Det er stadig aukande interesse og fokus på energieffektivitet i byggesektoren, og passivhus er i dag på veg til å verte forskriftskrav i Noreg. Det er likevel stor ueinigheit i om passivhusa er godt nok utreda for konsekvensar i bruk til at dette kan skje i nærmaste framtid. Mykje av kritikken som vert retta mot passivhus er at det vert store problem med overvarme om sommaren.I denne rapporten er det presentert erfaringar frå passivhus i Noreg, Sverige og Danmark og gjennomført simuleringar. Målet er å finne ut om det er eit større problem med overvarme i passivhus enn i andre hus med lågare isolasjonsstandard.Erfaringane og simuleringane presentert i rapporten viser at isolasjonsevna ikkje har betydeleg innverknad på det termiske inneklimaet. Problem med overvarme vil difor oppstå i like stor grad i passivhus og bygg med lågare isolasjonsstandard. Simuleringane viser vidare at både passivhus og hus med lågare isolasjonsstandard vil har store problem med overvarme dersom det ikkje vert iverksatt tiltak for å hindre det. Tre strategiar for å redusere problemet er•Forhindre varmetilskot•Planlegge metode for å fjerne varmeoverskot•Sørgje for tilstrekkeleg varmelagringDersom desse strategiane vert gjennomført, vil den gode isolasjonsevna i passivhus stenge varmen ute og på denne måten sikre eit betre termisk inneklima på varme dagar enn hus med lågare isolasjonsstandard.

A pesquisa por novos materiais e processos que possam garantir aeronaves mais leves e operacionalmente mais viáveis, tem-se dado praticamente em todos os componentes de uma aeronave, com consequência direta no menor consumo de combustível e benefícios para o fabricante, operadores e a população em geral com aplicação do conceito de \'aeronave verde\'. Nestes quesitos, materiais/processos, destacam-se as ligas de alumínio (2xxx e 7xxx) e a solda por fricção mistura (FSW- Friction Stir Welding) por sua relação custo/benefício. A soldagem por fricção de elementos estruturais aeronáuticos formados de materiais dissimilares que possuem propriedades mecânicas distintas é de grande interesse para a indústria aeronáutica, devido aos ganhos de peso e de custo de operação que esse tipo de junção pode gerar. Sendo assim foram avaliadas as principais propriedades mecânicas de interesse e correlacionar com a microestrutura de ligas dissimilares e similares soldadas pelo processo de FSW e a inteiração destas com os meios ambiente, criogênico e corrosivo aos quais, aeronaves podem ser sujeitas durante os voos. Para tal desenvolvimento a solda dissimilar foi realizada com as ligas de alumínio-lítio 2050-T84 e alumínio 7050-T7451, enquanto que a solda similar foi realizada com a liga de alumínio-lítio 2198-T851. Foram feitas análises de ciclo térmico durante a soldagem e ambas juntas foram classificadas como solda quente, que prevê intensa variação microestrutural e afetam as propriedades mecânicas de dureza, a tenacidade fadiga e corrosão fadiga. A caracterização microestrutural realizada pela técnica de EBSD evidenciou alta quantidade de CAA que resultou na redução da dureza e aumento da tenacidade à fratura na região de contato entre a peça de trabalho e o ombro da ferramenta. De contra partida, a taxa de propagação de trinca por fadiga aumentou ligeiramente no meio salino. / The research for new materials and processes that produce light materials and operationally viable, has occurred in almost all the components of an aircraft, with a direct consequence in the lower fuel consumption and benefits for the manufacturing, operators and the population in application of the concept of \'green aircraft\'. In these questions, materials/processes, the most important are aluminum alloys (2xxx and 7xxx) and friction stir welding for their cost/benefit ratio. Friction stir welding of aeronautical structural elements made of dissimilar materials with distinct mechanical properties is of great interest to the aeronautical industry due to the weight and operating costs that this type of joint can result. Thus, the main mechanical properties of interest and correlate with the microstructure of dissimilar and similar alloys welded by the FSW and their interaction with the ambient, cryogenic and corrosive environments to which aircraft may be subject during flight. To development, the dissimilar weld performed with the lithium-aluminum alloys 2050-T84 and aluminum 7050-T7451, while the similar solder performed with the lithium-aluminum alloy 2198-T851. Thermal cycle analyzes were done during welding and both joints were classified as hot welding, which provides intense microstructural variation and affect the mechanical properties of hardness, fatigue toughness and fatigue corrosion. The microstructural characterization performed by the EBSD technique evidenced a high amount of CAA that resulted in low hardness and high fracture toughness in the region of contact between the workpiece and the tool shoulder. On the other hand, the rate of crack propagation by fatigue increased slightly in the saline atmosphere.

