The thesis extends Lennart Krieg's modified linear viscoelastic fatigue life prediction framework to matrix-dominated angle-ply 45 glass-fiber/epoxy composite laminates. To account for matrix nonlinearity, Schapery's nonlinear viscoelastic constitutive theory was integrated into Krieg's fatigue life prediction equation via an augmentation parameter derived from creep-recovery tests. Applying a saturated capped augmentation parameter significantly improved life predictions, reducing root-mean-square errors across stress ratios (e.g. from 0.656 to 0.316 decades for R=0.3). Independent evaluations using dynamic mechanical analysis and stress-sweep testing yielded well-aligned fatigue limit estimates (69 - 77 MPa). Overall, this work provides a successful proof-of-concept for physics-based fatigue prediction in matrix-dominated composites ... Read more

Composite materials offer opportunities to reduce the structural mass of naval vessels, but their integration into primary hull structures changes the stiffness distribution, load transfer and mechanisms governing collapse. This thesis investigates how selective steel-composite hybridisation of a naval hull girder region influences its quasi-static progressive collapse behaviour and ultimate bending response. The assessment focuses on intact structures subjected to monotonic longitudinal bending.

A Smith-type progressive collapse model was adapted to represent steel and composite component responses, neutral-axis migration and reduced composite participation at the steel-composite interface. An all-steel reference box and three hybrid concepts incorporating Glass-Fibre Reinforced Polymer (GFRP) were evaluated using monolithic laminate and sandwich panels, first as isolated box girders and subsequently within a reference frigate cross-section. The steel formulation was assessed against the published Nishihara MST-3 experimental benchmark. Nonlinear finite element analyses in ANSYS provided component load-shortening curves for comparison within the same sectional solver, while separate complete-box models examined wall interaction and cohesive adhesive behaviour. Sensitivity analyses assessed the influence of material properties, interface participation and modelling assumptions.

Among the investigated concepts, B3, which replaces the side webs with GFRP while retaining the steel deck, bottom flange and corner framing, provided the most favourable balance between mass reduction, bending resistance and dependence on composite participation. In the analytical isolated-box assessment, the monolithic B3 design was 11.6% lighter than the steel reference while meeting or exceeding its sagging and hogging capacities. Following embedding and recalibration within the frigate cross-section, it reduced structural mass by 52.1 kg⋅m−1 relative to the section containing steel reference boxes, maintaining sagging capacity with a 1.17% reduction in hogging capacity. Sandwich variants offered no meaningful mass advantage within the adopted longitudinal-bending model.

The finite element comparisons showed that the predicted resistance depends on how component behaviour and structural interaction are represented. Using finite element component curves produced ultimate moments 0.7–17.5% below the corresponding analytical predictions. This sectional assessment predicted lower sagging resistance for B3 than for the steel reference, while its small hogging advanta
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This thesis investigates whether the picture-frame test can be used as an element-level validation method for conduction-welded thermoplastic composite joints. Pristine and defect-containing panels were tested under free-buckling and anti-buckling conditions, with their response assessed using force–displacement data, Digital Image Correlation, strain gauges, visual inspection, and ultrasonic C-scans. The experiments were compared with finite element models using Cohesive Zone Modelling and the Virtual Crack Closure Technique, based on independently obtained interface fracture properties. The results show that the picture-frame test can generate interface failure at panel scale, while also revealing the influence of buckling, weld geometry, manufacturing variability, and competing laminate damage on the structural response. The numerical analyses reproduce selected experimentally observed deformation and damage mechanisms and provide useful insight into the transfer of coupon-derived fracture properties to a larger structural scale. The picture-frame test can therefore be used as an element-level validation method, but its reliability is conditional rather than universal. ... Read more

This thesis investigates the application and extent of validity of a novel physics-based energy-balance approach with the Sliding Box analogy. The scope focuses on predictive modeling of fatigue crack growth in aluminum alloys at low temperatures. The motivation for this research arises from the increasing demand for reliable fatigue-life prediction methods in the context of hydrogen-powered aviation, where liquid-hydrogen storage tanks and adjacent structures are exposed to cyclic mechanical and thermal loading in cold environments. Traditional empirical approaches, such as Paris’ law, are limited by their reliance on extensive experimental calibration, especially when material properties and environmental factors vary significantly.

