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EP1045221B1 - Bremsvorrichtung für die Flugbahngeschwindigkeit eines Geschosses - Google Patents

Bremsvorrichtung für die Flugbahngeschwindigkeit eines Geschosses Download PDF

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Publication number
EP1045221B1
EP1045221B1 EP00106787A EP00106787A EP1045221B1 EP 1045221 B1 EP1045221 B1 EP 1045221B1 EP 00106787 A EP00106787 A EP 00106787A EP 00106787 A EP00106787 A EP 00106787A EP 1045221 B1 EP1045221 B1 EP 1045221B1
Authority
EP
European Patent Office
Prior art keywords
projectile
flap
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
EP00106787A
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English (en)
French (fr)
Other versions
EP1045221A1 (de
Inventor
Alain Bonnet
Bertrand Padiolleau
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 EP1045221A1 publication Critical patent/EP1045221A1/de
Application granted granted Critical
Publication of EP1045221B1 publication Critical patent/EP1045221B1/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.
  • Such devices are notably known in the field artillery.
  • Patent EP138942 thus describes a projectile artillery which includes a warhead braking device whose deployment is controlled on a trajectory.
  • Such an arrangement makes it possible to increase the precision of the artillery fire taking into account dispersions due to variations in the initial velocity of the projectile. Indeed, it is possible then to point the weapon in order to shoot more far from the target, a fire line measures the actual velocity of the projectile at the exit of the barrel of the weapon and a braking command is then transmitted to the projectile of so as to reduce its range and thus bring it to the point desired impact.
  • the braking device described by this patent comprises, either radially movable fingers or a surface flat front.
  • the surface of these braking means by relation to the projectile section is too small for their braking capacity is sufficient.
  • WO98 / 01719 describes another device for projectile braking. This device includes four airbrake plates stacked on top of each other and radially movable relative to the projectile.
  • the braking surface is thus greatly increased (it constitutes approximately twice the section of the projectile) with a reduced bulk inside the body of the projectile.
  • Plate shapes are complex to machine, they also have many notches that reduce their mechanical resistance, especially in their position fully deployed which is where the constraints are maximum.
  • each plate is guided by the cooperation of pins integral with the ends of the arms carried by the plate and which cooperate in notches of a neighboring plate as well as a bottom plate.
  • Arms have a certain flexibility which affects reliability guidance. This results in risks of jamming which are increased by the fact that the guide is double (on a plate neighbor and a bottom plate).
  • Patent US5826821 describes a braking device in which the flaps deploy by pivoting around axes parallel to the axis of the projectile.
  • the patent US5816531 describes a braking device comprising four flaps which translate radially with respect to the projectile. Each flap carries a rib sliding in a groove of a base plate and a finger which engages in a cam ensuring the synchronism of the opening of the shutters.
  • the devices described by these two patents are likely to jams and asymmetries.
  • the braking device according to the invention is of simple and inexpensive design and it has a improved mechanical resistance compared to the device previously described.
  • the subject of the invention is a braking device in translation of a projectile on its trajectory and comprising at least two radially deployable air brakes so as to increase the aerodynamic drag of the projectile, airbrakes produced in the form of translating flaps in a plane perpendicular to the axis of the device projectile characterized in that each flap has at least two closed grooves substantially parallel to a direction perpendicular to the axis of the projectile, each groove cooperating with a rod which is fixed relative to the projectile.
  • each rod can cooperate with two grooves of two adjacent flaps.
  • the device may include at least one piston pyrotechnic ensuring the locking of at least one of the flaps in the folded position.
  • At least two shutters are stacked on top of each other when are in their folded position, at least a first two components comprising means ensuring the maintenance of the second of the two flaps in the folded position.
  • the braking device has at least three components, a first component being locked by the pyrotechnic piston and bearing a first notch cooperating with a first pawn carried by a second flap to maintain the folded position of it, the second flap carrying a second notch cooperating with a second pawn carried by a third component to maintain it in the folded position, single pyrotechnic piston thus ensuring the locking of all three strands.
