EP1045221B1 - Aerodynamic brake for reducing the velocity of a projectile on its trajectory - Google Patents
Aerodynamic brake for reducing the velocity of a projectile on its trajectory 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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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)
Description
Le domaine technique de l'invention est celui des dispositifs de freinage en translation d'un projectile sur trajectoire.The technical field of the invention is that of braking devices in translation of a projectile on path.
De tels dispositifs sont notamment connus dans le domaine de l'artillerie.Such devices are notably known in the field artillery.
Le brevet EP138942 décrit ainsi un projectile d'artillerie qui comporte un dispositif de freinage d'ogive dont le déploiement est commandé sur trajectoire.Patent EP138942 thus describes a projectile artillery which includes a warhead braking device whose deployment is controlled on a trajectory.
Une telle disposition permet d'accroítre la précision des tirs d'artillerie en tenant compte des dispersions dues aux variations de la vitesse initiale du projectile. En effet, il est possible alors de pointer l'arme de façon à tirer plus loin que la cible visée, une conduite de tir mesure la vitesse réelle du projectile à la sortie du tube de l'arme et un ordre de freinage est ensuite transmis au projectile de façon à réduire sa portée et à l'amener ainsi au point d'impact souhaité.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.
Le dispositif de freinage décrit par ce brevet comprend, soit des doigts mobiles radialement, soit une surface frontale plane. La surface de ces moyens de freinage par rapport à la section du projectile est trop faible pour que leur capacité de freinage soit suffisante.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.
Le brevet WO98/01719 décrit un autre dispositif de freinage pour projectile. Ce dispositif comprend quatre plaques aérofreins empilées les unes sur les autres et mobiles radialement par rapport au projectile.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.
La surface de freinage se trouve ainsi fortement accrue (elle constitue environ le double de la section du projectile) avec un encombrement réduit à l'intérieur du corps du 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.
Cependant ce dispositif présente des inconvénients.However, this device has drawbacks.
Les formes de plaques sont complexes à usiner, elles comportent également de nombreuses échancrures qui réduisent leur résistance mécanique, notamment dans leur position totalement déployée qui est celle où les contraintes sont maximales. 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.
De plus le guidage de chaque plaque est assuré par la coopération de pions solidaires des extrémités de bras portés par la plaque et qui coopèrent dans des échancrures d'une plaque voisine ainsi que d'une plaque de fond. Les bras présentent une certaine flexibilité qui nuit à la fiabilité du guidage. Il en résulte des risques de coincement qui sont accrus par le fait que le guidage est double (sur une plaque voisine et une plaque de fond).In addition, 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).
Enfin, le déverrouillage des plaques est obtenu par l'intermédiaire de deux générateurs de gaz qui déplacent deux goupilles de maintien, chaque goupille immobilisant deux plaques. Une telle structure est susceptible de provoquer des dissymétries ou des coincements au moment du déploiement des plaques, ce qui risque de modifier la trajectoire du projectile d'une façon non reproductible.Finally, the unlocking of the plates is obtained by through two gas generators that move two holding pins, each pin securing two plates. Such a structure is likely to cause asymmetries or jamming when deploying plates, which could change the trajectory of the non-reproducible projectile.
Le brevet US5826821 décrit un dispositif de freinage dans lequel les volets se déploient par pivotement autour d'axes parallèles à l'axe du projectile. Le brevet US5816531 décrit un dispositif de freinage comprennant quatre volets qui se translatent radialement par rapport au projectile. Chaque volet porte une nervure coulissant dans une rainure d'une plaque de base et un doigt qui s'engage dans une came assurant le synchronisme de l'ouverture des volets. Les dispositifs décrits par ces deux brevets sont susceptibles de coincements et dissymétries.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.
C'est le but de l'invention que de proposer un dispositif de freinage en translation d'un projectile qui ne présente pas de tels inconvénients.It is the object of the invention to propose a device braking in translation of a projectile which does not have no such disadvantages.
Ainsi le dispositif de freinage selon l'invention est de conception simple et peu coûteuse et il présente une résistance mécanique améliorée par rapport au dispositif décrit précédemment.Thus 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.
Il est peu susceptible de coincements et il en résulte une symétrie d'ouverture des aérofreins qui est parfaite.It is unlikely to get caught and this results a symmetry of opening of the airbrakes which is perfect.