The research aims to expand and validate the Energy Balance with the Sliding Box analogy (EBSB) framework by comparing its predictions to a comprehensive experimental dataset covering both room-temperature and low-temperature conditions down to -30°C. The study considers a diversified selection of aluminum alloys with quasi-static property differences that emulate changes expected at low temperature. The investigated materials are 7075-T6, 2024-T3, 6061-T6, and an artificially over-aged 2024-A300. Additionally, thicknesses from 1 to 6.5 mm and two stress ratios, R=0.1 and R=0.5, are varied to evaluate their influence on the modeled fatigue crack-growth response. The methodology combines quasi-static tensile testing to determine case-specific elastic--plastic properties with constant-amplitude fatigue crack-growth experiments on standard geometry specimens. Crack growth is measured via periodic high-contrast image capture. Furthermore, Digital Image Correlation (DIC) is employed to evaluate plastic-zone development from periodic displacement-field measurements around the advancing crack tip.

The results demonstrate that the EBSB model—particularly in its direct sliding-box form—captures the general trends and order of magnitude of fatigue crack growth in aluminum alloys well. However, predictive accuracy is limited by the current formulation of the plastic energy dissipation term and by the treatment of stress-state transitions (plane stress/plane strain). The quantification of plastic-volume growth within the energy balance was varied in an attempt to capture increased energy absorption at low temperature. The model tends to overestimate crack-growth rates, especially for pronounced variations in yield strength and strain hardening relative to the 7075-T6 baseline. This effect is not mitigated by adopting larger plastic-zone approximations. For lower thicknesses of 7075-T6, however, using a larger plastic-zone estimate reduces model error, consistent with better agreement with the plane-stress assumption.

Overall, the EBSB model is sensitive to material-specific strain-energy absorption characteristics, particularly yield strength and the degree of strain hardening. Experimental observations confirm the expected increase in yield strength and work hardening at low temperature, but also reveal an unexpected decrease in ductility for the low-temperature 7075-T6 tests, highlighting the complex coupling between material behavior and environment. Improvements to the EBSB framework are proposed, including a parametrically defined plastic strain energy density derived from quasi-static stress--strain data and the introduction of a damping term to account for crack-shielding effects. Recommendations for future work include expanded cryogenic testing, improved DIC resolution, and the development of more robust analytical and numerical treatments to better capture strain hardening, stress-state transitions, and plastic-zone evolution. ... Read more

Additive Manufacturing (AM) has become the standard for the production of liquid propellant rocket engines, including the Throttleable Liquid Propulsion Demonstrator (TLPD) developed by the Łukasiewicz Research Network – Institute of Aviation. The aim of this thesis is twofold. The first goal is to calibrate a nonlinear material model of AM CuCrZr alloy based on experimental tests. The second goal is to perform a thermostructural analysis of the TLPD2 combustion chamber using that material model. Multiple types of tests were conducted, and manual calibration of the model achieved high accuracy. The model was applied to the FEM analysis of the TLPD2 chamber, showing elastic operation and no lifetime concerns. An additional analysis with increased pressure loads was conducted to compare the new material model with the old model based only on tensile tests. Large differences between the two models are present when plastic deformation occurs.

Related dataset 4TU.ResearchData: https://doi.org/10.4121/9072efcd-23ff-40bb-9b52-c490c28797cc
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The aviation sector is responsible for approximately 2.5% of global CO2 emissions. While the CO2 emissions reduced at a compound annual growth rate (CAGR) of 2.8% between 2000 and 2019, the passenger demand is projected to more than double by 2044 as compared to 2024 at a CAGR of about 4.2%, outpacing the reduction in emissions. Unconventional aircraft (for example blended wing body aircraft) are projected to reduce emissions by more than 20% as compared to widebody aircraft of comparable mission and size, making them instrumental for reducing aviation emissions. However, these novel configurations also introduce new crashworthiness challenges that must be addressed early in the design process to prevent cost overruns and delays at later stages of the design process.

