EP2455704A2 - Missile avec enveloppe extérieure couverte d'une couche ablative - Google Patents

Missile avec enveloppe extérieure couverte d'une couche ablative Download PDF

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Publication number
EP2455704A2
EP2455704A2 EP11008941A EP11008941A EP2455704A2 EP 2455704 A2 EP2455704 A2 EP 2455704A2 EP 11008941 A EP11008941 A EP 11008941A EP 11008941 A EP11008941 A EP 11008941A EP 2455704 A2 EP2455704 A2 EP 2455704A2
Authority
EP
European Patent Office
Prior art keywords
missile
matrix material
layer
ablation layer
outer shell
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
EP11008941A
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German (de)
English (en)
Other versions
EP2455704B1 (fr
EP2455704A3 (fr
Inventor
Peter Gerd Fisch
Gerd Elsner
Rainer Hezel
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.)
Diehl Defence GmbH and Co KG
Original Assignee
Diehl BGT Defence GmbH and Co KG
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.)
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Publication date
Application filed by Diehl BGT Defence GmbH and Co KG filed Critical Diehl BGT Defence GmbH and Co KG
Publication of EP2455704A2 publication Critical patent/EP2455704A2/fr
Publication of EP2455704A3 publication Critical patent/EP2455704A3/fr
Application granted granted Critical
Publication of EP2455704B1 publication Critical patent/EP2455704B1/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
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/34—Protection against overheating or radiation, e.g. heat shields; Additional cooling arrangements
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/25—Web or sheet containing structurally defined element or component and including a second component containing structurally defined particles
    • Y10T428/252—Glass or ceramic [i.e., fired or glazed clay, cement, etc.] [porcelain, quartz, etc.]

