EP0794405B1 - Verfahren und Einrichtung zum Verbringen einer grosskalibrigen Nutzlast über ein Einsatzgelände - Google Patents
Verfahren und Einrichtung zum Verbringen einer grosskalibrigen Nutzlast über ein Einsatzgelände Download PDFInfo
- Publication number
- EP0794405B1 EP0794405B1 EP97103395A EP97103395A EP0794405B1 EP 0794405 B1 EP0794405 B1 EP 0794405B1 EP 97103395 A EP97103395 A EP 97103395A EP 97103395 A EP97103395 A EP 97103395A EP 0794405 B1 EP0794405 B1 EP 0794405B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- payload
- space
- payload space
- load
- ogive
- 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
- F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
- F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
- F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
- F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
- F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles
- F42B12/62—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected parallel to the longitudinal axis of the projectile
-
- 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
- F42B10/56—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding of parachute or paraglider type
Definitions
- the invention relates to a method according to the preamble of claim 1 and a Claim device according to the preamble of claim 3.
- the generic measures are from EP-A-0062750 as a method and Device for distributing active parts of a carrier missile known, from there the payload space of a ballistic missile as a payload at least one Distribution unit is output (which then in turn later deposits secondary bodies). For that is provided by blasting off the ogive of the missile over the deployment area Open the payload space and deliver the payload from it in the direction of flight. The Payload should then swing out of the missile's trajectory, around the missile - that is Remaining unit from empty payload space and rear engine - collision-free To let payload pass.
- That generic pre-publication then deals with that in the individual Spread payload stacked secondary body. For this purpose, this will be pyrotechnic backwards, i.e. against the current direction of movement, separating it from there the payload articulated brake parachute pushed out of the payload.
- the result then the stack of secondary bodies braked relative to the movement of the payload is supposed to be out its aerodynamically stable composite can be solved by working on the individual one after the other Secondary bodies open screens, by means of which the individual secondary bodies are independent are braked by each other and are supposed to sink into the operational area.
- the invention is therefore based on the object, the generic measures in this regard to further train such critical payloads over the site can be released reliably from a movement projectile.
- the solution according to the invention is thus distinguished both in terms of the method and also with regard to the device for moving large-caliber payloads, that the activation of stabilization elements for one, separated from the stern and aerodynamically unstable, payload space is delayed by one too Avoid early volume increase associated with braking until the separated rear engine aerodynamically stable on the payload space spinning off the track flew by.
- brake sails can be issued (see US Pat. No. 4,726,543), or a parachute connected to the envelope of the payload space is stretched around the Envelope with the open separation point facing in the direction of movement and making it relative decelerate to the inertial mass of the payload and thereby the payload in the direction of flight to let it slide out of the cover at the front.
- the screen originally orientates this against the direction of flight Pointing load area tail in future stable in the direction of flight, whereupon a Lid separated and thus now the load compartment cover from the brake screen effect Submunition stack whose direction of movement is subtracted. So it is reproducible and fast Pushing out the submunition stack, despite inflow back pressure in front of the load area and despite negative pressure in the load area and the frictional forces against the inside of the load compartment, reliably and quickly takes place, it becomes in the load compartment resulting negative pressure by an extension aid in the form of a gas generator, as in Motor vehicle airbag is commercially available, not only compensated, but preferably even overcompensated to support the extension forces in support of the umbrella traction to overcome.
- the gas generator can be inflated Be used airbag, the deployment of which slides out of the submunition stack supports the load area. But if the inflation behavior of the locked gas bag is critical in terms of time or geometry, then there is a piston-like pressure distribution plate behind the parachute chamber, the last one to be pushed out of the load area Submunition more appropriate. So that the plate stands out reliably and then the parachute chamber can be opened, the plate remains by means of an eccentric attack Leash tied to the load room.
- This bondage can also serve as a holder for a pull-out line behind the last submunition of the Stack opens a small pilot screen to separate this rearmost submunition from the stack - and then a corresponding pull-out line from the settling Submunition to the pilot screen on the last element of the remaining submunition stack to tension, etc.
- this is important make sure that they are the sum of the axial height and the diameter of a submunition not exceed, because otherwise after disconnecting from the pilot screen flying in front a knotting with the own rear pilot screen and thereby a disturbance of the further parachute releases could occur.