A pesquisa por novos materiais e processos que possam garantir aeronaves mais leves e operacionalmente mais viáveis, tem-se dado praticamente em todos os componentes de uma aeronave, com consequência direta no menor consumo de combustível e benefícios para o fabricante, operadores e a população em geral com aplicação do conceito de \'aeronave verde\'. Nestes quesitos, materiais/processos, destacam-se as ligas de alumínio (2xxx e 7xxx) e a solda por fricção mistura (FSW- Friction Stir Welding) por sua relação custo/benefício. A soldagem por fricção de elementos estruturais aeronáuticos formados de materiais dissimilares que possuem propriedades mecânicas distintas é de grande interesse para a indústria aeronáutica, devido aos ganhos de peso e de custo de operação que esse tipo de junção pode gerar. Sendo assim foram avaliadas as principais propriedades mecânicas de interesse e correlacionar com a microestrutura de ligas dissimilares e similares soldadas pelo processo de FSW e a inteiração destas com os meios ambiente, criogênico e corrosivo aos quais, aeronaves podem ser sujeitas durante os voos. Para tal desenvolvimento a solda dissimilar foi realizada com as ligas de alumínio-lítio 2050-T84 e alumínio 7050-T7451, enquanto que a solda similar foi realizada com a liga de alumínio-lítio 2198-T851. Foram feitas análises de ciclo térmico durante a soldagem e ambas juntas foram classificadas como solda quente, que prevê intensa variação microestrutural e afetam as propriedades mecânicas de dureza, a tenacidade fadiga e corrosão fadiga. A caracterização microestrutural realizada pela técnica de EBSD evidenciou alta quantidade de CAA que resultou na redução da dureza e aumento da tenacidade à fratura na região de contato entre a peça de trabalho e o ombro da ferramenta. De contra partida, a taxa de propagação de trinca por fadiga aumentou ligeiramente no meio salino. / The research for new materials and processes that produce light materials and operationally viable, has occurred in almost all the components of an aircraft, with a direct consequence in the lower fuel consumption and benefits for the manufacturing, operators and the population in application of the concept of \'green aircraft\'. In these questions, materials/processes, the most important are aluminum alloys (2xxx and 7xxx) and friction stir welding for their cost/benefit ratio. Friction stir welding of aeronautical structural elements made of dissimilar materials with distinct mechanical properties is of great interest to the aeronautical industry due to the weight and operating costs that this type of joint can result. Thus, the main mechanical properties of interest and correlate with the microstructure of dissimilar and similar alloys welded by the FSW and their interaction with the ambient, cryogenic and corrosive environments to which aircraft may be subject during flight. To development, the dissimilar weld performed with the lithium-aluminum alloys 2050-T84 and aluminum 7050-T7451, while the similar solder performed with the lithium-aluminum alloy 2198-T851. Thermal cycle analyzes were done during welding and both joints were classified as hot welding, which provides intense microstructural variation and affect the mechanical properties of hardness, fatigue toughness and fatigue corrosion. The microstructural characterization performed by the EBSD technique evidenced a high amount of CAA that resulted in low hardness and high fracture toughness in the region of contact between the workpiece and the tool shoulder. On the other hand, the rate of crack propagation by fatigue increased slightly in the saline atmosphere.

Im Legierungssytem Ni-Mn-Ga tritt bei Zusammensetzungen nahe der stöchiometrischen Zusammensetzung Ni2MnGa der magnetische Formgedächtniseffekt auf. Darunter versteht man die Dehnung durch Bewegung von Zwillingsgrenzen im Magnetfeld. Einkristalle aus Ni-Mn-Ga mit einer tetragonalen 5M-Martensitstruktur zeigen magnetisch erzeugbare Dehnungen von bis zu 6 %. Diese großen Dehnungen verbunden mit der schnellen Schaltfrequenz von Magnetfeldern machen den Effekt interessant für technische Anwendungen z. B. als Aktoren. Derartige Einkristalle sind schwierig und teuer herzustellen, weshalb für technische Anwendung Polykristalle von Interesse sind. Diese lassen sich im Allgemeinen leichter und preiswerter herstellen. Um den magnetischen Formgedächtniseffekt in Polykristalle einzustellen, werden grobkörnige, texturierte Proben mittels des Verfahrens der gerichteten Erstarrung hergestellt. Die Gefügeuntersuchungen erfolgen mit metallographischen Schliffen und die Kornorientierungen werden mit der EBSD-Technik bestimmt. Um das Gefüge zu vergröbern, werden Glühungen nach einer aufgebrachten Warmverformung untersucht. Zur Verringerung der für die Bewegung der Zwillingsgrenzen notwendigen Spannung (Zwillingsspannung) werden die Proben im Druckversuch mechanisch trainiert. Dabei kann die Zwillingsspannung teilweise unter die magnetisch erzeugbare Spannung auf die Zwillingsgrenzen (Magnetospannung) abgesenkt werden. Eine weitere Absenkung der Zwillingsspannung wird durch eine plattenförmige Probengeometrie mit Dicken im Bereich der Korndurchmesser erreicht. An derartigen Proben wird magnetisch rückstellbare freie Dehnung durch Zwillingsgrenzenbewegung erzielt.

