Spelling suggestions: "subject:"[een] CARBON FIBER COMPOSITES"" "subject:"[enn] CARBON FIBER COMPOSITES""
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[pt] ANÁLISE EXPERIMENTAL DA ADERÊNCIA ENTRE O CONCRETO E COMPÓSITOS COM TECIDO DE FIBRAS DE CARBONO / [en] EXPERIMENTAL ANALISYS ON BOND BETWEEN CONCRETE AND CARBON FIBER COMPOSITES FABRICJULIANA MARTINELLI MENEGHEL 02 January 2006 (has links)
[pt] É descrito neste trabalho um programa experimental sobre a
aderência entre os
compósitos com tecido de fibras de carbono e o concreto.
Este programa
experimental consistiu em ensaios de tração-compressão de
corpos-de-prova
compostos de dois blocos de concreto (móvel e fixo)
colados por tiras de tecido
de fibra de carbono coladas nos lados opostos desses
blocos. Foram ensaiados
nove corpos-de-prova, com três resistências à compressão
aos 28 dias de 20,5
MPa, 28,7 MPa e 38,1 MPa e duas larguras do tecido iguais
a 50 mm e 100 mm.
Todos os corpos-de-prova foram concretados, instrumentados
e ensaiados no
Laboratório de Estruturas e Materiais da PUC-Rio. O
objetivo deste trabalho foi
estudar a influência da resistência do concreto e da
largura do tecido de fibra de
carbono sobre a resistência de aderência do sistema. Os
resultados mostraram
que a resistência de aderência pode ser considerada
independente da resistência
do concreto e da largura do tecido. Foi obtido, neste
estudo, um valor
característico de 1,45 MPa para a resistência de aderência. / [en] An experimental study on the bond between carbon fiber
fabric composites and
concrete is described in this work. This experimental
program consisted of
tension-compression tests of specimens with two concrete
blocks (movable and
fixed) jointed by carbon fiber fabric strips bonded on two
opposite sides of these
blocks. Nine specimens, with three concrete compressive
strength of 20,5MPa ,
28,7MPa and 38,1MPa at 28 days and two fabric width of 50
mm and 100
mm, were tested. All specimens had the same geometrical
characteristics. All the
specimens were cast, instrumented and tested in the
Structural and Materials
Laboratory at PUC-Rio. The objective of this work was to
study the influence of
concrete strength and the width of the fabric on the bond
strength of the system.
The results showed that the ultimate bond strength may be
considered
independent of concrete strength and of the width of the
fabric. A characteristic
value of 1.45 MPa was found for the bond strength.
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Fracture Toughness of Carbon Fiber Composite MaterialRea, Allison 14 December 2022 (has links)
No description available.
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Synthesis and Characterization of High Performance Polymers for Gas Separation and Water Purification Membranes and as Interfacial Agents for Thermplastic Carbon Fiber CompositesJoseph, Ronald Matthew 03 July 2018 (has links)
This dissertation focuses on the synthesis and characterization of high performance polymers, specifically polybenzimidazoles (PBIs) for gas separation applications and polyimides (PI) for water purification and as interfacial agents for thermoplastic carbon fiber composites.
Two methods for improving the gas transport properties (for H2/CO2 separation) of a tetraaminodiphenylsulfone (TADPS)-based polybenzimidazole were investigated. Low molecular weight poly(propylene carbonate) (PPC) and poly(ethylene oxide) (PEO) were incorporated as sacrificial additives that could be removed via a controlled heat treatment protocol. PBI films containing 7 and 11 wt% PPC (blend) and 13 wt% PEO (graft) were fabricated and the gas transport properties and mechanical properties after heat treatment were measured and compared to the PBI homopolymer. After heat treatment, the 7 wt% PPC blend exhibited the highest performance while retaining the toughness exhibited by the PBI homopolymer.
Novel sulfonated polyimides and their monomers were synthesized for use as interfacial agents and water purification membranes. Polyimides are high performance polymers that have high thermal, mechanical, and chemical stability. The objective was to assess structure-property relationships of novel sulfonated polyimides prepared by direct polymerization of the diamine monomers. A series of sulfonated polyimides was synthesized using an ester-acid polymerization method with varying degrees of sulfonation (20%, 30%, and 50% disulfonated and 50% and 100% monosulfonated polyimides). The results showed that the toughness of the polyimides in the fully hydrated state was much better than current commercial cation exchange membranes.
