DE3836442A1 - Impact-resistant material for flying objects - Google Patents

Impact-resistant material for flying objects

Info

Publication number
DE3836442A1
DE3836442A1 DE3836442A DE3836442A DE3836442A1 DE 3836442 A1 DE3836442 A1 DE 3836442A1 DE 3836442 A DE3836442 A DE 3836442A DE 3836442 A DE3836442 A DE 3836442A DE 3836442 A1 DE3836442 A1 DE 3836442A1
Authority
DE
Germany
Prior art keywords
thermoplastic
layers
material according
impact
reinforced
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.)
Ceased
Application number
DE3836442A
Other languages
German (de)
Inventor
Siegfried Dipl Ing Roth
Paul Dipl Ing Kaechele
Hans-Wolfgang Dr Rer Schroeder
Wolfgang Dipl Ing Unger
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.)
Dornier GmbH
Original Assignee
Dornier 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 Dornier GmbH filed Critical Dornier GmbH
Priority to DE3836442A priority Critical patent/DE3836442A1/en
Publication of DE3836442A1 publication Critical patent/DE3836442A1/en
Ceased legal-status Critical Current

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08L—COMPOSITIONS OF MACROMOLECULAR COMPOUNDS
    • C08L79/00—Compositions of macromolecular compounds obtained by reactions forming in the main chain of the macromolecule a linkage containing nitrogen with or without oxygen or carbon only, not provided for in groups C08L61/00 - C08L77/00
    • C08L79/04—Polycondensates having nitrogen-containing heterocyclic rings in the main chain; Polyhydrazides; Polyamide acids or similar polyimide precursors
    • C08L79/08—Polyimides; Polyester-imides; Polyamide-imides; Polyamide acids or similar polyimide precursors
    • C08L79/085—Unsaturated polyimide precursors
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08J—WORKING-UP; GENERAL PROCESSES OF COMPOUNDING; AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F, C08G or C08H
    • C08J5/00—Manufacture of articles or shaped materials containing macromolecular substances
    • C08J5/24—Impregnating materials with prepolymers which can be polymerised in situ, e.g. manufacture of prepregs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/06—Fibrous reinforcements only
    • B29C70/08—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers
    • B29C70/086—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers and with one or more layers of pure plastics material, e.g. foam layers
    • 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
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/06—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B27/08—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08L—COMPOSITIONS OF MACROMOLECULAR COMPOUNDS
    • C08L79/00—Compositions of macromolecular compounds obtained by reactions forming in the main chain of the macromolecule a linkage containing nitrogen with or without oxygen or carbon only, not provided for in groups C08L61/00 - C08L77/00
    • C08L79/04—Polycondensates having nitrogen-containing heterocyclic rings in the main chain; Polyhydrazides; Polyamide acids or similar polyimide precursors
    • C08L79/08—Polyimides; Polyester-imides; Polyamide-imides; Polyamide acids or similar polyimide precursors
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Abstract

Material for components subjected to impact stress, such as leading edges of wings, aerofoils or tailplanes on flying objects or of body parts on vehicles, comprising a plurality of fibre-reinforced thermoset layers (D) and a plurality of thermoplastic layers (T) lying in between. <IMAGE>

Description

Die Erfindung betrifft einen Werkstoff für schlagbean­ spruchte Bauteile nach dem Oberbegriff des Anspruchs 1.The invention relates to a material for whipped beans wanted components according to the preamble of claim 1.

Bekannt sind Flugzeuge, die vollständig aus faserverstärktem Kunststoff hergestellt sind. Bei diesen Flugzeugen werden Duroplaste eingesetzt. Diese verstärkten Duroplaste haben eine hohe Kerbempfindlichkeit. Einschläge durch Vogelschlag oder aufgewirbelte Steinchen können zur Auflösung des Schichtverbundes führen.Airplanes are made entirely of fiber-reinforced Plastic are made. With these aircraft Thermosets used. Have these reinforced thermosets high notch sensitivity. Bird strikes or whirled stones can dissolve the Lead shift network.

Aufgabe der Erfindung ist es, einen Werkstoff für schlagbe­ anspruchte Bauteile, wie Vorderkanten von Tragflächen oder Leitwerken an Fluggeräten oder an Karosserieteilen von Fahr­ zeugen vorzuschlagen, die eine verbesserte Impaktbeständig­ keit haben.The object of the invention is to provide a material for impact stressed components, such as leading edges of wings or Tail units on aircraft or body parts of Fahr testify to propose an improved impact resistant to have

Diese Aufgabe wird erfindungsgemäß gelöst von einem Werk­ stoff mit den Merkmalen des Anspruchs 1. Ausführungen der Erfindung und ein Herstellungsverfahren sind Gegenstände von Unteransprüchen.According to the invention, this object is achieved by a work fabric with the features of claim 1. Executions of Invention and a manufacturing process are subjects of subclaims.

