EP0367815B1 - Aerodynamische bremsvorrichtung für einen körper - Google Patents

Aerodynamische bremsvorrichtung für einen körper Download PDF

Info

Publication number
EP0367815B1
EP0367815B1 EP89905121A EP89905121A EP0367815B1 EP 0367815 B1 EP0367815 B1 EP 0367815B1 EP 89905121 A EP89905121 A EP 89905121A EP 89905121 A EP89905121 A EP 89905121A EP 0367815 B1 EP0367815 B1 EP 0367815B1
Authority
EP
European Patent Office
Prior art keywords
projectile
rear portion
thin strips
strips
secured
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
EP89905121A
Other languages
English (en)
French (fr)
Other versions
EP0367815A1 (de
Inventor
Jean-Pierre Pineau
Jean-Pierre Frehaut
Philippe Kerdraon
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.)
Thomson Brandt Armements SA
Original Assignee
Thomson Brandt Armements 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 Thomson Brandt Armements SA filed Critical Thomson Brandt Armements SA
Publication of EP0367815A1 publication Critical patent/EP0367815A1/de
Application granted granted Critical
Publication of EP0367815B1 publication Critical patent/EP0367815B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B30/00—Projectiles or missiles, not otherwise provided for, characterised by the ammunition class or type, e.g. by the launching apparatus or weapon used
    • F42B30/003—Closures or baseplates therefor
    • 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 invention relates to a device for aerodynamically braking a body, this braking being applicable in particular to the separation of bodies initially linked for example the rear part and the front part of a projectile or the separation of bodies or submunitions initially contained in the projectile.
  • the main application of this device can be carried out on a projectile rotating on itself containing payloads and the release of which is effected by the separation of the front part and the rear part, kept in contact in particular by a system pin, thanks to the action of propellant gases located at the front of the projectile; the latter having taken place, the rear part of the projectile tends to remain in the vicinity of the payload and thus risks causing discomfort during subsequent sequences: possibility of percussions with the payload preceding it ... To avoid this phenomenon , it is necessary to increase the aerodynamic drag of the rear part of the projectile.
  • US Pat. No. 4,648,321 A device performing braking of a rear part initially fixed to a front part of a rocket is described in US Pat. No. 4,648,321.
  • This patent describes a device for separating the payload 16 of a rocket 10 from the engine section 12. This separation is carried out by means of a special section 14.
  • This device consists of a deployable surface 50 housed in an internal part 30 of the section. This surface 50 is capable of two positions, a first when the section 14 is one with the rest of the rocket and a second deployed radially outwards so as to form an airbrake after separation.
  • the surface 50 has a shape such that in the first position its outer surface contributes to the continuity of the outer surface of the assembled body of the rocket. To this end, this surface can be defined as a part of the surface generated by a generator parallel to the axis of the rocket. Because of its complexity, such a device is necessarily expensive, so it is only justified to use it on expensive assemblies, for example rockets. In such assemblies the operation of each part must be verified by prior tests reproducing if possible the conditions of the flight. This concern does not concern projectiles which by their nature are intended to be produced in large numbers.
  • the present invention is essentially applicable to projectiles for which a compromise must be found between reliability and price.
  • One of the aims of the invention is therefore to produce an economical device ensuring the aerodynamic braking of a first body which it is desired to separate from a second body with which the first body was initially assembled to form an assembled body.
  • Another object of the invention is to conform this device so that its size provides only a minimum reduction in the volume available in the internal part of the first and second assembled bodies so as not to reduce the volume of the payload.
  • the invention therefore relates to a device for braking an element of a projectile having a longitudinal axis 00 ′ and intended to be driven in a rotational movement, the projectile comprising a front part and a rear part each having a body, an assembly of the two bodies forming a body of the projectile, the external peripheral surface of the body of the projectile delimiting an internal part and an external part, the front and rear parts being separable from each other, the rear part comprising braking means capable of two positions, a first when the front and rear parts are assembled and a second when these parts are separated, the braking means being constituted by surfaces which in the first position are housed in the part internal to the body of the projectile and which in the second position are at least partially deployed outside the body of the rear part, characterized in that the surfaces consist of strips of a material capable of plastic deformation fixed by one of their ends to the periphery of the body of the rear part, the transition from the first to the second position being obtained after separation of the front part and the rear part under the
  • FIG. 1 shows a cross section of the rear part of a projectile before the separation phase.
  • This projectile is provided with a braking device according to the invention.
  • the projectile has a rear part 1, a front part 2, a payload 3, a sliding tube 5 on which are lamellas 4 and a support piece 6.
  • the rear part 1 of the projectile is embedded, for example, in the front part 2 thereof in the recess 9 shown in this figure.