- Each Mine umbrella can be given some sliding behavior to be independent of the A broader distribution of the descending mines over the To reach the restricted area.
- the transition area between ogive and load area subjected to strong bending stresses because of the rocket rear engine already separated ogive-load space composite laterally from the previous ballistic trajectory of the Rocket swings out (Fig. 3) and experiences a strong cross-flow. Nevertheless it must be ensured that the ogive stands out reliably from the forehead of the load area, and that the opening of the brake parachute coupled to the load space does not hinder becomes.
- this is achieved in that between the load-bearing ogive construction and a load compartment end plate a separable connection is provided in the form of a coaxial cylinder guide, the friction fit for the Separation process must be overcome by the reaction gas pressure of a repulsion charge.
- an artillery missile 11 for example for deployment at least one so-called surface defense mine as a payload or submunition 12 into their field of operation 113, an armored vehicle to be locked against the passage potential combat area.
- the rocket 13 which can be launched from a mobile launcher 114, is included a stabilizing tail unit 27 at the rear end of its rear engine 17. The spends the rocket 13 into a ballistic during only a brief pushing period Trajectory 26 over the site 113.
- the hollow cylindrical payload space 19 for receiving e.g. at least a mine to be ejected in the manner of submunition 12 over deployment site 113.
- Transition area 121 a separating charge in the form of a on the hollow cylinder inner wall circumferential, radially outwardly acting cutting charge as Separator 16 provided; So practically one on the inner surface of the hollow cylinder radially attached explosive ring with also circumferential acute-angled, radially outward opening V-shaped insert.
- an (electronic or pyrotechnic) delay element started with a sufficient safety margin only at the payload space 19 emerging from the flight path 26 aerodynamic braking means then releases when it can be expected that the rear part 18 with the motor 17 long ago the web 26 flew past the payload space 19.
- aerodynamic braking in the example shown, it is a brake chimney 23 that faces the front open separation area 121 connected opposite to the shell 123 of the payload space 19 is. It is released, for example, by pyrotechnic blasting off the ogive hood 14, in the connection area to the sheath 123, the screen 23 was folded.
- the delivery device 11 shown in FIG. 2 for large-caliber submunitions 12 is preferably designed as an artillery missile 13 according to the MLRS / MARS system. It contains in its ogive designed as a ballistic hood 14 a time fuse 15 for the Initiate a separator 16 between the rocket engine 17 and the tail 18 of the axially in front of the same-sized load space 19 for the shipment of the full-caliber Submunitions 12.
- Another separating device 20 is in the transition area 21 from the ogive 14 to the load space 19 provided. It serves to abolish the constructive measures mentioned there Connection with release of the brake screen connected to the forehead 22 of the load space 19 23.
- a separating device 24 can also be located in the area of the rear of the load space 18 be provided to remove a rear lock lid 25 and the submunitions 12th slide coaxially out of the load space 19 to the front through the then pointing rear 18 to be able to leave.
- the problem is a trouble-free lifting of the load space 19 to its side Drifts off the path 26 of the rocket motor 17. Because the motor 17 flies in a stable direction literally in the slipstream directly behind the load space 19, which is caused by the dynamic pressure before the ogive 14 is braked. The result of this is that, despite activation of the motor separating device 16 the motor 17 then immediately unlocks the load compartment rear 18, so that both continue to form a relatively stable flight, from the trajectory 26 of the Load space 19 can not swing out as soon (to due to the cross flow, away from Track 26 of motor 17 braked for a quick and collision-free overtaking process to become).
- Another repulsion charge 31 serves - now between ogive 14 and load area forehead 22 - the rapid build-up of the highest possible relative speed between the two to increase the distance as quickly as possible so that the ogive 14 does not move with it almost suddenly unfolding and thereby braking screen 23 collides.
- the shell 10 of the rocket 13 has a predetermined breaking point, the separates when the ogive 14 is substantially coaxial from an end plate 22 in front of the Load space 19 is lifted.
- This separation process is time-controlled by firing one then evenly initiated low pressure repulsion charge 31 initiated after the Load space 19 including ogive 14 has been lifted off the rocket rear engine 17 and sideways whose ballistic path 26 is swung out, as shown in the sequence Fig. 4-5.