Historically, preliminary crashworthiness analysis has relied on linkage-kinematic joint representation of the aircraft, with characteristic curves for the kinematic joints derived using experimental or numerical campaigns. Even the most recent multi-body and FEM-kinematic joint hybrid models still depend on characteristic curves derived through simulations or experiments. Consequently, while these models are fast and ideal for preliminary crashworthiness analysis, design exploration is limited by the amount of component level test/simulation data, highlighting a clear research gap for analytical/semi-analytical models that can inform such multi-body models on the go with material and geometry data as inputs.

This thesis addresses that gap by focusing on the two dominant energy absorption mechanisms in metallic fuselage structures: axial crushing and plastic bending. For axial crushing of closed-section metallic tubular structures, existing models are evaluated and a generalized expression for various cross-section shapes is proposed. For bending collapse, a semi-analytical framework combining spring-linkage based elasto-plastic stage prediction, transition algorithm, and Kecman model for collapse stage prediction is proposed to obtain complete force–displacement curves. Although aircraft structures commonly use open sections, the scope of the present work is limited to closed sections in order to establish a robust and consistent methodological foundation within the available time frame.

Finally, the bending framework is extended to hybrid materials, specifically GLARE (Glass Laminate Aluminium Reinforced Epoxy). A maximum strain-based damage model based on the spring-linkage method is proposed, the approach predicts stiffness degradation and progressive central cracking failure for GLARE laminates. The results demonstrate that analytical and semi-analytical models can be further extended to hybrid systems, enabling fast, early-stage crashworthiness evaluation of unconventional aircraft designs utilizing hybrid materials. ... Read more

The fatigue behaviour of fibre-reinforced polymer composites is typically characterised by costly and time-consuming stress–life testing. This thesis explores an alternative, energy-based approach by adapting complex modulus-based linear viscoelastic theory to describe hysteresis energy dissipation in continuous fibre composites under tensile–tensile fatigue. A modified framework introducing energy-based R–ratio corrections enabled consistent definitions of a viscoelastic loss factor, cyclic dissipation ratios and critical dissipated energy (CDE) across stress levels and load ratios. Analysis of both a literature reference and experimentally tested laminates showed that effective loss factors correlated with Dynamic Mechanical Analysis (DMA) results. The intersection with pristine DMA values provided reliable estimates of high-cycle fatigue strength (HCFS), consistent with existing infrared thermography methods. CDE was identified as a robust fatigue failure criterion, independent of R in the intermediate to high-cycle regime. These findings highlight the potential of energy-based methods to reduce testing requirements while improving predictive capability in composite fatigue. ... Read more

Composite over-wrapped pressure vessels are the state-of-the-art for hydrogen storage, with Type IV vessels currently using a thermoplastic liner and a thermoset composite. The next innovation, Type V vessels, aims to use a thermoplastic composite over-wrap that acts as both the barrier and container, requiring new materials and manufacturing methods like automated fibre placement.

To accurately characterize the new materials, the effect of their manufacturing process must be captured. While the standard split-disk test exists for wound specimens, it underpredicts their burst strength and fatigue life. Other attempts in literature have improved strength estimations but are not viable in fatigue, thus creating a challenge.