A 100% disulfonated polyimide (sPI) and poly(amic acid) salt (PAAS) using the same monomers used for the synthesis of Ultem® were utilized as suspending agents for the fabrication of coated sub-micron polyetherimide (PEI) particles. Sub-micron particles were obtained using 1 wt% PAAS and 4 wt% sPI to coat the PEI. The PEI particles were coupled onto ozone treated carbon fibers using a silane coupling agent. SEM images showed a significant amount of particle coating on the treated carbon fibers compared to the non-silane treated carbon fibers. / PHD
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[en] EXPERIMENTAL INVESTIGATION OF THE BOND STRENGTH BETWEEN CFC-CONCRETE UNDER IMPACT LOADING / [pt] VERIFICAÇÃO EXPERIMENTAL DA ADERÊNCIA CFC-CONCRETO COM CARREGAMENTO DE IMPACTOANTONIO ROGERIO PELLISSARI 10 April 2008 (has links)
[pt] Neste trabalho realizou-se uma investigação experimental
sobre os efeitos de forças de impacto sobre a resistência
de aderência entre compósitos de fibras de carbono e o
concreto. O programa experimental consistiu de ensaios de
flexão de corpos-de-prova constituídos de dois blocos de
concreto unidos por uma rótula na região superior
(comprimida) e por tiras de compósito de fibras de
carbono coladas nas faces inferiores dos blocos. Foram
ensaiados 23 corpos-deprova, com resistências à compressão
do concreto variando de 25 MPa a 35 MPa. A principal
variável foi a taxa de carregamento ( expressa em termos de
tensão de aderência), variou entre 6,06 MPa/s (estático) a
3.690.485 MPa/s (dinâmico). Os resultados mostraram que a
resistência de aderência aumenta com o aumento da taxa de
carregamento. / [en] An experimental investigation on the effects of impact
loads on the bond
strength between carbon fiber composite and concrete is
described in this work.
The objective was to investigate the influence of loading
rate on the bond
strength. Concrete-fiber specimens were tested under
loading rates varying from
a minimum of 6,06 MPa/s (static) to a maximum of 3.690.485
MPa/s. In
addition, twenty tree concrete prisms were tested under
different loading rates in
order to investigate the effects of the loading rate on the
tensile strength of
concrete and carbon fiber separately. The results show that
the bond strength
increase with the increase of the loading rates.
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[en] STRUCTURAL RELIABILITY ANALYSIS APPLICATION TO THE DESIGN OF CARBON FIBRES REINFORCED POLYMER SHEAR STRENGTHENING OF REINFORCED CONCRETE BEAMS / [pt] ANÁLISE DE CONFIABILIDADE DE ESTRUTURAS APLICADA AO PROJETO DE REFORÇO À FORÇA CORTANTE DE VIGAS EM CONCRETO ARMADO COM COMPÓSITOS DE FIBRAS DE CARBONOMARCELA TORNO DE AZEREDO LOPES 06 December 2007 (has links)
[pt] A análise de confiabilidade aplicada ao projeto de
estruturas é uma
ferramenta que permite avaliar a probabilidade de falha da
estrutura para um
certo modo de comportamento e a sensibilidade deste
projeto em relação às
variáveis consideradas. Neste trabalho a análise de
confiabilidade é aplicada
ao projeto de reforço à força cortante com compósitos de
fibras de carbono de
vigas em concreto armado. Inicialmente, modelos e
prescrições normativas
para verificar a capacidade resistente do reforço à força
cortante são
implementados em MathCad. Os resultados teóricos são
comparados com os
obtidos de programas experimentais realizados por diversos
pesquisadores.
Posteriormente, um programa de confiabilidade de
estruturas é implementado
em liguagem C onde é utilizado o método FORM First Order
Reliability
Method. Este programa permite: avaliar a confiabilidade à
força cortante de
seções de vigas de concreto armado reforçadas ou não e
dimensionar a taxa
geométrica de reforço para um valor estabelecido de índice
de confiabilidade
de referência e este valor segue recomendações do Eurocode
EN1990 (2001).
As taxas geométricas de reforço são dimensionadas por dois
enfoques: o semiprobabilístico,
prática corrente de projetos, e o probabilístico, projeto
baseado
em confiabilidade. Os resultados obtidos são comparados.
