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        <title>Transactions on Aerospace Research Feed</title>
        <link>https://reference-global.com/journal/TAR</link>
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        <copyright>All rights reserved 2026, ŁUKASIEWICZ RESEARCH NETWORK – INSTITUTE OF AVIATION</copyright>
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        <item>
            <title><![CDATA[CFD Study of Ejector Nozzle Models]]></title>
            <link>https://reference-global.com/article/10.2478/tar-2026-0014</link>
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            <pubDate>Mon, 28 Sep 2026 00:00:00 GMT</pubDate>
            <description><![CDATA[This paper presents a CFD study of thrust-augmenting ejector nozzles for small turbojet engines, motivated by the theoretical prediction of Alperin and Wu that a substantial thrust increase is attainable at moderate subsonic flight speeds via a so-called “second solution” in which the flow at the exit of the mixing chamber is supersonic. The input parameters were derived from Alperin’s 1D theory; an axisymmetric baseline nozzle model was constructed and validated against a component-based thermodynamic model using the Grid Convergence Index; and 61 ejector nozzle configurations with area ratios α* = 4 and 5 were computed in ANSYS Fluent 2024R1 at M∞ = 0.6. Fields of Mach number, static pressure and static temperature, together with pathline patterns and integral thrust parameters, are presented and discussed. In none of the configurations tested, spanning annular and nose air intakes, varied mixing chamber geometries, and explicit specification of the secondary flow rate, could the second solution be reached: the flow at the mixing chamber exit remained subsonic in every case, corresponding to Alperin’s first solution, for which the thrust augmentation ratio is below unity. The contraction of the common exhaust unit was identified as the factor suppressing the secondary flow. These results indicate that ejector nozzles of the type studied cannot increase the thrust of a small turbojet at moderate subsonic flight speeds, and they cast doubt on the physical realizability of Alperin’s second solution in this regime.]]></description>
            <category>ARTICLE</category>
        </item>
        <item>
            <title><![CDATA[Three-Point Bending and Cohesive Zone Analysis of Resistance-Welded Carbon-Fiber-Reinforced Polycarbonate to Aluminum 7075 Single-Lap Joints]]></title>
            <link>https://reference-global.com/article/10.2478/tar-2026-0018</link>
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            <pubDate>Mon, 28 Sep 2026 00:00:00 GMT</pubDate>
            <description><![CDATA[Resistance-welded thermoplastic composite-metal hybrid joints may be useful for temporary or secondary aerospace repair concepts, but their small-coupon response is difficult to interpret because bending, peel, sliding and welding-induced residual stresses occur simultaneously. This paper presents an adapted three-point-bending study of six single-lap coupons made from carbon-fiber-reinforced polycarbonate and aluminum 7075. The test was used as a screening method to determine global stiffness, peak force and debonding behavior under a concentrated transverse load. The recorded force was converted to a nominal bending stress indicator using the test geometry. Peak forces ranged from 246.1 N to 293.7 N, with a mean value of 274.0 N. The corresponding nominal bending stress indicator ranged from 131.8 MPa to 157.3 MPa, with a mean value of 146.8 MPa. The apparent work per overlap area ranged from 0.615 mJ/mm2 to 0.804 mJ/mm2. The area under the force-displacement curve was not treated as fracture energy because it also includes adherend bending, contact work and residual-stress release. The calculated stress-displacement curves were used to calibrate an ANSYS cohesive-zone debonding model. The welding-induced residual state was introduced through an initial strain condition before mechanical loading. The calibrated model predicted a peak stress of approximately 156 MPa, corresponding to approximately 291 N. This value was about 6.3% above the experimental mean and remained within the experimental range.]]></description>
            <category>ARTICLE</category>
        </item>
        <item>
            <title><![CDATA[Assurance–Traceability–Risk Modeling for Verification-Ready Design of a Multi-Fuel Aircraft Reciprocating Engine Test Cell]]></title>
            <link>https://reference-global.com/article/10.2478/tar-2026-0013</link>
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            <pubDate>Mon, 28 Sep 2026 00:00:00 GMT</pubDate>
