DE102005039783B3 - Sandwich structure with resin-embedded carbon fiber-reinforced layers and integrated metal tube, useful e.g. in spacecraft, has thermal and structural optimization sandwich layers with differently oriented fibers - Google Patents

Sandwich structure with resin-embedded carbon fiber-reinforced layers and integrated metal tube, useful e.g. in spacecraft, has thermal and structural optimization sandwich layers with differently oriented fibers Download PDF

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DE102005039783B3
DE102005039783B3 DE200510039783 DE102005039783A DE102005039783B3 DE 102005039783 B3 DE102005039783 B3 DE 102005039783B3 DE 200510039783 DE200510039783 DE 200510039783 DE 102005039783 A DE102005039783 A DE 102005039783A DE 102005039783 B3 DE102005039783 B3 DE 102005039783B3
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sandwich
layers
thermal
carbon fibers
sandwich structure
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Reinhard Dr.-Ing. Schlitt
Harald Dipl.-Ing. Segelke
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ORBITALE HOCHTECHNOLOGIE BREME
ORBITALE HOCHTECHNOLOGIE BREMEN-SYSTEM AG
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ORBITALE HOCHTECHNOLOGIE BREME
ORBITALE HOCHTECHNOLOGIE BREMEN-SYSTEM AG
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    • E—FIXED CONSTRUCTIONS
    • E04—BUILDING
    • E04C—STRUCTURAL ELEMENTS; BUILDING MATERIALS
    • E04C2/00—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels
    • E04C2/30—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure
    • E04C2/34—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure composed of two or more spaced sheet-like parts
    • E04C2/36—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure composed of two or more spaced sheet-like parts spaced apart by transversely-placed strip material, e.g. honeycomb panels
    • E04C2/365—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure composed of two or more spaced sheet-like parts spaced apart by transversely-placed strip material, e.g. honeycomb panels by honeycomb structures
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • E—FIXED CONSTRUCTIONS
    • E04—BUILDING
    • E04C—STRUCTURAL ELEMENTS; BUILDING MATERIALS
    • E04C2/00—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels
    • E04C2/02—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by specified materials
    • E04C2/26—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by specified materials composed of materials covered by two or more of groups E04C2/04, E04C2/08, E04C2/10 or of materials covered by one of these groups with a material not specified in one of the groups
    • E04C2/284—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by specified materials composed of materials covered by two or more of groups E04C2/04, E04C2/08, E04C2/10 or of materials covered by one of these groups with a material not specified in one of the groups at least one of the materials being insulating
    • E04C2/296—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by specified materials composed of materials covered by two or more of groups E04C2/04, E04C2/08, E04C2/10 or of materials covered by one of these groups with a material not specified in one of the groups at least one of the materials being insulating composed of insulating material and non-metallic or unspecified sheet-material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
    • F28D15/00—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies
    • F28D15/02—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies in which the medium condenses and evaporates, e.g. heat pipes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F2265/00—Safety or protection arrangements; Arrangements for preventing malfunction
    • F28F2265/26—Safety or protection arrangements; Arrangements for preventing malfunction for allowing differential expansion between elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F2275/00—Fastening; Joining
    • F28F2275/02—Fastening; Joining by using bonding materials; by embedding elements in particular materials

Abstract

A sandwich structure with resin-embedded carbon fiber-reinforced covering layers containing integrated metal tubes has multiple sandwich layers, one (1) for structural requirements and other(s) (4) for thermal requirements. The carbon fibers in the covering layers of the structural layer (1) are isotropically oriented; and those in the thermal layer(s) (4) are perpendicular to the metal tube (5). A sandwich structure with carbon fiber-reinforced covering layers containing integrated metal tubes, with the fibers embedded in a hardened resin system, has multiple sandwich layers, one (1) for structural requirements and other(s) (4) for thermal requirements. The carbon fibers in the covering layers of the structural layer (1) are isotropically oriented; and the carbon fibers in the covering layers of the thermal layer(s) (4) are perpendicular to the integrated tubular metal profile (5).

Description

Die Erfindung betrifft eine Sandwich Struktur entsprechend dem Oberbegriff des Anspruchs 1, wobei die Struktur aus Sandwichlagen mit kohlenstofffaserverstärkten Deckschichten und mit integrierten metallischen Rohren besteht.The The invention relates to a sandwich structure according to the preamble of claim 1, wherein the structure of sandwich layers with carbon fiber reinforced cover layers and with integrated metallic tubes.