No enfoque
probabilístico, as taxas geométricas de reforço são
calculadas estabelecendo
que o valor do índice de confiabilidade equivalente,
avaliado utilizando
formulação de sistemas em série, seja maior ou igual ao
valor do índice de
confiabilidade de referência. Os valores dos índices de
confiabilidade,
considerando ou não a formulação de sistemas em série, das
probabilidades
de falha e dos fatores de importância das variáveis
aleatórias são obtidos para
a seção sem e com reforço. As coordenadas dos pontos de
projeto e os
coeficientes parciais de segurança são obtidos para a
seção reforçada. / [en] Structural reliability analysis provides a prediction of
the structural
probability of failure against some behavior mode and the
design sensibility with
respect to the random variables evaluated at the design
point. In this research
the reliability analysis is applied to design the carbon
fibres reinforced polymer
shear strengthening of reinforced concrete beams. First,
models and code
recommendations, available in literature, to verify the
shear strengthening are
implemented in MathCad. Further, a structural reliability-
based software, using
the First Order Reliability Method (FORM), is implemented
in C programming
language. This software provides the evaluation of the
shear reliability of
reinforced concrete beams cross-sections, either
strengthened or not by CFRP,
and the shear reinforcement ratio for a target reliability
index. The target
reliability index is established as defined by Eurocode EN
1990 (2001). The
random variables probabilistic models are based upon
code`s recommendations
available in specialized literature. The shear
reinforcement ratio is designed by
two approaches: semi-probabilistic, as the current design
practice, and the
probabilistic, reliability-based design. The results are
compared. In the
probabilistic approach, the shear reinforcement ratio
design aims to obtain a
series system reliability index value larger than a
predefined target value. The
reliability index values, their corresponding failure
probabilities and the
percentages of total uncertainty associated to which
random variable arise from
reliability-based design, developed for either
strengthened or not reinforced
concrete beams cross-sections. For the strengthened cross-
sections, the
design point and the partial safety factors are also
obtained.
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The effect of cooling rate on toughness and crystallinity in poly(ether ketone ketone) (PEKK)/G30-500 compositesDavis, Kedzie 18 September 2008 (has links)
Six poly(ether ketone ketone)/carbon composite panels were manufactured from powder coated towpreg. All six panels were initially processed using a hot press equipped with controlled cooling. Four of the panels were used to investigate the effect of cooling rate on crystallinity. A fifth panel was used to investigate the effect of annealing the composite after completion of the standard fabrication process. The sixth panel was used to investigate changes in toughness due to manufacturing towpreg with polymer that had been reclaimed from the towpreg fabrication system’s air cleaner.
Cooling rates of 2°C/min, 4°C/min, 6°C/min, and 8°C/min resulted in composites with crystallinities of 33%, 27%, 24%, and 23%, respectively. The principal investigation of the effect of cooling rate on crystallinity and mode I and mode II strain energy release rates, G<sub>Ic</sub> and G<sub>IIc</sub>, respectively, showed that G<sub>Ic</sub> and G<sub>IIc</sub> values increase with increasing cooling rate. Comparison of the toughness values as a function of crystallinity showed that the dependence of toughness on crystallinity is approximately equivalent to the dependence of toughness on cooling rate.
Comparison of the data from the annealed panel to that from the analogous principal panel showed that annealing increased the crystallinity and decreased the mode I strain energy release rate. There was no effect, however, on the mode II strain energy release rate. Comparison of the data from the panel made with reclaimed polymer to that from its analogous principal panel showed that the reclaimed polymer panel had equivalent crystallinity and G<sub>Ic</sub> values. On the other hand, the G<sub>IIc</sub> values in this panel were lower than in the analogous principal panel. / Master of Science
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A Study on the Vibrational Performance Characteristics of an E22 Isolator After Outgassing and Bake-OutMelendez, Alma 01 June 2014 (has links) (PDF)
The launch environment experiences many vibration, shock, and acoustic loads. A great concern is the high random vibration levels that can damage components and spacecraft structures, which can cause a mission failure. An effective method of reducing high frequency energy is using isolators. Overall, the need for vibration isolation has been increasing because there has been an increase in the use of mechanisms in which vibrations are prevalent. In addition, there has not been extensive research on the effects of isolators that are outgassed and cured. Therefore, it is important to investigate and understand the vibrational effects on isolators. It is convenient to outgas and cure isolators for the benefit of some components because that eliminates contamination, but outgassing and bake-out could potentially affect the frequency response of the isolator system in a negative way. It is valuable to investigate how much outgassing and bake-out might affect the performance, if any, of the vibration isolator in order to benefit companies who may need that kind of information. The vibration isolators used for the purpose of this research were twenty E22-02-40 isolators provided by Barry Controls, a Hutchinson Group Company. The E22-02-40 isolators were outgassed and cured (heated at high temperatures) in order to be turned from grade C into grade A level for outgassing. Then the vibrational performance of those isolators were tested and compared to the isolators that were not outgassed and not cured. Vibration tests were run in the flat frequency spectrum and high frequency spectrum. The maximum percent difference occurred in the grade A level isolators, in which the first frequency mode increased by 33.3 % in the z direction from the grade C isolators. A numerical finite element analysis was performed on Abaqus/CAE in order to verify the experimental results. In addition, a swelling test was conducted on the isolators to test their physical characteristics change after they were outgassed and cured.