Ainsi l'invention a pour objet un dispositif de freinage en translation d'un projectile 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 comporte au moins deux rainures fermées sensiblement parallèles à une direction perpendiculaire à l'axe du projectile, chaque rainure coopérant avec une tige qui est fixe par rapport au projectile.Thus, 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.
Avantageusement, chaque tige pourra coopérer avec deux rainures de deux volets adjacents.Advantageously, each rod can cooperate with two grooves of two adjacent flaps.
Le dispositif pourra comporter au moins un piston pyrotechnique assurant le verrouillage d'au moins un des volets en position repliée.The device may include at least one piston pyrotechnic ensuring the locking of at least one of the flaps in the folded position.
Selon un mode particulier de réalisation, 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.According to a particular embodiment, 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.
Selon un mode de réalisation le dispositif de freinage comporte au moins trois volets, un premier volet 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.According to one embodiment 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.
Chaque volet pourra présenter 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 en position repliée autour d'un support axial solidaire du projectile.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.
Le support axial pourra porter deux platines, une platine inférieure et une platine supérieure reliées par les tiges, les volets se trouvant disposés entre les deux platines lorsqu'ils sont en position repliée.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.
Selon un autre mode particulier de réalisation, au moins une rainure de chaque volet pourra comporter des moyens permettant de ralentir le mouvement de déploiement du volet.According to another particular embodiment, at least a groove in each component may include means allowing to slow down the movement of deployment of the shutter.
Les moyens permettant de ralentir le mouvement de déploiement pourront avantageusement être 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.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.
Les volets pourront généralement être solidaires d'une fusée d'ogive du projectile.The shutters can generally be joined to a projectile warhead rocket.
D'autres avantages de l'invention apparaítront à la lecture de la description qui va suivre de différents modes de réalisation, description faite en référence aux dessins annexés et dans lesquels.
- 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.
- FIG. 1 schematically shows a projectile equipped with a braking device according to the invention,
- FIG. 2 shows a partial longitudinal section of a projectile rocket equipped with a braking device according to a first embodiment of the invention,
- FIG. 3 shows this same device in the folded position and in section along the plane marked AA in FIG. 2,
- FIG. 4 is similar to FIG. 3 but shows the device in the deployed position,
- FIGS. 5a to 5f represent the braking flaps alone, FIGS. 5a, 5c and 5e being front views of said flaps and FIGS. 5b, 5d and 5f being side views of the different flaps, each of the front views being associated with its view lateral for a specific component (5a / 5b, 5c / 5d and 5e / 5f), FIG. 5b is a section of FIG. 5a along the plane marked BB in FIG. 5a,
- Figure 6 shows an alternative embodiment of the grooves of a brake flap.
En se reportant à la figure 1, un projectile d'artillerie
1 est doté au niveau de sa partie arrière d'une ceinture 2
destinée à prendre les rayures d'un tube d'arme (non
représenté) et à assurer l'étanchéité aux gaz propulsifs lors
du tir du projectile. Ce projectile porte à sa partie avant
une fusée 3 qui est destinée d'une façon classique et suivant
le type de projectile considéré (projectile explosif ou
projectile cargo) à assurer soit l'initiation d'une charge
explosive disposée à l'intérieur du projectile, soit
l'allumage d'une charge génératrice de gaz destinée à éjecter
sur trajectoire une charge utile disposée à l'intérieur du
projectile (sous munitions antichar ou grenades).Referring to Figure 1, an
A cet effet la fusée comporte un dispositif électronique
de commande 4 qui provoque l'initiation d'une charge
pyrotechnique 5 (qui est suivant le cas un relais de
détonation ou un générateur de gaz).For this purpose the rocket includes an
Conformément à l'invention, cette fusée 3 incorpore
également un dispositif de freinage en translation 6
permettant le déploiement radial sur trajectoire de volets de
freinage 7. Le déploiement des volets 7 est commandé par le
dispositif électronique de commande 4 en réponse à un ordre
reçu sur trajectoire par l'intermédiaire d'un récepteur 8 ou
bien élaboré par le dispositif électronique de commande 4
comme suite à une programmation préalable au tir, ou bien
encore modifiée dans les premiers instants suivant le tir
pour tenir compte de la vitesse initiale réelle du
projectile.According to the invention, this
La programmation sur trajectoire sera assurée par
l'intermédiaire du récepteur 8 qui pourra être de technologie
radar.The trajectory programming will be ensured by
via
La figure 2 montre cette fusée de façon plus détaillée.