  • the two parts 1 and 2 are kept in contact with each other by means of pins 12; it is at this point that the front part 2 of the projectile is separated from the rear part 1.
  • This separation is initialized, for example, thanks to the pulse caused by a gas generator located in the front part 2 of the projectile and not shown in the figure causing the breakage of the pin 12 thus releasing the two front and rear parts of the projectile as well as the payloads contained inside the latter.
  • a gas generator located in the front part 2 of the projectile and not shown in the figure causing the breakage of the pin 12 thus releasing the two front and rear parts of the projectile as well as the payloads contained inside the latter.
  • These strips 4 are arranged side by side inside the projectile thus forming a tube which can slide; they are also fixed at one of their ends to a tube 5 on which is placed a support piece 6; the shape of the latter is determined, for example, to include bosses serving to support the bottom of the payload 3; it is made, for example, from stamped sheet metal and its thickness is determined, for example, according to the resistance of the materials to avoid any deformation.
  • the support part 6 is provided, for example, with one or more lugs 7 which come, during ejection, to be braced on a shoulder 8 forming an integral part of the rear structure 1 of the projectile and allowing the lamellae 4 to fully play their role; these lugs 7 are made, for example, so that they are elastically erased during integration into the projectile when they pass in line with the shoulder 8; they can also be fixed, for example, on the lamellae (4) or on the tube (5) while retaining their function.
  • FIG. 2 shows a cross section of the rear part 1 of the projectile during the separation phase.
  • the projectile when the projectile has left its launch tube, it is rotated around the axis OO ′.
  • the separation of the front structure 2 of the projectile and its rear part 1 causes the release of the payloads contained inside the projectile.
  • the front part 2 of the projectile is propelled forward by means of propellant gases; the latter exert a force on the rear of the projectile facilitating, for example, the separation of the two parts 1 and 2 of the projectile.
  • the lamellae 4 are subjected to centrifugal force due to the rotation of the projectile. They thus exert a force which causes the start of separation between the rear part 1 and the payload 3.
  • This phenomenon is obtained by the sliding of the assembly 4, 5, 6 on the rear part 1 of the projectile. This makes it possible to obtain a greater deployment length than that allowed by the location between the rear part 1 and the payload 3.
  • the sliding of this assembly 4, 5, 6 is carried out up to the stop 8 of the rear part 1 where the pins 7 of the support part 6 lock the assembly 4, 5, 6.
  • Figure 3 shows a cross section of the rear part of the projectile after the separation phase.
  • the device according to the invention having come to abut against the notches provided for this purpose, the strips 4 are subjected to centrifugal force because the projectile has been rotated in its launching phase; they deploy as a fan, by bending, as shown in Figure 3, the speed of the projectile also producing effects on the latter.
  • FIG. 4 shows a fixing of the strips 4 according to another embodiment before the phase of separation of the front part 2 of the projectile and its rear part 1.
  • the strips 4 are arranged side by side inside the projectile; they are housed between the rear part of the payload 3 and the rear part of the projectile 1; they are fixed at one of their ends 12, for example, by a fixed fixing system, for example, one can use rivets 13 which pass through the lamellae 4 and come to bear on the rear part 1 of the projectile.
  • FIG. 5 represents the fixing system, previously described according to FIG. 4, after the separation of the front part 1 of the projectile and its rear part 2. Slats 4 fixed on the rear part 1, during the ejection of the front part 2 of the projectile, deploy and take the position shown in FIG. 5.
  • the non-fixed end 14 of the strips 4 comes to bear on the recess 9 of the rear part 1; it is at this moment that the lamellae 4 begin to play, on the one hand, their role of separation thanks to the action of the self-rotating forces on the lamellae which causes the creation of a pushing force on the front part 1 thus facilitating the separation of the front part 1 and the rear part 2, and on the other hand, their braking role thus allowing the payload 3 contained inside the projectile to be moved away from its rear part 1.
  • FIG. 6 shows a fixing of the strips 4 according to another embodiment after the phase of separation of the front part 2 of the projectile from its rear part 1.
  • the strips 4 have the same arrangement as in the previous description; the difference is in the fixing system; they are fixed, for example, to a mobile fixing system, for example, an axially sliding fixing which can be produced, for example, by a spiral spring 15 whose large coil 16 is fixed to the rear part 1 of the projectile, by example, by studs 17; the central turn 18 is fixed to the strips 4, for example, by a plate 19 provided with two rivets 20.
  • the central turn 18, which superimposed the large turn 16 moves longitudinally in the direction OO ′ and, stabilizes in the position shown in this figure 6 so that part 21 of the lamellae 4 lies in a plane perpendicular to the turn central 18 as well as direction OO ′.
  • the slats 4 then fulfill the function which has been described previously.
  • Figure 7 shows the deployment of the slats 4 according to the invention.
  • These strips 4 are arranged either in a layer, which, in this case, causes a fan-shaped deployment of the latter as shown by the strips 4 in solid lines in FIG. 7, or in several layers, which makes it possible to obtain continuous ring deployment.