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Ανάλυση της απόκρισης σύνθετων πολυμερών υλικών υπό συνθήκες φωτιάς. Εφαρμογή σε αεροπορικές κατασκευές / Fire response of composite aerostructuresΣικουτρής, Δημήτριος 01 February 2013 (has links)
The current dissertation, titled “Fire Response of Composite aerostructures” deals with a crucial subject of the aeronautics industry that is the fire response of composite aerostructures, more specifically the issue of interest in this work is the fuselage fire burnthrough from an external liquid jet-fuel pool fire. Other fire issues that “bother” the aeronautics industry are the fire spread inside the cabin, smoke generation and toxicity of the fumes, but these are not handled in the current dissertation.
Aircraft structures are designed to withstand various loading scenarios during their operational life. These loading scenarios are associated to a great extent with normal aircraft operation (flight manoeuvres, take-off and landing). However there are situations where the aircraft structures are required to assure the safety of the passengers and crew. In the case of an emergency crash landing, the threat of an external jet-fuel fire always exists. Considering that the aircraft structure survives the impact, the survivability of the passengers and crew onboard the aircraft depends solely on the fire resistance of the aircraft structure. A measure of the fire resistance of an aircraft structure is the time needed for the flames to penetrate the fuselage and spread inside the cabin, the so-called, burn-through time.
So far, the aircraft fire resistance has been extensively studied by conducting lab, medium and full scale tests. The early lab scale tests were performed by the Federal Aviation Administration (FAA) and involved the Bunsen-burner flammability test of coupons for developing fire safe interior materials. As the application of polymer materials on aircrafts kept increasing, the problem of fire burn-through due to external fire emerged. Marker was one of the first to perform full-scale fuselage burn-through tests to access the insulating performance of materials. Also a statistical analysis was performed by Cherry and Warren that accessed and analyzed data from past accidents and their work resulted in proving the importance of fuselage fire hardening and the passengers’ lives that could be saved using low-cost solutions. These works led the FAA to proposed new fire testing procedures for aircraft materials.
The scope of this dissertation was to assess the performance of various structural materials in a pool-fire scenario. A simplified approach is made, approximating the pool-fire conditions with a flat panel burn-through test in accordance to the ISO2685:1998(E) Standard.
The originality of the present work comes from the fact that it incorporates a multistage approach in order to investigate the behaviour and response of composite aircraft structures in the possibility of a fire event. The current approach goes down on material level in order to investigate and model the deterioration (decomposition) of the polymer composite. Thus, it investigates and proposes a methodology of how the thermophysical properties of the composite are deteriorated due to the fire event. It proceeds into developing a progressive-damage material model (material properties varying with the deterioration degree) and finally implementing this custom material model into a commercial FE package and solving the loading scenarios.
Being more specific the current work begins with a quick review of the literature where incidents and work done on the burnthrough event for the past 20-30 years are summarized. It progresses then to presenting the various types of polymers used in the aircraft industry and their basic decomposition mechanisms, from the unsaturated polyesters to the epoxies and phenolics and in the end reference to the thermoplastics is made. Every organic material, hence, polymers used in aerospace applications, present a set of response characteristics when subjected to fire, specifically the heat release rate, thermal stability index, limiting oxygen index, flammability index, time-to-ignition, surface flame spread, mass loss, smoke density and smoke toxicity.
Following is the backbone of this dissertation, the kinetics modelling. Two approaches are made, one simplified using single stage kinetics where the decomposition degree a is calculated based on the Arrhenius reaction theory and using the kinetic triplets (kinetic parameters) extracted from thermogravimetry, TGA, data using the Friedman multi-curve method. The second approach is more complicated and considers multi-stage decomposition of the polymer composite. Specifically a 3-stage reaction network is considered for every material, the LY-Ref, and the two modified batches, one with ammonium polyphosphate AP423 and the other both with AP423 and multi-wall carbon nanotubes MWCNT. Again the kinetic parameters, activation energy EA, frequency factor A, and reaction order n, are extracted for every step using the van Krevelen methodology. In the end using the reaction rates equations the reconstruction of the TGA curves is achieved with an error of less than 5% from the test data. Correlations that consider the material deterioration and affect the thermophysical properties of the materials are proposed. Those expressions are being developed for both of the two kinetic approaches, the single and multi stage.