Durch das Einbringen von thermoplastischen Folien gelingt eine wesentliche Verbesserung der Impaktbeständigkeit und des Durchbrandverhaltens der duroplastischen Faserverbund­ werkstoffe. Die Kerbempfindlichkeit wird wesentlich redu­ ziert. Die Schwingungsfestigkeit wird durch die Zähigkeit der Thermoplastfolie verbessert. Auch das Brandverhalten des Bauteils wird durch die Thermoplastfolie als Brand­ sperrschicht verbessert. Auftretende Schäden breiten sich durch die elastischen Eigenschaften der Thermoplastfolien nicht durch das ganze Bauteil auf, Ablösungen von Schich­ ten erfolgen kaum mehr. Dadurch ist die Damagetoleranz ver­ bessert. Die Thermoplaste verringern zusätzlich die feuchte Aufnahme des Werkstoffs, da sie als feuchte Sperrschichten wirken. Das Gewicht des Bauteils steigt nicht wesentlich.By inserting thermoplastic films a significant improvement in impact resistance and the burn-through behavior of the thermosetting fiber composite  materials. The notch sensitivity is significantly reduced graces. The vibration resistance is determined by the toughness the thermoplastic film improved. Also the fire behavior of the component is caused by the thermoplastic film as a fire barrier layer improved. Damage that occurs spreads due to the elastic properties of the thermoplastic films not through the entire component, detachments from Schich hardly anymore. This means that the tolerance for damage is ver improves. The thermoplastics also reduce the moisture Absorption of the material as it acts as a damp barrier Act. The weight of the component does not increase significantly.

Erfindungsgemäß wechseln sich die Schichten von Duroplast und Thermoplast gegenseitig ab, wobei bevorzugt außen Duro­ plastschichten liegen. In einem Beispiel sind 16 Duroplast­ prepregs mit 15 dazwischenliegenden Lagen Thermoplastfolie verbunden. Möglich ist sowohl ein unidirektionaler als auch ein multidirektionaler Lagenaufbau.According to the invention, the layers of thermoset change and thermoplastic from each other, preferably outside Duro plastic layers lie. In one example, 16 are thermosets prepregs with 15 layers of thermoplastic film in between connected. Both a unidirectional and is possible a multi-directional layer structure.

In einer Ausführung liegt die Dicke der Thermoplastschichten zwischen 0,2 und 0,01 mm. Sie liegt bevorzugt zwischen 0,01 und 0,02 mm. Die Dicke der Duroplaste übersteigt in der Regel die der Thermoplastschichten. Im Ausführungsbeispiel sind es 0,125 mm.In one embodiment, the thickness of the thermoplastic layers is between 0.2 and 0.01 mm. It is preferably between 0.01 and 0.02 mm. The thickness of the thermosets exceeds in the Rule of thermoplastic layers. In the embodiment it is 0.125 mm.

Die Thermoplastschichten können sowohl verstärkt als auch unverstärkt eingesetzt werden. Besonders günstig ist es, Folien zu verwenden.The thermoplastic layers can be reinforced as well be used unreinforced. It is particularly cheap To use foils.

Als Duroplastwerkstoffe eignen sich Polyimid (PI), Bisma­ leinimid (BMI), modifizierte BMI-Systeme oder Expoxidharz­ systeme. Polyimide (PI), Bisma are suitable as thermoset materials linimide (BMI), modified BMI systems or epoxy resin systems.  

Als Thermoplaste eignen sich besonders Polyetheretherketon (PEEK), Perfluorethylenpropylen (FEP), thermoplastisches Polyimid (PI).Polyetheretherketone are particularly suitable as thermoplastics (PEEK), perfluoroethylene propylene (FEP), thermoplastic Polyimide (PI).

Die Herstellung erfolgt erfindungsgemäß in einem Schritt, das heißt das Auflaminieren, das Bilden des Verbunds und das Aushärten der Duroplastprepregs geschieht gleichzeitig unter Einwirkung von Hitze und Druck. Alle bekannten Auto­ klav-, Preß- oder Wickeltechniken sind prinzipiell anwend­ bar.According to the invention, the production takes place in one step, that is, the lamination, the formation of the composite and the thermoset prepregs harden at the same time under the influence of heat and pressure. All known car In principle, clav, pressing or winding techniques are used bar.

Eine Ausführung der Erfindung wird anhand dreier Figuren gezeigt.An embodiment of the invention is based on three figures shown.

