EP0884554A1 - 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
EP0884554A1
EP0884554A1 EP98401348A EP98401348A EP0884554A1 EP 0884554 A1 EP0884554 A1 EP 0884554A1 EP 98401348 A EP98401348 A EP 98401348A EP 98401348 A EP98401348 A EP 98401348A EP 0884554 A1 EP0884554 A1 EP 0884554A1
Authority
EP
European Patent Office
Prior art keywords
ammunition
fins
projectile
gyroscopic effect
center
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
EP98401348A
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English (en)
French (fr)
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EP0884554B1 (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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Filing date
Publication date
Application filed by TDA Armements SAS filed Critical TDA Armements SAS
Publication of EP0884554A1 publication Critical patent/EP0884554A1/de
Application granted granted Critical
Publication of EP0884554B1 publication Critical patent/EP0884554B1/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
    • F42B10/02—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 dispersal on the ground of artillery ammunition stabilized by effect gyroscopic as well as a munition applying this process. 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 necessary to take a shot on goal which allows the shooter to quickly leave the firing position, 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 done 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 munition, that is to say substantially perpendicular to the axis of revolution.
  • actuators developing forces perpendicular to the speed of displacement of the munition, that is to say substantially perpendicular to the axis of revolution.
  • knowledge of the angular position actuators relative 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 operating mode described above is possible for moderate rolling ammunition up to 30 revolutions / s per example.
  • it hardly seems applicable to ammunition stabilized by gyroscopic effect because their roll speed is then too high, it is around 300 rpm for 155 mm ammunition and the expected dynamic performances of the actuator appear in this incompatible cases of classical aeromechanical systems with control surfaces for example.
  • 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 munitions 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 mm 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 set angularly with respect to the axis of the projectile, as shown in Figure 11.

Landscapes

  • 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)
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 true EP0884554A1 (de) 1998-12-16
EP0884554B1 EP0884554B1 (de) 2003-04-16

Family

ID=9507945

Family Applications (1)

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

Country Status (3)

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

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2916268A1 (fr) * 2007-05-15 2008-11-21 Saint Louis Inst Projectile et procede de pilotage associe
EP2921812A1 (de) 2014-03-18 2015-09-23 Nexter Munitions Kreiselstabilisiertes Geschoss

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2160324A1 (de) * 1971-12-04 1973-06-07 Messerschmitt Boelkow Blohm Flugkoerper mit entfaltbaren stabilisierungsflaechen
WO1981000908A1 (en) * 1979-09-27 1981-04-02 K Andersson Projectile,adapted to be given a rotation on firing,which makes the projectile spin-stabilized
US5398887A (en) * 1993-10-12 1995-03-21 Thiokol Corporation Finless aerodynamic control system

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2160324A1 (de) * 1971-12-04 1973-06-07 Messerschmitt Boelkow Blohm Flugkoerper mit entfaltbaren stabilisierungsflaechen
WO1981000908A1 (en) * 1979-09-27 1981-04-02 K Andersson Projectile,adapted to be given a rotation on firing,which makes the projectile spin-stabilized
US5398887A (en) * 1993-10-12 1995-03-21 Thiokol Corporation Finless aerodynamic control system

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2916268A1 (fr) * 2007-05-15 2008-11-21 Saint Louis Inst Projectile et procede de pilotage associe
EP2921812A1 (de) 2014-03-18 2015-09-23 Nexter Munitions Kreiselstabilisiertes Geschoss

Also Published As

Publication number Publication date
FR2764689B1 (fr) 1999-08-27
DE69813381T2 (de) 2004-03-04
EP0884554B1 (de) 2003-04-16
FR2764689A1 (fr) 1998-12-18
DE69813381D1 (de) 2003-05-22

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