A new test method was developed, which uses a polyurethane ring to apply cyclic internal pressure. It was designed through finite-element analyses, fine-tuned through rigorous tests, and benchmarked against the standard method. It showed improved strain distribution and near-consistent performance in fatigue tests. Hence, it demonstrated potential for more accurate static and fatigue strength characterization of wound composites, with room for improvement through better alignment and even friction. ... Read more

In this work, a conceptual design was created that integrates battery packs into the wings of a 90-seater electric aircraft. This was done under the challenging requirement of replacing over 35 tonnes of batteries more than once a year. The concept allows the batteries to move spanwise along a rail system and through the rib using a panel structure. The core of this concept is that it avoids the need to remove large skin panels of the wing. From the broader concept, a single component was analyzed in detail using non-linear finite-element models combined with fretting-fatigue analyses and physical testing. ... Read more

This dissertation introduces a comprehensive end-to-end framework related to Prognostics and Health Management (PHM) strategy, with the goal of utilizing raw sensor (placed on a structure's components) data to make maintenance decisions for extending the structure's lifecycle. The study addresses key challenges in PHM, such as dealing with high-dimensional, multi-modal data, extracting features, predicting Remaining Useful Life (RUL), managing uncertainty, modeling repair scenarios, and optimizing maintenance decisions. All these challenges are organized in phases. These phases are namely, i) data collection, ii) feature extraction, iii) Health Indicator (HI) construction, iv) prognostics, v) modeling of maintenance actions, and vi) Post-Prognosis Decision-Making (PPDM). Each phase of the PHM strategy is developed independently but integrated into a cohesive framework, ensuring modularity, transparency, and adaptability across diverse applications.

A major contribution to the framework is proving that neural networks, a preferable approach for handling complex data, can become interpretable, thus unveiling the black-box nature of such models. In this regard, the ISTRUST model, an interpretable Transformer-based architecture for predicting RUL directly from raw sequential image data of a structure under fatigue loads, is proposed. By leveraging attention mechanisms, the model captures critical spatiotemporal features of structural damage, offering insights into prediction accuracy and variability. The model's interpretability highlights the understanding of its predictions. Simultaneously, via this interpretation, it is shown that predicting RUL directly from high-dimensional raw data is challenging or even impossible, necessitating focusing on each phase of the PHM strategy separately instead of unifying the majority of the PHM strategy in one model.

Central to the framework is the development of the Deep Soft Monotonic Clustering (DSMC) model, designed to extract meaningful features and then construct HIs from multi-modal data. This model extracts monotonic features that are related to each component's degradation. Subsequently, it considers these features to perform monotonic clustering representing HIs and enables the integration of those HIs into prognostic models to predict RUL across diverse domains.

The dissertation further explores the impact of imperfect repairs on components, where repairs often leave the component in a state between fully restored and partially damaged. The health state of the component is measured via a stochastic recovery of the predicted RUL and a Bayesian inference-based model is employed to quantify this stochastic behavior. The imperfect repair (Bayesian) model can be also extended for multiple sequential repairs. This phase of the PHM strategy emphasizes the importance of understanding imperfect repair effectiveness to enhance maintenance strategies.

The final phase of the framework concerns PPDM. Given a set of maintenance actions, including replacements and imperfect repairs, and a set of operational conditions and constraints, PPDM is modeled as a Markov Decision Process and optimized via deep Reinforcement Learning. PPDM's ultimate target is to optimize the scheduling of maintenance actions proactively within a predefined horizon length.

Experimental validation is conducted on each of the proposed models. The ISTRUST model was validated on fatigue-loaded composite specimens, utilizing sequential raw image data taken by a camera. The DSMC model was tested using diverse datasets, including engineering and healthcare. The imperfect repair modeling was applied to tension-tension fatigue experiments on open-hole aluminum coupons, capturing stochastic recovery behavior after repairs. The same experiment was utilized for evaluating the PPDM framework.