Definitions

  • the invention relates to a missile having an outer shell and an outer coating applied thereto in the form of an ablation layer, which contains a matrix material intended for at least partial decomposition during a flight.
  • Air targets require fast missiles that are superior in maneuverability to their targets because of their high speed. Airspeeds over 1000 m / s are desirable here.
  • the invention is based on the consideration that in a flight in the atmosphere at high speed frictional heat is generated, through which the missile, in particular at its tip and at its tail, heats up.
  • This phenomenon is known from space travel, in which, for example, space gliders are equipped with a heat shield.
  • the thermal insulation effect of such a heat shield is achieved mainly by a pyrolysis resulting cooling boundary layer between the missile and the passing air of the atmosphere.
  • the material of the heat shield gasifies and thus forms around the heat shield a gas layer, which serves as a cooling boundary layer.
  • Such a heat shield is usually placed as a plate-shaped material on the missile and connected thereto.
  • this approach has the disadvantage that the application is complicated and therefore expensive and the heat shield has a relatively large thickness in order to be able to be placed as a layer can.
  • the high-speed phase of an unmanned guided missile in particular an anti-aircraft missile, lasts only a few seconds.
  • the effect of heat is thus lower than, for example, in a space glider.
  • the outer shell is thinner and sensitive electronic components are closer to the outer shell than a space glider.
  • a critical temperature is therefore lower than in a space glider.
  • the requirements for a heat shield with an ablation layer on an unmanned guided missile are therefore different insofar as it must provide only a short time against a relatively low heat, but the thermal shield within this time must be so good that the temperature of the underlying outer shell only slightly increases, for example by less than 50 K, in particular less than 30 K.
  • the thickness of the ablation layer is expediently below 1 mm, preferably below 0.7 mm, in particular below 0.5 mm. As a result, the weight of the missile can be kept low and its range high.
  • the missile is expediently an unmanned guided missile, in particular with a rocket engine, for example a missile intended for destroying targets with a destructive effect causing the destruction.
  • a rocket may be a ground-to-air missile or an air-to-air missile, a rocket to combat aerial targets.
  • the outer shell of the missile may be a metal shell that protects the interior components of the missile.
  • An ablation layer is characterized in that it is provided at an airspeed at which the missile is in regular operation, thermally decomposed.
  • thermal decomposition can be understood to mean that material of the ablation layer at least partially changes from a solid to a gaseous state when the temperature increases. Expediently, the thermal decomposition of the ablation layer loses at least 1% of its weight per minute, in particular per second, with material changing from the solid state to the gaseous state.
  • the above-mentioned amount of material advantageously relates only to the matrix material of the ablation layer.
  • outer coating is understood such a coating, which points radially outward.
  • An interior coating that faces an interior is not an exterior coating in that sense.
  • the glass hollow bodies are expediently glass hollow spheres. These are at least substantially spherical glass bodies which form a cavity in their interior. The sphericity is achieved when the smallest outer diameter in any direction is not less than 50%, in particular 80%, of the largest outer diameter of the glass hollow sphere in a different direction.
  • the cavity is expediently filled with gas, preferably at least 90%, in particular completely.
  • At least 80% of the glass hollow bodies contained in the matrix material have an outer diameter of 12 ⁇ m ⁇ 5 ⁇ m.
  • an average outer diameter of the glass hollow body e.g. a not quite spherical glass hollow sphere, are considered.
  • a further advantageous embodiment of the invention provides that the hollow glass body make up at least 20% of the layer volume of the ablation layer. As a result, a good thermal insulation effect of the ablation layer can be achieved. With a volume fraction of the hollow glass body up to 65%, the ablation layer can still remain mechanically stable in such a way that it does not flake off even in the case of reasonable strokes.
  • the invention is also directed to a method for producing a missile with an outer shell, in which an outer coating in the form of an ablation layer is applied to the outer shell, which at least partially Decomposition during a flight provided matrix material. It is proposed that glass hollow spheres are embedded in the matrix material according to the invention.
  • a thin ablation layer is particularly easy to apply in the form of a paint, for example, applied with a brush or sprayed through a nozzle on the outer shell.
  • the ablation layer is applied as a liquid material to the outer shell.
  • a liquid material is also understood to mean a viscous material that can be applied to the outer shell by spraying or spread as a layer.
  • the initially liquid material is such that it is curable after application to the outer shell and in particular cures independently. The curing can be done by drying, vulcanization, by a chemical reaction of two different components or in other ways.
  • a matrix material is a material into which the hollow glass body can be embedded in such a way that it is held firmly by the matrix material in its position in the matrix material.
  • the matrix material is a lacquer.
  • the matrix material is a self-hardening material.
  • the curing may be accomplished by the evaporation of a diluent, by vulcanization or as a chemical reaction, e.g. in a multi-component system.
  • the matrix material contains an epoxy resin, whereby a simple application and an independent curing can be achieved.
  • An epoxy resin can consist of polymers which harden from a liquid state into a solid state with the addition of a suitable hardener and form a thermosetting plastic.
  • the matrix material contains a polyester resin, with which also a simple application and a self-curing can be achieved.
  • the matrix material contains an elastomer.
  • a terpolymeres elastomer such as EPDM (ethylene-propylene-diene rubber).
  • a likewise suitable ablation layer can be achieved in that the matrix material contains a thermoplastic, PEEK (polyetheretherketone) being particularly suitable for its hardness and stability.
  • PEEK polyetheretherketone
  • isocyanates for example polyurethanes, which, however, are expediently not used as foam but as varnish.
  • the chemical composition of the matrix material is advantageously chosen so that the decomposition temperature of the matrix material is between 150 ° C and 250 ° C, in particular between 180 ° C and 220 ° C. Further, it is advantageous if the composition of matrix material and glass hollow bodies is selected so that the thickness of the ablation layer at an energy input of 1 MW / m 2 within 20 s between 50 .mu.m and 500 .mu.m shrinks, in particular between 50 .mu.m and 200 .mu.m. This energy input is typical at velocities of antimissile missiles in lower air layers, so that within a typical approach of a missile the corresponding layer thickness is given off by gasification and thus forms the thermal protection layer.