Elle a une forme générale et un encombrement analogue à celui
des fusées d'artillerie classiques. Elle comporte un corps 13
sur lequel est réalisé un filetage 9 destiné à permettre sa
solidarisation avec le projectile. La charge pyrotechnique 5
est disposée dans un godet solidaire du corps et elle
communique au travers d'un canal d'amorçage 10 avec un
composant d'initiation 11 (amorce ou inflammateur) à
déclenchement électrique, qui est lui même relié au
dispositif électronique de commande 4.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
D'une façon classique et qui n'est pas décrite ni
représentée en détails, le composant d'initiation 11 est
porté par un volet mobile 12 d'un dispositif de sécurité et
d'armement. In a conventional manner and which is neither described nor
shown in detail, the
Le corps 13 de la fusée comporte un cylindre axial 14 qui
relie une portion inférieure de la fusée comportant la charge
pyrotechnique 5 et une portion supérieure de la fusée
renfermant le dispositif électronique 4. Ce cylindre est
traversé par le canal d'amorçage 10. Le cylindre 14 reçoit le
dispositif de freinage 6 qui comprend un support axial de
volets 15 comportant une partie tubulaire 16 et deux platines
17 et 18. La partie tubulaire 16 est montée coaxialement au
cylindre 14 et présente donc un diamètre interne qui est égal
à celui du cylindre 14. Les platines supérieure 17 et
inférieure 18 sont planes et perpendiculaires à l'axe 20 de
la fusée et du projectile. Les deux platines 17 et 18
délimitent un volume annulaire à l'intérieur duquel sont
disposés les volets 7. Le support 15 est rendu solidaire en
translation et en rotation du corps de fusée, par exemple par
un écrou de blocage monté sur le cylindre 14 et non
représenté.The
Conformément à ce premier mode de réalisation de
l'invention, qui est également le mode de réalisation
préféré, trois volets 7a, 7b et 7c sont solidaires du support
15.In accordance with this first embodiment of
the invention, which is also the embodiment
preferred, three
Chaque volet est susceptible de se translater dans un
plan perpendiculaire à l'axe 20 du projectile. Il est guidé
dans sa translation par deux tiges cylindriques 21 (ici seule
une tige 21b est visible) qui sont fixes, disposées entre les
deux platines 17 et 18 et parallèles à l'axe 20 du
projectile.Each component is likely to translate into a
plane perpendicular to the
La figure 3 montre la répartition des tiges 21. Trois
tiges 21a, 21b et 21c sont prévues et réparties angulairement
d'une façon régulière autour de l'axe 20 de la fusée (à égale
distance de l'axe 20 et avec un angle de 120° entre chaque
position).Figure 3 shows the distribution of rods 21. Three
Chaque tige 21 est cylindrique et coopère avec deux trous
coaxiaux, l'un sur la platine supérieure 17 et l'autre sur la
platine inférieure 18. La tige comporte une collerette
permettant son centrage sur un lamage de la platine
supérieure et elle présente un diamètre légèrement supérieur
à celui des trous des platines afin d'assurer son blocage.Each rod 21 is cylindrical and cooperates with two holes
coaxial, one on the
Chaque volet 7a, 7b et 7c comporte deux rainures fermées
22, 23 parallèles à une direction 24 perpendiculaire à l'axe
20 du projectile.Each
Le volet supérieur 7a comporte ainsi deux rainures
22a,23a parallèles à une direction 24a.The
Le volet médian 7b comporte deux rainures 22b,23b
parallèles à une direction 24b.The
Le volet inférieur 7c comporte deux rainures 22c,23c
parallèles à une direction 24c.The
Les trois directions 24a, 24b et 24c, coupent l'axe 20 de
la fusée, elles sont perpendiculaires à cet axe et forment
entre elles des angles de 120°.The three
Chaque rainure coopère avec une tige fixe par rapport au projectile et plus particulièrement chaque tige coopère avec deux rainures de deux volets adjacents.Each groove cooperates with a rod fixed relative to the projectile and more particularly each rod cooperates with two grooves of two adjacent flaps.
