EP1192406B1 - Dispositif de neutralisation d'une charge utile - Google Patents
Dispositif de neutralisation d'une charge utile Download PDFInfo
- Publication number
- EP1192406B1 EP1192406B1 EP01958138A EP01958138A EP1192406B1 EP 1192406 B1 EP1192406 B1 EP 1192406B1 EP 01958138 A EP01958138 A EP 01958138A EP 01958138 A EP01958138 A EP 01958138A EP 1192406 B1 EP1192406 B1 EP 1192406B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- rocket
- payload
- vector
- satellite
- charge
- 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
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
Definitions
- the technical field of the invention is that of devices for neutralizing a payload transported by a vector.
- the payloads thus carried can be dangerous or toxic. It is therefore necessary in case vector theft incident to destroy them.
- liquid propellants extremely toxic and explosive (hydrazine, peroxide nitrogen). It is essential to destroy these thrusters by incident in order to avoid a fall to the ground of a large quantity of these materials.
- the envelope of the thrusters is destroyed. so as to release the propellants. These destroy themselves in interacting with each other as well than in contact with the atmosphere.
- the weapon is also a complex mechanism likely to fail when launching the rocket.
- the hollow charge jets have a reduced effectiveness against propellants with liquid propellants.
- the jet is consumed quickly by the liquid and the diameter drain holes made is low (of the order of mm).
- the geometry of the payload can differ greatly from one vector shot to another.
- the thrusters are no longer placed at the same locations and the vector needs to be changed in depth to allow the establishment of a new neutralization.
- the neutralization device ensures destruction in a simple and reliable way of a payload carried by a vector.
- This device is easily adaptable to different types payloads, it therefore simplifies adaptation of the vector to the load to be carried.
- the subject of the invention is a device for neutralization of a payload transported by a vector, like a rocket, characterized in that it comprises at least one explosive charge generating nucleus, returned charge integral with the vector by positioning means ensuring an orientation of its direction of action towards the payload.
- the positioning means may be adjustable to allow adaptation of the neutralization device at different structures and / or payload locations.
- the positioning means may also be fixed.
- the device may include at least two charges explosive nucleus generators.
- the core-generating charge (s) will have preferably a caliber greater than 50 mm.
- the neutralization device according to the invention applies more particularly to the destruction of the thrusters of a satellite embarked by a rocket.
- a vector 1 such as a rocket ballistics (of which only the head is represented) includes a housing 2 inside its warhead 3, housing receiving a payload 4 constituted by a satellite.
- Satellite 4 is linked to the vector warhead by flanges 5a, 5b. In a known manner, it is intended to be released on trajectory by the rocket at a given altitude ensuring its launch into Earth orbit.
- the means ensuring the opening of the warhead and the satellite release is not shown here and they don't are not part of the present invention.
- Satellite 4 contains one or more tanks liquid propellants.
- the satellite shown in Figure 1 comprises two tanks 6a and 6b superimposed and arranged substantially at the axis 7 of the rocket.
- the tanks 6a, 6b are connected to a nozzle 8.
- means are provided to neutralize the propellants contained in the tanks 6a, 6b by breaking their tanks allowing thus their release.
- the neutralization means have two charges explosives 9a, 9b generating the nucleus. Each charge 9 is secured to rocket 1 by means of positioning 10a, 10b which ensure a orientation of the direction of action 11a, 11b towards the load useful 4.
- a nucleus-generating charge is well known to the Man of the Trade. We can for example consult the patents FR2627580, FR2740212 and FR2741142 which describe a such charge. It includes an explosive charge 13 placed in an envelope 14 and to which is applied a metallic coating 12 in the shape of a cap.
- the explosive charge 13 is initiated by a means detonator 15 which is connected to a control means 16.
- the positioning means 10a, 10b which are described here are designed to give one or two degrees of freedom to the envelope 14 of the load they bear.
- stirrup 17 defining a direction 18a, 18b parallel to the axis 7 of the rocket.
- This stirrup will be pivotally mounted relative to a base 20 fixed to the rocket. The pivoting will thus take place around the direction 18a or 18b (arrow Z).
- the load 9 will be fixed inside the stirrup 17 by via a base 19 and it can therefore itself be tilted relative to the bracket 17.
- each load 9 makes it possible to give each load 9 an optimal orientation which will be adapted in depending on the nature and structure of the payload 4. Concretely we will tilt each load in such a way that its direction of action 11 meets one of the reservoirs 6 of the satellite 4.
- the bracket 17 may be fixed by compared to the base 20, the only degree of freedom of the load will then be its tilting with respect to the stirrup 17.
- the load 9a thus has a direction of action 11a which is inclined at an angle ⁇ to the direction 18a parallel to the axis of the rocket 1. This direction of action 11a meets the upper reservoir 6b.
- the load 9b has a direction of action 11b which is inclined by an angle ⁇ relative to the direction 18b parallel to the axis of the rocket 1. This direction of action 11b meets the lower reservoir 6a.
- the charges 9a and 9b are connected to the control means 16 which is intended to cause their initiation at a time given.
- This control means can advantageously be consisting of part of the control electronics / rocket guidance.