  • two layers of strips were used: the first being drawn in solid lines 4, the other 11 in dotted lines.
  • the two sets of strips each forming a tube in the rest state inside the projectile are offset by a certain angle in order to obtain the largest possible braking surface; the latter is obtained when the spaces 11 between the strips 4 of the first thickness are covered by the strips 10 of the second thickness.
  • the shaping of these strips is given by the rotational movement of the projectile acquired at launch.
  • the strips 4 are located next to each other and form a tube inside the projectile when they are distributed around the payload 3. They are relatively thin and are made, for example, of metallic or plastic material.
  • the shape of these strips 4 is, for example, that of a flat rectangle whose width and length give their orientation which is defined by the ratio Length Width ; the latter must be reduced to limit the risk of vibration due to the fact that the aerodynamic profile of the slats is unstable at high incidence.
  • the aerodynamic thrust center of the slats can be offset.
  • the device operates without the use of an extractor system and only undergoes disturbances due to its surroundings. It can even be used in the case where, for example, the payload 3 of the projectile has air brakes fixed on its rear part and opening under the influence of centrifugal force; these, when inserted inside the projectile before the separation and launching phase, can rest on the tube 5 which prevents them from rubbing against the rear part 1 during the sliding of the assembly 4 , 5, 6 on the latter 1. As a result, the relief stroke with friction of the airbrakes is considerably reduced.
  • FIG. 8 represents another application of the lamella braking device according to the invention.
  • the lamellae (4) are positioned, by one of their ends (22), on a body (23), for example, by embedding the latter in the structure of the body, so that, during the deployment of the strips (4), as shown in the figure, each of them comes to bear on the edge (24) of the body considered for allow to play their full role, namely: the body being rotated, the aerodynamic effects due to the speed of the projectile and the centrifugal forces exerted on the slats, the slats are positioned according to, for example, an angle ⁇ significantly increasing aerodynamic drag and therefore braking the body.
  • the slats (4) will be fixed at the other end (25), for example, by a system of pins (26) which makes it possible to keep the slats in contact with the body to initially increase the piercing of the body in the air and then decrease the bulk; this system for fixing the end (25) of the strips (4), for positioning the strips (4) along the body, can be produced in particular by a control system providing for the unlocking of the fixing system at a precise calculated time beforehand.
  • the aerodynamic forces act on the tear-off sockets constituted, for example, by the pins, the latter are torn off freely leaving the strips (4) deploying fulfilling their braking function.
  • This device according to the invention applies to any body driven by a high speed of rotation and remains effective for speeds of rotation which decrease because once deployed the device remains substantially in this position.
  • the invention can be applied in particular to any braking of a body in replacement of a braking stage as well as to pyrotechnic devices, for example military ones such as illuminants or infrared which must be braked before the start of their phase. operational.
  • the invention can also be applied to submunitions on board a projectile. Indeed, in order to disperse each submunition after its ejection from the projectile, the device according to the invention can be fixed on each submunition to brake and therefore separate these submunitions. To do this, each submunition must be provided with a number and a size of lamellae determined to give them different speeds.
  • the application of the device according to the invention to submunitions contained inside a projectile is as follows. In FIG.
  • each submunition 27 placed inside the projectile 28 is covered with a compact system, in this case spacers 29 and their fixing system, for example weights 30 so as to firstly, during ejection, to avoid causing significant radial stresses against the casing 31 of the projectile due to the centrifugal force created by the projectile rotating around its longitudinal axis, and secondly, to resist the stresses mechanical due to acceleration and imposed on the projectile at the start of the shot likely to damage certain submunitions.
  • the device according to the invention must be placed, for example, on each submunition, that is to say between the compact system and the submunition. Any other means of fixing the lamellae to the body of the submunition may be used.
  • this system as shown in Figure 10 consists, for example, to put as many metallic ribbons called foils 32 as elements of spacers not shown.
  • These foils are wound around the submunition 33 in the opposite direction of rotation with a winding angle limiting the risk of collision; this winding angle is a function of the number of spacer elements and the position of the junction between two spacer elements relative to the fixing of the foil, for example, on the submunition, for example, by welding 34 at one of its ends.
  • each foil is surrounded around the submunition with a winding angle of the order of 285 °.
  • the fixing of the foil on the submunition is made so that the tangential resistance is substantial but that the radial resistance is weaker so that the foil fixed, for example, by welding, does not resist the centrifugal force which causes the ejection of its last.