Sandwichstrukturen sind bekannt als Bestandteile von Leichtbaustrukturen, z.B. in Raumfahrzeugen. Sie bestehen meist aus Aluminium Deckschichten und einer Honigwabenstruktur, deren Material ebenfalls aus einer Aluminiumlegierung oder einem Kunststoff sein kann. Der Vorteil solcher Strukturen ist ihre große Steifigkeit bei niedrigem Gewicht.sandwich structures are known as components of lightweight structures, e.g. in spacecraft. They usually consist of aluminum cover layers and a honeycomb structure, their material also made of an aluminum alloy or a Plastic can be. The advantage of such structures is their great rigidity at low weight.

Solche Sandwichstrukturen werden auch als Abstrahlfläche für thermische Verlustleistungen von elektronischen Geräten verwendet. Zu diesem Zweck sind die Geräte auf die zum Satelliteninneren zeigende Fläche montiert. Die Verlustwärme fließt zur anderen, dem Weltraum zugewandten Seite, um dort abgestrahlt zu werden. In US 5,506,032 A ist beschrieben, dass zur besseren Verteilung der Wärme in der Sandwich Struktur häufig parallel verlaufende Wärmerohre zwischen die Deckschichten geklebt werden (embedded hegt pipe radiator).Such sandwich structures are also used as a radiating surface for thermal power losses of electronic devices. For this purpose, the devices are mounted on the surface facing the satellite interior. The heat loss flows to the other, the space-facing side to be radiated there. In US 5,506,032 A It is described that for better distribution of the heat in the sandwich structure frequently parallel heat pipes are glued between the cover layers (embedded hegt pipe radiator).

Bei großen Satelliten mit hoher Verlustleistung reichen die äußeren Satellitenflächen nicht mehr aus, um die Verlustwärme abzustrahlen. Es werden deshalb zusätzliche Radiatoren bereit gestellt, die in ihre vorbestimmte Position ausgefaltet werden, nachdem der Satellit im Erdorbit platziert ist. Zur Zuführung der Wärme vom Satellitenkörper zum entfalteten Radiator werden neuerdings Loop -Wärmerohre (Loop Heat Pipes) eingesetzt ( US 6,478,258 B1 ). Loop -Wärmerohre sind zwei-Phasen Wärmetransportsysteme, die Wärme durch Verdampfung und Kondensation übertragen, ähnlich wie bei normalen Wärmerohren. Ihr Vorteil liegt u.a. in den dünnen, flexiblen Transportleitungen, die durch den Entfaltvorgang nicht beschädigt werden. Eine gute Zusammenfassung des heutigen Standes der Technik bietet die Veröffentlichung SAE 981691.In large satellites with high power dissipation, the outer satellite surfaces are no longer sufficient to radiate the heat loss. Therefore, additional radiators are provided which fold out to their predetermined position after the satellite is placed in Earth orbit. To supply the heat from the satellite body to the deployed radiator, loop heat pipes have recently been used ( US Pat. No. 6,478,258 B1 ). Loop heat pipes are two-phase heat transfer systems that transfer heat through evaporation and condensation, similar to normal heat pipes. Their advantage lies, inter alia, in the thin, flexible transport lines, which are not damaged by the Entfaltvorgang. A good summary of the current state of the art is provided by the publication SAE 981691.

Bei allen Sandwichstrukturen, seien es solche mit integrierten herkömmlichen Wärmerohren oder Loop- Wärmerohren, bestehen Deckschichten und Rohre heute überwiegend aus Aluminiumlegierungen, also aus Metallen mit ähnlichen thermischen Ausdehnungskoeffizienten, d.h. die Strukturen werden bei Schwankungen der Betriebstemperatur nicht durch thermo-mechanischer Belastungen beeinträchtigt.at all sandwich structures, whether those with integrated conventional Heat pipes or Loop heat pipes, surface layers and pipes today consist predominantly of aluminum alloys, So from metals with similar coefficient of thermal expansion, i. the structures become with fluctuations of the operating temperature not by thermo-mechanical Impacts impaired.