Another crucial part of this work is the measurement and calibration of the applied fire load. Again two fire load approaches are used, one according to the ISO2685 Standard where a propane burner was manufactured and calibrated according to the Standard for medium scale samples testing and a lab scale butane burner for small samples. The ISO2685 burner was also CFD simulated and the models calibrated against analytical expressions, ISO requirements and real measurements. The CFD simulations were performed so the heat flux or heat transfer coefficient to be extracted and used as input for the later thermal FE burnthrough models. The heat flux distribution of the lab-scale AML burner on the specimen surface was measured via a water cooled Schmit-Boelter SBG01 heat flux sensor manufactured by Hukseflux.
Manufacturing and material details are presented concerning the samples used for every test campaign. Metallic (AL2024-T3) samples, CFRP neat and modified, and hybrid GLARE ones where manufactured. Also the experimental work performed is described. Cone calorimetry testing data are available, results from thermogravimetry tests, differential scanning calorimetry, and finally the burnthrough tests with both the testing apparatuses, the ISO2685 one and the AML lab-scale burner.
The modelling work in this dissertation involved thermal models that were developed into a commercial FE package. It was not part of this work to develop a thermal solver so a commercial one was selected and all the developed methodology was adapted to its requirements and specifications. The boundary conditions on the models are presented both for the ‘hot’ front surface and the rear ‘cooling’ one. For the ‘hot’ one the heat flux distribution is used and for the ‘cooling’ one an equivalent convection is applied that accounts for both convective and radiative cooling. The decomposing material model is implemented into to FE solver via user defined subroutines for the single stage kinetics and the multi-stage approach. Finally the simulations were run and the results and models were compared against the available experimental results.
Since so far the burnthrough response of aerostructures was limited to coupon, samples and medium size flat panels. A more realistic approach was performed by developing a mathematical model of a real size test. The certification tests conducted by the FAA are for full size fuselage sectors under the fire load of a burning jet-fuel pan pool-fire. A burning jet-fuel pool fire is a complex phenomenon on its own, combining it with a decomposing fuselage structure make the modeling approach even more difficult to simulate if not impossible. Required data for the pool-sizes under investigation were not available, so data for large external hydrocarbon pool fires from literature were used. Also, because the main characteristic of a jet-fuel (kerosene) pool fire is that the flames are not clear, on the contrary, great amount of shoot is produced making combustion modeling and radiative heat transfer to the fuselage even more of a challenge to model, it was decided to try and tackle this full-scale approach by a simplified the modeling approach. Instead of liquid fuel combustion, an equal hot air stream with mass flow, velocity and temperature properties extracted from literature correlation data was performed.
Conclusively, in terms of completeness the benefit analysis performed by Cherry and Warren is presented in brief. The objective of their analysis was to assess the potential benefits, in terms of reduction of fatalities and injuries, resulting from improvements in fuselage burnthrough resistance to ground pool fires. Fire hardening of fuselages will provide benefits in terms of enhanced occupant survival and may be found to be cost beneficial if low-cost solutions can be found. The maximum number of lives saved per year in worldwide transport aircraft accidents, over the period covered by the data, if hardening measures were applied, was assessed to be 12.5 for the aircraft in its actual configuration (when the accidents occurred) and 10.5 for the aircraft configured to later airworthiness requirements.
