EP1496333B1 - Verfahren und Vorrichtung zur Zerstörung von Festtreibstoffmotoren - Google Patents

Verfahren und Vorrichtung zur Zerstörung von Festtreibstoffmotoren Download PDF

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Publication number
EP1496333B1
EP1496333B1 EP04291225A EP04291225A EP1496333B1 EP 1496333 B1 EP1496333 B1 EP 1496333B1 EP 04291225 A EP04291225 A EP 04291225A EP 04291225 A EP04291225 A EP 04291225A EP 1496333 B1 EP1496333 B1 EP 1496333B1
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EP
European Patent Office
Prior art keywords
propellant
sections
solid
destroying
section
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Expired - Lifetime
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EP04291225A
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English (en)
French (fr)
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EP1496333A1 (de
Inventor
Marie Gaudre
Eric Marchand
Jean-Michel Tauzia
Jean-Louis Trichard
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Safran Ceramics SA
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SNPE Materiaux Energetiques SA
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B33/00—Manufacture of ammunition; Dismantling of ammunition; Apparatus therefor
    • F42B33/06—Dismantling fuzes, cartridges, projectiles, missiles, rockets or bombs

Definitions

  • the present invention is in the field of solid propellant engines. It relates more particularly to the destruction of reformed engines including engines that have reached the limit of operational use and are removed from service.
  • a solid propellant engine essentially comprises a hollow cylindrical envelope inside which is placed at least one block of solid propellant, to simplify we will say thereafter a block of propellant.
  • One end of the envelope is closed by a dome and the opposite end by a nozzle; the dome and the nozzle will be considered as part of the envelope.
  • the engines considered here are engines for which the solid propellant block has been secured to the envelope and can not be removed simply from the envelope. It is essentially engine called "molded-glued" for which the block of propellant is molded and glued during the manufacture of the engine in the envelope suitably prepared for this purpose. We will assimilate to this type of engine those for which the propellant block, prepared elsewhere, is introduced and wedged irreversibly in the envelope, this setting being wanted or accidental. We will retain the term glued molded motor to refer to the motors treated in this invention.
  • the destruction of an engine consists in first putting it in a state such that it can not perform its propulsion function and then in a second time to separate the envelope and the propellant to treat them separately, given that only the propellant presents a pyrotechnic risk that requires precautions and special conditions in its treatment for the disposal or recycling of certain elements.
  • the process and the destruction facility must be able to operate at a very high speed: it is therefore requested a process with simple and fast steps and a rustic installation.
  • US Patent 5,220,107 describes the fragmentation of a bare propellant block, that is to say not glued inside the casing of an engine, by cooling at very low temperature of the propellant block and using a grinder or a press to break it up.
  • US Pat. No. 5,025,632 describes the extraction of propellant from a molded-glued motor with a central channel using at least one jet of cryogenic liquid. This method of destruction derived from the "water knife”, is very long and does not meet the need for a large pace of work. Moreover, it is potentially dangerous because one works on a whole engine.
  • US Pat. No. 5,552,093 describes the extraction of the propellant from a molded-on engine which has been cooled by immersion in liquid nitrogen: the block is broken up by shocks applied in particular to the propellant block.
  • the application of shocks on even cooled propellant remains potentially dangerous and this danger is increased by the fact that one operates, again, on a whole engine.
  • fragments get stuck in the envelope and require additional manipulations to extract them from the envelope.
  • the present invention aims to solve the difficulties that are not taken into account by these various methods when it is necessary to design a destruction process at a very high rate and this without unreasonably increasing the parallel operating facilities to destroy a large number of engines.
  • the present method therefore relates to solid propellant engines for which the propellant block is integral with the casing; the engines that enter this process do not include an ignition device: it is removed and removed from the engine in a preparatory operation before delivery of the engines to the destruction site.
  • the motor casing is either all-metal or composite material.
  • the propellant block has a central channel that extends over its entire length or only a part: in the latter case the portion of the side opposite the nozzle has no channel.
  • the propellant block can be possibly full over its entire length, that is to say does not have a central channel.
  • the sections containing propellant have a length ratio "1" of the section on outer diameter "d" of the section less than or equal to 2.5, (1 / d ⁇ 2.5).
  • the method uses several jets arranged in parallel and prepositioned with respect to the motor to cut the different sections in a single operation.
  • the engine is immersed in the same liquid as that used for the jets; most commonly the liquid used is water.
  • the liquid and the shell and propellant chips resulting from the cutting operations are regularly removed for suitable treatments.
  • the sections containing propellant are, using appropriate handling means, transported and immersed in a bath of a neutral cryogenic liquid vis-a-vis the stub components; generally the cryogenic liquid used is liquid nitrogen.
  • the target end temperature for the engine section is at least 20 ° C lower than the glass transition temperature range of the propellant binder.
  • a temperature of between about -100 ° C. and about -80 ° C. is targeted for the propellant and the casing.
  • the sufficiently cooled sections are directed to a station to extract the propellant, weakened by the cold.
  • the propellant is extracted by imposing slight deformations on the envelope: these deformations remain in the elastic domain of deformation of the envelope at this temperature.
  • the propellant breaks into rather large fragments, typically about the size of a closed fist.
  • the section was arranged vertical axis and the propellant fragments fall by gravity and are recovered either on a conveyor belt or in a receptacle containing water to render the propellant fragments inert.
  • the engine section having a relatively small length relative to its diameter, 1 / d ⁇ 2.5, the propellant fragments do not get stuck in the envelope.
  • the cooled engine section vertical axis and opening of larger diameter directed downwards, is disposed between a stop and a cylinder head.