Overall, a holistic end-to-end PHM framework lays the groundwork for advancing Condition-based Maintenance (CBM) strategies. By integrating advanced models for each phase of the PHM strategy, the research highlights practical opportunities for embedding PHM into CBM and encourages further innovation and refinement by other researchers in the field. Although the proposed PHM framework has been an initial attempt towards this direction, its capabilities can be further enhanced through improvements in data scalability, exploration of varied PPDM formulations, sensitivity analyses across PHM phases, and practical integration with CBM for broader system-level maintenance optimization. ... Read more

Mission Aviation Fellowship (MAF) provides humanitarian aid using light aircraft to remote communities, separated by geographical obstacles or conflict. HumanAir aims to reduce their operating emissions by 50% while improving economic sustainability and maintaining operational versatility, by designing an innovative new aircraft within a timeframe of only 5 years. This report describes the design process and analysis of the HA-1 aircraft, the proposed solution to the problems encountered by MAF. The HA-1 aircraft achieves an emissions reduction of more than 50% while remaining competitive on cost, facilitated by the use of readily available Jet-A1 fuel instead of scarce leaded AVGAS. Therefore, the HA-1 will replace multiple of MAF’s ageing aircraft with a single sustainable alternative. ... Read more

Fibre-reinforced polymer (FRP) composites have become indispensable in aerospace engineering over the past two decades, driving the need for efficient and standardized testing protocols to certify their reliability. However, no standardized protocol currently exists for fatigue testing of FRPs, particularly due to fibre bridging—a phenomenon prominent in testing but rarely encountered in real-world applications. This study investigates existing fatigue data processing techniques, with a primary focus on a regression-based approach that could standardize fatigue data analysis. Current fatigue delamination characterization methods often rely on single-parameter empirical models, which struggle to capture the complex interaction between cyclic and monotonic load components, expressed as ∆√G and Gmax, respectively. This study demonstrates that the regression method’s zero-bridging technique effectively incorporates both parameters, offering a comprehensive view of delamination growth by isolating it from fibre bridging effects. This approach suggests a shift away from the traditional 2D analysis to a 3D framework, which considers both Gmax and ∆√G, enabling a more accurate depiction of delamination behaviour across various stress ratios. Notably, the results reveal that zero-bridging data align on a common plane under consistent stress ratios, shifting as stress ratios increase. Additionally, fibre orientation influences data clustering, with similar orientations exhibiting stronger convergence than dissimilar ones. Comparison of this regression-based method with the modified Paris law reveals significant discrepancies in its current implementation, suggesting alternative approaches to address these limitations. This study also highlights the impact of data size and selection on the model behaviour, stressing their importance in accurate model representation. This research validates the regression method as a promising candidate for standardizing fatigue data processing, improving the precision and reliability of post-test analysis for fibre-reinforced polymer composites. ... Read more

Additive Manufacturing (AM) has revolutionized the production of complex parts, particularly for superalloys in the aerospace industry due to their strength, corrosion resistance, and high-temperature performance. LPBF is notable for its precise control over complex geometries, with key parameters like laser power and scanning speed affecting the final product's quality. This study examines how build orientation, high stress ratios, and surface roughness impact the fatigue life of superalloy. Vertical and diagonal specimens were printed with identical heat treatments to isolate these variables. The diagonal specimens showed higher UTS but lower ductility compared to the vertical ones. Fatigue tests revealed that increased surface roughness in diagonal specimens reduced HCF performance, while their strength improved LCF behavior. Crack initiation was primarily at the surface in HCF, while internal defects caused some LCF failures. The proposed fatigue models aligned well with experimental data, offering valuable insights for future research. ... Read more

Fibre metal laminates (FML) were initially conceived as a hybrid material, aiming to create synergy between the impact resistance of metals and excellent fatigue resistance of fibre reinforced polymers. The purpose of this approach was to overcome the limitations of single-material structures. However, despite its considerable promise, the use of the FML concept has primarily been confined to aerospace applications and heavily relies on synthetic fibres that carry significant environmental implications. Hence, given the growing concerns about climate change and the challenges posed by recycling glass fibre composites, a new generation of FMLs with a reduced carbon footprint should be envisaged.