Ainsi la tige 21a assure le guidage de la rainure 23a du
volet 7a et de la rainure 22b du volet 7b.Thus the
La tige 21b assure le guidage de la rainure 23b du volet
7b et de la rainure 22c du volet 7c.The
Enfin, la tige 21c assure le guidage de la rainure 23c du
volet 7c et de la rainure 22a du volet 7a.Finally, the
Les différents volets sont empilés les uns sur les autres
lorsqu'ils se trouvent dans leur position repliée visible aux
figures 2 et 3. Le premier volet 7a, ou volet supérieur, se
trouve en contact avec la platine supérieure 17 et le
troisième volet 7c (ou volet inférieur) se trouve en contact
avec la platine inférieure 18.The different shutters are stacked on top of each other
when in their folded position visible to
Figures 2 and 3. The
Le deuxième volet 7b (ou volet intermédiaire) est disposé
entre le premier volet 7a et le troisième volet 7c. Une telle
disposition des volets assure leur tenue mécanique à
l'accélération développée lors du tir du projectile.The
Un jeu de l'ordre du dixième de millimètre est prévu
entre les tiges 21a, 21b et 21c et les rainures afin
d'autoriser le déplacement des volets de leur position de
stockage représentée à la figure 3 à leur position déployée
représentée à la figure 4.A play on the order of a tenth of a millimeter is planned
between the
Les volets sont visibles plus en détails sur les figures
5a à 5f. Chaque volet est réalisé par exemple en tôle d'acier
de 2 mm d'épaisseur et porte les deux rainures 22, 23
destinées à recevoir les tiges 21. Les volets pourront
également être réalisés en un autre matériau par exemple un
alliage léger (à base d'aluminium).The flaps are visible in more detail in the figures
5a to 5f. Each shutter is made for example of
Chaque volet présente un profil externe 25 couvrant un
arc de cercle dont le diamètre est sensiblement égal au
diamètre externe de la fusée 3.Each component has an
Chaque volet présente également une échancrure 26
destinée à permettre le positionnement du volet autour de la
partie tubulaire 16 du support axial 15. A cet effet
l'échancrure 26 comporte une portion hémicylindrique 27 de
même diamètre que celui de la partie tubulaire 16 et coaxiale
à l'axe 20 de celle-ci (c'est à dire aussi à l'axe de la
fusée et du projectile). La portion hémicylindrique 27 de
l'échancrure se raccorde à deux surfaces plane 28 et 29 qui
sont parallèles aux rainures 22, 23.Each section also has a
Une telle forme des volets permet d'obtenir une surface de volet maximale pour un encombrement minimal en position repliée.Such a shape of the flaps makes it possible to obtain a surface maximum flap for minimum space requirement folded.
Les différents volets présentent en outre quelques différences structurelles les uns avec les autres.The different components also present some structural differences with each other.
Ainsi le premier volet 7a porte un trou 30 qui est
destiné à recevoir la tige 31 d'un piston pyrotechnique 32
(voir figure 2).Thus the
Ce piston pyrotechnique est ici un rétracteur
pyrotechnique, il comprend une composition génératrice de gaz
qui est initiée électriquement par le dispositif de commande
4 et qui a pour effet de provoquer le retrait de la tige 31
hors du trou 30. Un tel composant pyrotechnique est bien
connu de l'Homme du Métier et il ne sera pas décrit plus en
détails. This pyrotechnic piston is here a retractor
pyrotechnic, it includes a gas generating composition
which is electrically initiated by the
La tige 31 du rétracteur assure le verrouillage du
premier volet 7a en position repliée.The
Le premier volet 7a porte également une première encoche
33 qui est destinée à coopérer avec un premier pion 34 porté
par le deuxième volet 7b pour assurer le maintien en position
repliée de celui ci.The
Le deuxième volet 7b porte une deuxième encoche 35 qui
est destinée à coopérer avec un deuxième pion 36 porté par le
troisième volet 7c pour assurer le maintien en position
repliée de celui ci.The
Un seul piston pyrotechnique 32 assure ainsi le
verrouillage de l'ensemble des trois volets et empêche le
déploiement de ceux ci comme suite aux efforts centrifuges
qui s'exercent sur eux lors du tir du projectile.A single
Les pions 34 et 36 sont constitués par des petites tiges
cylindriques montées dans des trous réalisés sur les volets
(voir figure 5f).
