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EP1006335B1 - Bremsvorrichtung für die Flugbahngeschwindigkeit eines Geschosses - Google Patents

Bremsvorrichtung für die Flugbahngeschwindigkeit eines Geschosses Download PDF

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Publication number
EP1006335B1
EP1006335B1 EP99402751A EP99402751A EP1006335B1 EP 1006335 B1 EP1006335 B1 EP 1006335B1 EP 99402751 A EP99402751 A EP 99402751A EP 99402751 A EP99402751 A EP 99402751A EP 1006335 B1 EP1006335 B1 EP 1006335B1
Authority
EP
European Patent Office
Prior art keywords
flap
projectile
flaps
braking device
folded position
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
EP99402751A
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English (en)
French (fr)
Other versions
EP1006335A1 (de
Inventor
Alain Bonnet
Anne-Laure Cros
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.)
Giat Industries SA
Original Assignee
Giat Industries SA
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 Giat Industries SA filed Critical Giat Industries SA
Publication of EP1006335A1 publication Critical patent/EP1006335A1/de
Application granted granted Critical
Publication of EP1006335B1 publication Critical patent/EP1006335B1/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
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
    • F42B10/50—Brake flaps, e.g. inflatable

Definitions

  • the technical field of the invention is that of braking devices in translation of a projectile on path.
  • Patent EP138942 thus describes a projectile artillery which has an ogive braking device whose deployment is controlled on trajectory.
  • Such an arrangement makes it possible to increase the precision artillery fire, taking into account the dispersions due variations in the initial velocity of the projectile.
  • the braking device described by this patent includes either radially movable fingers or a flat frontal surface.
  • the surface of these means of braking compared to the projectile section is too much low so that their braking capacity is sufficient.
  • WO98 / 01719 discloses another device for projectile braking. This device includes four air brake plates stacked one on the other and radially movable relative to the projectile.
  • the braking surface is thus greatly increased (it is about twice the section of the projectile) with a small footprint inside the body of the projectile.
  • Plate shapes are complex to machine, they also have many indentations that reduce their mechanical strength, especially in their fully deployed position which is the one where the constraints are maximum.
  • the unlocking of the plates is obtained by via two gas generators that move two holding pins, each pin immobilizing two plates.
  • Such a structure is likely to cause dissymmetries or jams at the time of plate deployment which may change the trajectory of the projectile in a non-reproducible manner.
  • US-5826821 also discloses a system of plates mounted rotating relative to the projectile, treacherous to brake a projectile. Each component has an indentation allowing its guidance in rotation compared to a finger. Such a structure is likely to cause dissymmetries that change the trajectory of the projectile.
  • the braking device according to the invention is of simple and inexpensive design and it presents a improved mechanical strength compared to the device previously described.
  • the subject of the invention is a device for braking in translation of a projectile on its trajectory and including at least two deployable airbrakes radially so as to increase aerodynamic drag of the projectile, each airbrake consisting of a pivoting flap around a fulcrum of the projectile and parallel to the axis of the latter, characterized in that each shutter has an external profile covering a circle whose diameter is substantially equal to that of a outer part of the projectile and a notch intended for allow the flap to fold around an axial support integral with the projectile.
  • the device for braking comprises at least one pyrotechnic piston ensuring the locking of at least one of the shutters folded position.
  • At least two shutters are stacked on each others when in their folded position, at least a first of the two components comprising means ensuring the maintenance of the second of two components folded position.
  • the braking device can have at least four components, a first component being locked by the pyrotechnic piston and carrying a first pion ensuring the retention in folded position of a second component, a third component bearing a second cooperating counter with a first solidarity holding surface of the second component, a fourth component carrying a third cooperating counter with a second solidarity holding surface of the third shutter, a single pyrotechnic piston thus ensuring Lock all four shutters.
  • Each component may have an external profile covering an arc of a circle whose diameter is substantially equal to that of an external part of the projectile and an indentation intended to allow the folding of the flap around a support axial integral with the projectile.