Fatigue and fracture testing and analyses were performed on four engineering materials: a low-strength aluminum alloy (D16CzATWH), a high-strength aluminum alloy (Al7050-T7351), a low-strength steel (A36 steel), and a high-strength steel (9310 steel). Large-crack testing included compression precracked constant amplitude and compression precracked load reduction over a wide range of stress ratios. Single- and multiple-spike overload tests were conducted on some of the materials. Fatigue and small-crack testing were also performed at constant amplitude loading at a constant load ratio on the newly designed single edge notch bend specimen. Using the FADD2D boundary element code, two-dimensional stress analysis was performed on the new specimen to determine the stress intensity factor as a function of crack size for surface and through cracks at the edge notch. Collected fatigue crack growth rate data was used to develop a material model for the FASTRAN strip-yield crack growth code. FASTRAN was used to simulate the constant amplitude and spike overload tests, as well as the small-crack fatigue tests. The fatigue crack growth simulation results have shown that both low-cycle and high-cycle fatigue can be modeled accurately as fatigue crack growth using FASTRAN and that FASTRAN can be used to accurately predict the acceleration and retardation in fatigue crack growth rates after a spike overload. The testing has shown that the starting fatigue crack growth rate of any load-shedding test has significant influence on load history effects, with lower starting rates yielding lower crack growth thresholds and faster rates. Through inspection of fatigue surfaces, it has been shown that beveling of pin-holes in the crack growth specimens is necessary to ensure symmetric crack fronts and that the presence of debris along the fatigue surfaces can cause considerable crack growth retardation.

This work details an adaptation of the friction taper plug welding (FTPW) process to repair fatigue damage in 6.35mm AA 7050 t-7451 plate. Aircraft components experience fatigue damage around fastener holes. This damage can be mitigated by enlarging fastener holes. There is no effective repair procedure once holes reach a maximum allowable size. Damaged components must be replaced. A suitable repair process would lead to substantial savings in both time and money. A simulated repair process was developed by machining holes in 6.35mm AA 7050 t-7451 plate. These hoes were then plugged using the FTPW process. Microhardness testing and metallographic analysis were used to map the effects of thermomechanical processing in a repair. Simulated repairs were machined into a tensile sample. A 6.35mm hole was bored axially through the repair center to simulate a new fastener hole. Static tensile testing was used to measure ultimate tensile strength and yield strength in the repair. Samples were also subjected to fatigue testing at stresses ranging from 170MPa to 340MPa at a stress ration of R=0.1. The same tensile and fatigue testing was done with unaltered material. A 7.94mm hole was bored through the center of this material to simulate an enlarged fastener hole. This provides baseline level of properties. Ultimate tensile strength of the base material is reduced by 15% and yield strength by 29%. Fatigue properties at a stress of 303 MPa are reduced by 22%. Fracture surfaces of poor performing samples reveal defects on the weld interface.

