EP1045221B1 - Dispositif de freinage en translation d'un projectile sur trajectoire - Google Patents
Dispositif de freinage en translation d'un projectile sur trajectoire Download PDFInfo
- 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
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Images
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).
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Vibration Dampers (AREA)
- Braking Arrangements (AREA)
Description
- la figure 1 montre schématiquement un projectile équipé d'un dispositif de freinage selon l'invention,
- la figure 2 représente en coupe longitudinale partielle une fusée de projectile équipée d'un dispositif de freinage selon un premier mode de réalisation de l'invention,
- la figure 3 montre ce même dispositif en position repliée et en coupe suivant le plan repéré AA sur la figure 2,
- la figure 4 est analogue à la figure 3 mais montre le dispositif en position déployée,
- les figures 5a à 5f représentent les volets de freinage seuls, les figures 5a, 5c et 5e étant des vues frontales desdits volets et les figures 5b, 5d et 5f étant des vues latérales des différents volets, chacune des vues frontales étant associée à sa vue latérale pour un volet déterminé (5a/5b, 5c/5d et 5e/5f), la figure 5b est une coupe de la figure 5a suivant le plan repéré BB sur la figure 5a,
- la figure 6 représente une variante de réalisation des rainures d'un volet de freinage.
Claims (10)
- Dispositif (6) de freinage en translation d'un projectile (1) sur sa trajectoire et comprenant au moins deux aérofreins déployables radialement de façon à accroítre la traínée aérodynamique du projectile, aérofreins réalisés sous la forme de volets se translatant dans un plan perpendiculaire à l'axe du projectile dispositif caractérisé en ce que chaque volet (7) comporte au moins deux rainures (22, 23) fermées sensiblement parallèles à une direction (24) perpendiculaire à l'axe (20) du projectile (1), chaque rainure coopérant avec une tige (21) qui est fixe par rapport au projectile.
- Dispositif de freinage selon la revendication 1, caractérisé en ce que chaque tige (21) copère avec deux rainures de deux volets adjacents.
- Dispositif de freinage selon la revendication 2, caractérisé en ce qu'il comporte au moins un piston pyrotechnique (32) assurant le verrouillage d'au moins un des volets (7) en position repliée.
- Dispositif de freinage selon la revendication 3, caractérisé en ce qu'au moins deux volets se trouvent empilés les uns sur les autres lorsqu'ils se trouvent dans leur position repliée, au moins un premier des deux volets comportant des moyens assurant le maintien du deuxième des deux volets en position repliée.
- Dispositif de freinage selon la revendication 4, caractérisé en ce qu'il comporte au moins trois volets (7a,7b,7c), un premier volet (7a) étant verrouillé par le piston pyrotechnique et portant une première encoche coopérant avec un premier pion porté par un deuxième volet pour assurer le maintien en position repliée de celui ci, le deuxième volet portant une deuxième encoche coopérant avec un deuxième pion porté par un troisième volet pour assurer le maintien en position repliée de celui ci, un seul piston pyrotechnique assurant ainsi le verrouillage de l'ensemble des trois volets.
- Dispositif de freinage selon une des revendications 1 à 5, caractérisé en ce que chaque volet (7) présente un profil externe, couvrant un arc de cercle dont le diamètre est sensiblement égal à celui d'une partie externe du projectile, et une échancrure destinée à permettre le positionnement du volet (7) en position repliée autour d'un support axial solidaire du projectile.
- Dispositif de freinage selon la revendication 6, caractérisé en ce que le support axial (15) porte deux platines (17,18), une platine inférieure (18) et une platine supérieure (17) reliées par les tiges, les volets (7) se trouvant disposés entre les deux platines lorsqu'ils sont en position repliée.
- Dispositif de freinage selon une des revendications 6 ou 7, caractérisé en ce que au moins une rainure de chaque volet comporte des moyens permettant de ralentir le mouvement de déploiement du volet.
- Dispositif de freinage selon la revendication 8, caractérisé en ce que les moyens permettant de ralentir le mouvement de déploiement sont constitués par une forme particulière de la rainure et/ou une forme particulière de l'échancrure, la rainure et/ou l'échancrure comportant au moins une ondulation.
- Dispositif selon une des revendications 1 à 9, caractérisé en ce que les volets (7) sont solidaires d'une fusée (3) d'ogive du projectile.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9904861 | 1999-04-16 | ||
FR9904861A FR2792400B1 (fr) | 1999-04-16 | 1999-04-16 | Dispositif de freinage en translation d'un projectile sur trajectoire |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1045221A1 EP1045221A1 (fr) | 2000-10-18 |
EP1045221B1 true EP1045221B1 (fr) | 2003-09-17 |
Family
ID=9544550
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00106787A Expired - Lifetime EP1045221B1 (fr) | 1999-04-16 | 2000-03-30 | Dispositif de freinage en translation d'un projectile sur trajectoire |
Country Status (4)
Country | Link |
---|---|
US (1) | US6325325B1 (fr) |
EP (1) | EP1045221B1 (fr) |
DE (1) | DE60005239T2 (fr) |
FR (1) | FR2792400B1 (fr) |
Families Citing this family (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE60233113D1 (de) | 2001-02-01 | 2009-09-10 | Bae Systems Land & Armaments | Zweidimensionale geschossflugbahnkorrekturvorrichtung |
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 (fr) * | 2008-08-28 | 2010-03-04 | Denel (Pty) Ltd | Dispositif d'augmentation de traînée d'un projectile |
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 |
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 |
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 |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
-
1999
- 1999-04-16 FR FR9904861A patent/FR2792400B1/fr not_active Expired - Lifetime
-
2000
- 2000-03-30 EP EP00106787A patent/EP1045221B1/fr not_active Expired - Lifetime
- 2000-03-30 DE DE60005239T patent/DE60005239T2/de not_active Expired - Lifetime
- 2000-04-12 US US09/548,343 patent/US6325325B1/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
DE60005239T2 (de) | 2004-07-15 |
US6325325B1 (en) | 2001-12-04 |
EP1045221A1 (fr) | 2000-10-18 |
DE60005239D1 (de) | 2003-10-23 |
FR2792400B1 (fr) | 2002-05-03 |
FR2792400A1 (fr) | 2000-10-20 |
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Legal Events
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PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
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