These figures are completely significant and give an extra confirmation that this work on investigating the fire response of composite aerostructures is on the right track. As the work of Cherry and Warren concluded, the fire hardening measures in order to be applicable need to be cost efficient. The concept under which this whole dissertation stepped on was to investigate the fire response of composite aerostructures and the possibility of hardening the structure itself without the use of extra protective layers that add cost and weight to the overall aircraft and its maintenance. In the end it was concluded that there is the possibility of hardening the fuselage structure by design and by material. Incorporating composites into the structure it is possible to prolong the burnthrough time at least for 4-5 minutes before auto ignition occurs on the inner side of the fuselage. Auto ignition of the inner side fuselage cabin materials is mentioned since in NONE of the burnthrough tests of the CFRP composites and the GLARE samples flame penetration was observed. / Στην παρούσα διατριβή με τίτλο «Ανάλυση της απόκρισης σύνθετων πολυμερών υλικών υπό συνθήκες φωτιάς. Εφαρμογή σε αεροπορικές κατασκευές» πραγματοποιείται εργασία στην αριθμητική προσομοίωση και πειραματική διερεύνηση της συμπεριφοράς αεροπορικών κατασκευών σε συνθήκες φωτιάς. Στην μέχρι τώρα βιβλιογραφία οι διάφοροι έλεγχοι για πιστοποίηση των αεροπορικών υλικών αλλά και των αεροσκαφών στο σύνολό τους αποτελούνταν από εκτενείς πειραματικές δοκιμές σε μεσαία κλίμακα καθώς και σε πλήρους κλίμακας κατασκευές. Οι προδιαγραφές των ελέγχων ορίζονται από την Ομοσπονδιακή Διεύθυνση Αεροπλοΐας των Ηνωμένων Πολιτειών της Αμερικής, Federal Aviation Administration FAA. Όπως γίνεται αντιληπτό πλήρους κλίμακας δοκιμές είναι χρονοβόρες αλλά και οικονομικά ασύμφορες, για τον λόγο αυτό τα τελευταία χρόνια πραγματοποιούνται προσπάθειες από την FAA για καθιέρωση Προτύπων ελέγχου μικρής κλίμακας τα οποία σε συνδυασμό με αριθμητικά μοντέλα θα είναι σε θέση να προβλέπουν την συμπεριφορά των αεροπορικών κατασκευών σε συνθήκες φωτιάς από την φάση του σχεδιασμού τους. Θα εξασφαλίζεται έτσι καλύτερη διαχείριση οικονομικών και υλικών πόρων. Στην βιβλιογραφία ο μεγαλύτερος όγκος αριθμητικής μοντελοποίησης έχει πραγματοποιηθεί στους τομείς της ναυπηγικής και των θαλάσσιων κατασκευών καθώς επίσης και τα τελευταία χρόνια στον τομέα της αστικής δόμησης. Αριθμητική δουλεία πάνω στην συμπεριφορά των αεροπορικών κατασκευών είναι υπερβολικά περιορισμένη και εκεί στοχεύει να συμβάλει η παρούσα διατριβή. Οι αεροπορικές κατασκευές εκτός των περιορισμών και προδιαγραφών που θέτουν οι άλλες εφαρμογές απαιτούν την ελαχιστοποίηση του προστιθέμενου βάρους στην κατασκευή.
Διάφοροι τύποι πολυμερών συνθέτων υλικών χρησιμοποιούνται στην βιομηχανία, διακρινόμενα σε θερμοσκληρυνόμενα και θερμοπλαστικά. Αρχικά παρουσιάζονται τα θερμοσκληρυνόμενα ξεκινώντας από τους ευρέως χρησιμοποιούμενους πολυεστέρες και βινυλεστέρες, στις φαινολικές και εποξικές ρητίνες καταλήγοντας στους υψηλής θερμοκρασίας κυανεστέρες. Εν συνεχεία γίνεται αναφορά στα συνήθη χρησιμοποιούμενα θερμοπλαστικά, πολυπροπυλένιο PP, Poly-ether ether-ketone PEEK και polyphenylene Sulphide PPS. Φυσικά δεν παραλείπεται να γίνει σύντομη αναφορά και στις τυπικές διεργασίες θερμικής αποσύνθεσης των προαναφερθέντων πολυμερών.
Η συμπεριφορά των σύνθετων πολυμερών υλικών σε συνθήκες φωτιάς περιγράφεται από κάποια χαρακτηριστικά μεγέθη τα οποία χρησιμοποιούνται για την ποιοτική και ποσοτική σύγκριση των διαφόρων υποψήφιων αεροπορικών υλικών. Συγκεκριμένα τα μεγέθη αυτά είναι: Heat Release Rate HRR, Thermal Stability Index TSI, Limited Oxygen Index LOI, Extinction Flammability Index ESI, Time-to-Ignition, Surface Flame Spread, Mass Loss, Smoke Density, Smoke Toxicity. Οι διαδικασίες ελέγχου και τα υπολογιζόμενα μεγέθη γίνονται βάσει διεθνών Προτύπων που κυρίως για τον τομέα της αεροναυπηγικής ορίζονται από την Ομοσπονδιακή Διεύθυνση Αεροπλοΐας FAA.