  • Each section may have an external profile, covering a circular arc whose diameter is substantially equal to that of an external part of the projectile, and a notch intended to allow positioning of the flap in position folded around an axial support integral with the projectile.
  • the axial support can carry two plates, one plate lower and an upper plate connected by the rods, the flaps being arranged between the two plates when in the folded position.
  • At least a groove in each component may include means allowing to slow down the movement of deployment of the shutter.
  • the means to slow the movement of deployment may advantageously consist of a particular shape of the groove and / or a particular shape of the notch, the groove and / or the notch comprising at minus a ripple.
  • the shutters can generally be joined to a projectile warhead rocket.
  • an artillery projectile 1 has a belt at its rear part 2 intended to take the scratches from a weapon tube (not shown) and to ensure sealing against propellant gases during of the projectile.
  • This projectile carries on its front part a rocket 3 which is intended in a conventional and following manner the type of projectile considered (explosive projectile or cargo projectile) to ensure either the initiation of a charge explosive disposed inside the projectile, either ignition of a charge generating gas intended to eject on the trajectory a payload arranged inside the projectile (under anti-tank ammunition or grenades).
  • the rocket includes an electronic device command 4 which causes the initiation of a charge pyrotechnic 5 (which is depending on the case a relay of detonation or a gas generator).
  • this rocket 3 incorporates also a translational braking device 6 allowing the radial deployment on trajectory of flaps of braking 7.
  • the deployment of the 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 pre-firing programming, or further modified in the first moments after firing to take into account the actual initial speed of the projectile.
  • the trajectory programming will be ensured by via receiver 8 which may be of technology radar.
  • 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 attachment to the projectile.
  • the pyrotechnic charge 5 is placed in a bucket secured to the body and it communicates through a priming channel 10 with a initiation component 11 (primer or igniter) to electrical trip, 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 charge pyrotechnic 5 and an upper portion of the rocket containing 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 of flaps 15 comprising a tubular part 16 and two plates 17 and 18.
  • the tubular part 16 is mounted coaxially to the cylinder 14 and therefore has an internal diameter which is equal to that of cylinder 14.
  • the upper plates 17 and lower 18 are planar and perpendicular to the axis 20 of the rocket and projectile.
  • the two plates 17 and 18 delimit an annular volume inside which are arranged the flaps 7.
  • the support 15 is made integral in translation and rotation of the rocket body, for example by a locking nut mounted on the cylinder 14 and not represented.
  • three flaps 7a, 7b and 7c are integral with the support 15.
  • Each component is likely to translate into a plane perpendicular to the axis 20 of the projectile. He is guided in its translation by two cylindrical rods 21 (here alone a rod 21b is visible) which are fixed, arranged between the two plates 17 and 18 and parallel to the axis 20 of the projectile.
  • Figure 3 shows the distribution of rods 21.
  • Three rods 21a, 21b and 21c are provided and distributed angularly in a regular manner around the axis 20 of the rocket (at equal distance from axis 20 and with an angle of 120 ° between each position).
  • Each rod 21 is cylindrical and cooperates with two holes coaxial, one on the upper plate 17 and the other on the lower plate 18.
  • the rod has a collar allowing its centering on a counterbore of the plate higher and it has a slightly larger diameter to that of the plate holes to ensure its blocking.
  • Each flap 7a, 7b and 7c has two closed grooves 22, 23 parallel to a direction 24 perpendicular to the axis 20 of the projectile.
  • the upper flap 7a thus comprises two grooves 22a, 23a parallel to a direction 24a.
  • the middle flap 7b has two grooves 22b, 23b parallel to a direction 24b.
  • the lower flap 7c has two grooves 22c, 23c parallel to a direction 24c.
  • Each groove cooperates with a rod fixed relative to the projectile and more particularly each rod cooperates with two grooves of two adjacent flaps.
  • the rod 21a guides the groove 23a of the shutter 7a and the groove 22b of shutter 7b.
  • the rod 21b guides the groove 23b of the flap 7b and the groove 22c of the flap 7c.
  • the rod 21c guides the groove 23c of the shutter 7c and the groove 22a of shutter 7a.
  • the different shutters are stacked on top of each other when in their folded position visible to Figures 2 and 3.