Aus Wettbewerbsgründen gibt es in neuerer Zeit Bestrebungen, das Gewicht der kommerziellen und anderer Satelliten weiter zu senken. In diesem Zusammenhang denkt man daran, die Deckschichten der oben beschriebenen Sandwich Strukturen aus kohlenstofffaserverstärkten Material herzustellen. Die notwendige gute thermische Leitfähigkeit der Deckschichten wird hierbei durch hochleitende Kohlenstofffasern erzielt. Da die Wärmerohre und Loop – Wärmerohre wegen technischer Gründe weiterhin aus Metall bestehen sollen, ergibt sich bei diesen Entwicklungen das Problem der ungleichen thermischen Ausdehnungskoeffizienten und der einhergehenden thermo-mechanischer Belastung bei Änderung der Betriebstemperatur.Out competitive reasons There are recent efforts, the weight of commercial and other satellites continue to lower. In this context thinks on it, the outer layers of the sandwich structures described above carbon fiber reinforced Produce material. The necessary good thermal conductivity The cover layers is here by highly conductive carbon fibers achieved. Because the heat pipes and loop heat pipes for technical reasons continue to be made of metal, results from these developments the problem of unequal coefficients of thermal expansion and the concomitant thermo-mechanical stress on change the operating temperature.

Bei Sandwichstrukturen mit integrierten herkömmlichen Wärmerohren gibt es im Ansatz bereits Vorschläge, um das Problem der verschieden Ausdehnungskoeffizienten zu lösen. Beispielsweise in JP 2000129857 A , JP 2001153576 A und JP 2000130971 A wird eine Sandwichstruktur mit kohlenstofffaserverstärkten Deckschichten und integrierten metallischen Wärmerohren beschrieben, bei der die Wärmerohre mit flexiblen Kleber an die Kohlenstofffaserdeckschichten montiert werden, während im Bereich der Honigwabenstruktur ein nicht-flexibler, höher belastbarer Strukturkleber eingesetzt wird. Der flexible Kleber nimmt die Verschiebung zwischen Metallrohr und Kohlenstofffaserdeckschicht auf, ohne thermo-mechanische Lasten zu erzeugen.In sandwich structures with integrated conventional heat pipes, there are already proposals in the approach to solve the problem of different expansion coefficients. For example in JP 2000129857 A . JP 2001153576 A and JP 2000130971 A describes a sandwich structure with carbon-fiber-reinforced cover layers and integrated metallic heat pipes, in which the heat pipes are attached to the carbon fiber cover layers with flexible adhesive, while in the area of the honeycomb structure a non-flexible, higher-strength structural adhesive is used. The flexible adhesive absorbs the displacement between metal tube and carbon fiber topcoat without generating thermo-mechanical loads.

Eine andere Ausführungsart ist in US 2002/0102384 A1 dargelegt. Hier wird zwischen metallischem Wärmerohr und Kohlenstofffaserdeckschicht eine nichtmetallische Folie mit hoher thermischer Leitfähigkeit gelegt, die durch den Herstellungsprozess der Sandwichstruktur zwischen den Bauteilen angepresst wird. Es entsteht so ein guter Wärmeübergang, wobei gleichzeitig eine relative Bewegung beider Bauteile zugelassen wird, also thermo-mechanischer Belastungen vermieden werden.A another embodiment is set forth in US 2002/0102384 A1. Here is between metallic heat pipe and carbon fiber topcoat a non-metallic film with high thermal conductivity put through the process of manufacturing the sandwich structure between the components is pressed. It creates a good heat transfer, while allowing a relative movement of both components is, so thermo-mechanical stresses are avoided.

EP 0438938 A1 beschreibt eine weitere Ausführungsart, bei der die Kohlenstofffaserdeckschicht auf beiden Seiten in den integralen Flansch des Wärmerohrs eingelassen wird. Hier wird die höhere thermische Expansion des metallischen Wärmerohrs in der Weise ausgenutzt, dass bei großer Überhitzung der Sandwichstruktur das Wärmerohr thermisch entkoppelt und geschützt wird. EP 0438938 A1 describes a further embodiment in which the carbon fiber cover layer is embedded on both sides in the integral flange of the heat pipe. Here, the higher thermal expansion of the metallic heat pipe is exploited in such a way that at great overheating of the sandwich structure, the heat pipe is thermally decoupled and protected.