  • each component may include a heel stop for cooperating with a complementary surface of the axial support so as to stop the opening movement of the shutter.
  • the arc length of the outer profile of each shutter and the length of different heels can be chosen such so that, in the deployed position, the free end of at least a component is supported on a neighboring component or on the projectile.
  • the axial support can carry two plates, a platinum lower and upper plate, each platinum supporting at least two of the pivots of the flaps which located between the two decks when they are find in folded position.
  • each flap may comprise a circular toothed portion arranged around the pivot, portion which meshes with a pinion central coaxial to the projectile, central gear which ensures thus a solidarity of the different components.
  • the pyrotechnic piston can then lock the central gear.
  • the shutters can in all cases be solidarity of a projectile warhead.
  • an artillery projectile 1 is provided at the rear of a belt 2 intended to take the stripes of a weapon tube (no represented) and to seal the propellant the shot of the projectile.
  • This projectile carries to its front part a rocket 3 which is intended in a conventional manner and following the type of projectile considered (explosive projectile or cargo projectile) to ensure either the initiation of a explosive placed inside the projectile, either igniting a gas generating charge for ejecting on a trajectory a payload arranged inside the projectile (under anti-tank ammunition or grenades).
  • the rocket comprises an electronic device command 4 which causes the initiation of a load pyrotechnic 5 (which is a relay of detonation or a gas generator).
  • this rocket 3 incorporates also a device for braking in translation 6 allowing radial deployment on trajectories 7.
  • the deployment of flaps 7 is controlled by the electronic control device 4 in response to an order received on trajectory via a receiver 8 or well developed by the electronic control device 4 as a result of a pre-shooting program, or changed again in the first moments after shooting to take into account the actual initial velocity of the projectile.
  • Figure 2 shows this rocket in more detail. It has a general shape and a size similar to that classic artillery rockets. It has a body 13 on which is made a thread 9 intended to allow its solidarization with the projectile.
  • the pyrotechnic charge 5 is placed in a cup attached to the body and she communicates through a priming channel 10 with a initiation component 11 (primer or igniter) to electric trigger, which is itself connected to the electronic control device 4.
  • the initiation component 11 is carried by a movable flap 12 of a safety device and armament.
  • the body 13 of the rocket comprises an axial cylinder 14 which connects a lower portion of the rocket carrying the load pyrotechnic 5 and an upper portion of the rocket enclosing the electronic device 4. This cylinder is crossed by the priming channel 10.
  • the cylinder 14 receives the braking device 6 which comprises an axial support fins 15 having a tubular portion 16 and two plates 17 and 18.
  • the tubular portion 16 is mounted coaxially with the cylinder 14 and therefore has a diameter internal which is equal to that of the cylinder 14.
  • the turntables upper 17 and lower 18 are flat and perpendicular to the axis 20 of the rocket and the projectile.
  • the two plates 17 and 18 define an annular volume to inside which are arranged the flaps 7.
  • the support of fins 15 is made integral in translation and in rotation of the rocket body for example by a nut of blocking mounted on the cylinder 14 and not shown.
  • flaps 7a, 7b, 7c and 7d are integral with the support 15.
  • Each component is articulated in relation to the support around a pivot 19 (19a, 19b, 19c, 19d) parallel to the axis 20 of the rocket (and therefore the projectile).
  • pivots 19 are not represented only schematically in FIG. upper platen 17 carries two pivots 19a and 19b which ensure the attachment of the two flaps 7a and 7b. Platinum lower 18 door two pivots 19c and 19d which ensure the fastening of the two shutters 7c and 7d.
  • the pivots are regularly distributed angularly around the axis 20 of the rocket.
  • the different shutters are stacked on top of each other when they are in their folded position, the first flap 7a in contact with the upper plate 17 and the fourth component 7d being in contact with the bottom plate 18.
  • the second flap 7b is disposed between the first component 7a and the third component 7c, the latter being arranged itself between the second flap 7b and the fourth part 7d.
  • Figures 6 and 7 show in detail the structure of a pivot 19.
  • Figure 6 shows the structure of a pivot (19a or 19d) securing the shutters that are directly in contact with the plates 17 and 18, that is to say that of shutters 7a and 7d.
  • the pivot 19a (or 19d) is constituted by a nut 21 having an enlarged head 21a which is housed in a countersunk 22 fitted on the shutter.