  • the first flap 7a, or upper flap, is is in contact with the upper plate 17 and the third flap 7c (or lower flap) is in contact with the bottom plate 18.
  • the second flap 7b (or intermediate flap) is arranged between the first part 7a and the third part 7c. Such a arrangement of the flaps ensures their mechanical strength at the acceleration developed when firing the projectile.
  • a play on the order of a tenth of a millimeter is planned between the rods 21a, 21b and 21c and the grooves so authorize the movement of the flaps from their position storage shown in Figure 3 in their deployed position shown in Figure 4.
  • Each shutter is made for example of sheet steel 2 mm thick and carries the two grooves 22, 23 intended to receive the rods 21.
  • the flaps may also be made of another material for example a light alloy (aluminum based).
  • Each component has an external profile 25 covering a arc of circle whose diameter is substantially equal to outer diameter of the rocket 3.
  • Each section also has a notch 26 intended to allow the positioning of the flap around the tubular part 16 of the axial support 15.
  • the notch 26 has a semi-cylindrical portion 27 of same diameter as that of tubular part 16 and coaxial to the axis 20 thereof (i.e. also to the axis of the rocket and projectile).
  • the semi-cylindrical portion 27 of the notch is connected to two flat surfaces 28 and 29 which are parallel to the grooves 22, 23.
  • the different components also present some structural differences with each other.
  • the first flap 7a carries a hole 30 which is intended to receive the rod 31 of a pyrotechnic piston 32 (see figure 2).
  • This pyrotechnic piston is here a retractor pyrotechnic, it includes a gas generating composition which is electrically initiated by the control device 4 and which has the effect of causing the withdrawal of the rod 31 out of hole 30.
  • a pyrotechnic component is indeed known to those skilled in the art and will not be described further in details.
  • the rod 31 of the retractor locks the first flap 7a in the folded position.
  • the first flap 7a also carries a first notch 33 which is intended to cooperate with a first pin 34 carried by the second flap 7b to maintain the position folded of this one.
  • the second flap 7b carries a second notch 35 which is intended to cooperate with a second pin 36 carried by the third flap 7c to maintain the position folded of this one.
  • a single pyrotechnic piston 32 thus ensures the locks all three components and prevents deployment of these as a result of centrifugal efforts which are exerted on them during the firing of the projectile.
  • Pawns 34 and 36 are made up of small rods cylindrical mounted in holes made on the shutters (see figure 5f).
  • Figure 3 shows the three flaps in their position folded and locked.
  • the cutting of the rocket was carried out so as to remove the upper plate 17. Only the first flap 7a is completely visible. The three rods 21a, 21b and 21c are cut. The second part 7b is partially visible in the notch 26 of the first part. The third component is hidden.
  • This figure shows how the different holding means so as to ensure a locking of the three flaps.
  • the pin 36 carried by the third flap 7c is positioned in the notch 35 of the second part 7b.
  • the third component does therefore cannot open.
  • the device control electronics 4 will cause withdrawal of the rod 31 of the pyrotechnic piston out of hole 30.
  • the first flap 7a goes open by translating in direction 24a.
  • the notch 33 then releases the pin 34, which releases the second part 7b which can also open.
  • Notch 35 then releases the pawn 36, which releases the third flap 7c which in turn can open.
  • the opening of the three flaps is practically simultaneous.
  • the result is symmetry and reproducibility of the opening which avoids disturbances to the braking trajectory of the projectile.
  • Figure 4 shows the flaps in their position deployed.
  • each component is stopped by the implementation abutment of the different grooves 22 and 23 on their rods 21 respectively.
  • the rod 21a thus constitutes a stop for the grooves 23a and 22b
  • the rod 21b constitutes a stop for the grooves 23b and 22c
  • the rod 21c forms the stop of the grooves 23c and 22a.
  • Such an arrangement makes it possible to control the amplitude radial opening of the shutters.
  • each flap when the flaps are in the deployed position, the ends of each flap which are located on either side of the notch 26 are supported on a neighboring flap or on the lower plate 18 (which constitutes a surface solid support of the rocket therefore of the projectile and perpendicular to the axis of the latter).
  • the rigidity of the device is improved braking in the deployed position, therefore its mechanical resistance to bending.
  • the opening diameter D obtained is of the order of 118 mm for an initial diameter of the lower plate of approximately 61mm or an increase in diameter of around 93%.