  • the cylinder axis is horizontal and perpendicular to the axis of the engine section. The displacement of the cylinder head is calculated so that the deformation of the envelope remains in the field of elastic deformation of the envelope.
  • the cooled engine section is driven between two rolls rolling mill, these rollers are appropriately spaced to impose, again, a deformation which remains in the field of elastic deformation of the envelope.
  • the rollers slightly drive and deform the engine section from the bottom of said section to its upper part which facilitates the extraction of propellant fragments by gravity.
  • the empty envelope section optionally includes some residual traces of small thickness of propellant remained glued at certain points of the interior of the envelope.
  • the empty section is retrieved for a subsequent step of deactivating such residues.
  • this deactivation is done in a closed chamber which includes burners whose flames burn the traces of propellant.
  • the fumes are folded down and washed with water, so no gaseous effluents are released into the atmosphere. Wash waters are collected for treatment and decontamination according to known methods.
  • the deactivation of any propellant residues adhering to the interior of the casing is done by soaking the empty casing section in said liquid.
  • the oxidizing charge is dissolved in the liquid, there remains on the inner wall of the casing only matrix flakes consisting of binder and combustible load without pyrotechnic danger.
  • the kinetics of diffusion of the oxidizing charge and of its dissolution in the liquid is advantageously accelerated by heating the liquid.
  • the liquid containing the oxidizing charge in solution is recovered for further processing by known methods. Frequently the oxidizing charge is ammonium perchlorate and the liquid used to dissolve it is water.
  • a section containing propellant is relatively short and will not be propulsive in case of accidental ignition: it will not have disordered and untimely movements that can spread the incident to an entire station.
  • precautions must be taken with regard to thermal effects.
  • the fragments of propellants obtained after the elastic deformation of the envelope are generally quite large: a few centimeters, about the size of a closed fist. To move to the next stage of treatment of the propellant, it is necessary to proceed to a finer grinding of said fragments so as to obtain grains of propellant, grains whose dimensions are of the order of at most one centimeter and preferably a few millimeters.
  • This grinding can be done in different ways but preferably using knife mills and advantageously the grinding is done under water spray.
  • the next step of treatment of the propellant, thus granulated is the dissolution of the oxidizing charge in a suitable liquid, for example water when the oxidizing charge is perchlorate.
  • the liquid which contains the oxidizing charge in solution is separated from the solid residue; the latter comprises the binder and the possible combustible charge, it does not present a pyrotechnic risk.
  • the solid residue is either directly landfilled in a landfill or upgraded to extract the metal fuel charge after known and conventional treatments for industrial waste.
  • the liquid is either treated by biodegradation processes such as that described in patent FR 2 788 055 or its corresponding US Pat. No. 6,328,891 for degrading the oxidizing charge, or treated to enhance said oxidizing charge and recrystallize it by known methods.
  • Figure 1 schematically shows an installation for carrying out the method.
  • Figure 2 is a basic plan of a propellant fragmentation plant after cooling the section.
  • Figure 1 shows schematically the succession of different positions for the implementation of the method.
  • Figure 1a) in plan Figure 1b) in profile.
  • the engines are brought to a storage workshop, identified for the traceability of the operation and are placed one by one on a conveyor and are introduced, one by one, by a first airlock in the installation.
  • the engine is immersed in a tank containing water and positioned on a bench rotating relative to a ramp of several jets high pressure suitably arranged: the engine is cut into sections.
  • the high-pressure ramps are made with standard equipment such as DIGITAL CONTROL, feeding high-pressure jets, about 300 MPa with two pumps.
  • DIGITAL CONTROL standard equipment
  • feeding high-pressure jets about 300 MPa with two pumps.
  • the other sections 10 of the engine are hooked to another conveyor and pass, through an airlock, to the cooling station 2 by immersion in the cryogenic liquid: this station essentially comprises a bath of great length in which are immersed several suitably spaced sections; the sections move as the process progresses and thus stay in the liquid for a long time, which favors their cooling down to temperatures of about -100 ° C.
  • the suitably oriented section is deformed by compression of the envelope: the propellant, weakened, cracked and cracked by cooling is fragmented. The fragments are recovered for further processing.
  • the empty propellant casing sections are directed to a residue deactivation station 6.
  • the deactivation of the sections is, in this example, made by immersing said sections in a tank containing water.
  • the propellant fragments are directed to a fine grinding station 4 using knife mills with water spray.
  • High-performance standard devices with some security adaptations, can process up to 1000kg / hour of propellant.
  • the grains obtained after fine grinding are introduced to the dissolution station 5 in a large volume reactor, said reactor is perfectly stirred and thermoregulated to increase the kinetics of dissolution of the oxidizing charge in water.
  • FIG. 2 schematically represents views a) of profile and b) in plan of an apparatus 11 for extracting the propellant from a section 10 of cooled engine.
  • the apparatus essentially comprises a rectangular frame 13, anchored on four legs with a stop 14 on one side of the frame and a hydropneumatic jack 15 fixed on the opposite side; the cylinder is arranged horizontally.
  • the motor section 10 to be treated is hooked, vertical axis to a handling means shown schematically by reference 12. Said handling means brings the motor section 10 between the stop 14 and the cylinder rod 16.
  • the cylinder rod 16 is supported on the envelope of the engine section about one-third of its height from the bottom of the section.
  • the displacement of the jack rod 16 is determined to impose a deformation to the envelope which remains in the elastic domain of the deformations thereof and to break up the cold propellant and separate it from the envelope.
  • a receptacle 17, containing water to render inert the propellant fragments which fall by simple effect of gravity is placed under the engine section; said receptacle 17 is only shown in Figure 2a).
  • This device is placed in a suitable room with entry and exit locks and all servitudes necessary for remote operation.