In DE 10340092 A1 wird eine Ausführungsart beschrieben, bei der gegen die Innenflächen der kohlenstofffaserverstärkten Deckschichten metallische Kondensierrohre eines Loop-Wärmerohrs angebracht sind. Die Rohre haben integrierte Flansche zur Vergrößerung der Kontaktfläche zur Deckschicht. Zum Ausgleich der thermo-mechanischen Spannungen, hervorgerufen durch die ungleichen thermischen Ausdehnungskoeffizienten, sind flanschfreie Abschnitte der Kondensierrohre gebogen und nicht mit den Deckschichten verbunden. Andere Rohre sind am Rande der Struktur, jedoch außerhalb des Sandwichkerns verlegt.In DE 10340092 A1 An embodiment is described in which metallic condenser tubes of a loop heat pipe are mounted against the inner surfaces of the carbon fiber reinforced cover layers. The tubes have integrated flanges to increase the contact surface with the cover layer. To compensate for the thermo-mechanical stresses caused by the unequal coefficients of thermal expansion, flange-free sections of the condenser tubes are bent and not connected to the cover layers. Other pipes are laid at the edge of the structure, but outside the sandwich core.

Zitierte SchriftenQuoted writings

Patentliteraturpatent literature

  • US 5.506,032 A Structural Panel Having Integral Heat Pipe Network US 5,506,032 A Structural Panel Having Integral Heat Pipe Network
  • US 6,478,258 B1 Spacecraft Multiple Loop Heat Pipe Thermal System for Internal Equipment Panel Applications US Pat. No. 6,478,258 B1 Spacecraft Multiple Loop Heat Pipe Thermal System for Internal Equipment Panel Applications
  • JP2000129857 A Carbon Fiber Skin Heat Pipe Panel JP2000129857 A Carbon Fiber Skin Heat Pipe Panel
  • JP2001153576 A Carbon Fiber Skin Heat Pipe Panel and Heat Pipe JP2001153576 A Carbon Fiber Skin Heat Pipe Panel and Heat Pipe
  • JP2000130971 A Carbon Fiber Skin Heat Pipe Panel JP2000130971 A Carbon Fiber Skin Heat Pipe Panel
  • US2002/0102384 A1 Embedded Heat pipe Sandwich Panel Constructed Using Dissimilar MaterialsUS2002 / 0102384 A1 Embedded Heat Pipe Sandwich Panel Constructed Using Dissimilar Materials
  • EP0438938 A1 Spacecraft Radiator System EP0438938 A1 Spacecraft Radiator System
  • DE10340092 A1 Sandwich Struktur mit Kohlenfaserverstärkten Deckschichten und integrierten metallischen Kondensierrohren DE10340092 A1 Sandwich structure with carbon fiber reinforced facings and integrated metallic condensing tubes

NichtpatentliteraturNon-patent literature

  • SAE 981691 Deployable Radiators – A Multi-Discipline Approach, 28th ICES, July 13-16, 1998SAE 981691 deployable radiator - A Multi-Discipline Approach, 28 th ICES, July 13-16, 1998

Die vorliegende Erfindung betrifft die Integration von metallischen Rohren in Sandwichstrukturen mit Kohlenstofffaserdeckschichten. Die Rohre, die je nach Ausführungsart aus eine Aluminiumlegierung oder aus rostfreiem Stahl bestehen, können sowohl einen rechteckigen Querschnitt haben oder als zylindrische Rohre mit integrierten Flanschen ausgeführt sein.The The present invention relates to the integration of metallic Tubes in sandwich structures with carbon fiber facings. The pipes, depending on the design consist of an aluminum alloy or of stainless steel, can both have a rectangular cross section or as cylindrical Be executed pipes with integrated flanges.

Detaillierte Beschreibung der ErfindungDetailed description the invention

Ausführungsbeispiele der Erfindung sind in Zeichnungen dargestellt und werden im Folgenden näher beschrieben.embodiments The invention are illustrated in drawings and will be described in more detail below.

Es zeigenIt demonstrate

1: Querschnitt der Sandwichstruktur mit eingebetteten Rohren 1 : Cross section of the sandwich structure with embedded tubes

2: Kohlenstofffaserausrichtung in einer Deckschicht des Sandwich zur optimalen Strukturauslegung 2 : Carbon fiber registration in a sandwich topcoat for optimal structure design

3: Kohlenstofffaserausrichtung in einer Deckschicht der thermischen Sandwichlage zur verbesserten Fortleitung der Wärme, die mit den Rohrprofilen herangeführt wird 3 : Carbon fiber alignment in a top layer of the thermal sandwich layer for improved dissipation of the heat introduced by the tube profiles