  • the device according to the invention ensures obtaining a large and rigid braking surface for reduced dimensions and mechanical strength important.
  • Figure 6 shows an alternative embodiment of a shutter braking.
  • This component corresponds to the first component 7a, it therefore has a hole 30 for receiving the retractor rod pyrotechnic and a notch 33 to immobilize a second part.
  • each groove 22 and 23 has an undulation 37.
  • the corrugation thus divides each groove into two portions straight lines 38a and 38b separated by another straight portion 38c parallel to the previous ones.
  • the amplitude of the corrugation is about 2 mm and its length is about 4 mm.
  • a ripple 39 is produced at the flat surface 29 and a complementary hollow 40 is arranged at the level of the flat surface 28.
  • Ripples are therefore a means of slow down the deployment movement of the shutter. We reduce thus the shock of abutment of each flap against the guide rods at the end of the deployment movement, which increases the reliability of the device.
  • the invention can of course be applied to all types of large caliber (more than 50mm) or medium projectiles 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)
  • Braking Arrangements (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 Widerstand des Projektils erhöht wird, wobei die Bremsklappen in Form von Klappen ausgeführt sind, die sich in einer Ebene senkrecht zur Projektilachse verschieben, wobei die Vorrichtung dadurch gekennzeichnet ist, dass jede Klappe (7) wenigstens zwei geschlossene, zu einer Richtung (24) senkrecht zur Achse (20) des Projektils (1) nahezu parallele Rillen (22, 23) umfasst, wobei jede Rille mit einer Stange (21) zusammenwirkt, die in Bezug auf das Projektil feststehend ist.
  2. Abbremsvorrichtung nach Anspruch 1, dadurch gekennzeichnet, dass jede Stange (21) mit zwei Rillen zweier benachbarter Klappen zusammenwirkt.
  3. Abbremsvorrichtung nach Anspruch 2, dadurch gekennzeichnet, dass sie wenigstens einen pyrotechnischen Kolben (32) umfasst, der die Verriegelung von wenigstens einer der Klappen (7) in gefalteter Position gewährleistet.
  4. Abbremsvorrichtung nach Anspruch 3, dadurch gekennzeichnet, dass wenigstens zwei Klappen aufeinander geschichtet sind, wenn sie sich in ihrer gefalteten Position befinden, wobei wenigstens eine Erste der beiden Klappen Mittel umfasst, welche das Festhalten der Zweiten der beiden Klappen in gefalteter Position gewährleistet.
  5. Abbremsvorrichtung nach Anspruch 4, dadurch gekennzeichnet, dass sie wenigstens drei Klappen (7a, 7b, 7c) umfasst, wobei eine erste Klappe (7a) durch den pyrotechnischen Kolben verriegelt wird und eine erste Einkerbung trägt, die mit einem ersten Klötzchen zusammenwirkt, das von einer zweiten Klappe getragen wird, um deren Festhalten von dieser in gefalteter Position zu gewährleisten, wobei die zweite Klappe eine zweite Einkerbung trägt, die mit einem zweiten Klötzchen zusammenwirkt, das von einer dritten Klappe getragen wird, um deren Festhalten in gefalteter Position zu gewährleisten, wobei so ein einziger pyrotechnischer Kolben die Verriegelung der Baugruppe von drei Klappen gewährleistet.
  6. Abbremsvorrichtung nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass jede Klappe (7) ein äußeres Profil, das einen Kreisbogen abdeckt, dessen Durchmesser nahezu gleich dem eines äußeren Abschnittes des Projektils ist, und einen bogenförmigen Ausschnitt aufweist, der dafür vorgesehen ist, die Positionierung der Klappe (7) in gefalteter Position um eine axiale, fest mit dem Projektil verbundene Stütze zu erlauben.
  7. Abbremsvorrichtung nach Anspruch 6, dadurch gekennzeichnet, dass die axiale Stütze (15) zwei Platten (17, 18) trägt, eine untere Platte (18) und eine obere Platte (17), die durch die Stangen verbunden sind, wobei die Klappen (7) sich zwischen den beiden Platten angeordnet befinden, wenn sie in gefalteter Position sind.
  8. Abbremsvorrichtung nach einem der Ansprüche 6 oder 7, dadurch gekennzeichnet, dass wenigstens eine Rille von jeder Klappe Mittel aufweist, die die Bewegung zum Entfalten der Klappe verlangsamen.
  9. Abbremsvorrichtung nach Anspruch 8, dadurch gekennzeichnet, dass die Mittel, die es erlauben, die Bewegung zum Entfalten zu verlangsamen, durch eine besondere Form der Rille und/oder eine besondere Form des bogenförmigen Ausschnittes gebildet werden, wobei die Rille und/oder der bogenförmige Ausschnitt wenigstens eine Wellung aufweist.
  10. Abbremsvorrichtung nach einem der Ansprüche 1 bis 9, dadurch gekennzeichnet, dass die Klappen (7) mit einem Geschosszünder (3) des Projektils fest verbunden sind.
EP00106787A 1999-04-16 2000-03-30 Bremsvorrichtung für die Flugbahngeschwindigkeit eines Geschosses Expired - Lifetime EP1045221B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9904861A FR2792400B1 (fr) 1999-04-16 1999-04-16 Dispositif de freinage en translation d'un projectile sur trajectoire
FR9904861 1999-04-16