- the initiation of charge (s) 9 will be caused on trajectory at a given time. This initiation may advantageously be remotely controlled from the ground in case of detection of a serious event (rupture of the rocket, loss of path).
- the initiation may also be triggered automatically by the rocket electronics in case of loss of ground connection (loss of guidance and / or control).
- the charges 9a, 9b have a diameter of the order of 50 to 150mm (for example 80mm).
- Their coating may be of iron or nickel. They generate as a result of their initiation a homokinetic metal core of approximately 100 g which is driven at a speed of around 2000 m / s.
- Such a nucleus is stable up to distances of the order 25 m, i.e. distances far greater than the maximum distance separating a load from one of the tanks propellant.
- the tanks 6 are therefore perforated by the cores thus generated. This results in a dynamic overpressure which blew up the tanks.
- the device according to the invention can be placed in the rocket at a location relatively distant from the payload.
- the speed and stability of the cores allows reliably destroy the payload despite the distance.
- the device according to the invention therefore allows, with a simple structure, compact and easy to integrate into the rocket, to ensure the safe destruction of the payload and especially liquid propellants contained in the tanks 6.
- the reliability of the device is higher than that of existing devices and at lower cost.
- Figure 2 shows a rocket 1 identical to that previously described but carrying a satellite 4 which has a different structure.
- This satellite comprises two tanks 6a, 6b of propellants which are arranged parallel to each other and both and across axis 7.
- the positioning means 10a and 10b make it possible to modify the orientations of action directions 11a and 11b loads so that each direction of action meets a reservoir 6a or 6b.
- the directions of action 11a and 11b are inclined by the same angle ⁇ with respect to the directions 18a / 18b defined by the stirrups 17 and parallel to the axis 7 of the rocket 1.
- Load adjustment will be carried out during payload integration.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Position Fixing By Use Of Radio Waves (AREA)
- Small-Scale Networks (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Monitoring And Testing Of Transmission In General (AREA)
- Selective Calling Equipment (AREA)
- Radio Relay Systems (AREA)
- Monitoring And Testing Of Nuclear Reactors (AREA)
- Toys (AREA)
- Catching Or Destruction (AREA)
Description
- la figure 1 représente schématiquement une vue partielle d'une fusée emportant un satellite et équipée d'un dispositif de neutralisation selon l'invention,
- la figure 2 est une vue de la même fusée emportant un satellite d'architecture interne différente.
Claims (6)
- Dispositif de neutralisation d'une charge utile (4) transportée par un vecteur (1), tel une fusée, caractérisé en ce qu 'il comporte au moins une charge explosive (9a, 9b) génératrice de noyau, charge rendue solidaire du vecteur (1) par des moyens de positionnement (10a, 10b) assurant une orientation de sa direction d'action (11a, 11b) vers la charge utile (4).
- Dispositif de neutralisation suivant la revendication 1, caractérisé en ce que les moyens de positionnement (10a, 10b) sont réglables de façon à permettre une adaptation du dispositif de neutralisation à différentes structures et/ou localisations de la charge utile (4).
- Dispositif de neutralisation suivant la revendication 1, caractérisé en ce que les moyens de positionnement (10a,10b) sont fixes.
- Dispositif de neutralisation suivant une des revendications 1 à 3, caractérisé en ce qu'il comporte au moins deux charges explosives (9a, 9b) génératrices de noyau.
- Dispositif de neutralisation suivant une des revendications 1 à 4, caractérisé en ce que la ou les charges génératrices de noyau (9a, 9b) ont un calibre supérieur à 50 mm.
- Application d'un dispositif de neutralisation suivant une des revendications 1 à 5 à la destruction du ou des propulseurs d'un satellite (4) embarqué par une fusée (1).