Die erfindungsgemäße Anordnung einer Sandwichstruktur mit integrierten metallischen Rohren 1 besteht aus mehreren Sandwichlagen, wobei ein Sandwich (1) aus zwei Deckschichten (3) und einem Kernmaterial (2) zusammengesetzt ist und so ausgelegt ist, dass es den strukturellen Anforderungen der Gesamtstruktur gerecht wird (z.B. in Hinblick auf die geforderte Steifigkeit). Dazu besteht das Kernmaterial (2) vorzugsweise aus einer metallischem Honigwabenstruktur und die Deckschichten (3) aus mehreren Lagen Kohlenstofffasern, die in einem geeigneten aushärtbaren Harz eingelagert sind und deren Ausrichtung möglichst isotrop, d.h. nach strukturellen Anforderungen optimiert ist. Das Sandwich (1) ist auf einer oder beiden Seiten mit thermisch optimierten Sandwich-Lagen (4) verbunden, die aus je einem Kernmaterial (6) und einer Deckschicht (7) besteht und in denen die metallischen Rohrprofile (5) eingebettet sind. Das Kernmaterial (6) der thermischen Sandwichlagen (4) ist so ausgewählt, dass es verbleibende thermische Spannungen zwischen der Kombination Deckschicht (7)/metallischen Rohrprofilen (5) und dem für strukturelle Anforderungen ausgelegte Sandwich (1) ausgleichen kann (z.B. geeignete offenporige oder geschlossenporige Kunststoffschäume). Die Deckschichten (7) der thermischen Sandwichlagen bestehen aus mehreren Lagen thermisch hochleitfähiger Kohlenstofffasern, die in einem geeigneten aushärtbaren Harz eingelagert sind und deren Ausrichtung nach thermischen Gesichtspunkten optimiert ist. Die Rohrprofile sind sowohl mit der Deckschicht (7) als auch mit dem Kernmaterial (6) verklebt, wobei vorzugsweise Folienkleber und Spleißkleber verwendet werden.The inventive arrangement of a sandwich structure with integrated metallic tubes 1 consists of several sandwich layers, with a sandwich ( 1 ) of two outer layers ( 3 ) and a nuclear material ( 2 ) and is designed to meet the structural requirements of the overall structure (eg, in terms of required stiffness). For this purpose, the nuclear material ( 2 ) preferably of a metallic honeycomb structure and the outer layers ( 3 ) of several layers of carbon fibers, which are incorporated in a suitable curable resin and whose orientation is as isotropic, that is optimized according to structural requirements. The sandwich ( 1 ) is on one or both sides with thermally optimized sandwich layers ( 4 ), each consisting of a core material ( 6 ) and a cover layer ( 7 ) and in which the metallic tube profiles ( 5 ) are embedded. The nuclear material ( 6 ) of the thermal sandwich layers ( 4 ) is selected so that there is residual thermal stress between the combination topcoat ( 7 ) / metallic pipe profiles ( 5 ) and the structural requirements sandwich ( 1 ) (eg suitable porous or closed-cell plastic foams). The cover layers ( 7 ) of the thermal sandwich layers consist of several layers of highly thermally conductive carbon fibers, which are incorporated in a suitable hardenable resin and their orientation is optimized according to thermal considerations. The tube profiles are compatible with both the top layer ( 7 ) as well as with the nuclear material ( 6 ), preferably using film adhesive and splice adhesive.

In 2 ist die Ausrichtung der Kohlenstofffasern in den Deckschichten der thermischen Sandwichlagen (4) in Bezug auf die Orientierung der eingebetteten metallischen Rohrprofile (5) angegeben. Zur Fortleitung der Wärme, die mit den Profilrohren (5) herangeführt wird, werden alle Lagen mit thermisch hochleitfähigen Fasern verwendet, deren Ausrichtung (8) senkrecht zu den Profilrohren gewählt wird. Bei dieser Anordnung wird der aushärtbare Harz, in dem die Fasern eingebettet sind, und das Klebematerial zur Anbindung der Rohrprofile so gewählt, dass die thermischen Ausdehnungskoeffizienten in diesem Verbund übereinstimmen. Entsprechend werden thermische Spannungen zwischen Profilrohr (5) und Deckschicht vermieden (7).In 2 is the orientation of the carbon fibers in the cover layers of the thermal sandwich layers ( 4 ) with regard to the orientation of the embedded metallic tube profiles ( 5 ). For the transmission of the heat, which with the profile tubes ( 5 ), all layers are used with thermally highly conductive fibers whose orientation ( 8th ) is selected perpendicular to the profile tubes. With this arrangement, the thermosetting resin in which the fibers are embedded and the bonding material for connecting the tubular profiles are selected so that the thermal expansion coefficients in this composite coincide. Accordingly, thermal stresses between the profile tube ( 5 ) and cover layer avoided ( 7 ).

