EP2557389A2 - Composant structurel pour un système de corps volant opérationnel - Google Patents

Composant structurel pour un système de corps volant opérationnel Download PDF

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Publication number
EP2557389A2
EP2557389A2 EP20120005609 EP12005609A EP2557389A2 EP 2557389 A2 EP2557389 A2 EP 2557389A2 EP 20120005609 EP20120005609 EP 20120005609 EP 12005609 A EP12005609 A EP 12005609A EP 2557389 A2 EP2557389 A2 EP 2557389A2
Authority
EP
European Patent Office
Prior art keywords
metal foam
missile
foam body
component
structural component
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
Application number
EP20120005609
Other languages
German (de)
English (en)
Other versions
EP2557389B8 (fr
EP2557389A3 (fr
EP2557389B1 (fr
Inventor
Thomas Dr. Klaffert
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.)
MBDA Deutschland GmbH
Original Assignee
LFK Lenkflugkoerpersysteme GmbH
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 LFK Lenkflugkoerpersysteme GmbH filed Critical LFK Lenkflugkoerpersysteme GmbH
Priority to PL12005609T priority Critical patent/PL2557389T3/pl
Publication of EP2557389A2 publication Critical patent/EP2557389A2/fr
Publication of EP2557389A3 publication Critical patent/EP2557389A3/fr
Application granted granted Critical
Publication of EP2557389B1 publication Critical patent/EP2557389B1/fr
Publication of EP2557389B8 publication Critical patent/EP2557389B8/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F42B12/72—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the material