            <description><![CDATA[This study developed and applied an Assurance–Traceability–Risk (ATR) framework for Phase 1 conceptual design assurance of a multi-fuel aircraft reciprocating engine test cell for aviation education and applied research. The study addressed the need for a pre-construction method that links stakeholder requirements, technical feasibility assessments, safety controls, and verification planning prior to fabrication or commissioning. Using Design Science Research and a convergent mixed-methods design, the study integrated stakeholder inputs, technical expert interviews, requirements coding, traceability analysis, hazard-control mapping, Expert Feasibility Validation, and Verification Readiness Index scoring. The requirements baseline identified 42 stakeholder-derived requirements across seven categories: fuel architecture, controls and interlocks, instrumentation and data acquisition, ventilation and exhaust, structural layout, procedures, and verification readiness. Traceability analysis showed that all requirements were source-linked, 92.9% were linked to design features, 83.3% to verification methods, and 81.0% were trace-complete. Safety mapping identified 18 hazard scenarios, with 88.9% linked to controls and 77.8% having dual-control coverage. The overall VRI was 78.2/100, indicating moderate-to-high readiness. Carbureted and EFI configurations showed stronger feasibility, while DI remained conditionally feasible. The study demonstrates conceptual feasibility and verification readiness, not operational effectiveness. Full validation requires Phase 2 engineering, commissioning, and controlled engine-run testing.]]></description>
            <category>ARTICLE</category>
        </item>
        <item>
            <title><![CDATA[Emerging Technologies for the Diagnosis and Testing of Avionics Components in Defense Aviation Maintenance: A Systematic Review (2020–2025)]]></title>
            <link>https://reference-global.com/article/10.2478/tar-2026-0015</link>
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            <pubDate>Mon, 28 Sep 2026 00:00:00 GMT</pubDate>
            <description><![CDATA[Emerging technologies offer promising tools for aircraft maintenance, but their application to the unscheduled diagnosis and testing of avionics components is poorly documented, particularly in military contexts. This systematic literature review, following PRISMA guidelines, covers technologies applied to avionics maintenance between 2020 and 2025. Searches of Scopus and Google Scholar returned 2,949 records; 47 studies were included after screening and assessed through the Technology–Organization–Environment (TOE) framework. The Colombian Army's flight control computer (FCC) maintenance challenges serve as a motivating case. Four thematic categories were identified: diagnostics and testing of aeronautical components; diagnostics and testing of avionics components; FCC diagnostics and testing; and efficiency in aeronautical maintenance. Simulation-based testing, particularly hardware-in-the-loop approaches, reduces diagnostic times and costs; artificial intelligence and machine learning improve diagnostic accuracy but depend on data infrastructure that defense organizations frequently lack. Technological complexity and organizational readiness are the principal barriers to adoption. The review found limited application of these technologies to FCC post-repair validation, identifying this as a gap and a research priority.]]></description>
            <category>ARTICLE</category>
        </item>
        <item>
            <title><![CDATA[Safety as an Instrumental Condition for Achieving System Objectives: A Goal-Oriented Model Grounded in the Principle of Probability Adequacy]]></title>
            <link>https://reference-global.com/article/10.2478/tar-2026-0016</link>
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            <pubDate>Mon, 28 Sep 2026 00:00:00 GMT</pubDate>
            <description><![CDATA[Problem statementReducing the accident rate in aviation requires safety to be ensured at every stage of risk management. The risk management context is the formalized set of conditions within which objectives are defined and risk criteria are established, so that an event is classified as a risk only insofar as it affects the achievability of those objectives. Under these conditions, safety cannot be treated as an independent goal: doing so produces a methodological disconnect, distorts the hierarchy of goals, creates conflict between functional activity and safety requirements, and drives an orientation toward zero risk. This conceptual and theoretical study develops a formalized, goal-oriented