<p dir="ltr">The production of aluminum components by laser powder bed fusion additive manufacturing (LPBF-AM) offers simultaneous weight reduction benefits through low material density and topology optimization. The primary limitation of the method – hot cracking in high-strength compositions – is addressed by the reactive additive manufacturing (RAM) process, which introduces ceramic-forming metallic particles to powder feedstock. <i>In situ</i> reactions subsequently inoculate equiaxed grains, prevent cracking, and strengthen the resulting alloy. The adoption of RAM alloys in aerospace applications requires the elimination of heterogeneous defects, requiring an understanding of laser processing effects and feedstock quality. To meet these needs, the collected work presents characterization methods based on x-ray tomography, seeking to establish novel descriptors for RAM feedstock and microstructures.</p><p dir="ltr">In the first two chapters, x-ray microscopy (XRM) is applied to produce multi-dimensional particle measurements for feedstock powder qualification. Evolving existing measure-and-classify processes, a method is described to characterize AA7050-RAM2 feedstock that is rapid, interpretable, and descriptive of the highly deformed particles observed. Applying the developed methodology to an analysis of recycled AA7050-RAM2 rationalizes decreasing particle sizes by identifying the selective removal of specific shape classes. Combined with quantitative electron microscopy of particle microstructures, sieving and heat effects are comprehensively reported, demonstrating a modernized powder analysis workflow.</p><p dir="ltr">In the second two chapters, the characteristic reactions seen in LPBF of AA7050-RAM2 are characterized. Correlative SEM/EDS and nanoindentation identified reactive phases and their mechanical properties and found a correlation between the extent of the Al-Ti reaction and the degree of particle remelting. Using 3D XRM measurements, the populations and distributions of low- and high-reaction particles were quantified, raising questions regarding homogenization mechanisms in laser-processed, particle-reinforced alloys. Thus, thin wall samples were produced and characterized to visualize convective and thermal history effects within symmetrical tracks. Novel observed mechanisms include thermal grain coarsening, keyhole-induced convection, and pore segregation by size. The accumulated microstructural quantification and novel perspective on pore movement provide a basis to improve contouring processes in RAM alloys and to better align fluid dynamics models of printing with experimental data.</p>

Made available in DSpace on 2017-07-21T20:43:45Z (GMT). No. of bitstreams: 1 Natany Dayani de Souza Assai.pdf: 1950917 bytes, checksum: a6c8b87bcaabbbdbf5ca798360a90bcc (MD5) Previous issue date: 2014-08-27 / The residual stress may decrease and redistribute through a process called relaxation. The relaxation of the residual stress is an important phenomenon in relation to the estimated fatigue resistance of the material and can occur due to static mechanical loading, thermal, cyclical and extension fatigue effects. Residual stresses are usually harmful for overlapping the operating voltage, while the fatigue resistance of metals and alloys can be improved by compressive residual stresses present in the surface layer by means of shot peening surface. The fatigue life with the compressive residual stress field caused by shot peening or sophisticated models for modeling voltage field Compressive Residual (CTRC) usually does not take into account the possibility of this change during the cyclic loading, ie , place the relaxation process, which also changes the fatigue life. This study aimed to obtain the residual stress profile relaxation by cyclic loading on aluminum alloy samples 7050- T7541 with shot peening glass and ceramics subjected to axial fatigue test. The technique for determining the residual stress was the X-ray diffraction for measuring accurately the redistribution of residual stresses along the depth of fatigue produced by the process. The removal of layers of material was performed by electrolytic attack. Hereby, it was possible to establish the relationship between the maximum stress and number of cycles in relation to the greater or lesser relaxation test specimens in different regimes of cyclic peening conditions with spherical glass and ceramics in the longitudinal and transverse directions. The results showed that the samples with the longitudinal direction shot peening redistribution showed higher compressive residual stresses in the transverse direction along the depth. For the samples of shot peening ceramic was virtually no relaxation on the surface only in depth when compared to the original profile, samples of ceramic shot peening obtained relaxation in remote locations of the surface, due to the influence of roughness. The redistribution of stresses for samples of shot peening glass were higher than those with shot peening ceramic along the depth in all cyclic regimens studied in the L and T directions. The residual stress relaxation occurred in both directions did not compromise beneficial effect of shot peening increase the fatigue life thereof, in relation to the base material. / As tensões residuais podem diminuir e se redistribuir por meio de um processo chamado relaxação. A relaxação das tensões residuais é um fenômeno importante no que se refere à previsão da resistência à fadiga dos materiais e pode ocorrer devido a carga mecânica estática, térmica, cíclica como efeitos de extensão da fadiga. As tensões residuais geralmente são prejudiciais por se sobreporem às tensões de serviço, enquanto a