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  • Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • General Engineering & Computer Science (AREA)
  • Processing Of Solid Wastes (AREA)
  • Transition And Organic Metals Composition Catalysts For Addition Polymerization (AREA)
  • Solid Fuels And Fuel-Associated Substances (AREA)
  • Drilling And Exploitation, And Mining Machines And Methods (AREA)
  • Disintegrating Or Milling (AREA)

Claims (12)

  1. Verfahren zur Zerstörung eines Festtreibstoffmotors, wobei der eingegossene und verklebte Motor im Wesentlichen aus einem Propergolblock und einer Ummantelung besteht und das Verfahren dadurch gekennzeichnet ist, dass es die folgenden Stufen umfasst:
    - der Motor wird im rechten Winkel zur Motorachse in Teilstücke (10) zerschnitten,
    - die Teilstücke (10), die kein Propergol enthalten, werden aus der weiteren Bearbeitung herausgenommen,
    - die Teilstücke (10), die Propergol enthalten, werden auf eine Temperatur gekühlt, die weit unter dem Bereich der Glasübergangstemperatur des Bindemittels des Propergols liegt.
    - das Propergol wird zerstückelt und von der Ummantelung jedes Teilstücks (10) abgetrennt, wobei das Teilstück (10) von dem in ihm enthaltenen Propergol befreit wird,
    - die leeren Teilstücke (10) der Ummantelung werden für eine ergänzende Desaktivierungsstufe der Rückstände gesammelt,
    - das zerstückelte Propergol wird für eine Nachbehandlung gesammelt.
  2. Verfahren zur Zerstörung eines Festtreibstoffinotors, nach Anspruch 1, dadurch gekennzeichnet, dass das Verhältnis von Länge zu Außendurchmesser der Propergol enthaltenden Teilstücke (10) geringer oder gleich 2,5 ist.
  3. Verfahren zur Zerstörung eines Festtreibstoffmotors nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass das Zerschneiden des Motors mittels eines Flüssigkeitsstrahls unter Hochdruck erfolgt.
  4. Verfahren zur Zerstörung eines Festtreibstoffmotors nach Anspruch 3, dadurch gekennzeichnet, dass der Motor für das Zerschneiden in einen Behälter getaucht wird, der die gleiche Flüssigkeit enthält, die verwendet wird, um eine Rampe mit mehreren zum Motor angeordneten Hochdruckstrahlen zu beschicken.
  5. Verfahren zur Zerstörung eines Festtreibstoffmotors nach jedem der Ansprüche 1 bis 4 dadurch gekennzeichnet, dass die Propergol enthaltenden Teilstücke (10) durch Eintauchen in eine kälteerzeugende Flüssigkeit gekühlt werden.
  6. Verfahren zur Zerstörung eines Festtreibstoffmotors nach Anspruch 5, dadurch gekennzeichnet, dass die kälteerzeugende Flüssigkeit flüssiger Stickstoff ist.
  7. Verfahren zur Zerstörung eines Festtreibstoffmotors nach Anspruch 5 oder 6, dadurch gekennzeichnet, dass das Teilstück (10) auf eine Temperatur zwischen ungefähr -100° C und ungefähr - 80° C gekühlt wird.
  8. Verfahren zur Zerstörung eines Festtreibstoffmotors nach jedem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass die Ummantelung jedes gekühlten Teilstücks (10) durch Krafteinwirkungen elastisch verformt wird, um das Propergol zu zerstückeln, wobei die Bruchstücke in einem Behälter gesammelt werden.
  9. Verfahren zur Zerstörung eines Festtreibstoffmotors nach jedem der Ansprüche 1 bis 8, dadurch gekennzeichnet, dass jedes leere Teilstück (10) durch Verbrennen der Rückstandsspuren von Propergol desaktiviert wird unter Rückgewinnung und Reinigung der Abgase.