  • a good thermal protection effect can also be achieved if the ablation layer loses 50 ⁇ m to 150 ⁇ m in thickness at a temperature of 200 ° C within 20 seconds.
  • the ablation layer need not be the only layer on the outer shell of the missile and may be attached to an underlying layer and / or below an overlying layer. Several layers underneath and / or above are also conceivable. A good mechanical resistance of the ablation layer can be achieved if it comprises a base layer and a cover layer applied thereto, which is free of glass hollow bodies. Due to the thermal insulation effect of the hollow glass body in the base layer with the glass hollow bodies, the heat transfer from the cover layer is delayed in the outer shell of the missile.
  • the mechanically stable cover layer can protect the underlying base layer and is expediently designed so that it also functions as an ablation layer, analogous to the base layer. In a high-speed flight of the missile first the cover layer and then the base layer is decomposed, both layers cool the outer shell by Ablationsrial.
  • the cover layer may be a lacquer layer, and it is in particular thinner than the base layer, for example, with a thickness of not more than 300 microns.
  • the material of the cover layer is kept at least substantially the same as the matrix material of the base layer, so that both layers have at least substantially the same ablation effect and thus the same cooling effect.
  • a particularly stable layer on the outer shell can be achieved if the ablation layer is applied to a primer layer, which in turn is applied to the outer shell.
  • the primer layer is expediently formed from the same material as the matrix material of the ablation layer. If the ablation layer is coated with a further layer which is free of glass hollow bodies, an aerodynamically advantageous surface can be produced.
  • Such a cover layer can also be understood as part of the ablation layer, since the cover layer is expediently likewise an ablation layer.
  • the invention is further directed to the use of a matrix material in which hollow glass bodies are embedded. It is proposed that the matrix material according to the invention be used as an ablation layer provided for at least partial evaporation during a flight and forming an outer coating on the outer shell of a missile.
  • Fig. 1 shows a schematic representation of a missile 2 with a wing 6-bearing fuselage 4 and a hood 8, which forms the tip of the missile 2, and the a arranged under the hood 8 Dom 10 protects.
  • the missile 2 is an unmanned missile in the form of an anti-aircraft missile for controlling air targets with an unillustrated active, which is provided for destroying the air target by blowing.
  • the hull 4 and the hood 8 form an outer shell of the missile 2, wherein the wings 6 can be optionally referred to as parts of the outer shell.
  • the wings 6 can be optionally referred to as parts of the outer shell.
  • On the outer shell several layers are applied, for example in the form of a paint, in Fig. 2 are shown.
  • Fig. 2 shows a section through the tip of the missile 2. Shown is an outer shell 12 made of metal and a coating 14 applied thereto. The coating 14 is also applied to the wings 6. It is composed of two layers 16, 18, wherein the layer 16 is a primer layer on the metallic outer shell 12. On this primer, the layer 18 is applied as an outer coating, which therefore points radially outward from the view of the outer shell 12 and is formed as Ablations Mrs.
  • This ablation layer 18 comprises a base layer 20 and a cover layer 22 applied thereon.
  • the base layer 20 of the ablation layer 18 is formed from a matrix material 24 with glass hollow bodies 26 embedded therein, wherein both the layers 16 and 18 and the glass hollow bodies 26 are not drawn to scale, but are too thick or too large.
  • the matrix material 24 is a self-hardening material in the form of an epoxy resin or a polyester resin, in which the hollow glass body 26 are firmly and immovably embedded after hardening of the matrix material 24.
  • the cover layer 22 consists of the same material as the matrix material 24 and is applied to the base layer 20 in the form of a covering lacquer layer. The cover layer 22 is free of glass hollow bodies 26.
  • the primer layer 16 is made of a different material than the matrix material 24.
  • the primer layer 16 is about 200 .mu.m thick
  • the ablation layer 18 is about 700 .mu.m thick, with about 500 .mu.m on the base layer 20 and about 200 .mu.m on the cover layer 22.
  • the glass hollow bodies 26 are hollow glass spheres with an average outer radius of 12 ⁇ m, 90% of the hollow glass body 26 having an outer diameter of 12 ⁇ m ⁇ 3 ⁇ m. The glass hollow bodies 26 make up about 25% by volume of the base layer 20.
  • the primer layer 16 is made of the same material as the matrix material 24 of the base layer 20, whereas the cover layer 22 is made of a different material, eg, another lacquer to reduce the surface roughness caused by the base layer 20 bearing the glass hollow bodies 26 .
  • the primer layer 16 is a layer of paint called Seevenax (Seevenax is a registered trademark DE 841645 the company Mankiewicz Gebr. & Co. (GmbH & Co. KG), Hamburg) as an adhesion-promoting layer exist.
  • Seevenax is a registered trademark DE 841645 the company Mankiewicz Gebr. & Co. (GmbH & Co. KG), Hamburg) as an adhesion-promoting layer exist.
  • a plurality of layers Seevenax with 25 vol .-% glass hollow body 26 are applied as a base layer 20 until a layer thickness of 500 microns is reached.
  • a topcoat is used, for example, Alexit Noridur 406 (Alexit is a registered trademark DE 61721 Mankiewicz Gebr. & Co. (GmbH & Co. KG), Hamburg; Noridur is a registered trademark DE 667526 the company Mankiewicz Gebr. & Co. (GmbH & Co. KG), Hamburg).
  • the matrix material 26 can be mixed with a diluent into which the glass hollow bodies 26 have previously been introduced.
  • the thinner with the glass hollow bodies 26 are first stirred and then stirred together with the matrix material 24.
  • 1250 g of Seevenax, 250 g of hardener and 300 g of diluent are possible and advantageous, 50 g of glass hollow body 26 being stirred into 400 g of thinner.
  • a viscous mixture of not yet cured matrix material 24 and glass body coupons 26, also referred to as a liquid mixture can be applied to the primer layer 16 by means of a Sprühlack Anlagens réelle in several layers, wherein a layer initially hardens before a further layer is applied. After curing of the uppermost layer of the base layer 20, the cover layer 22 can then also be applied and cured by the device for spray application.
  • the base layer 20 thus obtained has a decomposition temperature of about 200 ° C and shrinks at an energy input of 1 MW / m 2 within 20 s by about 70 microns. In this way, it forms a sufficient heat protection, so that the outer shell 12 is heated at this energy input within 20 s by not more than 30 ° C.
  • the ablation layer 18 can also be applied without a covering layer 22 and expediently covers at least the front part of the outer shell 12 of the missile 2, for example the outer shell 12 over a length of at least 10% of the entire missile 2. Expediently, the ablation layer 18 covers the entire fuselage 4 as an outer coating, whereby the wings can be coated by the Ablations Mrs.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Laminated Bodies (AREA)
  • Paints Or Removers (AREA)
EP11008941.4A 2010-11-17 2011-11-10 Missile avec enveloppe extérieure couverte d'une couche ablative Active EP2455704B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102010051752A DE102010051752A1 (de) 2010-11-17 2010-11-17 Flugkörper mit einer Außenhülle und einer darauf aufgebrachten Ablationsschicht