resistência à fadiga dos metais e ligas pode ser melhorada por tensões residuais compressivas presentes nas camadas superficiais por meio do tratamento de superfície de shot peening. A vida em fadiga com o campo de tensão residual compressiva originada pelo shot peening ou modelos sofisticados para a modelagem do Campo de Tensão Residual Compressivo (CTRC), geralmente não leva em consideração, a possibilidade deste alterar-se durante o carregamento cíclico, ou seja, ocorrer o processo de relaxação, que também altera a vida em fadiga. Este trabalho teve como objetivo obter o perfil de tensão residual de relaxação por carregamento cíclico em amostras de liga de alumínio 7050- T7541 com shot peening de vidro e cerâmica submetidas a ensaio de fadiga axial. A técnica para determinação das tensões residuais foi a difração de raios X que permite medir com precisão a redistribuição de tensões residuais ao longo da profundidade produzidas pelo processo de fadiga. A remoção das camadas de material foi realizada por ataque eletrolítico. Por meio deste, foi possível constatar a relação entre a tensão máxima e quantidade de ciclos no que se refere à maior ou menor relaxação de corpos de prova em diferentes regimes cíclicos nas condições de shot peening com esfera de vidro e cerâmica nas direções longitudinal e transversal à laminação.Os resultados mostraram que as amostras com shot peening na direção longitudinal apresentaram redistribuição de tensões residuais compressivas maiores que no sentido transversal ao longo da profundidade. Para os corpos de prova de shot peening de cerâmica praticamente não houve relaxação na superfície apenas na profundidade quando comparado ao perfil original, as amostras de shot peening de cerâmica obtiveram a relaxação em posições mais afastadas da superfície, devido a influência da rugosidade. A redistribuição de tensões para as amostras de shot peening de vidro foram superiores em relação aquelas com shot peening de cerâmica ao longo da profundidade em todos os regimes cíclicos estudados nas direções L e T. A relaxação de tensão residual ocorrida em ambas direções não comprometeu o efeito benéfico do shot peening no aumento da vida em fadiga das mesmas em relação ao material base.

Ce travail vise à comprendre l’évolution de la texture cristallographique et l’anisotropie du comportement mécanique après laminage à chaud et traitements thermiques d’un Al-Cu-Li 2050 et d’un Al-Zn-Mg-Cu 7050, et expliquer leurs différences. La texture est analysée par EBSD et RX après des essais de compression plane à chaud et après des laminages à chaud industriels. L’anisotropie est étudiée sur des tôles fortes industrielles après différents détensionnements et dans différents états microstructuraux par des essais de traction à 0°, 45° et 90° par rapport à DL. Enfin, nous comparons nos mesures à des résultats simulés par des modèles de plasticité cristalline (modèles de Taylor). Il est montré que, déformés dans des conditions identiques, les deux alliages développent les mêmes textures de laminage jusqu'à une déformation de 2.6. La présence de 1% massique de Li n’est à priori pas responsable d’une texture particulière. En revanche la température de laminage, qui est généralement plus élevée pour les Al-Cu-Li que pour les Al-Zn-Mg-Cu, a un impact important aux grandes déformations, notamment en favorisant la composante Laiton {110}<112>. L'anisotropie d'une tôle laminée de 2050 est pour une large part due à la texture cristallographique. Elle augmente quand un détensionnement est effectué par traction dans la direction DL et diminue quand il est effectué à 45°/DL. La précipitation durcissante, composée de T1 Al2CuLi en forme de plaquettes sur les plans {111}Al, augmente la résistance de la direction préalablement tractionnée mais n'est pas responsable dans nos conditions expérimentales d'une forte aggravation de l'anisotropie. Dans le 7050, l'anisotropie diminue entre l’état mûri naturellement et l’état sur-revenu. La précipitation de sur-revenu du 7050 atténue l'effet de la texture cristallographique sur l'anisotropie et rend, en comparaison, le 2050 d’autant plus anisotrope. / This work aims to understand hot rolling texture evolution and anisotropy of mechanical behaviour on an Al-Cu-Li 2050 and an Al-Zn-Mg-Cu 7050, and aims to explain their differences. Crystallographic textures are analysed by EBSD and X-ray after hot plane strain compressions and after industrial hot rolling. Anisotropy of industrial hot rolled plates is investigated after different stretching and different ageing treatments by means of tensile tests at 0°, 45° and 90° to RD. Experimental results are compared to predictions using plasticity models (Taylor models). It is shown that, under the same processing conditions, the two alloys develop the same rolling textures up to strain of 2.6 ; it can be concluded that the presence of 1wt% of Li does not by itself favour a particular texture. However, it is shown that Brass component {110}<112> is favoured by an increasing rolling temperature, which is generally higher in the Al-Cu-Li than in the Al-Zn-Mg-Cu. Anisotropy of hot rolled 2050 is for a large part caused by crystallographic texture. It increases when stretch axis is at 0° and decreases when stretch axis is at 45°. Hardening precipitation, made by plate shape T1 Al2CuLi lying on the {111}Al, increases yield strength in the stretched direction but it is not responsible in our experimental conditions for a high increase of anisotropy. Anisotropy of 7050 is less important in the over aged state than in the natural aged state. Over ageing precipitation of 7050 reduces the effect of crystallographic texture on the anisotropy and makes 2050 appearing much more anisotropic.