Es zeigen:Show it:

Fig. 1 Schnitte durch einen erfindungsgemäßen Werkstoff, FIG. 1 cuts through an inventive material,

Fig. 2 und 3 Ultraschalldarstellungen von Schäden nach einem Impakt an einem Bauteil des Standes der Technik (Fig. 2) und an einem erfindungsgemäßen Bauteil (Fig. 3). Fig. 2 and 3 ultrasound representations of damage following a impact on a component of the prior art (Fig. 2) and on an inventive component (Fig. 3).

Fig. 1 zeigt zwei Schnitte durch einen erfindungsgemäßen Werkstoff. Der Werkstoff besteht aus faserverstärkten Duro­ plastschichten D und unverstärkten Thermoplastschichten T. Der Duroplast ist hier mit unidirektionalen Fasern ver­ stärkt. Das obere Foto zeigt einen Schnitt senkrecht zu den Fasern, das untere Foto zeigt einen Schnitt parallel zu den Fasern. Die Fasern sind oben als helle Punkte zu erkennen, unten als helle Streifen. Zwischen den faserverstärkten Duroplastschichten D liegen abwechselnd die dunklen Thermo­ plastschichten T. Fig. 1 shows two sections through a material according to the invention. The material consists of fiber-reinforced Duro plastic layers D and unreinforced thermoplastic layers T. The thermoset is reinforced with unidirectional fibers. The upper photo shows a section perpendicular to the fibers, the lower photo shows a section parallel to the fibers. The fibers can be seen as light dots at the top and light stripes at the bottom. Between the fiber-reinforced Duroplastschichten D are alternately dark thermoplastic layers T.

Fig. 2 zeigt einen Ultraschall-Scan eines Werkstücks aus faserverstärkten Duroplastschichten ohne dazwischenliegende Thermoplastschichten. Das Werkstück ist am Rand eingespannt und wurde von einem Probekörper in der Mitte mit 24 J Ener­ gie getroffen. Deutlich zu erkennen sind die geschädigten Bereiche, in denen sich die Schichten voneinander gelöst haben. Da dort der Schall an den Grenzflächen diffus reflek­ tiert wird, erscheinen die geschädigten Bereiche auf dem Foto schwarz. Fig. 2 shows an ultrasonic scanning of a workpiece of fiber reinforced Duroplastschichten without intervening thermoplastic layers. The workpiece is clamped on the edge and was hit by a specimen in the middle with 24 J energy. The damaged areas in which the layers have come apart are clearly visible. Since the sound is diffusely reflected at the interfaces, the damaged areas appear black in the photo.

Fig. 3 zeigt einen Ultraschall-Scan eines Werkstoffs aus faserverstärkten Duroplastschichten mit erfindungsgemäß dazwischen angeordneten Thermoplastschichten. Nach Aufprall des gleichen Prüfkörpers mit der gleichen Energie ist nur ein geringer Schaden zu erkennen. Die schwarzen Schichten, die Auflösungen des Verbandes zeigen, sind wesentlich kleiner als bei dem Werkstoff, der nicht mit Thermoplast­ folien verstärkt wurde. Fig. 3 shows an ultrasonic scanning of a material of fiber-reinforced Duroplastschichten with the present invention interposed thermoplastic layers. After the impact of the same test specimen with the same energy, only minor damage can be seen. The black layers, which show dissolutions of the bandage, are much smaller than with the material that was not reinforced with thermoplastic films.

Claims (6)