Claims (19)

  1. Bremseinrichtung für ein Element eines Geschoßes, das eine Längsachse OO′ besitzt und dazu vorgesehen ist, zu einer Drehbewegung angetrieben zu werden und einen vorderen Teil (2) und einen hinteren Teil (1) aufweist, welche jeweils einen Körper besitzen, wobei die Zusammenfügung der beiden Körper einen Geschoßkörper ergibt, wobei die äußere Umfangsfläche des Geschoßkörpers einen inneren Teil gegenüber einem äußeren Teil abgrenzt, wobei der vordere Teil (2) und der hintere Teil (1) voneinander getrennt werden können, wobei der hintere Teil (1) Bremsmittel aufweist, die zu zwei Positionen fähig sind, zu einer ersten, wenn der vordere Teil (2) und der hintere Teil (1) zusammengefügt sind, und zu einer zweiten, wenn diese Teile voneinander getrennt sind, wobei die Bremsmittel von Flächen gebildet sind, die sich in der ersten Position im inneren Teil des Geschoßkörpers befinden und die in der zweiten Position wenigstens teilweise in die äußere Umgebung des Körpers des hinteren Teils (1) aufgeklappt sind, dadurch gekennzeichnet, daß die Flächen von Lamellen (4) aus einem zu plastischen Verformungen fähigen Material gebildet und mit einem ihrer Enden am Umfang des Körpers des hinteren Teils befestigt sind, wobei der Übergang von der ersten zur zweiten Position nach der Trennung des vorderen Teils und des hinteren Teils unter der Wirkung von Zentrifugalkräften erzielt wird.
  2. Einrichtung gemäß Anspruch 1, dadurch gekennzeichnet, daß die Lamellen (4) an einem Rohr (5) mit Mittelachse OO′ befestigt sind.
  3. Einrichtung gemäß Anspruch 2, dadurch gekennzeichnet, daß das Rohr (5) zwei Positionen einnehmen kann, eine erste vor der Trennung und eine zweite nach der Trennung, wobei der Übergang von der ersten in die zweite Position durch eine Verschiebung nach vorne entlang der Mittelachse OO′ gebildet wird.
  4. Einrichtung gemäß einem der Ansprüche 2 oder 3, dadurch gekennzeichnet, daß das Rohr (5) an einem Trägerstück (6) befestigt ist, welches an jedem seiner Enden Vorsprünge (7) aufweist, die mit dem hinteren Teil zusammenwirken, um zu verhindern, daß sich das Stück (6) vorm hinteren Teil (1) löst.
  5. Einrichtung gemäß Anspruch 4, dadurch gekennzeichnet, daß die durch die Vorsprünge (7) verwirklichte Verriegelung der Einrichtung bei der Verschiebung des Rohrs (5), der Lamellen (4) und des Trägerstücks (6) durch Anstoßen der Vorsprünge (7) an einem am hinteren Teil befestigten Anschlag (8) bewerkstelligt wird.
  6. Einrichtung gemäß einem der Ansprüche 2 oder 3, dadurch gekennzeichnet, daß das Rohr (5) Vorsprünge aufweist, die mit einem Anschlag (8) des hinteren Teils zusammenwirken, um zu verhindern, daß sich das Rohr (5) vom hinteren Teil löst.
  7. Einrichtung gemäß Anspruch 1, dadurch gekennzeichnet, daß die Lamellen (4) am hinteren Teil des Geschoßes (1) durch Nieten (13) befestigt sind.