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0009813 | 2000-01-26 | ||
FR0009813A FR2812384B1 (fr) | 2000-07-26 | 2000-07-26 | Dispositif de neutralisation d'une charge utile |
PCT/FR2001/002317 WO2002008684A1 (fr) | 2000-07-26 | 2001-07-17 | Dispositif de neutralisation d'une charge utile |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1192406A1 EP1192406A1 (fr) | 2002-04-03 |
EP1192406B1 true EP1192406B1 (fr) | 2004-11-17 |
Family
ID=8852948
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP01958138A Expired - Lifetime EP1192406B1 (fr) | 2000-07-26 | 2001-07-17 | Dispositif de neutralisation d'une charge utile |
Country Status (7)
Country | Link |
---|---|
US (1) | US6718883B2 (fr) |
EP (1) | EP1192406B1 (fr) |
AT (1) | ATE282814T1 (fr) |
AU (1) | AU2001279875A1 (fr) |
DE (1) | DE60107181T2 (fr) |
FR (1) | FR2812384B1 (fr) |
WO (1) | WO2002008684A1 (fr) |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7690287B2 (en) * | 2006-07-18 | 2010-04-06 | Maegerlein Stephen D | Explosive neutralizer and method |
WO2009045619A1 (fr) * | 2007-07-30 | 2009-04-09 | Thomas Blake K | Renforçateur d'amorçage de détonateur de charge creuse permettant de réduire la létalité dielle, monté dans des bombes impliquant des dommages collatéraux réduits (rcdb) qui comportent des charges de perforation ou des charges explosives de grande puissance difficiles à allumer |
DE102012110450B4 (de) * | 2012-10-31 | 2014-07-17 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Objekt für eine Mission in den Weltraum |
DE102016219627A1 (de) * | 2016-10-10 | 2018-04-12 | Bayerische Motoren Werke Aktiengesellschaft | Unbemanntes luftfahrzeug, energiespeichermodul und verfahren zur steuerung eines unbemannten luftfahrzeugs |
Family Cites Families (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3382800A (en) * | 1964-11-09 | 1968-05-14 | Navy Usa | Linear-shaped charge chemical agent disseminator |
CH526764A (de) * | 1970-07-17 | 1972-08-15 | Oerlikon Buehrle Ag | Geschoss mit einem Geschossmantel |
US3707918A (en) * | 1971-02-26 | 1973-01-02 | Susquehanna Corp | Aerosol disseminator |
US3913483A (en) * | 1972-08-11 | 1975-10-21 | Us Army | Grenade with fuze |
CH580798A5 (fr) * | 1974-05-24 | 1976-10-15 | Contraves Ag | |
US3995549A (en) * | 1975-03-17 | 1976-12-07 | The United States Of America As Represented By The Secretary Of The Navy | Rocket/missile motor explosive insert detonator |
DE3048617A1 (de) * | 1980-12-23 | 1982-07-22 | Dynamit Nobel Ag, 5210 Troisdorf | Gefechtskopf mit sekundaerkoerpern als nutzlast |
US4459915A (en) * | 1982-10-18 | 1984-07-17 | General Dynamics Corporation/Convair Div. | Combined rocket motor warhead |
US4961382A (en) * | 1986-05-27 | 1990-10-09 | Motorola, Inc. | Penetrating projectile having a self-destructing piercing front end |
USH345H (en) * | 1987-03-30 | 1987-10-06 | The United States Of America As Represented By The Secretary Of The Army | Missile canting shaped charge warhead |
FR2627580B1 (fr) | 1988-02-18 | 1993-02-19 | France Etat Armement | Procede permettant d'obtenir un noyau comportant des ailettes stabilisatrices et charge militaire faisant application |
US5203844A (en) * | 1989-10-05 | 1993-04-20 | Leonard Byron P | Multiple payload/failure mode launch vehicles |
US5565647A (en) * | 1991-05-24 | 1996-10-15 | Giat Industries | Warhead with sequential shape charges |
US5271330A (en) * | 1991-09-27 | 1993-12-21 | General Dynamics Corporation, Convair Division | Oxygen enhanced cruise missile weapon system |
US5817969A (en) * | 1994-08-26 | 1998-10-06 | Oerlikon Contraves Pyrotec Ag | Spin-stabilized projectile with payload |
US5507231A (en) * | 1994-10-13 | 1996-04-16 | Thiokol Corporation | Solid fuel launch vehicle destruction system and method |
FR2740212B1 (fr) | 1995-10-20 | 1997-12-05 | Giat Ind Sa | Charge explosive generatrice de noyau |
FR2741142B1 (fr) | 1995-11-13 | 1998-01-02 | Giat Ind Sa | Charge generatrice de noyau ayant une tenue a l'acceleration amelioree |
DE59704496D1 (de) * | 1996-03-08 | 2001-10-11 | Diehl Stiftung & Co | Verfahren und Einrichtung zum Verbringen einer grosskalibrigen Nutzlast über ein Einsatzgelände |
US6279482B1 (en) * | 1996-07-25 | 2001-08-28 | Trw Inc. | Countermeasure apparatus for deploying interceptor elements from a spin stabilized rocket |
-
2000
- 2000-07-26 FR FR0009813A patent/FR2812384B1/fr not_active Expired - Fee Related
-
2001
- 2001-07-17 AU AU2001279875A patent/AU2001279875A1/en not_active Abandoned
- 2001-07-17 AT AT01958138T patent/ATE282814T1/de not_active IP Right Cessation
- 2001-07-17 DE DE60107181T patent/DE60107181T2/de not_active Expired - Fee Related
- 2001-07-17 EP EP01958138A patent/EP1192406B1/fr not_active Expired - Lifetime
- 2001-07-17 US US10/069,021 patent/US6718883B2/en not_active Expired - Fee Related
- 2001-07-17 WO PCT/FR2001/002317 patent/WO2002008684A1/fr active IP Right Grant
Also Published As
Publication number | Publication date |
---|---|
WO2002008684A1 (fr) | 2002-01-31 |
DE60107181T2 (de) | 2005-12-08 |
US20020134271A1 (en) | 2002-09-26 |
DE60107181D1 (de) | 2004-12-23 |
AU2001279875A1 (en) | 2002-02-05 |
FR2812384A1 (fr) | 2002-02-01 |
ATE282814T1 (de) | 2004-12-15 |
EP1192406A1 (fr) | 2002-04-03 |
US6718883B2 (en) | 2004-04-13 |
FR2812384B1 (fr) | 2002-12-06 |
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