Publications (2)

Publication Number Publication Date
EP1045221A1 EP1045221A1 (de) 2000-10-18
EP1045221B1 true EP1045221B1 (de) 2003-09-17

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EP00106787A Expired - Lifetime EP1045221B1 (de) 1999-04-16 2000-03-30 Bremsvorrichtung für die Flugbahngeschwindigkeit eines Geschosses

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US (1) US6325325B1 (de)
EP (1) EP1045221B1 (de)
DE (1) DE60005239T2 (de)
FR (1) FR2792400B1 (de)

Families Citing this family (17)

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Publication number Priority date Publication date Assignee Title
AU2002245348A1 (en) 2001-02-01 2002-08-12 United Defense Lp 2-d projectile trajectory corrector
FR2820495A1 (fr) 2001-02-02 2002-08-09 Anthena Soc Projectile pour munitions a portee reduite
US20040041059A1 (en) * 2002-09-03 2004-03-04 Kennedy Kevin D. Device for projectile control
US7163176B1 (en) 2004-01-15 2007-01-16 Raytheon Company 2-D projectile trajectory correction system and method
FR2891618B1 (fr) * 2005-10-05 2010-06-11 Giat Ind Sa Dispositif d'entrainement de gouvernes de projectile.
US7963442B2 (en) * 2006-12-14 2011-06-21 Simmonds Precision Products, Inc. Spin stabilized projectile trajectory control
US8049149B2 (en) * 2008-05-16 2011-11-01 Raytheon Company Methods and apparatus for air brake retention and deployment
US8193476B2 (en) * 2008-06-13 2012-06-05 Raytheon Company Solid-fuel pellet thrust and control actuation system to maneuver a flight vehicle
WO2010023636A1 (en) * 2008-08-28 2010-03-04 Denel (Pty) Ltd Projectile drag augmentation device
US8294072B2 (en) * 2010-05-27 2012-10-23 Raytheon Company Projectile that includes as needed pressure-relieving wrap-around tail fins
SE536255C2 (sv) * 2012-02-06 2013-07-23 Bae Systems Bofors Ab Bromspanel för ett tändrör eller en projektil
JP5510979B1 (ja) * 2013-02-15 2014-06-04 防衛省技術研究本部長 抵抗翼構造体
FR3017943B1 (fr) * 2014-02-27 2016-02-12 Nexter Munitions Fusee d'ogive de projectile d'artillerie comportant un dispositif de freinage en translation
SE1800208A1 (sv) * 2018-10-30 2020-05-01 Bae Systems Bofors Ab Bromsanordning, tändrör samt projektil
SE547810C2 (sv) * 2021-05-19 2025-12-02 Bae Systems Bofors Ab Projektil och tändrör för anordning på projektilen
CN113670139B (zh) * 2021-08-02 2022-08-16 南京理工大学 制导炮弹用减旋装置及制导炮弹船尾
CN113720213B (zh) * 2021-08-02 2022-10-14 北京理工大学 制导炮弹用船尾及制导炮弹

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US2840326A (en) * 1949-12-24 1958-06-24 Martin Co Aerodynamic brake for aircraft
US3188958A (en) * 1963-03-11 1965-06-15 James D Burke Range control for a ballistic missile
FR2071271A5 (en) * 1969-12-23 1971-09-17 Serat Parachute anti-tank mine - with braking surfaces
DE2104914A1 (de) * 1971-02-03 1972-08-17 Rheinmetall GmbH, 4000 Düsseldorf Trägergeschoß mit absprengbarem Geschoßboden
SE445952B (sv) 1983-03-25 1986-07-28 Bofors Ab Anordning for att minska projektilspridning
GB9614133D0 (en) 1996-07-05 1997-03-12 Secr Defence Means for increasing the drag on a munition
US5762291A (en) * 1996-10-28 1998-06-09 The United States Of America As Represented By The Secretary Of The Army Drag control module for stabilized projectiles
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

Also Published As

Publication number Publication date
FR2792400B1 (fr) 2002-05-03
DE60005239T2 (de) 2004-07-15
DE60005239D1 (de) 2003-10-23
US6325325B1 (en) 2001-12-04
FR2792400A1 (fr) 2000-10-20
EP1045221A1 (de) 2000-10-18

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