  8. Einrichtung gemäß Anspruch 1, dadurch gekennzeichnet, daß die Lamellen (4) am hinteren Teil (1) durch eine axial verschiebbare Spiralfeder (15) befestigt sind.
  9. Einrichtung gemäß Anspruch 8, dadurch gekennzeichnet, daß die Spiralfeder (15) am hinteren Teil (1) des Geschoßes befestigt ist.
  10. Einrichtung gemäß einem der vorangehenden Ansprüche, dadurch gekennzeichnet, daß die Lamellen (4) in der ersten Position in einer Lage angeordnet sind.
  11. Einrichtung gemäß einem der vorangehenden Ansprüche, dadurch gekennzeichnet, daß die Lamellen in der ersten Position in mehreren Lagen angeordnet sind.
  12. Einrichtung gemäß Anspruch 10, dadurch gekennzeichnet, daß das Aufklappen der Lamellen (4) in Form eines unterbrochenen Kranzes ausgeführt wird.
  13. Einrichtung gemäß Anspruch 11, dadurch gekennzeichnet, daß die Lamellen (4) in der aufgeklappten Position einen ununterbrochenen Kranz bilden.
  14. Einrichtung gemäß einem der vorangehenden Ansprüche, dadurch gekennzeichnet, daß das aerodynamische Schubzentrum der Lamellen (4) durch Verbleiung oder andere Mittel aus der Mittellage versetzt ist, um eine winkelmäßig stabile Verschiebung derselben zu erzielen.
  15. Einrichtung gemäß einem der Ansprüche 1 bis 14, dadurch gekennzeichnet, daß der Geschoßkörper vor der Trennung des vorderen Teils (2) und des hinteren Teils (1) Körper (23) oder Submunition (27) beherbergt, die nach der Trennung den Geschoßkörper verlassen können.
  16. Einrichtung gemäß Anspruch 15, dadurch gekennzeichnet, daß die Körper (23) oder die Submunition (27) mit plastisch verformbaren Lamellen (25, 35) ausgerüstet sind, die zwei Positionen einnehmen können, eine erste Position, wenn sich der Körper (23) oder die Submunition (27) im Inneren des Geschoßes befindet, und eine zweite, wenn sich der Körper (23) oder die Submunition (27) außerhalb des Geschoßes befindet, und daß in der ersten Position wenigstens ein Teil der Fläche einer jeden Lamelle entlang der Umfangsfläche der Munition angeordnet ist und daß in der zweiten Position wenigstens ein Teil der Fläche einer jeden Lamelle radial in die äußere Umgebung des Körper oder der Submunition aufgeklappt ist.
  17. Einrichtung gemäß Anspruch 16, dadurch gekennzeichnet, daß um die Submunition (33) auf die Lamellen (35) Metallfolien (32) gewickelt sind, derart, daß eine plötzliche Öffnung der Einrichtung vermieden wird.
  18. Einrichtung gemäß Anspruch 17, dadurch gekennzeichnet, daß die Metallfolien mit einem ihrer Enden durch Verschweißen (34) befestigt sind.
  19. Einrichtung gemäß einem der vorangehenden Ansprüche, dadurch gekennzeichnet, daß das Befestigungssystem ein Steuersystem ist.
EP89905121A 1988-04-12 1989-04-11 Aerodynamische bremsvorrichtung für einen körper Expired - Lifetime EP0367815B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8804830 1988-04-12
FR8804830A FR2629908B1 (fr) 1988-04-12 1988-04-12 Dispositif de freinage aerodynamique d'un corps