- the problem is, however, that very large transverse forces 37 on the cross flow Act on the composite of ogive 14 and load compartment 19.
- a comparatively high one Stretchability, in particular low bending stiffness, of the central pin 39 allows this pitching movement 41 of the rocket shell 10 carrying ogive construction 38 opposite the Hollow piston 40, which in turn is rigid in the hollow cylinder 42 coaxially in front of the load area end plate 22 is located (trained or supported on it).
- the ogive in the transition area 9 experiences an axially displaceable radial guide in the Around their long axis.
- peripheral radial support near the shell 10 opposite a collar 45, which, open to the front, coaxially in front of the end plate 22 of the load space 19 extends into the interior of the ogive 14.
- One with the load-bearing ogive construction 38 connected in one part or in several parts by the central pot 43 annular storage compartment 32 open to the load compartment 19 for the load compartment brake screen 23 protrudes at a radial distance between the ring wall 44 and the collar wall 45 into the front of the collar 45.
- a low-pressure repulsion charge 31 is used to lift the ogive 14 off the end plate 22 ignited between end plate 22 and hollow piston 40, which burns evenly increasing reaction gas pressure in a burst capsule 48 surrounding the charge 31, until outflow bores sealed with a film are torn open by the excess pressure.
- the reaction gas pressure of the burning charge 31 can then be in the interior of the Impact hollow piston 40 until a predetermined breaking point running around the bursting capsule 48 49 tears open around the hollow piston 40 - guided coaxially in the hollow cylinder 42 - from the end plate 42 and thus also the load-bearing ogive construction 38 while breaking open the Sheath predetermined breaking points in the transition area 9 to move away from the load space 19.
- This lifting of the cassette 32 from the end plate 22 of the load space 19 begins when the build-up of the reaction gas pressure inside the hollow piston 40 to an axial force leads, which is greater than the constructively predetermined frictional force along the cylinder surface between the hollow piston 40 and the hollow cylinder 42 enclosing it for the axial guidance.
- a gas generator 35 is installed on the inside of the load chamber end 22, how it is used as standard in passenger car airbags and thus as Large-volume product is inexpensive and reliable available.
- the generator 35 delivers Sufficient gas volume quickly enough to deal with the vacuum that would otherwise occur fill up and also a weak axial pressure between the load area forehead 22 and the neighboring submunition 12, which is sufficient to build the frictional and dynamic pressure forces opposing the inertial delivery movement at least to the extent that an undisturbed and rapid axial Delivery of the submunitions 12 from the forward-oriented, open load compartment rear 18 is ensured.
- the energy released by the gas generator 35 can also be dimensioned so large that that it is sufficient for shearing brackets on the rear lid 25, so that here no further detonative separating device has to be implemented (the function of which by the previous function of the motor separation device 16 could be jeopardized).
- the reaction gas act directly on the adjacent end face of the submunitions 12.
- a plate 36 which acts as a flat extension piston in the load chamber 19. It's on an eccentrically located coupling point 37 by means of a line 38 to the load area forehead 22 bound so that the plate 36 is not in a stable connection with the submunition 12 from the Load chamber 19 emerges, but from the last emerging submunition 12 by pivoting is safely distracted from their path.
- the axially stack of submunitions which is still stable at first 12-12 is separated by small pilot screens 39 (Fig. 7). They are made using pull-out lines 40 released in succession; namely the pilot screen 39 on the one in the direction of flight as the last located submunition, with respect to which the pull cord 40 on the load compartment 19 or (better still) is attached to the piston plate 36 (Fig. 5).
- the screen 39 thus brakes the rear submunition 12 relative to the ones in front, whereby a pull line 40 the pilot screen 39 in the now rear of the remaining stack pulls out from submunitions 12-12, only to be separated from it, ..., and so on (Fig. 7).
- the pilot screens 39 Released, for example, via a pyrotechnic delay element (in the drawing not visible) the pilot screens 39 finally pull on the respective submunition 12 whose main or mine screen 41 (or previously only an auxiliary screen for further braking) out, on which the respective submunition 12 (Fig. 8) with uncritical rate of descent descends safely into the restricted area 113, since the previously separated submunitions 12 can no longer collide with these screens 41.