  • a screw 23 has its head in contact with the plate 17 (or 18) and ensures the solidarization of the shutter and the plate.
  • a game of the order tenth of a millimeter is provided during assembly so to authorize the pivoting of the flap around the axis 24 of the pivot 19.
  • Figure 7 shows the structure of a pivot (19b or 19c) securing the shutters which are not directly in contact with turntables 17 and 18, it is say that of intermediate flaps 7b and 7c.
  • This pivot also has a nut 21 whose head widened is lodged in a blind spot and a screw 23 whose head is in contact with the plate 17 (or 18). It differs from the pivot of Figure 6 by the presence of a spacer 25 which ensures the spacing between the plate and the component considered. The thickness of the spacer is equal to that of the shutter which is inserted between the plate and the shutter intermediate considered.
  • Each shutter is made for example of sheet steel 2 mm thick and carries a bore 32 for receiving the pivot 19 and on which is fitted the countersink 22.
  • the shutters can also be made of another material for example a light alloy (aluminum-based).
  • Each component has an external profile 26 covering a arc of circle whose diameter is substantially equal to outer diameter of the rocket 3.
  • Each flap also has a notch 27 intended to allow the folding of the flap around the part tubular 16 of the axial support 15.
  • the notch 27 has a hemicylindrical portion 28 of the same diameter as that of the tubular portion 16 and coaxial with the axis 20 of this one (that is to say also to the axis of the rocket and the projectile).
  • the semicylindrical portion 28 of the notch is connects, from one side to a flat surface 29 which is perpendicular to the plane defined by the axis 24 of the pivot 19 considered and the axis 20 of the rocket and the other two cylindrical surfaces 30 and 31 the first (30) coaxial with pivot 19 and the second (31) axis parallel to that of the pivot and of radius equal to that of the tubular portion 16.
  • the surface 31 constitutes a stop stub that is intended for cooperate with the axial support 15 to stop the movement opening of section 7.
  • the cylindrical surfaces 30 and 31 are arranged at vicinity of the pivot 19 and the axis 20 of the rocket is located between the axis 24 of the pivot and the flat surface 29. It results from a such a provision that a pivoting movement of each shutter around its axis 24 is allowed without there being interference between the flat surface 29 and the tubular part 16. It also follows from the form thus adopted for shutters obtaining a maximum flap surface for a minimal space in folded position.
  • the different components also have some structural differences with each other.
  • the first flap 7a carries a hole 33 which is intended to receive the rod 35 of a pyrotechnic piston 34 (see Figure 2).
  • This pyrotechnic piston is here a retractor pyrotechnic, it comprises a composition generating gas which is initiated electrically by the control device 4 and has the effect of causing the withdrawal of the rod 35 out of the hole 33.
  • a pyrotechnic component is well known to the skilled person and it will not be described more in details.
  • the rod 35 of the retractor ensures the locking of the first flap 7a in the folded position.
  • the first component 7a also carries a first piece 36 which is intended to maintain the folded position of the second part 7b. For this purpose it cooperates with a notch 37 which is arranged on the outer circular profile 26 of the second part 7b.
  • the third part 7c carries a second piece 38 which is intended to cooperate with the flat surface 29 of the second component 7b when the latter is in the folded position.
  • This flat surface then constitutes a first surface of maintenance which prohibits the opening of the third shutter when the second flap is in the folded position.
  • the fourth component 7d carries a third pawn 39 which in a similar way cooperates with the flat surface 29 of the third component 7c when the latter is in position folded.
  • This flat surface constitutes a second surface that prohibits the opening of the fourth when the third flap is in the folded position.
  • a single pyrotechnic piston 34 ensures the locking all four shutters 7a, 7b, 7c and 7d and prevents the deployment of these as a result of efforts centrifugals which are exerted on them during the firing of the projectile.
  • the pieces 36, 38 and 39 are constituted by small cylindrical rods mounted in holes made on the shutters.
  • Figure 3 shows the four flaps in their position folded and locked.
  • the rocket cut was made in order to remove the upper platen 17. Only the first flap 7a is completely visible, its pivot 19a to the right of the figure with the nut 21 cut. The second part 7b is partially visible in the indentation of the first component, its pivot 19b is at the top of the figure with the nut 21 cut and the spacer 25 visible. The third component is hidden, its pivot 19c is at the bottom of the figure, the fourth pane is also hidden, its pivot 19d is found to the left of the figure.
