 which shows ammunition in the form of a shell composed of a cylindrical body 1, a conical head 2 and a base 3.
  • ⁇ D gcos ⁇ Ap mvx F 1+ Ap mvx F
  • ⁇ D gcos ⁇ u 1 + u 2
  • a decrease in roll speed can be achieved by example by aerodynamic brakes. However these decrease the ammunition stability margin. In addition, this results in a decrease of parameter u, and therefore offers little room for correction.
  • a third solution implemented by the invention consists in modifying the static margin x F.
  • the airfoils 4 used here remain fixed after deployment. Their role is only to modify the aerodynamic center of thrust F in order to vary the static margin x F.
  • the airfoils 4 must also be angularly wedged, as shown in Figure 9, so as to maintain the roll speed of the ammunition.
  • the airfoils 4 are placed at the level of the base 3 of the projectile.
  • the deployment of the fins 4 can be obtained naturally by centrifugal effect.
  • the fins are wedged angularly with respect to the axis of the projectile, as shown in Figure 11.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Claims (6)

  1. Verfahren für die Steuerung der seitlichen Abweichung von gyroskopisch stabilisierten Geschossen (1), dadurch gekennzeichnet, daß es darin besteht, die Beschleunigung der durch den gyroskopischen Effekt bedingten horizontalen Ablenkung zu modulieren, indem das aerodynamische Schubzentrum F des Geschosses (1) variiert wird.
  2. Verfahren nach Anspruch 1, dadurch gekennzeichnet, daß es darin besteht, am hinteren Ende (3) des Geschosses einfahrbare Flügel (4) anzuordnen, um zu einem bestimmten Zeitpunkt der Bahn die Druckverteilung auf das Geschoß zu modifizieren, indem das Schubzentrum zum hinteren Ende des Geschosses verschoben wird, um die geforderte Korrektur der Ablenkung vorzunehmen.
  3. Verfahren nach Anspruch 2, dadurch gekennzeichnet, daß es darin besteht, die Flügel (4) unter einem bestimmten Neigungswinkel in bezug auf die Längsachse des Geschosses (1) am Geschoß (1) radial festzustellen, um seine Rollgeschwindigkeit nicht zu beeinflussen.
  4. Geschoß, das durch den gyroskopischen Effekt rotatorisch stabilisiert, für die Ausführung des Verfahrens nach einem der Ansprüche 1-3 geeignet ist und von dem Typ ist, der einen zylindrischen Körper (1) umfaßt, der zwischen einem konischen Kopf (2) und einer Hülse (3) angeordnet ist, dadurch gekennzeichnet, daß es einfahrbare Flügel (4) umfaßt, die radial an der Hülse (3) angeordnet sind, um dann, wenn sie ausgefahren sind, die durch den gyroskopischen Effekt bedingte horizontale Ablenkung des Geschosses zu korrigieren.
  5. Munition nach Anspruch 4, dadurch gekennzeichnet, daß die Flügel (4) relativ zur Längsachse des Geschosses unter einem Winkel η geneigt sind, derart, daß tg η = pd/V (11) gilt, wobei p die Rollgeschwindigkeit ist, d der Abstand zwischen der Mittelachse des Geschosses und dem Schwerpunkt des Flügels (4) ist und V die Geschwindigkeit des Geschosses (1) ist.
  6. Geschoß nach Anspruch 5, dadurch gekennzeichnet, daß jeder Flügel (4) eine Oberfläche Sa besitzt, die durch die Beziehung Sa = Sc CNc 4CNa .xF0 - xF1 xF1 - La definiert ist, worin Sc die Fläche des Hauptspants des Geschosses ist, CNc die Auftriebszahl des Körpers des Geschosses ist, CNa die Auftriebszahl des Flügels ist, xF0 das Stabilitätsmaß des Geschosses ohne Flügel ist, xF1 das Stabilitätsmaß des Geschosses mit Flügeln ist und La der Hebelarm des Flügelauftriebs ist.
EP19980401348 1997-06-13 1998-06-05 Verfahren zum Kontrollieren der seitlichen Streuung von kreiselstabilisierten Geschossen Expired - Lifetime EP0884554B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9707352A FR2764689B1 (fr) 1997-06-13 1997-06-13 Procede pour le controle de la dispersion laterale des munitions stabilisees par effet gyroscopique
FR9707352 1997-06-13

Publications (2)

Publication Number Publication Date
EP0884554A1 EP0884554A1 (de) 1998-12-16
EP0884554B1 true EP0884554B1 (de) 2003-04-16

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Application Number Title Priority Date Filing Date
EP19980401348 Expired - Lifetime EP0884554B1 (de) 1997-06-13 1998-06-05 Verfahren zum Kontrollieren der seitlichen Streuung von kreiselstabilisierten Geschossen

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EP (1) EP0884554B1 (de)
DE (1) DE69813381T2 (de)
FR (1) FR2764689B1 (de)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2916268B1 (fr) * 2007-05-15 2010-09-10 Saint Louis Inst Projectile et procede de pilotage associe
FR3018908B1 (fr) 2014-03-18 2016-03-04 Nexter Munitions Projectile gyrostabilise

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2160324C2 (de) * 1971-12-04 1982-04-08 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Flugkörper mit entfaltbaren Stabilisierungsflächen
SE432670B (sv) * 1979-09-27 1984-04-09 Kurt Andersson Sett att stabilisera en artilleriprojektil och i slutfasen korrigera dess bana och artilleriprojektil for genomforande av settet
US5398887A (en) * 1993-10-12 1995-03-21 Thiokol Corporation Finless aerodynamic control system

Also Published As

Publication number Publication date
DE69813381T2 (de) 2004-03-04
DE69813381D1 (de) 2003-05-22
FR2764689A1 (fr) 1998-12-18
EP0884554A1 (de) 1998-12-16
FR2764689B1 (fr) 1999-08-27

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