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Braking Arrangements (AREA)
- Superstructure Of Vehicle (AREA)
- Time-Division Multiplex Systems (AREA)
Description
- Fig. 1
- Eine Ablaufdarstellung zur Veranschaulichung des erfindungsgemäßen Verfahrens,
- Fig. 2
- in abgebrochener Längsschnitt-Darstellung eine erfindungsgemäß ausgestattete Rakete,
- Fig. 3 bis Fig. 8
- den Ablieferungsvorgang aus einer Rakete gemäß Fig. 1 und Fig. 2, nämlich
- Fig. 3
- den Anflug der Rakete über das Sperrgebiet,
- Fig. 4
- die Situation unmittelbar nach Abtrennen des Raketenmotors,
- Fig. 5
- die Gegebenheiten kurz nach Abtrennen der Ogive,
- Fig. 6
- das Ausschieben der Submunitionen aus dem gewendeten Lastraum,
- Fig. 7
- das Separieren des abgelieferten Submunitionsstapels und
- Fig. 8
- das Absinken der voneinander getrennten Submunitionen; sowie
- Fig. 9
- den Übergangsbereich vom Lastraum zur noch nicht gemäß Fig. 5 abgetrennten Ogive im abgebrochenen Längsschnitt.
Claims (10)
- Verfahren zum Verbringen einer großkalibrigen Nutzlast, wie insbesondere einer Mine oder einer Submunition, mittels einer Artillerie-Rakete mit Heckmotor und Heckleitwerk hinter ihrem Nutzlastraum in ballistischer Flugbahn über ein Einsatzgelände, über dem die Nutzlast axial aus dem Nutzlastraum ausgegeben wird, dadurch gekennzeichnet, daß über dem Einsatzgelände zunächst der Nutzlastraum vom Motor getrennt wird, um danach die Nutzlast am nun offenen Trennbereich aus dem Nutzlastraum auszugeben, wofür dieser mittels aerodynamischer Abbremsung gedreht wird, aber dieses erst nachdem der Motor längs seiner bisherigen Flugbahn den abgetrennten und aus der bisherigen Flugbahn ausgetretenen Nutzlastraum passiert hat.
- Verfahren nach Anspruch 1,
dadurch gekennzeichnet, daß eine Zeitverzögerung zur Freigabe der aerodynamischen Bremsmittel des abgetrennten Nutzlastraumes beim Abtrennen vom Heckmotor gestartet wird. - Einrichtung in Form einer Artillerie-Rakete (13) mit Heckmotor (16) und Heckleitwerk (15), die in ihrem in Flugrichtung vor dem Heckmotor (16) gelegenen Nutzlastraum (19) wenigstens eine großkalibrige Nutzlast (12) enthält, zum Verbringen der Nutzlast (12) über ein Einsatzgebiet (13), über dem die Nutzlast (12) aus dem Nutzlastraum (19) axial ausgebbar ist, dadurch gekennzeichnet, daß der Nutzlastraum (19) unter Öffnung eines Trennbereiches (21) mittels einer pyrotechnischen Ladung vom Heckmotor (16) abtrennbar ist, womit eine Zeitverzögerung für das Auslösen aerodynamischer Bremsmittel (Fallschirm 22) am Nutzlastraum (19) startbar ist, die erst abläuft, wenn der Heckmotor (16) den abgetrennten und dadurch aerodynamisch instabil gewordenen Nutzlastraum (19) passiert haben müßte.