La figure 3 montre les trois volets dans leur position repliée et verrouillée.Figure 3 shows the three flaps in their position folded and locked.
La coupe de la fusée a été réalisée de façon à retirer la
platine supérieure 17. Seul le premier volet 7a est
complètement visible. Les trois tiges 21a,21b et 21c sont
coupées. Le deuxième volet 7b est partiellement visible dans
l'échancrure 26 du premier volet. Le troisième volet est
caché.The cutting of the rocket was carried out so as to remove the
Cette figure montre comment coopèrent entre eux les différents moyens de maintien de façon à assurer un verrouillage des trois volets.This figure shows how the different holding means so as to ensure a locking of the three flaps.
On voit ainsi que, lorsque le premier volet 7a se trouve
immobilisé par la tige 31 du piston pyrotechnique introduite
dans le trou 30, le pion 34 du deuxième volet est positionné
dans l'encoche 33 du premier volet 7a. Le deuxième volet ne
peut donc pas se déployer.It can thus be seen that, when the
Le pion 36 porté par le troisième volet 7c est positionné
dans l'encoche 35 du deuxième volet 7b. Le troisième volet ne
peut donc pas s'ouvrir. The
A un instant donné sur trajectoire, le dispositif
électronique de commande 4, va provoquer le retrait de la
tige 31 du piston pyrotechnique hors du trou 30. Sous
l'action de la force centrifuge le premier volet 7a va
s'ouvrir en se translatant suivant la direction 24a.
L'encoche 33 libère alors le pion 34, ce qui libère le
deuxième volet 7b qui peut lui aussi s'ouvrir. L'encoche 35
libère alors le pion 36, ce qui libère le troisième volet 7c
qui peut a son tour s'ouvrir.At a given moment on the trajectory, the
Du fait de l'emploi d'un seul dispositif de verrouillage (le piston pyrotechnique), l'ouverture des trois volets est pratiquement simultanée. Il en résulte une symétrie et une reproductibilité de l'ouverture qui évite les perturbations à la trajectoire de freinage du projectile.Due to the use of a single locking device (the pyrotechnic piston), 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.
Le guidage du mouvement d'ouverture est assuré à la fois
par les rainures 22 et 23 et par le contact des surfaces
planes 28 et 29 de chaque volet avec la partie tubulaire 16
du support axial 15. On évite ainsi tout basculement ou
coincement qui serait provoqué par une mise en rotation
partielle de chaque volet autour des tiges 21 par l'action de
la force centrifuge.The guiding of the opening movement is ensured at the same time
by
La figure 4 montre les volets dans leur position déployée.Figure 4 shows the flaps in their position deployed.
Le déploiement de chaque volet est arrêté par la mise en
butée des différentes rainures 22 et 23 sur leurs tiges 21
respectives. La tige 21a constitue ainsi une butée pour les
rainures 23a et 22b, la tige 21b constitue une butée pour les
rainures 23b et 22c et la tige 21c forme la butée des
rainures 23c et 22a.The deployment of each component is stopped by the implementation
abutment of the
Une telle disposition permet de maítriser l'amplitude d'ouverture radiale des volets.Such an arrangement makes it possible to control the amplitude radial opening of the shutters.
Avec la configuration selon l'invention, lorsque les
volets se trouvent en position déployée, les extrémités de
chaque volet qui sont situées de part et d'autre de
l'échancrure 26 se trouvent en appui sur un volet voisin ou
sur la platine inférieure 18 (qui constitue une surface
d'appui solidaire de la fusée donc du projectile et
perpendiculaire à l'axe de ce dernier).With the configuration according to the invention, when the
flaps are in the deployed position, the ends of
each flap which are located on either side of
the
On accroít ainsi la rigidité de l'appui. De plus, en
position déployée, les surfaces planes 28 et 29 de chaque
volet sont encore en contact avec la partie tubulaire 16 du
support axial 15.This increases the rigidity of the support. In addition, in
deployed position, the
En réduisant ainsi l'amplitude de l'ouverture des volets
tout en assurant un maintien de ces derniers à la fois
axialement par la platine inférieure et radialement par la
partie tubulaire 16, on améliore la rigidité du dispositif de
freinage en position déployée, donc sa résistance mécanique à
la flexion.By thus reducing the amplitude of the opening of the flaps
while ensuring that these are maintained at the same time
axially by the bottom plate and radially by the
Le diamètre d'ouverture D obtenu est de l'ordre de 118 mm pour un diamètre initial de la platine inférieure d'environ 61mm soit un accroissement du diamètre de l'ordre de 93%.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%.
