EP1192406A1 - Device for neutralising a payload - Google Patents
Device for neutralising a payloadInfo
- Publication number
- EP1192406A1 EP1192406A1 EP01958138A EP01958138A EP1192406A1 EP 1192406 A1 EP1192406 A1 EP 1192406A1 EP 01958138 A EP01958138 A EP 01958138A EP 01958138 A EP01958138 A EP 01958138A EP 1192406 A1 EP1192406 A1 EP 1192406A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- payload
- rocket
- vector
- charge
- neutralization device
- 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.)
- Granted
Links
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 allowing the neutralization of a payload transported by a vector.
- the satellites which are carried by ballistic rockets generally comprise extremely toxic and explosive liquid propellants (hydrazine, nitrogen peroxide). It is essential to destroy these propellants in the event of an incident in order to avoid the fall to the ground of a large quantity of these materials. Concretely, the casing of the propellants is destroyed so as to release the propellants. These destroy themselves by reacting to each other on contact with each other and on contact with the atmosphere.
- the weapon requires the production of explosive projectiles equipped with security systems and a delayed release.
- the weapon is also a complex mechanism susceptible to failure when the rocket launches.
- the hollow charge jets have a reduced efficiency against propellants with liquid propellants.
- the jet is consumed quickly by the liquid and the diameter of the drainage holes made is small (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 in the same places and the vector must be modified in depth to allow the installation of a new neutralization system.
- the neutralization device makes it possible to ensure in a simple and reliable manner the destruction of a payload carried by a vector.
- the subject of the invention is a device for neutralizing a payload transported by a vector, such as a rocket, characterized in that it comprises at least one explosive charge generating a nucleus, charge made integral with the vector by means of positioning ensuring an orientation of its direction of action towards the payload.
- the positioning means may be adjustable so as to allow adaptation of the neutralization device to different structures and / or locations of the payload.
- the positioning means may also be fixed.
- the device may include at least two explosive charges generating a nucleus.
- the core-generating charge (s) will preferably have a caliber greater than 50 mm.
- FIG. 1 schematically represents a partial view of a rocket carrying a satellite and equipped with a neutralization device according to the invention
- FIG. 2 is a view of the same rocket carrying a satellite of different internal architecture.
- a vector 1 such as a ballistic rocket (of which only the head is represented) comprises 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 the trajectory by the rocket at a given altitude ensuring its putting into Earth orbit.
- the means ensuring the opening of the warhead and the release of the satellite are not shown here and they do not form part of the present invention.
- Satellite 4 contains one or more tanks of liquid propellants.
- the satellite shown in Figure 1 has two tanks ⁇ a and ⁇ b superimposed and arranged substantially at the axis 7 of the rocket.
- the reservoirs 6a, 6b are connected to a nozzle 8.
- means are provided for neutralizing the propellants contained in the reservoirs 6a, 6b by rupturing their reservoirs thus allowing their release.
- the neutralization means comprise two explosive charges 9a, 9b which generate the nucleus.
- Each load 9 is made integral with the rocket 1 by positioning means 10a, 10b which make it possible to orient the direction of action 11a, 11b towards the payload 4.
- a nucleus-generating charge is well known to those skilled in the art. We can for example consult the patents FR2627580, FR2740212 and FR2741142 which describe a such charge. It comprises an explosive charge 13 placed in an envelope 14 and to which a metal coating 12 in the form of a cap is applied.
- the explosive charge 13 is initiated by a detonator means 15 which is connected to a control means 16.
- the positioning means 10a, 10b which are described here are designed so as to give one or two degrees of freedom to the casing 14 of the load which they support.
- positioning means comprising a 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 means of a base 19 and it can therefore itself be tilted relative to the stirrup 17.
- each load 9 makes it possible to give each load 9 an optimal orientation which will be adapted as a function of the nature and structure of the payload 4. Concretely, each load will be inclined in such a way that its direction of action 11 meets one of the tanks 6 of satellite 4.
- stirrup 17 can be fixed relative to the base 20, the only degree of freedom of the load will then be its tilting relative to the stirrup 17.
- the load 9a thus has a direction of action 11a which is inclined at an angle ⁇ relative to the direction 18a parallel to the axis of the rocket 1. This direction of action 11a meets the upper reservoir ⁇ b.
- the load 9b has an action direction 11b which is inclined at an angle ⁇ relative to the direction 18b parallel to the axis of the rocket 1. This action direction 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 given time.
- This control means may advantageously consist of a part of the rocket's control / guidance electronics.
- the initiation of the charge (s) 9 will be caused on the trajectory at a given instant. This initiation can advantageously be remotely controlled from the ground in the event of detection of a serious event (rupture of the rocket, loss of trajectory).
- the initiation may also be triggered automatically by the rocket electronics in the event of loss of the ground link (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. Following their initiation, they generate a core of homokinetic metal of approximately 100 g and which is driven at a speed of approximately 2000 m / s.
- Such a core is stable up to distances of the order of 25 m, ie distances much greater than the maximum distance separating a load from one of the propellant tanks.
- the tanks 6 are therefore perforated by the cores thus generated. This results in a dynamic overpressure which explodes 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 ensures reliable destruction of the payload despite the distance.
- the device according to the invention therefore makes it possible, with a simple structure, compact and easy to integrate into the rocket, to ensure the safe destruction of the payload and in particular of the liquid propellants contained in the tanks 6.