- Einrichtung nach Anspruch 3,
dadurch gekennzeichnet, daß die Nutzlast (12) mittels Bremsschirm-Zuges koaxial aus dem Heck (18) des gestreckt-hohlzylindrischen Lastraums (19) ablieferbar ist, wozu einerseits zwischen dem Lastraum (19) und dem Motor (17) und andererseits zwischen dem Lastraum (19) und einer Ogive (14) jeweils eine pyrotechnische Trenneinrichtung (16, 24) und eine pyrotechnische Ladung (28, 31) zur rascheren Vergrößerung des gegenseitigen Abstandes dieser getrennten Teile vorgesehen sind, mit an die Stirn (22) des Lastraumes (19) gekoppeltem Bremsschirm (23), der nach Abheben der Ogive (14) entfaltbar ist und dadurch das Heck (18) in Flugrichtung voraus einstellt, ehe eine zwischen der LastraumStirn (22) und der benachbarten Nutzlast (12) im Lastraum (19) wirkende Ausschubhilfe (34) den Last-Stapel (12-12) dann in Flugrichtung voraus aus dem Lastraum-Heck 18 hinausschiebt. - Einrichtung nach Anspruch 4,
dadurch gekennzeichnet, daß, zwischen einem Gasgenerator (35) und der benachbarten Nutzlast (12) eine als flacher Ausschub-Kolben dienende Platte (36) angeordnet ist, die mittels einer Leine (38) an den Lastraum (19) gefesselt ist. - Einrichtung nach einem der Ansprüche 3 bis 5,
dadurch gekennzeichnet, daß ein vom Lastraum (19) fort topfförmig sich öffnender Heck-Deckel (25) vorgesehen ist, innerhalb dessen die Abhebe-Ladung (28) für den abgetrennten Motor (17) angeordnet ist. - Einrichtung nach einem der Ansprüche 3 bis 6,
dadurch gekennzeichnet, daß eine Ausziehleine (40) vorgesehen ist, die einerseits lösbar an einem Pilotschirm (39), mit welchem die Nutzlast (12) ausgestattet ist, und andererseits an der in Ausschubriditung dahinter gelegenen Nutzlast (12) oder direkt bzw. indirekt an dem Lastraum (19) befestigt ist. - Einrichtung nach einem der Ansprüche 3 bis 7,
dadurch gekennzeichnet, daß im Zuge des Abhebens der Ogive (14) von der Lastraum-Stirn (22) der Bremsschirm (23) aus einer Kassette (32) freigebbar ist, wofür die in der Ogive (14) gelegene und zum Lastraum (19) hin geöffnete, einen Kolben (40) ringförmig umgebende Kassette (32) von der Lastraum-Stirnplatte (22) unter koaxialer Führung des zentralen Kolbens (40) in einem Hohlzylinder (42) abgehoben wird. - Einrichtung nach Anspruch 8,
dadurch gekennzeichnet, daß die Fallschirm-Kassette (32) über einen zentralen Topf (43) einem Hohlkolben (40) gegenüber verschwenkbar und mit diesem koaxial verbunden ist. - Einrichtung nach einem der Ansprüche 4 bis 9,
dadurch gekennzeichnet, daß die Nutzlasten (12) Flächenverteidigungsminen mit an ihrem Minenkörper außen anliegenden und dadurch den Lastraum (19) vollkalibrig ausfüllenden Aufricht- und Standeinrichtungen sind.
Applications Claiming Priority (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19609012 | 1996-03-08 | ||
DE1996109012 DE19609012A1 (de) | 1996-03-08 | 1996-03-08 | Verfahren und Projektil zum Verbringen einer Nutzlast über ein Einsatzgelände |
DE19630796 | 1996-07-31 | ||
DE1996130796 DE19630796C2 (de) | 1996-07-31 | 1996-07-31 | Verbringungseinrichtung für großkalibrige Submunition |
DE1996144380 DE19644380A1 (de) | 1996-07-31 | 1996-10-25 | Verbringungseinrichtung für großkalibrige Submunition |
DE19644380 | 1996-10-25 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0794405A1 EP0794405A1 (de) | 1997-09-10 |
EP0794405B1 true EP0794405B1 (de) | 2001-09-05 |
Family
ID=27215999
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP97103395A Expired - Lifetime EP0794405B1 (de) | 1996-03-08 | 1997-03-01 | Verfahren und Einrichtung zum Verbringen einer grosskalibrigen Nutzlast über ein Einsatzgelände |
Country Status (4)
Country | Link |
---|---|
US (1) | US5760330A (de) |
EP (1) | EP0794405B1 (de) |
DE (1) | DE59704496D1 (de) |
NO (1) | NO313722B1 (de) |