risk management framework in which safety is a function of the balance between the probability of threats and the effectiveness of preventive measures.AimTo formulate the risk management context within a goal-oriented framework, in which safety is treated as an instrumental attribute reflecting the adequacy of risk treatment measures relative to predefined risk acceptance criteria and the achievement of the system’s objective, including in aviation.ConclusionsSafety should be interpreted as an instrumental attribute of the adequacy of risk management decisions, not an autonomous goal; treating it as such (its teleologization) reduces the functional effectiveness and resilience of sociotechnical systems. The resulting goal-oriented framework provides a methodological basis for improving risk-informed management under uncertainty.]]></description>
            <category>ARTICLE</category>
        </item>
        <item>
            <title><![CDATA[Advanced Composite Vibration Damping Mount for Enhanced UAV Payload Stability: A Comprehensive Review]]></title>
            <link>https://reference-global.com/article/10.2478/tar-2026-0017</link>
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            <pubDate>Mon, 28 Sep 2026 00:00:00 GMT</pubDate>
            <description><![CDATA[Unmanned aerial vehicles (UAVs) are now widely used in military, commercial, agricultural, and surveillance applications, where payload stability is critical to mission success. However, UAV structures remain highly susceptible to vibrations from the propulsion system, aerodynamic disturbances, and structural dynamics, which degrade sensitive payloads such as cameras, LiDAR sensors, and communication equipment through image distortion, sensor inaccuracy, and reduced reliability. Conventional isolation methods, such as rubber mounts, spring-damper systems, and tuned mass dampers, are simple and inexpensive but offer only narrow operating bandwidths, added weight, and limited adaptability. This review examines advanced composite materials, including fiber-reinforced polymers, viscoelastic sandwich composites, hybrid composites, and smart materials such as piezoelectric elements and shape memory alloys, as more effective alternatives. Their damping mechanisms (fiber–matrix friction, matrix viscoelasticity, and constrained-layer damping) enable broadband vibration suppression with minimal weight penalty, offering better frequency coverage, fatigue resistance, and payload protection than conventional isolators. Key challenges remain in material optimization, structural integration, environmental durability, and manufacturing scalability. Future research directions include multifunctional smart composites, machine-learning-assisted design, self-sensing and self-healing materials, and full-scale UAV validation.]]></description>
            <category>ARTICLE</category>
        </item>
        <item>
            <title><![CDATA[Aerolang: A Dimensionally-Aware Domain-Specific Language for Real-Time Flight Control with Integrated Morphing Wing Physics]]></title>
            <link>https://reference-global.com/article/10.2478/tar-2026-0011</link>
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            <pubDate>Wed, 17 Jun 2026 00:00:00 GMT</pubDate>
            <description><![CDATA[Safety-critical flight software for autonomous aerial vehicles must respect the physics of flight and the constraints of embedded hardware. Existing practice relies on general-purpose languages where physical units are implicit and dimensional consistency is enforced only by reviews, unit tests, and flight campaigns—leaving systems vulnerable to catastrophic unit mismatches such as the Mars Climate Orbiter loss. This paper introduces AeroLang, a domain-specific language for flight control that makes physical units and real-time constraints first-class language citizens. AeroLang programs combine explicit SI unit annotations, declarative real-time loop periods, and an @EMBEDDED mode that statically forbids unbounded allocation. A complete compiler pipeline is presented: an LALR(1) parser, a semantic type checker performing compile-time dimensional analysis, and a Python code generator producing zero-overhead control components. The language is demonstrated through a morphing-wing UAV controller coupled to a free-vortex-wake aerodynamic model and an Euler-Bernoulli aeroelastic model. All dimensional inconsistencies are caught at compile time, the generated controller executes with negligible overhead, and the closed-loop system reproduces morphing-wing efficiency gains of approximately 11.3% in lift-to-drag ratio, consistent with published literature.]]></description>
            <category>ARTICLE</category>