Definitions

  • the invention relates to a mechanical structural component for an operational missile system, to a method for producing the structural component in connection with the use of metal foam for the structural component.
  • structural components represent weight, stiffness and accuracy-relevant components for integrated drive kinematics, which can also decisively influence the integration effort during assembly of the missile.
  • a first aspect of the invention relates to a structural component for a missile, in particular for an operational missile system.
  • the missile may be an unmanned missile.
  • the missile may have a drive, but need not include a drive.
  • missile in the following with the English term “missile” which can describe a rocket, a cruise missile and a projectile.
  • a missile in this sense can be designed to detect a potential target, to head for this goal and / or to develop a desired effect there.
  • the missile may include means and devices to perform at least one of these tasks independently. It is also possible that the missile is remotely controlled at least temporarily.
  • the missile may be a military missile, so may be used to combat a target.
  • the missile may comprise an explosive device and / or be designed for single use.
  • the missile is used for reconnaissance purposes and / or returns to its launch site.
  • a structural component may be a component of the missile which serves for mechanical support, mechanical vibration damping, electrical ground connection, electromagnetic shielding, as heat sink and / or for thermal shielding of at least one further component of the missile.
  • This further component may include, for example, the drive, the controller, and / or the payload of the missile. It is also possible that another component is another structural component.
  • a structural component may comprise at least one mechanical interface for a further component, via which the further component is mechanically supported by the structural component.
  • a structural component can essentially form the complete support structure of the missile or at least one segment of the missile.
  • the structural component comprises a metal foam body.
  • the metal foam body can serve for mechanical stiffening and / or mechanical damping and / or electrical shielding or ground connection of the structural component or the missile.
  • a metal foam can be described as a solid metal body, which has randomly distributed cavities (or pores) in its interior, the volume of which accounts for most of the volume filled by the solid.
  • the metal for example, aluminum or an aluminum alloy can be used.
  • metal foam can provide numerous benefits in terms of both the manufacture of the missile and the missile itself.
  • the structural components can be compared with the construction of bone, which have high strength with low weight.
  • Metal foam is usually easy to process and to the desired shape. Even complicated shaped parts can be produced by foaming a corresponding shape and possibly by a subsequent mechanical finishing. In combination with the low material consumption thus the total piece costs of missiles, especially for large quantities, can be reduced.
  • inner and outer contours of the missile structures can be made easier without gaining weight be, resulting in a manufacturability with reduced tooling costs.
  • the molds can be made simpler.
  • the mechanical interfaces to other components can be redesigned due to the use of metal foam, which can also lead to further cost reduction.
  • connections to other components or components of the missile can be created with foamed inlays and large-area adhesive surfaces.
  • Another aspect of the invention relates to a use of metal foam for a structural component of a missile or the use of metal foam in a structural component of a missile.
  • the metal foam body comprises closed-cell metal foam.
  • closed cell metal foam a dense (i.e., liquid and gas impermeable) metal foam body having smooth surfaces can be provided.
  • the pores are mostly not in communication with each other.
  • the metal foam body can be constructed like a bone in this case.
  • the metal foam body may comprise open-pored metal foam.
  • the pores can be largely crosslinked with each other.
  • the metal foam body can thus be constructed like a sponge.
  • the structural component with an outer surface forms an outer portion of the missile.
  • a surface of the structural component may form an outer surface of the missile.
  • Such outer or inner boundary surfaces of the foam body may additionally be provided by a (non-bearing) coating or thin-walled parts adhering thereto (such as sheet metal parts, pipes, etc.) and stiffen.
  • the missile may for example be at least partially constructed of segments of metal foam that provide the inner support structure and the outer shell of the missile.
  • the outer surface may form part of the shell or the outer skin of the missile.
  • the structural component can provide struts inside the missile.
  • a part or the entire integral structure of the missile may be formed with the metal foam.
  • the missile may comprise a plurality of segments.
  • the support structure of the missile or at least the segment may consist essentially entirely of metal foam. In this way, it is possible to dispense almost completely with further supporting structures in addition to the metal foam.
  • the metal foam body is formed by machining a metal foam blank.
  • the metal foam body can be produced within a (reusable mold) and can be partially post-machined after solidification. Especially with closed-pore metal foam, a subsequent processing by changing the surface or by the visibility of the pores can be seen.
  • the metal foam body is formed within a foaming mold or by foaming a mold. Possibilities for forming metal foam are described below.
  • a metal powder can be mixed with a blowing agent and then compacted into semi-finished products, which are poured into a mold and liquefied by heating. The propellant gasses in the liquid phase and creates the voids that remain after solidification of the metal.
  • the metal foam body has a first density at at least one first location and a second density that differs from the first density at at least one second location.
  • the bulk density of the semifinished products from this starting material and / or the structure of the casting mold can be achieved via the composition of the starting material, so that the foaming density in places via the metering of the blowing agent or via the locally introduced mass of compacted semi-finished products (according to bulk density) at the first Produces more gas than at a second location, which in the first place larger pores and the density of the metal foam at this point decreases.
  • the metal foam body may have a closed shell with a porous core, which has a density distribution corresponding to the mechanical load, as it is known from the bone structure.
  • the structural component comprises at least one component of the missile that completely or partially into the metal foam body foamed or enclosed.
  • Several components at the same time can be foamed into the metal foam. In this way, complicated support structures for the component can be completely eliminated.
  • the mechanical connection of several components can be realized in a simple manner.
  • the structural component comprises at least one insert (also called an inlay), which is connected to the metal foam body and which serves for fastening a further component of the missile.
  • the insert can be foamed during the production of the metal foam body or can be glued into a corresponding recess of the metal foam body.
  • Such inserts can form reference and contact surfaces and at the same time form elements such as threads, adhesive surfaces, etc. record.
  • Another aspect of the invention relates to a method for producing a structural component of a missile with metal foam.
  • a metal foam body of the structural component can be formed by machining a metal foam blank.
  • the metal foam body can also be produced in the desired shape (for example by forming the metal foam body contour corresponding to the mold to be foamed out) and then optionally post-processed.