Publications (3)

Publication Number Publication Date
EP2455704A2 true EP2455704A2 (fr) 2012-05-23
EP2455704A3 EP2455704A3 (fr) 2014-07-16
EP2455704B1 EP2455704B1 (fr) 2016-01-27

Family

ID=44992489

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11008941.4A Active EP2455704B1 (fr) 2010-11-17 2011-11-10 Missile avec enveloppe extérieure couverte d'une couche ablative

Country Status (3)

Country Link
US (1) US20120121892A1 (fr)
EP (1) EP2455704B1 (fr)
DE (1) DE102010051752A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017007059A1 (de) 2017-07-26 2019-01-31 Bundesrepublik Deutschland, vertreten durch das Bundesministerium der Verteidigung, vertreten durch das Bundesamt für Ausrüstung, Informationstechnik und Nutzung der Bundeswehr Verfahren zur Herstellung eines Rohrabschnitts einer Flugkörperaußenhülle und Rohrabschnitt einer Flugkörperaußenhülle

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2496090C1 (ru) * 2012-05-11 2013-10-20 Николай Борисович Болотин Зенитная ракета и жидкостный ракетный двигатель
CN112177697B (zh) * 2020-09-09 2022-02-22 西安交通大学 基于热分解反应的热防护耦合开式布雷顿发电系统
JP7840664B2 (ja) * 2021-11-17 2026-04-06 三菱重工業株式会社 飛行体の耐熱構造および飛行体の耐熱構造の製造方法
EP4397938A1 (fr) * 2023-01-09 2024-07-10 MBDA UK Limited Structure de missile
WO2024149970A1 (fr) * 2023-01-09 2024-07-18 Mbda Uk Limited Structure de missile

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US4031059A (en) * 1974-01-21 1977-06-21 Martin Marietta Corporation Low density ablator compositions
US4077921A (en) * 1977-01-19 1978-03-07 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Sprayable low density ablator and application process
US5457471A (en) * 1984-09-10 1995-10-10 Hughes Missile Systems Company Adaptively ablatable radome
US4753169A (en) * 1985-12-23 1988-06-28 General Dynamics, Pomona Division Ablating electromagnetic shield sheath
US4837250A (en) * 1987-07-23 1989-06-06 Usbi Booster Production Company, Inc. Trowelable ablative coating composition and method of use
DE4132234C2 (de) * 1991-09-27 1997-05-07 Rheinmetall Ind Ag Wuchtgeschoß
US5661198A (en) * 1993-09-27 1997-08-26 Nissan Motor Co., Ltd. Ablator compositions
US20040018309A1 (en) * 2002-07-25 2004-01-29 Carrier Corporation Furnace parts protected by thermally and chemically resistant coatings
US6933334B2 (en) * 2003-06-25 2005-08-23 United Technologies Corporation Silicone-cork ablative material
BRPI0716537A2 (pt) * 2006-09-11 2013-09-17 Dsm Ip Assets Bv material isolante tÉrmico

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None

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017007059A1 (de) 2017-07-26 2019-01-31 Bundesrepublik Deutschland, vertreten durch das Bundesministerium der Verteidigung, vertreten durch das Bundesamt für Ausrüstung, Informationstechnik und Nutzung der Bundeswehr Verfahren zur Herstellung eines Rohrabschnitts einer Flugkörperaußenhülle und Rohrabschnitt einer Flugkörperaußenhülle

Also Published As

Publication number Publication date
US20120121892A1 (en) 2012-05-17
DE102010051752A1 (de) 2012-05-24
EP2455704B1 (fr) 2016-01-27
EP2455704A3 (fr) 2014-07-16

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