On voit donc que le dispositif selon l'invention assure l'obtention d'une surface de freinage importante et rigide pour un encombrement réduit et une tenue mécanique importante.It can therefore be seen that the device according to the invention ensures obtaining a large and rigid braking surface for reduced dimensions and mechanical strength important.
Diverses variantes sont possibles sans sortir du cadre de l'invention.Various variants are possible without departing from the scope of the invention.
Ainsi il est possible de faire varier le nombre de volets.So it is possible to vary the number of shutters.
La figure 6 montre une variante de réalisation d'un volet de freinage.Figure 6 shows an alternative embodiment of a shutter braking.
Ce volet correspond au premier volet 7a, il est donc doté
d'un trou 30 pour recevoir la tige du rétracteur
pyrotechnique et d'une encoche 33 pour immobiliser un
deuxième volet.This component corresponds to the
Il diffère des volets précédemment décrits en ce que
chaque rainure 22 et 23 comporte une ondulation 37.
L'ondulation partage ainsi chaque rainure en deux portions
rectilignes alignées 38a et 38b séparées par une autre
portion rectiligne 38c parallèle aux précédentes. L'amplitude
de l'ondulation est d'environ 2 mm et sa longueur est
d'environ 4 mm. It differs from the previously described components in that
each
Par ailleurs une ondulation 39 est réalisée au niveau de
la surface plane 29 et un creux complémentaire 40 est aménagé
au niveau de la surface plane 28. Ces dispositions autorisent
la translation latérale du volet 7 par rapport au support
cylindrique 15 lors du passage des ondulations 37 par les
tiges 21.Furthermore, a
Une telle structure permet d'assurer un freinage du
mouvement d'ouverture du volet 7. En effet, lorsque la tige
21 arrive au niveau de l'ondulation 37, le jeu entre rainure
et tige se répartit différemment, le volet se translate
latéralement par rapport au support 15, la rainure frotte
contre la tige consommant ainsi de l'énergie et réduisant la
vitesse de déplacement du volet.Such a structure ensures braking of the
Les ondulations constituent donc un moyen permettant de ralentir le mouvement de déploiement du volet. On réduit ainsi le choc de mise en butée de chaque volet contre les tiges de guidage à la fin du mouvement de déploiement, ce qui accroít la fiabilité du dispositif.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.
Il est possible de donner des formes différentes aux différentes ondulations: des formes sinusoïdales, des moletages, des traitements de surface particuliers, une variation de la largeur des rainures....It is possible to give different forms to different undulations: sinusoidal shapes, knurling, special surface treatments, variation of the width of the grooves ....
L'invention peut bien entendu s'appliquer à tous types de projectiles de gros calibre (supérieur à 50mm)ou de moyen calibre (inférieur ou égal à 50mm).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).
Claims (10)
- A device (6) for the translational braking of a projectile (1) on its trajectory and comprising at least two radially deployable air brakes so as to increase the aerodynamic drag of the projectile, said air brakes being made in the shape of flaps translating in a plane perpendicular to the axis of the projectile, device characterized in that each flap (7) comprises at least two closed grooves (22, 23) essentially parallel to a direction (24) perpendicular to the axis (20) of the projectile (1), each groove cooperating with a rod (21) that is fixed with respect to the projectile.
- A braking device according to Claim 1, characterized in that each rod (21) cooperates with two grooves of two adjacent flaps.
- A braking device according to Claim 2, characterized in that it comprises at least one pyrotechnic piston (32) that ensures the locking of at least one of the flaps (7) in the folded position.
- A braking device according to Claim 3, characterized in that at least two flaps are stacked on top of each other when they are in their folded position, at least a first of the two flaps comprising means to ensure the keeping of the second of the two flaps in the folded position.
- A braking device according to Claim 4, characterized in that it comprises at least three flaps (7a, 7b, 7c), a first flap (7a) being locked by the pyrotechnic piston and carrying a first notch cooperating with a first pin carried by a second flap to ensure the keeping of the latter in the folded position, the second flap carrying a second notch cooperating with a second pin carried by a third flap to ensure the keeping of the latter in the folded position, a single pyrotechnic piston thus ensuring the locking of all of the three flaps.