  • a plurality of metal foam bodies can be connected or foamed together by means of other methods within a common mold. In particular mechanically processed foam surfaces can form ideal conditions for solid potting to be integrated components by their open porosity.
  • the method comprises the steps of providing a hollow body blank and reshaping the hollow body blank by means of a hydroforming process to form a hollow body with a desired contour, which can represent an outer skin and / or inner skin of the missile.
  • a desired contour which can represent an outer skin and / or inner skin of the missile.
  • This is also a bulkhead, z. B. as thermal protection against an engine duct, feasible.
  • a deliberately introduced, thermal bias for selectively influencing the thermal expansion and deformation properties of the later structural component can be generated.
  • the method comprises the steps of coating at least one inner surface of a hollow body or bodies with an adhesive layer, for example nickel, and forming the metal foam body by foaming the hollow body.
  • the casting mold can be a later component of the missile. It is also possible that a hollow body is foamed, which then forms an inner contour of the metal foam body.
  • the structural component can be formed as a hybrid structure of a metal foam body and an example thin-walled hollow body. Due to the adhesion of the metal foam to nickel-plated surfaces, there is an almost unlimited possibility of expansion to hybrid structures in connection with thin-walled profiles, which can be attached and integrated in a kink-resistant and buckling-free manner. For this purpose, both outer and inner contours come into question, which can be produced by hydroforming process.
  • the method comprises the step of: lathering and / or foaming a component of the missile into the metal foam body.
  • a component of the missile For example, components of drive, Control and / or payload are connected in this way firmly with the support structure.
  • the method comprises the steps of coating the metal foam body with a coating for protecting outer surfaces, inner surfaces and / or interface surfaces of the missile.
  • the Fig. 1 shows an operational missile system 10 in the form of a cruise missile 10 with elevation and Leitruder 12, which has a substantially torpedo-shaped outer contour.
  • the cruise missile 10 is divided into a plurality of sections or segments 14a, 14b, 14c, 14d in the longitudinal direction, which can be manufactured separately from each other and finally connected to each other.
  • each of the segments 14a, 14b, 14c, 14 comprises a structural component 18a, 18b, 18c, 18d.
  • the structural component 18a comprises a metal foam body 20a, 20a ', in which a plurality of inserts 24 are incorporated, which have connecting elements such as a thread, an adhesive surface or a spring tongue.
  • a component 22a for example a camera system, is partially surrounded by the metal foam body 20a, 20a 'and connected via the inserts 24 to the metal foam body 20a, 20a'.
  • the part of the metal foam body 20a has a higher density than the part of the metal foam body 20a '.
  • a payload 22a such as an explosive device, may also be fastened in the metal foam body 20a, 20a '.
  • the structural component 18b comprises two metal foam bodies 20b, 20b '.
  • the tubular metal foam body 20b has been foamed, for example, in a recyclable form, the metal foam body 20b ', for example, cut out of a blank.
  • the metal foam bodies 20b, 20b ' were connected to each other and to a component 22b, for example a control computer and the resulting structural component 18b coated with a coating 28 which is to protect the missile 10 from the weather.
  • the individual metal foam bodies 20b, 20b ' may either be milled out of a metal foam blank or foamed in a reusable form. Thereafter, the two bodies 20b, 20b 'may be joined together (e.g. by gluing, soldering or welding) and coated with a coating 28.
  • the structural component 18c comprises a thin-walled tubular hollow body 26 in the interior of which a component 18c, for example a tank, is arranged.
  • the component 18 c is foamed into a metal foam body 20 c, which in turn was produced by foaming the hollow body 26.
  • the structural component 18d comprises a metal foam body 20d, which has been produced from a metal foam blank by reworking. Into the cylindrical opening in the metal foam body 20d, a member 22d such as an electromechanical adjusting system was inserted and bonded to the metal foam body 20d.
  • the electromechanical actuating system 22d can be foamed in metal foam analogously to 18c.
  • Metal foam can generally be made in the following manner: First, a starting material comprising a metal and a blowing agent is provided. Subsequently, the starting material is heated, wherein the metal is liquefied and the propellant releases a gas, so that pores are formed in the metal and the metal foam is formed.
  • the starting material can be placed in a mold and then heated. Also, the starting material may be first heated and then filled in liquid form into the mold. After solidification of the liquid metal, the pores remain in the metal.
  • the Fig. 3 shows a flowchart for a method for producing the structural component 18d from a blank, which is reworked.
  • a metal foam blank is provided, which in the present case may have substantially the shape of a cylinder.
  • the blank is machined, for example, by milling a cylinder opening and / or by removing material on the outside) to form the metal foam body 20d.
  • a step S14 the component 22d is inserted into the metal foam body 20d and glued.
  • a step S16 the outer surface of the metal foam body 20d is coated with a coating, for example to form an environmentally resistant outer surface.
  • the Fig. 3 shows a flowchart for a method for producing the structural component 18c by foaming.
  • a metal blank for example a pipe
  • a base component 26 is formed by hydroforming the metal blank.
  • hydroforming a blank is placed in a reusable form which, for example, in a tube, can form an internal cavity mold with two punches at the end. Thereafter, a pressure is built up on the (or in) the blank, so that the blank is applied to a surface of the mold.
  • the metal blank is subjected to high pressure in the interior, which presses it against the inside of the mold.
  • the base component 26 is coated on the inside with nickel.
  • a step S36 the component 22c is inserted into the base component 26.
  • a step S38 the component 22c is foamed in the base component 26, so that the metal foam body 20c is formed. Due to the nickel coating, the metal foam body connects to the base component 26.
  • the Fig. 3 shows a flowchart for a method for producing the structural component 18a by foaming or foaming.
  • a reusable form is provided.
  • the mold can be provided on its inner surfaces with a release agent.
  • a first quantity of primary material is arranged at a first position of the mold and a second quantity of primary material is arranged at a second position of the mold.
  • a step S54 the inserts 24 are arranged in the mold.
  • a step S56 the starting material is heated in the mold so that a metal foam 20a having a first pore size is formed at the first location and a metal foam 20a 'having a second pore size is formed at the second location.
  • a step S58 the reusable mold is removed after cooling the metal foam.
  • a step S60 the component 22a is inserted into the metal foam body 20a, 20a 'and the component 22a is connected to the metal foam body 20a, 20a' via the inserts 24.
  • a step S62 the structural component 18a is coated with a coating 28.
  • the openings in the metal foam body 20a, 20a 'for the inserts 24 can also be milled in the metal foam body 20a, 20a' or provided during casting become.
  • the inserts 24 can then be glued into these openings in this case.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Laminated Bodies (AREA)
  • Powder Metallurgy (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Polyurethanes Or Polyureas (AREA)
EP12005609.8A 2011-08-06 2012-08-02 Composant structurel pour un système de corps volant opérationnel Active EP2557389B8 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL12005609T PL2557389T3 (pl) 2011-08-06 2012-08-02 Komponent strukturalny dla operacyjnego zespołu pocisku