Η αριθμητική προσομοίωση προυποθέτει γνώση της συμπεριφοράς των πολυμερών υλικών σε συνθήκες υψηλής θερμοκρασίας, για τον σκοπό αυτό πραγματοποιήθηκαν πειράματα απώλειας μάζας με χρήση θερμογραβιμετρίας TGA κατά την διάρκεια της οποίας η απώλεια μάζας καθώς και ο ρυθμός αυτής παρακολουθούνται και καταγράφονται σαν συνάρτηση του ρυθμού θέρμανσης. Μέσα από αυτά τα δεδομένα μπορεί να πραγματοποιηθεί εκτίμηση του τρόπου αποσύνθεσης του πολυμερούς. Αρχικά πραγματοποιήθηκε η θεώρηση της μονοβάθμιας αντίδρασης (single-stage reaction) που αποτελεί και την πλέον απλουστευμένη προσέγγιση. Στην θεώρηση αυτή θεωρείται πως η πολυμερής μήτρα περνάει από την «παρθένα» κατάσταση στην απανθρακομένη μέσα σε ένα βήμα. Η περιγραφή της αντίδρασης αυτής γίνεται με μια μονοβάθμια αντίδραση τύπου Arrhenius.
Σε δεύτερο βήμα χρησιμοποιήθηκε κινητική θεωρία πολλαπλών σταδίων (multi-stage kinetics) σύμφωνα με την οποία πραγματοποιήθηκε ακριβέστερη προσέγγιση της απόσύνθεσης της πολυμερούς μήτρας των συνθέτων υλικών με απόκλιση μικρότερη του 5% από τα πειραματικά δεδομένα της θερμογραβιμετρείας (thermogravimetry). Και στις δύο προσεγγίσεις της αποσύνθεσης υπολογίσθηκαν οι κινηματικές παράμετροι: συντελεστής συχνότητας A (frequency factor), ενέργεια ενεργοποίησης ΕΑ (activation energy), τάξη αντίδρασης n (reaction order) για κάθε στάδιο. Με την ολοκλήρωση αυτού του σταδίου υπήρχε μια αξιόπιστη δυνατότητα αναπαράστασης της διαδικασίας αποσύνθεσης στο πείραμα της θερμογραβιμετρίας.
Είναι γνωστό ότι οι διακυμάνσεις της θερμοκρασίας επηρεάζουν της τιμές των θερμοφυσικών ιδιοτήτων των υλικών. Αναλογιζόμενοι ότι στην διαρκεία της επιβολής της φλόγας στα σύνθετα υλικά όχι μόνο η θερμοκρασία αλλά και η σύσταση μεταβάλλεται συνεχώς λόγω της αποσύνθεσης κρίθηκε αναγκαία η ανάπτυξη μιας μεθοδολογίας που θα συμπεριλαμβάνει την επίδραση της αποσύνθεσης στην μεταβολή των θερμοφυσικικών ιδιοτήτων (θερμική αγωγιμότητα, ειδική θερμοχωρητικότητα και πυκνότητα) της πολυμερούς μήτρας και κατά συνέπεια του συνθέτου υλικού. Οι εξαγόμενες μαθηματικές σχέσεις χρησιμοποιήθηκαν στην αριθμητική προσομοίωση που ακολούθησε.
Με σκοπό την ορθή αριθμητική μοντελοποίηση κρίνεται αναγκαία η μέτρηση και βαθμονόμηση του θερμικού φορτίου τον πειραματικών δοκιμών. Το μετρούμενο θερμικό φορτίου χρησιμοποιήθηκε εν συνεχεία ως φόρτιση στα αναπτυχθέντα μοντέλα. Χρησιμοποιήθηκαν δύο πειραματικές διατάξεις εφαρμογής φλόγας, μία μεσαίας κλίμακας σύμφωνα με τις διατάξεις του FAA Standard, που περιγράφεται στο ISO2685:1998(E) “Aircraft – Environmental test procedure for airborne equipment – Resistance to fire in designated fire zones” και μίας εργαστηριακής κλίμακος. Πραγματοποιήθηκε μέτρηση με θερμοζεύγη και καλορίμετρο νερού καθώς και αριθμητική μοντελοποίηση με χρήση CFD για την πρώτη διάταξη. Ενώ για την εργαστηριακής κλίμακας έγινε μέτρηση με θερμοζεύγη και ενός αισθητήρα θερμικού φορτίου «water-cooled Hukseflux Schmit-Boelter SBG01 sensor».
Εν συνεχεία πραγματοποιήθηκε η κατασκευή των δοκιμίων των υποψήφιων υλικών καθώς και οι πειραματικές δοκιμές και έλεγχοι τους. Συγκεκριμένα πραγματοποιήθηκε: Θερμιδομετρία κώνου (cone calorimetry), Θερμογραβιμετρία (thermogravimetry), Θερμιδομετρία Διαφορικής Ανίχνευσης (Differencial Scanning Calorimetry, DSC), Μέτρηση Θερμικής αγωγιμώτητας, Δοκιμή διείσδυσης φλόγας (Fire burnthrough penetration).