Research on flax fibre composites reveals convincing mechanical properties and remarkable damping capacities. However, the broader adoption of these composites remains restricted primarily due to issues related to low impact resistance, moisture absorption and flammability concerns. The FML concept presents a viable solution to surmount these constraints, consequently facilitating the integration of these materials into primary structures. Hence, the research endeavour aimed to attain comprehensive insights into FLAx REinforced aluminium (FLARE), particularly focusing on its impact resistance and vibration damping capabilities, which are believed to be the principal benefits of this hybrid material.

The research goal was divided into three distinct research tasks: conducting experimental analyses to characterise the damping behaviour of FLARE, evaluating the impact resistance through experimental means, and validating predictive tools to offer initial insights into the design principles governing such a FML. FLARE, along with flax fibre reinforced epoxy (FFRE) and GLARE specimens, were manufactured using wet layup combined with vacuum bagging techniques.

First, tensile tests were conducted to validate the applicability of the metal volume fraction (MVF) approach in predicting the mechanical properties of FLARE. Intriguingly, the well-known non-linear behaviour exhibited by flax was not observed in the case of FLARE. The results revealed that while the MVF method provided a satisfactory approximation, it was the "inelastic" modulus of FFRE that predominantly contributed to the stiffness of FLARE.

Dynamic mechanical analysis and vibration beam tests were carried out to assess the influence of incorporating metallic layers on the vibration damping characteristics of flax fibre composites. The investigation revealed that the metallic layer predominantly governs the damping behaviour of the FML. Notably, an inverse rule of mixture emerged as the most effective means of approximating its loss factor.

Low-velocity impact tests were conducted to gain insights into the impact response of FLARE in comparison to conventional FMLs. The analysis indicated that the aluminium layers play a significant role in energy absorption, whereas the composite strength emerges as the critical factor influencing impact resistance. A quasi-static analytical model was also assessed, offering an initial estimation of the impact response, yet it warrants further refinement.

In conclusion, the FML concept holds promise for FLARE, but its application requires a novel approach compared to previous methods, to render FLARE viable for practical real-world applications. ... Read more

In recent years, the wind energy industry shows more and more interest in composite materials manufactured with a new process called pultrusion. The advantage of pultruded composite plates includes high fiber volume fraction, low price and simplified blade manufacturing. However, pultruded plates are fully cured and crosslinking is absent at interlaminar interface, which may lead to potential risks when being applied into the real structure. This project focuses on characterizing and evaluating this new type of material.

Microscopy and burn-off test were carried out to measure the actual fiber volume fraction in the material. Roughness of interlaminar surface was measured with microscope by focus variation. These parameters are essential to understand the material.

To characterize the mechanical behaviour of the material, multiple different types of mechanical tests were carried out. Mode-I and mode-II interlaminar fracture toughness were tested with Double Cantilever Beam(DCB) and End-Notched Flexure(ENF) specimens. A new test procedure was developed to measure the mode-I interlaminar fatigue toughness of the material. For in-plane tensile and compression test, Finite Elements Methods(FEM) was used to optimize the specimen geometry in order to obtain results closest to actual material behaviour. During the tensile test, acoustic emission was measured to monitor the damage in the specimens in these tests. Fatigue tests with stress ratio R=0.1 and R=-1 were carried out to understand the fatigue behaviour of the material. ... Read more

This study evaluates the potential danger of hail impacts on stiffened composite aircraft structures. Test specimen are created using Carbon Fiber Reinforced Polymer (CFRP) with and without an Aluminium longitudinal stringer. These specimen are first indented to explore the effect and behaviour of stiffening elements and varying boundary conditions. Then an impact gun is used to impact the specimen with ice balls, simulating hail impacts in order to assess the potential danger of hail stones impacting the stiffened structure. It is concluded that the critical locations for damage formation are where deformations are most suppressed, such as the stringers and ribs of the aircraft. In these locations more damage at the same energy levels as well as a lower threshold energy level for damage initiation is observed. Additionally, it is shown that repeated impacts in close proximity of each other, such as during hailstorms, can increase the resulting damage compared to separate single impacts. Ice impacts demonstrate only a fraction of the kinetic energy is absorbed during an impact, but large hailstones occurring during rare hailstorms can definitely cause serious damage in the critical locations in aircraft. So, for future research, testing and certifying the potential of hail impacts must be recognised and determined in the critical stiffened locations within an aircraft ... Read more

Fibre Metal Laminates (FMLs) have been widely utilised in aircraft structures for their specific strength, durability and damage tolerance. Most aircraft structures, due to their size, require joining, and FMLs allow for a special type of joint called the splice, a unique but a lesser known joint.