1. Werkstoff für schlagbeanspruchte Bauteile, wie Vorder­ kanten von Tragflächen oder Leitwerken an Fluggeräten oder von Karosserieteilen an Fahrzeugen, enthaltend
  • - mehrere faserverstärkte Duroplastschichten (D) und
  • - mehrere dazwischenliegende Thermoplastschichten (T).
1. Containing material for components subject to impact, such as leading edges of wings or tail units on aircraft or of body parts on vehicles
  • - Several fiber-reinforced thermosetting layers ( D ) and
  • - Several intermediate thermoplastic layers ( T ).
2. Werkstoff nach Anspruch 1, gekennzeichnet durch eine Dicke der Thermoplastschichten (T) zwischen 0,2 und 0,01 mm, bevorzugt zwischen 0,02 und 0,01 mm.2. Material according to claim 1, characterized by a thickness of the thermoplastic layers ( T ) between 0.2 and 0.01 mm, preferably between 0.02 and 0.01 mm. 3. Werkstoff nach Anspruch 1 oder Anspruch 2, dadurch gekennzeichnet, daß der Thermoplast unverstärkt in Folienform eingesetzt ist.3. Material according to claim 1 or claim 2, characterized characterized in that the thermoplastic is not reinforced in Foil form is used. 4. Werkstoff nach einem der vorhergehenden Ansprüche, gekennzeichnet durch die Verwendung von Polyimid (PI) oder Bismaleimimid (BMI) als Duroplast.4. Material according to one of the preceding claims, characterized by the use of polyimide (PI) or bismaleimimide (BMI) as a thermoset. 5. Werkstoff nach einem der vorhergehenden Ansprüche, gekennzeichnet durch die Verwendung von Polyether­ etherketon (PEEK), Perfluorethylenpropylen (FEP) oder Polyimid (PI) als Thermoplast. 5. Material according to one of the preceding claims, characterized by the use of polyether etherketone (PEEK), perfluoroethylene propylene (FEP) or polyimide (PI) as a thermoplastic.   6. Verfahren zur Herstellung eines Werkstoffs nach einem der vorhergehenden Ansprüche, gekennzeichnet durch wechselnde Schichtung von unausgehärteten Duroplast­ prepregs und Thermoplastfolien und anschließendes Aushärten und Laminieren in einem Arbeitsgang durch Anwendung von Druck und Wärme.6. Process for producing a material according to a of the preceding claims, characterized by alternating layering of uncured thermoset prepregs and thermoplastic films and subsequent Cure and laminate in one step Application of pressure and heat.
DE3836442A 1988-10-26 1988-10-26 Impact-resistant material for flying objects Ceased DE3836442A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE3836442A DE3836442A1 (en) 1988-10-26 1988-10-26 Impact-resistant material for flying objects

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Application Number Priority Date Filing Date Title
DE3836442A DE3836442A1 (en) 1988-10-26 1988-10-26 Impact-resistant material for flying objects

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DE3836442A1 true DE3836442A1 (en) 1990-05-03

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Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4404604A1 (en) * 1994-02-14 1995-08-17 Hella Kg Hueck & Co Plastics lighting reflectors esp. for motor vehicle headlamps
EP0730951A1 (en) * 1995-03-04 1996-09-11 British Aerospace Public Limited Company A composite laminate
WO1998038031A2 (en) * 1997-02-27 1998-09-03 Advanced Composites Group Ltd. Improvements in or relating to moulding methods and moulded articles
DE102009014973A1 (en) * 2009-03-18 2010-09-23 Deutsches Zentrum für Luft- und Raumfahrt e.V. Shuttering element for land vehicles and air- or spacecrafts, comprises a self-supporting external wall having fiber-reinforced polymer materials, and an internal wall having thermoplastic reinforced with thermoplastic fiber
DE102009037171A1 (en) * 2009-08-03 2011-02-10 Deutsches Zentrum für Luft- und Raumfahrt e.V. Wall element for land-, aircraft- and space vehicle, comprises molded part made of fiber-reinforced plastic material and having outer surface, where plastic film is disposed on outer surface with high tensile strength in area-wise manner
US7997534B2 (en) 2006-10-13 2011-08-16 Airbus Operations Gmbh Connecting structure for an aircraft or spacecraft and method for producing the same
WO2015004431A1 (en) * 2013-07-12 2015-01-15 The University Of Sheffield Composites
DE102006048641B4 (en) * 2006-10-13 2015-04-16 Airbus Operations Gmbh Connection structure for an aircraft or spacecraft and method of manufacturing the same
DE102015119351A1 (en) * 2015-11-10 2017-05-11 Proreta Tactical GmbH Ballistic protective plate and protection device
CN110216931A (en) * 2019-05-31 2019-09-10 华南理工大学 A kind of carbon fiber-reinforced resin mixing laminate and its forming method

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1569307A1 (en) * 1964-09-04 1970-03-26 E I Du Pont Nemours & Company Laminate
DE1959635A1 (en) * 1968-11-27 1970-06-11 Gen Tire & Rubber Co Laminate structure
US3616177A (en) * 1969-09-17 1971-10-26 Du Pont Laminar structures of polyimides and wire insulated therewith
DE2345796A1 (en) * 1972-09-11 1974-03-21 Rhone Poulenc Sa COMPOSITE PRODUCTS BASED ON HEAT RESISTANT RESIN
DE1694010B2 (en) * 1968-02-10 1975-04-17 Walter Dr.Phil. 6233 Kelkheim Dannoehl Reinforced plastic
GB2043532A (en) * 1979-01-26 1980-10-08 Toho Beslon Co Heat mouldable laminate and process of moulding same
DE2943964A1 (en) * 1979-10-31 1981-05-14 Technochemie Gmbh, Verfahrenstechnik, 6901 Dossenheim FIBER MATERIALS PRE-IMPREGNATED WITH DUROMER POLYIMIDE RESINS, AND METHOD FOR THE PRODUCTION THEREOF
EP0075033A1 (en) * 1981-09-18 1983-03-30 Hexcel Corporation Sheet material, process for its production and a composite structure