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE201110109693 DE102011109693B3 (de) 2011-08-06 2011-08-06 Strukturkomponente für ein operationelles Flugkörpersystem

Publications (4)

Publication Number Publication Date
EP2557389A2 true EP2557389A2 (fr) 2013-02-13
EP2557389A3 EP2557389A3 (fr) 2015-05-13
EP2557389B1 EP2557389B1 (fr) 2018-04-11
EP2557389B8 EP2557389B8 (fr) 2018-05-23

Family

ID=46642329

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12005609.8A Active EP2557389B8 (fr) 2011-08-06 2012-08-02 Composant structurel pour un système de corps volant opérationnel

Country Status (4)

Country Link
EP (1) EP2557389B8 (fr)
DE (1) DE102011109693B3 (fr)
ES (1) ES2672391T3 (fr)
PL (1) PL2557389T3 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015013350A1 (de) * 2015-10-15 2017-04-20 Mbda Deutschland Gmbh Lenkflugkörper und Verfahren zum Herstellen eines Lenkflugkörpers
DE102015013349B4 (de) 2015-10-15 2023-05-17 Mbda Deutschland Gmbh Verfahren zum Betreiben eines Waffensystems

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3380382A (en) * 1966-07-20 1968-04-30 Army Usa Gun launched liquid rocket
US3674585A (en) * 1969-10-07 1972-07-04 Windecker Research Inc Method of making an aircraft wing structure
DE19912618C2 (de) * 1999-03-22 2002-06-27 Meleghy Hydroforming Gmbh & Co Bauteil mit partieller Verstärkung und Verfahren zu dessen Herstellung
GB2402196B (en) * 2003-05-29 2006-05-17 Rolls Royce Plc A laminar flow nacelle for an aircraft engine
DE10328047B3 (de) * 2003-06-23 2005-04-14 Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. Aus Metallschaumbausteinen aufgebautes Bauteil und Verfahren zu seiner Herstellung
DE102005037305B4 (de) * 2005-08-02 2007-05-16 Hahn Meitner Inst Berlin Gmbh Verfahren zur pulvermetallurgischen Herstellung von Metallschaumstoff und von Teilen aus Metallschaumstoff
DE102006056136A1 (de) * 2006-11-28 2008-05-29 Zoe Gmbh & Co. Kg Leichtbau-Formteil und entsprechendes Herstellungsverfahren
US8430029B2 (en) * 2008-01-31 2013-04-30 Bae Systems Information And Electronic Systems Integration Inc. Inertial delay fuse

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Also Published As

Publication number Publication date
EP2557389B8 (fr) 2018-05-23
EP2557389A3 (fr) 2015-05-13
ES2672391T3 (es) 2018-06-14
EP2557389B1 (fr) 2018-04-11
DE102011109693B3 (de) 2012-09-13
PL2557389T3 (pl) 2018-09-28

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