The bulk of research into the splice joint has been conducted in the early 2000s for the A380 program, where a specific type of splice has been implemented, the overlap splice. While it is a proven design, it was expected that other splice designs could be as good if not better than the overlap splice. Further, the pre-existing design guidelines on the splices were not suited for detailed design that would target specific mechanical strengths of the joint, like durability and
damage tolerance. Therefore, this research focused on design iterations of the two splice types, the butt splice and the overlap splice, that would provide insights into splice design guidelines against fatigue and demonstrate which splice configuration is a superior joint. An extension
of this research focuses on identification of location and lifetime to damage initiation within the splice using analytical numerical methods, which was previously done on uninterrupted FMLs, but not on spliced FMLs.

Research comprises of a multi-disciplinary approach, combining Finite Element Method (FEM), numerical predictive modelling and experimental investigations that then also doubled as means of validation of the models built. Design iterations were based on the influence that the parameters, labeled a through e, within the splice joint have on the overall stress field within the joint and how that affects the joint’s fatigue life to damage initiation, Ni, a fatigue
performance indicator of the study. It has been discovered that changing the tolerances within the splices provides little influence on the stress field within the splice, which resulted in several iterations of the splice design approaching smaller and more lightweight joint alterations. The designs showed excellent durability characteristics when compared to the Limit of Validity (LOV) cycles set by the aviation authorities, such as EASA and FAA. The Finite Element (FE) model was able to accurately depict the stress field within the splice, validated by the experimental data through strain fields captured using Digital Image Correlation (DIC) technique, and consequently accurately pointed to the location of damage initiation, which in all cases was the outer-most overlap on the flush side of the joint. Along with the adapted predictive numerical model it was possible to predict the damage initiation lives in the spliced specimens with a blunt notch. The predictions in the samples without the notch resulted in far lesser agreement with experiments. This was likely caused by to the limitations of the model, which only took into account quasi-static loading without damage and is highly dependent on the reference data used.

It was concluded that splices can be designed smaller and lighter than previously done due to the tighter tolerances allowed within the splice. Overlaps of 5 mm in both the unnotched butt splice and the unnotched overlap splice, however, resulted in an alternative damage progression mode, specifically a complete delamination of the external overlap rather than metal fatigue cracking. This is attributed to the rising average shear stress in the adhesive. Regardless, the smallest and lightest iterations of the butt splice and the overlap splice with
5 mm overlaps and gaps between aluminium interruptions showed excellent durability and the design iterations were found to affect the damage initiation life very little, considering that fatigue damage initiation is a subject to scatter. It is hard to draw a concrete conclusion on the damage tolerance of the updated designs due to alternative damage modes and lack of research thereof. While both splice types were deemed to be successful in their role of a joining structure, the butt splice was concluded to be superior to the overlap splice when it came to fatigue performance, consistently developing visible damage later than the overlap splice. This gap in fatigue performance is expected to expand if thicker layers or larger number of layers are to be considered. This is because of the secondary bending which occurred in the joint, more so for the overlap splice than the butt splice judging from FEA results and experiments.