- the reliability of the device is greater to that of existing devices and at lower cost.
- FIG. 2 shows a rocket 1 identical to that previously described but carrying a satellite 4 which has a different structure.
- This satellite comprises two reservoirs 6a, 6b of propellants which are arranged parallel to one another and on either side of the axis 7.
- the positioning means 10a and 10b make it possible to modify the orientations of the directions of action 11a and 11b of the charges so that each direction of action encounters a reservoir 6a or 6b.
- 11b are inclined by the same angle ⁇ relative to the directions 18a / 18b defined by the stirrups 17 and parallel to the axis 7 of the rocket 1.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Small-Scale Networks (AREA)
- Position Fixing By Use Of Radio Waves (AREA)
- Monitoring And Testing Of Transmission In General (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Selective Calling Equipment (AREA)
- Monitoring And Testing Of Nuclear Reactors (AREA)
- Radio Relay Systems (AREA)
- Toys (AREA)
- Catching Or Destruction (AREA)
Abstract
Description
Claims
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0009813 | 2000-07-26 | ||
FR0009813A FR2812384B1 (en) | 2000-07-26 | 2000-07-26 | DEVICE FOR NEUTRALIZING A PAYLOAD |
PCT/FR2001/002317 WO2002008684A1 (en) | 2000-07-26 | 2001-07-17 | Device for neutralising a payload |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1192406A1 true EP1192406A1 (en) | 2002-04-03 |
EP1192406B1 EP1192406B1 (en) | 2004-11-17 |
Family
ID=8852948
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP01958138A Expired - Lifetime EP1192406B1 (en) | 2000-07-26 | 2001-07-17 | Device for neutralising a payload |
Country Status (7)
Country | Link |
---|---|
US (1) | US6718883B2 (en) |
EP (1) | EP1192406B1 (en) |
AT (1) | ATE282814T1 (en) |
AU (1) | AU2001279875A1 (en) |
DE (1) | DE60107181T2 (en) |
FR (1) | FR2812384B1 (en) |
WO (1) | WO2002008684A1 (en) |
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 |
EP2174091A4 (en) * | 2007-07-30 | 2013-04-03 | Blake K Thomas | Shaped charge fuse booster system for dial lethality in reduce collateral damage bombs (rcdb) that include penetrating warheads of warheads with high explosives that are difficult to ignite |
DE102012110450B4 (en) * | 2012-10-31 | 2014-07-17 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Object for a mission into space |
DE102016219627A1 (en) * | 2016-10-10 | 2018-04-12 | Bayerische Motoren Werke Aktiengesellschaft | UNMANUFACTURED AIRCRAFT, ENERGY STORAGE MODULE AND METHOD FOR CONTROLLING AN UNMANUFACTURED AIRCRAFT |
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 (en) * | 1970-07-17 | 1972-08-15 | Oerlikon Buehrle Ag | Bullet with a bullet jacket |
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 (en) * | 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 (en) * | 1980-12-23 | 1982-07-22 | Dynamit Nobel Ag, 5210 Troisdorf | COMBAT HEAD WITH SECONDARY BODIES AS A PAYLOAD |
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 (en) | 1988-02-18 | 1993-02-19 | France Etat Armement | PROCESS FOR OBTAINING A CORE COMPRISING STABILIZING FINS AND APPLIED MILITARY LOAD |
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 (en) | 1995-10-20 | 1997-12-05 | Giat Ind Sa | EXPLOSIVE CHARGE GENERATOR OF CORE |
FR2741142B1 (en) | 1995-11-13 | 1998-01-02 | Giat Ind Sa | CORE GENERATOR LOAD HAVING IMPROVED ACCELERATION RESISTANCE |
EP0794405B1 (en) * | 1996-03-08 | 2001-09-05 | Diehl Stiftung & Co. | Method and device for dispersing a large caliber payload above a target |
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/en not_active Expired - Fee Related
-
2001
- 2001-07-17 DE DE60107181T patent/DE60107181T2/en not_active Expired - Fee Related
- 2001-07-17 AT AT01958138T patent/ATE282814T1/en not_active IP Right Cessation
- 2001-07-17 EP EP01958138A patent/EP1192406B1/en not_active Expired - Lifetime
- 2001-07-17 WO PCT/FR2001/002317 patent/WO2002008684A1/en active IP Right Grant
- 2001-07-17 US US10/069,021 patent/US6718883B2/en not_active Expired - Fee Related
- 2001-07-17 AU AU2001279875A patent/AU2001279875A1/en not_active Abandoned
Non-Patent Citations (1)
Title |
---|
See references of WO0208684A1 * |
Also Published As
Publication number | Publication date |
---|---|
FR2812384B1 (en) | 2002-12-06 |
FR2812384A1 (en) | 2002-02-01 |
DE60107181D1 (en) | 2004-12-23 |
WO2002008684A1 (en) | 2002-01-31 |
ATE282814T1 (en) | 2004-12-15 |
DE60107181T2 (en) | 2005-12-08 |
US6718883B2 (en) | 2004-04-13 |
EP1192406B1 (en) | 2004-11-17 |
AU2001279875A1 (en) | 2002-02-05 |
US20020134271A1 (en) | 2002-09-26 |
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