In 3 ist die Orientierung der Kohlenstofffasern in den Deckschichten des Struktur- optimieren Sandwich (1) angegeben. Es werden Fasern mit strukturoptimierten Eigenschaften und gewöhnlich geringer thermischer Leitfähigkeit verwendet, deren Ausrichtung (9) isotrop in allen Richtungen erfolgt, um eine gute Gesamtsteifigkeit der integrierten Sandwichstruktur zu erzielen.In 3 is the orientation of the carbon fibers in the surface layers of the structure-optimizing sandwich ( 1 ). Fibers with structure-optimized properties and usually low thermal conductivity are used whose orientation ( 9 ) Isotropic in all directions, to ensure good overall stiffness of the integrated To achieve sandwich structure.

Claims (5)

Eine Sandwichstruktur mit kohlenstofffaserverstärkten Deckschichten, in denen metallische Rohre integriert sind, wobei die Kohlenstofffasern in einem ausgehärteten Harzsystem eingebettet sind, dadurch gekennzeichnet, dass die Sandwichstruktur aus mehreren Sandwichlagen besteht, wobei ein Sandwich (1) nach strukturellen Erfordernissen und mindestens eine weitere Sandwichlage (4) nach thermischen Erfordernissen mit eingelassenen metallischen Rohren (5) so angeordnet sind, dass (a) durch isotrope Orientierung der Kohlenstofffasern in den Deckschichten des Sandwiches (1) und (b) durch Ausrichtung der Kohlenstofffasern in den Deckschichten der thermischen Sandwichlage (4) senkrecht zu den integrierten metallischen Rohrprofilen thermo-mechanische Lasten, hervorgerufen durch unterschiedliche thermische Ausdehnungskoeffizienten, vermieden und gleichzeitig das thermische und mechanische Verhalten der Struktur optimiert werden.A sandwich structure with carbon-fiber-reinforced cover layers, in which metallic tubes are integrated, wherein the carbon fibers are embedded in a cured resin system, characterized in that the sandwich structure consists of several sandwich layers, wherein a sandwich ( 1 ) according to structural requirements and at least one further sandwich layer ( 4 ) according to thermal requirements with embedded metallic tubes ( 5 ) are arranged so that (a) by isotropic orientation of the carbon fibers in the outer layers of the sandwich ( 1 ) and (b) by alignment of the carbon fibers in the cover layers of the thermal sandwich layer ( 4 ) perpendicular to the integrated metallic tube profiles thermo-mechanical loads, caused by different thermal expansion coefficients, avoided while optimizing the thermal and mechanical behavior of the structure. Sandwichstruktur nach Anspruch 1 dadurch gekennzeichnet, dass die thermisch optimierte Sandwichlage (4) auf einer Seite oder auf beiden Seiten des Struktur – optimierten Sandwiches (1) angeordnet ist.Sandwich structure according to claim 1, characterized in that the thermally optimized sandwich layer ( 4 ) on one side or on both sides of the structure - optimized sandwich ( 1 ) is arranged. Sandwichstruktur nach Anspruch 2 dadurch gekennzeichnet, dass in den thermisch optimierten Sandwichlagen die Deckschichten aus mehreren Lagen thermisch hoch- leitender Kohlenstofffasern bestehen, wobei die Faserausrichtung in allen Lagen senkrecht zu den integrierten Rohrprofilen verlaufen.Sandwich structure according to claim 2, characterized that in the thermally optimized sandwich layers, the outer layers consist of several layers of thermally highly conductive carbon fibers, wherein the fiber orientation in all positions perpendicular to the integrated Run pipe profiles. Sandwichstruktur nach Anspruch 3 dadurch gekennzeichnet, dass die Anzahl der Lagen mit thermisch hochleitenden Kohlenstofffasern nach thermischen Anforderungen bestimmt werden.Sandwich structure according to claim 3, characterized that the number of layers with thermally highly conductive carbon fibers determined according to thermal requirements. Sandwichstruktur nach Anspruch 2 oder 3 dadurch gekennzeichnet, dass das aushärtbare Harzsystem, in dem die Kohlenstofffasern eingebettet sind, und die Klebung zwischen Profilrohren und Deckschichten so ausgeführt sind, dass sich die thermischen Ausdehnungen der genannten Komponenten angleichen und thermo-mechanische Spannungen vermieden werden.Sandwich structure according to claim 2 or 3, characterized that the curable Resin system in which the carbon fibers are embedded, and the Gluing between profile tubes and cover layers are designed so that the thermal expansions of said components Adjust and thermo-mechanical stresses are avoided.
DE200510039783 2005-08-22 2005-08-22 Sandwich structure with resin-embedded carbon fiber-reinforced layers and integrated metal tube, useful e.g. in spacecraft, has thermal and structural optimization sandwich layers with differently oriented fibers Expired - Fee Related DE102005039783B3 (en)