It is recommended that a more extensive FE model is developed using the model built in this research as a foundation. The current model could be expanded in several ways, such as simulations of damage progression, individual modelling of the fibre layers, fibre failure models, and a curing simulation. This will improve the validity of the methodology, specifically concerning the unnotched splice specimens, and improve the predictions of not only initiation lives, but also failure lives.
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The Flying-V (FV) represents a novel aircraft configuration that integrates the cabin and two half-wings into a V-shaped structure, promising increased aerodynamic efficiency and an estimated 20% reduction in fuel consumption. Unlike conventional aircraft or other blended wing-body designs, the FV can be scaled to generate a family of aircraft models, which enhances its commercial viability. However, the V-shaped cabin introduces significant eccentricity in the fuselage section, creating unique challenges for crashworthiness.

Aircraft crashworthiness refers to the capability of the airframe to protect occupants during an impact. Regulatory standards for large passenger aircraft (CS-25) require verification of four key criteria: maintaining a survivable volume for occupants, limiting accelerations and loads, retaining items of mass, and preserving occupant egress paths. Historical accident data highlight the importance of these criteria: between 2011 and 2020, 54% of fatal crashes occurred during landing or final approach, accounting for roughly 40% of casualties, emphasizing the vulnerability during these phases. Typically, crashworthiness is assessed via drop tests on a representative fuselage section, focusing on loads and accelerations transmitted to occupants.

To understand how fuselage ovalization and the vertical position of the floor structure affect crash performance, parametric studies were conducted on a conventional aircraft, the Fokker F-28. A parametric CAD model of the F-28’s fuselage section was created and linked to a finite element model (FEM) in Abaqus. Virtual drop tests were performed at 9.1 m/s to evaluate occupant accelerations, dynamic response index, and energy absorption. Ovalization studies varied the fuselage eccentricity from 0 (circular) to 0.75 (approximating the FV’s eccentricity), while floor beam height was varied in 50 mm increments. Results indicated that increasing fuselage eccentricity and floor height generally led to higher occupant accelerations due to reduced crushable volume and shorter impact durations.

For the FV, a preliminary FEM was constructed using previous structural optimization results, which assumed constant frame height and thickness. Four crash concepts were assessed: two conventional designs with four and six floor struts and two unconventional designs featuring vertical crushable elements. The unconventional concepts failed to absorb sufficient energy, leading to high occupant accelerations due to the absence of plastic hinges in the frames. The six-strut conventional concept was overly stiff, also increasing occupant accelerations. The four-strut conventional concept appeared most promising but did not achieve full crashworthiness in this initial study.

Overall, the research shows that the FV’s eccentric fuselage presents unique crashworthiness challenges. Future work should focus on coupled static-dynamic optimization, incorporating both quasi-static operational loads and crashworthiness criteria. This approach will allow designers to iteratively adjust structural parameters such as frame height, thickness, and floor beam placement to improve energy absorption while maintaining stiffness for operational loads. Developing crashworthy designs early in the preliminary design phase is essential to ensure occupant safety without compromising the aerodynamic benefits of the FV configuration. ... Read more

Fiber Metal Laminates needs to be seen as a construct of its individual constituents rather than a material on which the industry has capitalized on. Therefore, analytical models must be made in order to predict the mechanical behavior of the laminates which would reduce the big test matrix for defining empirical values for design allowables. An analytical model made to predict the mid-section stress distribution of Fiber Metal Laminate plate with a centre round hole under uni-axial tension. The σ 0 ε-curve of the laminate is defined by the Metal Volume Fraction. Assuming that the elasto-plastic energy of a small strip is equal to the uni-axial imaginary elastic energy, the σ 0 ε-state of these small strips can be calculated. The elastic peak stress profile at the midsection is defined by a decreasing exponential equation with three parameters. The centre of the small strips are the points where the value of interest are determined. Predicting the net-section stress distribution under elasto-plastic loading is determined iteratively by using the Finite Width Correction Factor as a convergence factor between the applied and net-section load. The analytical model gives quite good and accurate results far into the plastic regime validated by DIC experiments and strain gauges. One of the major findings was that indeed it is possible to have delamination and fiber-bridging beneath the plastic zone, which had implications for determining accurately the Blunt Notch Strength. ... Read more