Publications (2)

Publication Number Publication Date
EP0367815A1 EP0367815A1 (de) 1990-05-16
EP0367815B1 true EP0367815B1 (de) 1993-02-10

Family

ID=9365235

Family Applications (1)

Application Number Title Priority Date Filing Date
EP89905121A Expired - Lifetime EP0367815B1 (de) 1988-04-12 1989-04-11 Aerodynamische bremsvorrichtung für einen körper

Country Status (5)

Country Link
US (2) US5054400A (de)
EP (1) EP0367815B1 (de)
FR (1) FR2629908B1 (de)
HK (1) HK44095A (de)
WO (1) WO1989009919A1 (de)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5060574A (en) * 1990-07-02 1991-10-29 Honeywell Inc. Projectile base plug with enhanced drag-producing separation capability
GB2248804A (en) * 1990-10-19 1992-04-22 Marconi Gec Ltd Air-launched buoys
DE4124658C2 (de) * 1991-07-25 1996-08-14 Rheinmetall Ind Gmbh Einrichtung zum Abbau der Drehzahl von Submunition
FR2684754B1 (fr) * 1991-12-10 1995-04-07 Thomson Brandt Armements Obus dont le culot fait office de pot de parachute d'une sous-munition.
SE503719C2 (sv) * 1992-06-30 1996-08-12 Bofors Ab Sätt och anordning för separation av substridsdelar
SE508857C2 (sv) * 1997-03-25 1998-11-09 Bofors Ab Fenstabiliserad base-bleedgranat
FR2807278B1 (fr) * 2000-03-31 2005-11-25 Thomson Marconi Sonar Sas Dispositif pour controler la navigation d'un objet sous- marin remorque
GB2365952A (en) * 2000-08-16 2002-02-27 Secr Defence Drag brake for a munition
US6997110B2 (en) * 2001-09-05 2006-02-14 Omnitek Partners, Llc. Deployable bullets
JP6278780B2 (ja) * 2014-03-28 2018-02-14 株式会社小松製作所 旋回飛翔体

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US674509A (en) * 1900-09-01 1901-05-21 Robert Macmartin Explosive shell.
US1276575A (en) * 1917-05-09 1918-08-20 Frederick M Ross Projectile.
US2324678A (en) * 1941-03-27 1943-07-20 Robert R Clark Bullet
US3115831A (en) * 1961-09-26 1963-12-31 Suter Henry Flexible rotochute
US3114315A (en) * 1961-09-26 1963-12-17 William E Trump Dive brake
US3572250A (en) * 1969-03-10 1971-03-23 Aerospace Systems Co Cone for aeroballistic member
US3710715A (en) * 1970-11-24 1973-01-16 Us Army Volute spring stabilizer
US3834311A (en) * 1971-06-01 1974-09-10 Mb Ass Cartridge
US4008667A (en) * 1973-12-13 1977-02-22 The L.O.M. Corporation Controlled range bullet
US4648321A (en) * 1985-04-04 1987-03-10 The United States Of America As Represented By The Secretary Of The Navy Missile separation system
DE3643291A1 (de) * 1986-12-18 1988-06-23 Rheinmetall Gmbh Drallstabilisiertes traegergeschoss
DE3643294A1 (de) * 1986-12-18 1988-06-23 Rheinmetall Gmbh Geschoss
US4699062A (en) * 1987-02-11 1987-10-13 The United States Of America As Represented By The Secretary Of The Navy VLA (alwt) airframe clamshell opener assembly
US4798143A (en) * 1987-05-06 1989-01-17 Douglas Graham Gas dispensing projectile