  • This figure shows how they cooperate with each other different means of support in order to ensure locking the four shutters.
  • the pin 38 carried by the third flap 7c is in contact with the flat surface 29 of the second flap 7b.
  • the third shutter can not open.
  • the pin 39 carried by the fourth component 7d is in contact with the flat surface 29 of the third flap 7c.
  • the fourth shutter can not open.
  • the device electronic control 4 will cause the withdrawal of the rod 35 of the pyrotechnic piston. Under the action of force centrifuge the first flap 7a will open. The pawn 36 comes out then notch 37, which releases the second component 7b which can also open. Surface 29 moves away from the counter 38, which releases the third flap 7c, which in turn opens and releases the fourth component 7d.
  • Figure 4 shows the shutters in their position deployed.
  • each shutter is stopped by the contact from its stop butt 31 with the tubular portion 16 of the support axial 15.
  • Such an arrangement allows to control the angle opening of shutters.
  • the arc length of the outer profile 26 of each flap and the length of the different stub heels are chosen from such so that, in the deployed position, the free end 40 of each flap (the end farthest from the pivot 19) is found in support of or in relation to a neighboring component or in support or opposite the lower plate 18 (which constitutes a support surface integral with the rocket and the projectile and perpendicular to the axis of the latter).
  • the fourth component 7d is in support by its free end 40 on the lower plate 18.
  • the third flap 7c is supported by its end 40 on the fourth shutter 7d and next to the turntable 18 which increases the rigidity of the support.
  • the first and the second flap have their free ends respectively facing the third flap and bottom plate 18.
  • the opening diameter D obtained is of the order of 118 mm for an initial diameter of the lower platinum of about 61mm is an increase in diameter of the order of 90%.
  • the device according to the invention ensures obtaining a large and rigid braking surface for reduced bulk and mechanical strength important.
  • Figure 8 shows a variant in which the flaps 7 are devoid of abutment heel. They unfold totally under the effect of centrifugal force and allow to obtain a maximum opening diameter D 1 of the order of 140 mm from an initial diameter of about 61 mm.
  • the free ends of the shutters can not be found not in support or in comparison with another flap or platinum lower. This results in flap flexion and less rigidity for the device.
  • Figures 9 and 10 show a second mode of embodiment of the invention.
  • This mode differs from the previous ones in that all the shutters 7 are fixed on the body 13 by means of screws 41 which constitute the pivots of the shutters. Seven shutters 7 are planned and stacked on top of each other in folded position ( Figure 9). In order to allow the fixation of each shutter on the body 13, screws 41 of length different for each component as well as appropriate spacers (not shown).
  • Each flap 7 consists of a sheet of sheet metal of steel having an outer profile 26 covering an arc of circle whose diameter is substantially equal to the diameter external of the rocket.
  • Each flap 7 also has a notch 27 comprising a semicylindrical portion 28 for allow the flap to fold around the axial cylinder 14, integral with the rocket body 13, and coaxial with the axis 20 of this one (that is to say also to the axis of the rocket and the projectile).
  • a central gear cylindrical 42 is mounted coaxially with the axial cylinder 14 and free in rotation with respect to this one.
  • the teeth of this pinion are parallel to the axis 20 of the rocket and they meshes with toothed circular portions 43 made on all flaps 7 and coaxial with their pivot 41.
  • the central pinion 42 has an upper flange 44 on which is made a hole in which comes accommodating the rod 35 of the pyrotechnic piston 34 which thus ensures immobilization in rotation of the central pinion 42, therefore also locking all the shutters in their folded position and against the effect of centrifugal forces.
  • the device control electronics will initiate the pyrotechnic piston 34.
  • the rod 35 is extracted from its hole in the collar 44 pinion 42 which is thus unlocked.
  • Strength centrifugal action on the shutters will cause their opening, which will be accomplished symmetrically by relative to the axis 20 of the projectile because of the presence of toothed portions 43 and central pinion 42.
  • the opening is continues to the position shown in Figure 10 in which flaps are in abutment on the central gear.
  • the opening diameter D 2 that can be obtained with this embodiment of the invention is of the order of 130 mm from an initial diameter of about 61 mm.
  • the invention can of course apply to all types of large projectiles (greater than 50mm) or medium caliber (less than or equal to 50mm).