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EP3042854A1 (en) * 2015-01-08 2016-07-13 The Boeing Company Spacecraft and spacecraft radiator panels with composite face-sheets
US10018426B2 (en) 2016-05-12 2018-07-10 The Boeing Company Composite heat pipes and sandwich panels, radiator panels, and spacecraft with composite heat pipes

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EP0438938A2 (en) * 1989-12-22 1991-07-31 Grumman Aerospace Corporation Spacecraft radiator system
US5506032A (en) * 1994-04-08 1996-04-09 Martin Marietta Corporation Structural panel having integral heat pipe network
JP2000129857A (en) * 1998-10-26 2000-05-09 Mitsubishi Electric Corp Carbon fiber skin heat pipe panel
JP2000130971A (en) * 1998-10-28 2000-05-12 Mitsubishi Electric Corp Carbon fiber skin heat pipe panel
JP2001153576A (en) * 1999-11-22 2001-06-08 Mitsubishi Electric Corp Carbon fiber skin heat pipe panel and heat pipe
US20020102384A1 (en) * 2001-01-29 2002-08-01 Peck Scott O. Embedded heat pipe sandwich panel constructed using dissimilar materials
US6478258B1 (en) * 2000-11-21 2002-11-12 Space Systems/Loral, Inc. Spacecraft multiple loop heat pipe thermal system for internal equipment panel applications
DE10340092A1 (en) * 2003-08-30 2005-05-04 Ohb Orbitale Hochtechnologie B Radiator with sandwich structure for use in satellites, includes integral loop heat pipe comprising flanged aluminum profiles

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EP0438938A2 (en) * 1989-12-22 1991-07-31 Grumman Aerospace Corporation Spacecraft radiator system
US5506032A (en) * 1994-04-08 1996-04-09 Martin Marietta Corporation Structural panel having integral heat pipe network
JP2000129857A (en) * 1998-10-26 2000-05-09 Mitsubishi Electric Corp Carbon fiber skin heat pipe panel
JP2000130971A (en) * 1998-10-28 2000-05-12 Mitsubishi Electric Corp Carbon fiber skin heat pipe panel
JP2001153576A (en) * 1999-11-22 2001-06-08 Mitsubishi Electric Corp Carbon fiber skin heat pipe panel and heat pipe
US6478258B1 (en) * 2000-11-21 2002-11-12 Space Systems/Loral, Inc. Spacecraft multiple loop heat pipe thermal system for internal equipment panel applications
US20020102384A1 (en) * 2001-01-29 2002-08-01 Peck Scott O. Embedded heat pipe sandwich panel constructed using dissimilar materials
DE10340092A1 (en) * 2003-08-30 2005-05-04 Ohb Orbitale Hochtechnologie B Radiator with sandwich structure for use in satellites, includes integral loop heat pipe comprising flanged aluminum profiles

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3042854A1 (en) * 2015-01-08 2016-07-13 The Boeing Company Spacecraft and spacecraft radiator panels with composite face-sheets
US9878808B2 (en) 2015-01-08 2018-01-30 The Boeing Company Spacecraft and spacecraft radiator panels with composite face-sheets
EP3620395A1 (en) * 2015-01-08 2020-03-11 The Boeing Company Spacecraft and spacecraft radiator panels with composite face-sheets
US10018426B2 (en) 2016-05-12 2018-07-10 The Boeing Company Composite heat pipes and sandwich panels, radiator panels, and spacecraft with composite heat pipes

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