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1569307A1 (en) * 1964-09-04 1970-03-26 E I Du Pont Nemours & Company Laminate
DE1694010B2 (en) * 1968-02-10 1975-04-17 Walter Dr.Phil. 6233 Kelkheim Dannoehl Reinforced plastic
DE1959635A1 (en) * 1968-11-27 1970-06-11 Gen Tire & Rubber Co Laminate structure
US3616177A (en) * 1969-09-17 1971-10-26 Du Pont Laminar structures of polyimides and wire insulated therewith
DE2345796A1 (en) * 1972-09-11 1974-03-21 Rhone Poulenc Sa COMPOSITE PRODUCTS BASED ON HEAT RESISTANT RESIN
GB2043532A (en) * 1979-01-26 1980-10-08 Toho Beslon Co Heat mouldable laminate and process of moulding same
DE2943964A1 (en) * 1979-10-31 1981-05-14 Technochemie Gmbh, Verfahrenstechnik, 6901 Dossenheim FIBER MATERIALS PRE-IMPREGNATED WITH DUROMER POLYIMIDE RESINS, AND METHOD FOR THE PRODUCTION THEREOF
EP0075033A1 (en) * 1981-09-18 1983-03-30 Hexcel Corporation Sheet material, process for its production and a composite structure

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
- DE-Buch: ELIAS, H.G.: Neue polymere Werkstoffe 1969-1974, CarlHanser Verlag, München, Wien 1975, S. 140 *
- DE-Buch: Neue polymere Werkstoffe für die industrielle Anwendung, 2. Folge, Carl Hanser Verlag, München, Wien 1983, S. 286 *
DE-Z: SAECHTLING, Hansjürgen: Kunststoffe für den Innenausbau. In: VDI, Bd. 94, Nr. 29, 11.10.1952, S. 962-968 *

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4404604A1 (en) * 1994-02-14 1995-08-17 Hella Kg Hueck & Co Plastics lighting reflectors esp. for motor vehicle headlamps
EP0730951A1 (en) * 1995-03-04 1996-09-11 British Aerospace Public Limited Company A composite laminate
US5806796A (en) * 1995-03-04 1998-09-15 British Aerospace Public Limited Company Composite laminate
WO1998038031A2 (en) * 1997-02-27 1998-09-03 Advanced Composites Group Ltd. Improvements in or relating to moulding methods and moulded articles
WO1998038031A3 (en) * 1997-02-27 1998-12-17 Advanced Composites Group Ltd Improvements in or relating to moulding methods and moulded articles
DE102006048641B4 (en) * 2006-10-13 2015-04-16 Airbus Operations Gmbh Connection structure for an aircraft or spacecraft and method of manufacturing the same
US7997534B2 (en) 2006-10-13 2011-08-16 Airbus Operations Gmbh Connecting structure for an aircraft or spacecraft and method for producing the same
DE102009014973A1 (en) * 2009-03-18 2010-09-23 Deutsches Zentrum für Luft- und Raumfahrt e.V. Shuttering element for land vehicles and air- or spacecrafts, comprises a self-supporting external wall having fiber-reinforced polymer materials, and an internal wall having thermoplastic reinforced with thermoplastic fiber
DE102009014973B4 (en) * 2009-03-18 2011-10-27 Deutsches Zentrum für Luft- und Raumfahrt e.V. An element
DE102009037171A1 (en) * 2009-08-03 2011-02-10 Deutsches Zentrum für Luft- und Raumfahrt e.V. Wall element for land-, aircraft- and space vehicle, comprises molded part made of fiber-reinforced plastic material and having outer surface, where plastic film is disposed on outer surface with high tensile strength in area-wise manner
WO2015004431A1 (en) * 2013-07-12 2015-01-15 The University Of Sheffield Composites
US10618262B2 (en) 2013-07-12 2020-04-14 The University Of Sheffield Composites
DE102015119351A1 (en) * 2015-11-10 2017-05-11 Proreta Tactical GmbH Ballistic protective plate and protection device
DE102015119351B4 (en) 2015-11-10 2022-12-29 Proreta Tactical GmbH Ballistic protection device
CN110216931A (en) * 2019-05-31 2019-09-10 华南理工大学 A kind of carbon fiber-reinforced resin mixing laminate and its forming method

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