        </item>
        <item>
            <title><![CDATA[Numerical Simulation of Composite Structural Failure: A Review of Methods and Correlation with Destructive Tests]]></title>
            <link>https://reference-global.com/article/10.2478/tar-2026-0010</link>
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            <pubDate>Wed, 17 Jun 2026 00:00:00 GMT</pubDate>
            <description><![CDATA[Advanced composite structures are widely used in aerospace and related industries, yet manufacturing defects and in-service damage can significantly reduce their structural integrity, necessitating costly destructive testing. This article reviews numerical methods for simulating composite structural failure, drawing on literature from 2015 to 2024, and assesses their correlation with destructive test results. Progressive damage models, cohesive zone modeling, and finite element implementation strategies are discussed across a range of scenarios including bolted joint failures, open-hole tension, compression-after-impact, and bonded repairs. Well-calibrated models are shown to predict failure loads within 5–15% of experimental values and to reproduce failure modes including fiber fracture, matrix cracking, and delamination. The choice of failure criterion – Hashin, Puck, or LaRC – is found to significantly affect accuracy in matrix-dominated cases. The review concludes that validated numerical simulation offers a credible complement to physical testing in composite certification, with remaining challenges in multiscale modeling, environmental effects, and regulatory acceptance identified as priorities for future research.]]></description>
            <category>ARTICLE</category>
        </item>
        <item>
            <title><![CDATA[CFD Comparison of Selected Distributed Propulsion Configurations for an Inverted-Joined-Wing Airplane]]></title>
            <link>https://reference-global.com/article/10.2478/tar-2026-0012</link>
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            <pubDate>Wed, 17 Jun 2026 00:00:00 GMT</pubDate>
            <description><![CDATA[This paper addresses the aerodynamic performance of an inverted joined wing aircraft subject to propulsion subsystem modifications. The original aircraft, which suffers from poor pitching moment characteristics, is modified through propulsion redesign, with a focus on distributed propulsion. The extended design freedom was expected to offer a new perspective on aircraft performance. Several concepts were analyzed using high-fidelity Computational Fluid Dynamics (CFD). The study confirmed these expectations, significantly improving cruise performance. The electric ducted fans (EDF) configurations proved the most promising, due to their stronger influence on the stream around the wing. Conventional propellers, mounted at a distance from the wing, did not affect the aerodynamics as significantly. Further optimization of distributed propulsion layout and geometry is expected to improve the aircraft’s performance metrics.]]></description>
            <category>ARTICLE</category>
        </item>
        <item>
            <title><![CDATA[Evidence-Grounded Decision Support for Aircraft Line Maintenance Using Conformal Prediction and Retrieval-Augmented NLP from Technical Log Records]]></title>
            <link>https://reference-global.com/article/10.2478/tar-2026-0009</link>
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            <pubDate>Wed, 17 Jun 2026 00:00:00 GMT</pubDate>
            <description><![CDATA[Aircraft line maintenance requires rapid triage of short defect narratives despite variable documentation quality, which can weaken coding consistency and traceability. This study develops and evaluates an evidence-grounded decision-support pipeline using secondary records from the Federal Aviation Administration Service Difficulty Reporting System. The corpus comprised 4,430 deduplicated events from 2021 to 2023 across 10 receiving regions and 290 aircraft make–model combinations, with a heavily imbalanced distribution of Joint Aircraft System/Component (JASC) codes as supervised labels; broader Air Transport Association chapter groupings were used only for post hoc aggregation. Validation used a chronological 70/10/20 train/calibration/test split, with calibration reserved for conformal tuning, plus a station hold-out protocol to assess cross-site transferability. The pipeline combined a lightweight text classifier for JASC triage, term frequency–inverse document frequency (TF-IDF) retrieval to identify label-consistent precedents, and split-conformal prediction with a review-required abstention rule. On the temporal test set, the TF-IDF representation with a linear support vector machine classifier achieved top-1 accuracy of 0.509 and top-3 accuracy of 0.683, while retrieval achieved Recall@10 = 0.688 and mean reciprocal rank = 0.466. Conformal prediction attained empirical coverage of 0.919 at a 90% target. Performance declined directionally under station shift, highlighting the need for monitoring, governance, and human oversight in deployment. Overall, the study contributes a deployment-aligned evaluation protocol integrating retrieval and conformal prediction for auditable line-maintenance triage.]]></description>