In der vorliegenden Arbeit werden die Zusammenhänge zwischen der magnetischen Mikrostruktur und der Ausrichtung der Kristallite, sowohl in Sintermagneten als auch in feinkristallinen, warmumgeformten Magneten auf Nd2Fe14B- und Pr2Fe14B-Basis, untersucht. Die EBSD-Technik (electron backscatter diffraction) wurde für Sintermagnete und für feinkristalline, warmumgeformte Magnete auf Nd2Fe14B-Basis erstmals erfolgreich eingesetzt, um eine quantitative Texturanalyse durchzuführen. Die Polfiguren des hoch texturierten Sintermagneten bzw. warmumgeformten Magneten zeigen eine stark ausgeprägte [001] Fasertextur. Aus dem Vergleich von REM-, EBSD- und Kerr-Untersuchungen an ein- und derselben Probenoberfläche der Sintermagnete konnte quantitativ gezeigt werden, wie die Domänenstruktur von der individuellen Orientierung der Nd2Fe14B-Körner abhängt. Die Domänenstruktur der hoch texturierten Sintermagnete weist auf eine starke magnetostatische Wechselwirkung zwischen den Kristalliten hin. In den Heißpresslingen und in den warmumgeformten Magneten auf Nd2Fe14B-Basis und Pr2Fe14B-Basis wurden Wechselwirkungsdomänen mittels Magnetkraftmikroskopie nachgewiesen. Die Wechselwirkungsdomänen, deren Größe stark vom Umformgrad abhängt, sind immer größer als die einzelnen Kristallite. Die Bildung der Wechselwirkungsdomänen wurde auf magnetostatische Wechselwirkung zwischen den Kristalliten zurückgeführt, was mit Hilfe der Wohlfarth-Analyse der Remanenzverhältnisse bestätigt werden konnte. Die magnetische Mikrostruktur der warmumgeformten Magnete wurde mit einem Modell, das auf der Bildung von Ketten magnetischer Momente (parallel zur Kettenachse) beruht, beschrieben. Unterhalb der Temperatur des Spinumorientierungsüberganges der Nd2Fe14B-Phase weisen die Sintermagnete rechteckige Domänenmuster auf. Diese magnetische Mikrostruktur wird durch eine spezifische Verteilung der Domänenwände in Bezug auf Änderungen der magnetischen Anisotropie ausgebildet. Im Gegensatz dazu ändern sich die Wechselwirkungsdomänen in dem warmumgeformten Magneten nicht, was auf die starke magnetostatische Wechselwirkung zwischen den Kristalliten zurückgeführt wurde. / In this work, the correlation between magnetic domain structure and grain alignment in sintered and die-upset magnets, based on Nd2Fe14B and Pr2Fe14B compounds, is investigated. For the first time, EBSD (electron backscatter diffraction) has been successfully applied to conduct a quantitative analysis of the texture of sintered and die-upset Nd2Fe14B magnets. Pole figures of the highly textured sintered and die-upset magnets show a strong [001] fiber texture. By a comparison of SEM, EBSD and Kerr images of the same surface of sintered magnets it was possible to correlate the domain structure of individual grains to their orientation. The domain structure of the highly textured sintered magnet indicates to the presence of a strong magnetostatic interaction between individual grains. Interaction domains have been studied in hot-pressed und die-upset magnets based on Nd2Fe14B and Pr2Fe14B compounds by MFM. The lateral expansion of interaction domains is always larger than grain size and depends from the degree of deformation. The formation of interaction domains is attributed to magnetostatic interaction between individual grains, which has been confirmed by a Wohlfarth’s analysis of the remanence ratio. The magnetic domain structure of die-upset magnets can be described by a model, based on the formation of chains of magnetic moments parallel to the chain direction. Below the spinreorientation temperature of the Nd2Fe14B phase, sintered magnets show a rectangular domain structure. This domain structure is formed by a specific domain wall distribution corresponding to changes of the magnetocrystalline anisotropy. In contrast to this, the interaction domains in the die-upset magnets show no changes below the spinreorientation temperature, what can be also ascribed to the magnetostatic interaction between individual grains.