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DE10130383A1 (de) * | 2001-06-23 | 2003-01-09 | Diehl Munitionssysteme Gmbh | Artillerie-Projektil mit austauschbarer Nutzlast |
DE102004046571A1 (de) * | 2004-09-24 | 2006-04-06 | Rheinmetall Landsysteme Gmbh | Vorrichtung zum Verbringen einer Nutzlast, insbesondere zur Neutralisierung von Minen oder dergleichen |
US20070018033A1 (en) * | 2005-03-22 | 2007-01-25 | Fanucci Jerome P | Precision aerial delivery of payloads |
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US8979031B2 (en) * | 2008-06-10 | 2015-03-17 | Roy L. Fox, Jr. | Aerial delivery system with munition adapter and latching release |
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US8222583B2 (en) * | 2009-03-23 | 2012-07-17 | Lockheed Martin Corporation | Drag-stabilized water-entry projectile and cartridge assembly |
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US20120043411A1 (en) * | 2010-06-01 | 2012-02-23 | L2 Aerospace | Unmanned aerial vehicle system |
US8403267B2 (en) * | 2010-11-29 | 2013-03-26 | Raytheon Company | Ejection system and a method for ejecting a payload from a payload delivery vehicle |
US8708285B1 (en) | 2011-01-11 | 2014-04-29 | The United States Of America As Represented By The Secretary Of The Navy | Micro-unmanned aerial vehicle deployment system |
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SE541612C2 (sv) * | 2016-09-15 | 2019-11-12 | Bae Systems Bofors Ab | Modifierbar delningsbar projektil och metod för att modifiera en projektil |
WO2018236448A2 (en) * | 2017-03-28 | 2018-12-27 | Skyworks Global Inc. | PRECISION DELIVERY VEHICLE |
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DE3608109A1 (de) * | 1986-03-12 | 1987-09-17 | Diehl Gmbh & Co | Bremseinrichtung fuer ein drallstabilisiertes projektil |
DE3722038A1 (de) * | 1987-07-03 | 1989-01-19 | Diehl Gmbh & Co | Drohne mit gefechtskopf |
DE3806731A1 (de) * | 1987-07-10 | 1989-01-26 | Diehl Gmbh & Co | Submunitions-wirkteil, sowie flechettes-gefechtskopf und flechettes dafuer |
FR2619441B1 (fr) * | 1987-08-14 | 1993-05-07 | Thomson Brandt Armements | Bombe antipiste a haute perforation |
DE3800330A1 (de) * | 1988-01-08 | 1989-07-20 | Diehl Gmbh & Co | Abwurfkoerper mit fallschirm |
DE3817265A1 (de) * | 1988-05-20 | 1989-11-30 | Diehl Gmbh & Co | Standvorrichtung fuer eine mine |
DE3823446A1 (de) * | 1988-07-11 | 1990-01-18 | Diehl Gmbh & Co | Einrichtung zum ausziehen eines bremsschirmes einer submunition |
US5109749A (en) * | 1988-10-25 | 1992-05-05 | Oea, Inc. | Explosively actuated separable structure |
US4955813A (en) * | 1989-09-21 | 1990-09-11 | Fochler Stephen H | Multi-pronged thumbtack |
DE3937762C2 (de) * | 1989-11-14 | 1993-11-25 | Diehl Gmbh & Co | Artilleriegeschoß-Submunition |
DE4123649C2 (de) * | 1991-07-17 | 1993-11-11 | Rheinmetall Gmbh | Ausstoßvorrichtung |
FR2683309B1 (fr) * | 1991-11-06 | 1993-12-31 | Giat Industries | Obus cargo ejectant une charge utile au moyen d'un piston. |
DE4304058C2 (de) * | 1993-02-11 | 2002-04-18 | Diehl Stiftung & Co | Verfahren und Vorrichtung zum Bekämpfen von Zielobjekten mit Submunitionen |
-
1997
- 1997-03-01 DE DE59704496T patent/DE59704496D1/de not_active Expired - Lifetime
- 1997-03-01 EP EP97103395A patent/EP0794405B1/de not_active Expired - Lifetime
- 1997-03-05 US US08/811,687 patent/US5760330A/en not_active Expired - Lifetime
- 1997-03-06 NO NO19971027A patent/NO313722B1/no not_active IP Right Cessation
Also Published As
Publication number | Publication date |
---|---|
NO971027D0 (no) | 1997-03-06 |
EP0794405A1 (de) | 1997-09-10 |
NO971027L (no) | 1997-09-09 |
DE59704496D1 (de) | 2001-10-11 |
US5760330A (en) | 1998-06-02 |
NO313722B1 (no) | 2002-11-18 |
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