            <category>ARTICLE</category>
        </item>
        <item>
            <title><![CDATA[Design and Performance Analysis of a Propeller for a Hybrid Turbo-Electric Propulsion System of a Regional Aircraft]]></title>
            <link>https://reference-global.com/article/10.2478/tar-2026-0008</link>
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            <pubDate>Wed, 17 Jun 2026 00:00:00 GMT</pubDate>
            <description><![CDATA[Meeting the ACARE environmental goals is a central driver of current EU aerospace research, and hybrid turbo-electric propulsion systems (HTEPS) are emerging as a promising route to reducing the environmental impact of regional aviation. This paper reports the design and performance analysis of a propeller for the HTEPS of an advanced regional aircraft. Twenty propeller variants were generated using Zhukovsky’s vortex theory and the Adkins–Liebeck BEMT algorithm, with a NASA GA(W) aerofoil section, and were evaluated at Max Cruise (H = 6000 m, M = 0.45) and Take-off (H = 0, M = 0) by CFD analysis in ANSYS CFX using the SST turbulence model with Gamma–Theta transition. The effects of blade number and maximum diameter on Cruise efficiency and Take-off thrust were studied, leading to the selection of a seven-bladed propeller with a maximum diameter of 4.15 m. The performance of the selected propeller was then calculated over a wide range of flight Mach numbers. The final variant exhibits a maximum efficiency above 0.86, which remains almost constant over the range M = 0.35 to M = 0.65. Joint operation of the propeller and the HTEPS was simulated under three engine control laws (Power = const, T41 = const, PRtot = const). The PRtot = const law is shown to offer the highest propeller efficiency at elevated flight speeds, together with benefits for gas-turbine efficiency and for fuel-cell performance through the supply of higher-pressure bleed air. The 3D geometry of the propeller’s aerodynamic surfaces has been generated and is intended for use in subsequent aeroacoustic CFD analysis.]]></description>
            <category>ARTICLE</category>
        </item>
        <item>
            <title><![CDATA[Physics-Informed Telemetry Simulation and Shap-Based Explainable Machine Learning for Multi-Sensor UAV Fault Diagnosis]]></title>
            <link>https://reference-global.com/article/10.2478/tar-2026-0007</link>
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            <pubDate>Wed, 17 Jun 2026 00:00:00 GMT</pubDate>
            <description><![CDATA[Unmanned Aerial Vehicles (UAVs) rely on tightly coupled onboard sensors for stable and safe flight; however, early-stage fault detection remains challenging due to noisy telemetry, nonlinear dynamics, and limited labelled fault data. This study presents a simulation-driven, explainable machine-learning framework for multi-sensor UAV fault diagnosis within digital-twin environments. A physics-informed telemetry generator produces synchronized accelerometer, gyroscope, motor RPM, battery voltage, and GPS signals with systematic injection of representative fault modes, including motor degradation, battery sag, IMU drift, and GPS anomalies. The multivariate time series is segmented using overlapping windows and transformed into a 60-dimensional statistical feature space designed for interpretability and computational efficiency. A Random Forest classifier achieves 99.33% test accuracy and an AUC of 0.997 under controlled simulation conditions. SHAP-based explainability quantifies feature-level contributions, highlighting the dominant influence of gyroscope drift and battery-voltage descriptors consistent with known degradation mechanisms. The framework provides a lightweight, reproducible, and interpretable diagnostic pipeline for simulation-based verification and early-stage UAV health-monitoring development.]]></description>
            <category>ARTICLE</category>
        </item>
        <item>
            <title><![CDATA[The Influence of a Hybrid Turboelectric Power Plant Energy System on the Performance and Emissions of A Passenger Aircraft]]></title>