- A braking device according to any of Claims 1 to 5, characterized in that each flap (7) presents an external profile covering an arc of a circle whose diameter is essentially equal to that of an external part of the projectile, and a notch intended to allow the positioning of the flap (7) in the folded position around an axial support integral with the projectile.
- A braking device according to Claim 6, characterized in that the axial support (15) carries two plates (17, 18), a lower plate (18) and an upper plate (17) connected by the rods, the flaps (7) being placed between the two plates when they are in the folded position.
- A braking device according to any of Claims 6 or 7, characterized in that at least one groove of each flap comprises means allowing the deployment movement of the flap to be slowed down.
- A braking device according to Claim 8, characterized in that the means allowing the deployment movement to be slowed down consist of a particular shape of the groove and/or a particular shape of the notch, the groove and/or the notch having at least one wave.
- A device according to any of Claims 1 to 9, characterized in that the flaps (7) are integral with a nose fuse (3) of the projectile.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9904861 | 1999-04-16 | ||
FR9904861A FR2792400B1 (en) | 1999-04-16 | 1999-04-16 | DEVICE FOR BRAKING IN TRANSLATION OF A PROJECTILE ON A TRAJECTORY |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1045221A1 EP1045221A1 (en) | 2000-10-18 |
EP1045221B1 true EP1045221B1 (en) | 2003-09-17 |
Family
ID=9544550
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00106787A Expired - Lifetime EP1045221B1 (en) | 1999-04-16 | 2000-03-30 | Aerodynamic brake for reducing the velocity of a projectile on its trajectory |
Country Status (4)
Country | Link |
---|---|
US (1) | US6325325B1 (en) |
EP (1) | EP1045221B1 (en) |
DE (1) | DE60005239T2 (en) |
FR (1) | FR2792400B1 (en) |
Families Citing this family (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6502786B2 (en) | 2001-02-01 | 2003-01-07 | United Defense, L.P. | 2-D projectile trajectory corrector |
FR2820495A1 (en) | 2001-02-02 | 2002-08-09 | Anthena Soc | PROJECTILE FOR AMMUNITION WITH REDUCED RANGE |
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 (en) * | 2005-10-05 | 2010-06-11 | Giat Ind Sa | DEVICE FOR DRIVING PROJECTILE GOVERNMENTS. |
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 (en) * | 2012-02-06 | 2013-07-23 | Bae Systems Bofors Ab | Brake panel for a spark plug or projectile |
JP5510979B1 (en) * | 2013-02-15 | 2014-06-04 | 防衛省技術研究本部長 | Resistance wing structure |
FR3017943B1 (en) | 2014-02-27 | 2016-02-12 | Nexter Munitions | ARTILLERY PROJECTILE OGIVE SHAFT HAVING A BRAKING DEVICE IN TRANSLATION |
SE1800208A1 (en) * | 2018-10-30 | 2020-05-01 | Bae Systems Bofors Ab | Brake device, spark plug and projectile |
CN113720213B (en) * | 2021-08-02 | 2022-10-14 | 北京理工大学 | Stern for guided projectile and guided projectile |
CN113670139B (en) * | 2021-08-02 | 2022-08-16 | 南京理工大学 | Rotation reducing device for guided projectile and tail of guided projectile |
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 (en) * | 1971-02-03 | 1972-08-17 | Rheinmetall GmbH, 4000 Düsseldorf | Carrier floor with blastable floor |
SE445952B (en) | 1983-03-25 | 1986-07-28 | Bofors Ab | DEVICE FOR REDUCING PROJECT DISTRIBUTION |
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/en not_active Expired - Lifetime
-
2000
- 2000-03-30 EP EP00106787A patent/EP1045221B1/en not_active Expired - Lifetime
- 2000-03-30 DE DE60005239T patent/DE60005239T2/en 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 |
---|---|
US6325325B1 (en) | 2001-12-04 |
DE60005239D1 (en) | 2003-10-23 |
DE60005239T2 (en) | 2004-07-15 |
EP1045221A1 (en) | 2000-10-18 |
FR2792400A1 (en) | 2000-10-20 |
FR2792400B1 (en) | 2002-05-03 |
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