Καθώς ο χαρακτηρισμός της αποσύνθεσης των πολυμερών υλικών, η μεταβολή των θερμοφυσικών ιδιοτήτων, η μέτρηση και βαθμονόμηση του επιβαλλόμενου θερμικού φορτίου καθώς και οι πειραματικές δοκιμές έχουν ολοκληρωθεί ακολουθεί η αριθμητική προσομοίωση. Οι συνοριακές συνθήκες θερμικού φορτίου και ψύξης επιλέχθησαν ως εξής. Ως φόρτιση θεωρήθηκε η κατανομή του θερμικού φορτίου (σε kW/m2) στην εμπρός επιφάνεια του πάνελ. Στην ψύξη της πίσω επιφάνειας λήφθηκε υπόψη τόσο η ελεύθερη μεταφορά θερμότητας με επαφή όσο και η ακτινοβολία. Το μοντέλο της συμπεριφοράς του υλικού διαμορφώθηκε κατάλληλα ώστε να γίνει κατανοητό από τις απαιτήσεις ενός εμπορικού κώδικα Πεπερασμένων Στοιχείων επίλυσης θερμικών προβλημάτων και προσομοιώθηκαν οι πειραματικές δοκιμές διείσδυσης φλόγας των δύο πειραματικών διατάξεων, μεσαίας και εργαστηριακής κλίμακος.
Πλέον της αριθμητικής προσομοίωσης της συμπεριφοράς σε φωτιά επίπεδων δοκιμίων αεροπορικών κατασκευών, πραγματοποιήθηκε προσπάθεια απλουστευμένης μοντελοποίησης των συνθηκών φλόγας ενός λιμνάζοντος όγκου καυσίμου αεροσκαφών στο εξωτερικό μιας ατράκτου. Δημιουργήθηκε ένα τρισδιάστατο ρευστομηχανικό μοντέλο πρόβλεψης του θερμικού φορτίου στην επιφάνεια μιας τυπικής ατράκτου σύμφωνα με τις προδιαγραφές γεωμετρίας του Προτύπου “Full-scale test evaluation of Aircraft fuel fire burnthrough resistance improvements” DOT/FAA/AR-98/52,1999. Τα ρευστομηχανικά αποτελέσματα συγκρίθηκαν με δεδομένα βιβλιογραφίας για μεγάλες φλεγόμενες δεξαμενές λιμνάζοντος καυσίμου.
Εκτός από την μελέτη της απόκρισης των αεροπορικών κατασκευών σε συνθήκες φλόγας σκοπός της παρούσας εργασίας είναι και η παρουσίαση λύσεων οι οποίες θα έχουν την δυνατότητα της βελτίωσης της συμπεριφοράς των υπαρχουσών δομών καθώς και των μελλοντικών σύνθετων δομών. Ενδεικτικά αναφέρεται η δυνατότητα χρήσης νανοεγκλεισμάτων, και βελτιωμένων μονωτικών υλικών, π.χ. aerogels. Όπως έχει ήδη αναφερθεί οι αεροπορικές κατασκευές θέτουν τον περιορισμό της ελαχιστοποίησης του προστιθέμενου βάρους, για τον λόγο αυτό η ενίσχυση των συνθέτων υλικών θα πρέπει να πραγματοποιηθεί σε επίπεδο υλικού και σχεδιασμού. Πρέπει δηλαδή η ίδια η κατασκευή που είναι ικανή να φέρει τα μηχανικά φορτία να εξασφαλίζει και την πιστοποίηση της FAA για συνθήκες φωτιάς.
Συνοψίζοντας, η παρούσα διατριβή πραγματοποιεί μια καινοτόμο, γρήγορη και αρκετά ακριβή προσέγγιση του σημαντικότατου ζητήματος της συμπεριφοράς των πολυμερικών σύνθετων αεροπορικών δομών σε συνθήκες φωτιάς Η πολυπλοκότητα του όλου φαινομένου επέβαλε την πραγματοποίηση παραδοχών και απλουστεύσεων. Καθώς όμως με την αυξανόμενη χρήση των συνθέτων υλικών στις αεροπορικές κατασκευές, ο τομέας της ασφάλειας σε συνθήκες φλόγας είναι συνεχώς αυξανόμενος και απαιτητικός. Για αυτό οι παραδοχές και θεωρήσεις της παρούσας διατριβής μπορούν να βελτιωθούν με χρήση νέων υπολογιστικών μεθόδων και πειραματικών δεδομένων με στόχο την ακόμα ακριβέστερη πρόβλεψη της συμπεριφοράς τον αεροπορικών δομών σε συνθήκες φλόγας.
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