  10. Verfahren zur Zerstörung eines Festtreibstoffmotors nach jedem der Ansprüche 1 bis 8, dadurch gekennzeichnet, dass jedes leere Teilstück (10) durch Eintauchen des Teilstücks in eine das Oxidationsmittel auflösende Flüssigkeit desaktiviert wird.
  11. Anlage zur Zerstörung eines Festtreibstoffmotors, wobei der Motor im Wesentlichen aus einem Propergolblock besteht, der in einer Ummantelung verklebt ist, dadurch gekennzeichnet, dass sie folgendes umfasst:
    - eine Vorbereitungsstation für die Motoren, die durch eine Schleuse verbunden ist mit:
    - einer Station für das Zerschneiden (1) des Motors in Teilstücke (10),
    - einer Station für die Kühlung (2) der Propergol enthaltenden Teilstücke (10),
    - mindestens einer Station für die Zerstückelung(3) des Propergols unter Rückgewinnung der Bruchstücke des Propergols und der leeren Teilstücke (10) der Ummantelung,
    - einer Station für die Desaktivierung (6) der Propergolrückstände der leeren Teilstücke (10) der Ummantelung.
  12. Anlage zur Zerstörung eines Festtreibstoffmotors nach Anspruch 11, dadurch gekennzeichnet, dass sie folgendes umfasst:
    - eine Station für die Feinzerkleinerung(4) der Propergolrückstände,
    - eine Station für die Auflösung (5) des Sauerstoffträgers des fein zerkleinerten Propergols.
EP04291225A 2003-07-10 2004-05-13 Verfahren und Vorrichtung zur Zerstörung von Festtreibstoffmotoren Expired - Lifetime EP1496333B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0308474A FR2857357B1 (fr) 2003-07-10 2003-07-10 Procede et installation de destruction de moteurs a propergol solide
FR0308474 2003-07-10

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EP1496333A1 EP1496333A1 (de) 2005-01-12
EP1496333B1 true EP1496333B1 (de) 2006-08-16

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US (1) US7249553B1 (de)
EP (1) EP1496333B1 (de)
AT (1) ATE336707T1 (de)
DE (1) DE602004001938T2 (de)
ES (1) ES2270306T3 (de)
FR (1) FR2857357B1 (de)

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DE102004034784B4 (de) * 2004-07-09 2009-08-27 Spreewerk Lübben GmbH Verfahren und Vorrichtung zur Delaborierung von explosivstoffhaltigen Körpern
DE102008041973A1 (de) * 2008-09-10 2010-03-11 Grv Luthe Kampfmittelbeseitigung Gmbh Verfahren und Vorrichtung zur Delaborierung von Munition mit brennbarem Inhalt und zur Rückgewinnung des Munitionshüllenmaterials
JP5436672B2 (ja) * 2009-08-21 2014-03-05 ダイナセーフ インターナショナル エービー ロケットモーターの安全な破壊のための閉鎖容器装置
FR2976659B1 (fr) 2011-06-15 2013-07-19 Roxel France Procede alternatif de demantelement de moteurs a propergol solide
CN110030886B (zh) * 2019-05-22 2024-03-22 中国人民解放军32181部队 火箭炮弹推进剂自动倒出装置及火箭炮弹分解设备
CN110006298B (zh) * 2019-05-22 2023-10-13 中国人民解放军32181部队 火箭炮弹自动化分解作业线

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Publication number Publication date
ATE336707T1 (de) 2006-09-15
DE602004001938T2 (de) 2007-03-08
ES2270306T3 (es) 2007-04-01
FR2857357B1 (fr) 2005-08-19
FR2857357A1 (fr) 2005-01-14
DE602004001938D1 (de) 2006-09-28
EP1496333A1 (de) 2005-01-12
US20070161844A1 (en) 2007-07-12
US7249553B1 (en) 2007-07-31

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