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

Claims (10)

  1. Vorrichtung (6) zum Abbremsen der Translationsbewegung eines Projektils (1) auf seiner Flugbahn, die wenigstens zwei derartig radial entfaltbare Bremsklappen umfasst, dass der aerodynamische Luftwiderstand des Projektils zunimmt, wobei jede Bremsklappe aus einer Klappe (7) gebildet wird, die um einen fest mit dem Projektil verbundenen und parallel zu dessen Achse (20) liegenden Drehpunkt (19) dreht, dadurch gekennzeichnet, dass jede Klappe (7) ein äußeres Profil (26) aufweist, das einen Kreisbogen, dessen Durchmesser nahezu gleich dem eines äußeren Abschnittes des Projektils ist, und einen bogenförmigen Ausschnitt (27) abdeckt, der dafür vorgesehen ist, das Einfalten der Klappe (7) um eine fest mit dem Projektil verbundene axiale Abstützung (15) herum zu ermöglichen.
  2. Abbremsvorrichtung nach Anspruch 1, dadurch gekennzeichnet, dass sie wenigstens einen pyrotechnischen Kolben (34) umfasst, der die Verriegelung wenigstens einer der Klappen (7) in eingefalteter Stellung gewährleistet.
  3. Abbremsvorrichtung nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass wenigstens zwei Klappen aufeinander geschichtet vor liegen, wenn sie sich in ihrer eingefalteten Stellung befinden, wobei eine Erste der beiden Klappen Mittel (36,38,39,29) umfasst, die das Festhalten der Zweiten der beiden Klappen in eingefalteter Stellung gewährleistet.
  4. Abbremsvorrichtung nach irgendeinem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass sie wenigstens vier Klappen (7a, 7b, 7c, 7d) umfasst, wobei eine erste Klappe (7a) durch den pyrotechnischen Kolben (34) verriegelt wird und ein erstes Klötzchen (36) trägt, das das Festhalten einer zweiten Klappe (7b) in eingefalteter Stellung gewährleistet, eine dritte Klappe (7c) ein zweites Klötzchen (38) trägt, das mit einer ersten, mit der zweiten Klappe (7b) einstückig ausgebildeten Haltefläche (29) zusammenwirkt, eine vierte Klappe (7d) ein drittes Klötzchen (39) trägt, das mit einer zweiten, mit der dritten Klappe (7c) einstückig ausgebildeten Haltefläche (29) zusammenwirkt und ein einziger pyrotechnischer Kolben (34) so die Verriegelung der Baugruppe der vier Klappen gewährleistet.
  5. Abbremsvorrichtung nach Anspruch 1, dadurch gekennzeichnet, dass jede Klappe (7) eine Anschlagnase (31) umfasst, die dafür vorgesehen ist, derartig mit einer komplementären Fläche der axialen Abstützung (15) zusammen zu wirken, dass die Bewegung zur Öffnung der Klappe (7) gestoppt wird.
  6. Vorrichtung nach Anspruch 5, dadurch gekennzeichnet, dass die Bogenlänge des äußeren Profils (26) einer jeden Klappe (7) und die Länge der verschiedenen Nasen (31) in der Weise gewählt werden, dass in entfalteter Stellung das freie Ende wenigstens einer Klappe entweder an einer Nachbarklappe oder auch am Projektil anliegt.
  7. Abbremsvorrichtung nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass die axiale Abstützung (15) zwei Platten (17, 18) trägt, eine untere Platte (18) und eine obere Platte (17), wobei jede Platte wenigstens zwei der Drehpunkte (19) der Klappen (7), die so zwischen den zwei Platten angeordnet sind, trägt, wenn sie sich in eingefalteter Stellung befinden.
  8. Vorrichtung nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass jede Klappe (7) einen gezahnten, kreisförmigen Abschnitt (43) umfasst, der um den Drehpunkt (41) herum angeordnet ist, wobei der Abschnitt in ein zentrales Ritzel (42) koaxial zum Projektil eingreift, und wobei das zentrale Ritzel so eine Vereinigung der verschiedenen Klappen gewährleistet.
  9. Vorrichtung nach der Ansprüche 2 bis 7, dadurch gekennzeichnet, dass der pyrotechnische Kolben (34) die Verriegelung des zentralen Ritzels (42) gewährleistet.
  10. Vorrichtung nach einem der Ansprüche 1 bis 9, dadurch gekennzeichnet, dass die Klappen (7) fest mit einem Geschossspitzen-Zünder (3) des Projektils verbunden sind.
EP99402751A 1998-11-30 1999-11-05 Bremsvorrichtung für die Flugbahngeschwindigkeit eines Geschosses Expired - Lifetime EP1006335B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9815101 1998-11-30
FR9815101A FR2786561B1 (fr) 1998-11-30 1998-11-30 Dispositif de freinage en translation d'un projectile sur trajectoire

Publications (2)

Publication Number Publication Date
EP1006335A1 EP1006335A1 (de) 2000-06-07
EP1006335B1 true EP1006335B1 (de) 2003-07-23

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EP99402751A Expired - Lifetime EP1006335B1 (de) 1998-11-30 1999-11-05 Bremsvorrichtung für die Flugbahngeschwindigkeit eines Geschosses

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US (1) US6310335B1 (de)
EP (1) EP1006335B1 (de)
DE (1) DE69909719T2 (de)
FR (1) FR2786561B1 (de)

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US5816531A (en) * 1997-02-04 1998-10-06 The United States Of America As Represented By The Secretary Of The Army Range correction module for a spin stabilized projectile
US5826821A (en) * 1997-08-04 1998-10-27 The United States Of America As Represented By The Secretary Of The Army Drag control module for range correction of a spin stabil

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FR2786561A1 (fr) 2000-06-02
DE69909719D1 (de) 2003-08-28
FR2786561B1 (fr) 2001-12-07
US6310335B1 (en) 2001-10-30
DE69909719T2 (de) 2004-04-08
EP1006335A1 (de) 2000-06-07

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