Also Published As

Publication number Publication date
HK44095A (en) 1995-03-31
FR2629908A1 (fr) 1989-10-13
US5140909A (en) 1992-08-25
FR2629908B1 (fr) 1993-05-14
EP0367815A1 (de) 1990-05-16
US5054400A (en) 1991-10-08
WO1989009919A1 (fr) 1989-10-19

Similar Documents

Publication Publication Date Title
EP0367815B1 (de) Aerodynamische bremsvorrichtung für einen körper
EP0541411B1 (de) Vorrichtung zum Auswerfen der Submunitionen aus einem Trägergeschoss
FR2595811A1 (fr) Projectile porteur pour sous-munitions
EP0438343B1 (de) Penetratormunition für Ziele mit hohem mechanischem Widerstand
EP0294281B1 (de) System zum Halten von Tochtergeschossen in einem sich um seine Längsachse drehenden Geschoss
EP2546597B1 (de) Täuschsystem zur Montage an einem Luftfahrzeug
EP1006335A1 (de) Bremsvorrichtung für die Flugbahngeschwindigkeit eines Geschosses
EP0130893B1 (de) Trägergeschoss für Streumunition
EP0105001B1 (de) Sicherheitseinrichtung mit einem umlaufenden Käfig für ein Drallgeschoss
FR3011919A1 (fr) Dispositif de freinage en rotation d'une enveloppe d'une charge utile, et projectile gyrostabilise equipe d'un tel dispositif
EP0034532A2 (de) Streubare Mine vom Zweirichtungs-Hohlladungstyp
EP0756151B1 (de) Vorrichtung zum Zünden einer Treibladung für eine aus einem Trägergeschoss geworfene Submunition
FR2552871A1 (fr) Projectile antichar agissant en vitesse defilante
EP0319379A1 (de) Abwurfkörper mit aerodynamischen Bremsmitteln
FR2769083A1 (fr) Procede de guidage d'un missile et missile pour la mise en oeuvre du procede
FR2644881A1 (fr) Dispositif de liaison entre un premier et deuxieme troncon d'un projectile gyrostabilise
EP1371935B1 (de) Vorrichtung und Munition für den Schutz eines Fahrzeuges oder einer Plattform gegen Drohungen
FR2656082A1 (fr) Systeme deployable pour l'emport et la sustentation d'une munition.
FR2691799A1 (fr) Munition en particulier sous-munition destinée à être éjectée d'un projectile porteur.
EP2546143B1 (de) Geschützabschusssystem, insbesondere als Gegenmaßnahme von einem Luftfahrzeug aus
EP0767356B1 (de) Drallabbremsende Mittel für ein Trägermunitionsubgeschoss
EP0685059B1 (de) Schlagbolzensicherung und verfahren zu seiner herstellung
FR2679644A1 (fr) Dispositif transporteur de charges utiles.
FR2801099A1 (fr) Systeme d'amorcage de la charge explosive d'une sous- munition
FR2657157A1 (fr) Dispositif de correction de courbure d'un trajectoire d'une munition perforante pour des cibles a haute resistance mecanique.

Legal Events

Date Code Title Description
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

17P Request for examination filed

Effective date: 19891120

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB IT SE

17Q First examination report despatched

Effective date: 19910731

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB IT SE

REF Corresponds to:

Ref document number: 68904875

Country of ref document: DE

Date of ref document: 19930325

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 19930305

ITF It: translation for a ep patent filed

Owner name: JACOBACCI CASETTA & PERANI S.P.A.

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
EAL Se: european patent in force in sweden

Ref document number: 89905121.3

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 19960319

Year of fee payment: 8

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Effective date: 19970411

REG Reference to a national code

Ref country code: FR

Ref legal event code: CL

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 19970411

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 20030404

Year of fee payment: 15

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20030408

Year of fee payment: 15

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20030424

Year of fee payment: 15

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20040412

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20041103

EUG Se: european patent has lapsed
PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20041231

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED.

Effective date: 20050411