            <link>https://reference-global.com/article/10.2478/tar-2026-0004</link>
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            <pubDate>Wed, 18 Mar 2026 00:00:00 GMT</pubDate>
            <description><![CDATA[This study investigates how the architecture and key parameters of a hybrid turboelectric power plant (HTEPP) energy system influence the performance and environmental characteristics of a light regional passenger aircraft. Three HTEPP configurations are analyzed: (i) kerosene and liquid hydrogen supplied to both the combustion chamber and a fuel cell (FC), (ii) kerosene supplied to the combustion chamber with hydrogen supplied only to the FC, and (iii) kerosene supplied to the combustion chamber with hydrogen produced onboard via kerosene reforming for FC supply. A 20-seat aircraft concept derived from the L-410UVP-E family is developed and upgraded to accommodate the HTEPP, using the AI-450S-2 L-410UVP-E family is developed and upgraded to accommodate the HTEPP, using the AI-450S-2 turboprop engine and AI-P500V5 propellers. The study applies a semi-empirical aerodynamic method and a modular simulation framework (“Integration 2.2”) to estimate mission power demand, subsystem mass/volume characteristics, payload–range capability, and gross harmful emissions consistent with ICAO Annex 16 methodology. Results show that range gains from the HTEPP are modest due to mass penalties, whereas emissions reductions are more pronounced: approximately 21.1% for Scheme 1, 16.2% for Scheme 2, and 10.3% for Scheme 3. Turbine inlet gas temperature decreases by about 6–8% across all schemes, implying potential durability benefits. The findings highlight the central role of energy-management strategy and hybridization degree in determining feasible architectures and performance trade-offs for regional hybrid-electric aircraft.]]></description>
            <category>ARTICLE</category>
        </item>
        <item>
            <title><![CDATA[A Dynamic Predictive Likelihood Framework for Anticipatory Adaptive Nested Optimization in Airline Seat Reservation Control]]></title>
            <link>https://reference-global.com/article/10.2478/tar-2026-0003</link>
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            <pubDate>Wed, 18 Mar 2026 00:00:00 GMT</pubDate>
            <description><![CDATA[This study develops a novel dynamic framework for anticipatory and adaptive airline seat inventory control under stochastic customer demand. The proposed approach integrates predictive likelihood estimation, nested protection-level optimization, and adaptive decision updating within a unified mathematical structure. Demand arrivals are modeled over a discrete booking horizon divided into multiple decision epochs, allowing continuous revision of protection levels and booking limits as new information becomes available. Unlike classical static approaches such as Littlewood's rule and EMSR heuristics, the proposed model combines global non-nested optimization with local nested protection-level adjustment based on predictive likelihood functions of customer demand. The framework enables real-time updating of allocation decisions while maintaining consistency with capacity constraints and revenue dominance conditions. In addition, a statistical procedure based on Weibull modeling of reservation times is introduced to detect structural changes in customer demand or competitive pricing strategies through minimization of misrecognition probability. Numerical simulations demonstrate that the proposed dynamic approach improves expected revenue relative to non-nested allocation and heuristic EMSR methods under representative parameter settings. The results suggest that predictive likelihood-based adaptive optimization provides a rigorous and computationally tractable alternative to heuristic seat allocation rules.]]></description>
            <category>ARTICLE</category>
        </item>
        <item>
            <title><![CDATA[Suborbital Spaceflight Regulation: A Case-Based Commentary on Managing Risk Beyond the Learning Period]]></title>
            <link>https://reference-global.com/article/10.2478/tar-2026-0002</link>
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            <pubDate>Wed, 18 Mar 2026 00:00:00 GMT</pubDate>
            <description><![CDATA[This study presents a qualitative, case-based risk assessment to evaluate participant safety and regulatory accountability in suborbital spaceflight. Currently, the suborbital flight sector is operating under a regulatory “learning period” moratorium that offers minimal oversight from the Federal Aviation Administration’s Office of Commercial Space Transportation (FAA-AST). A qualitative Bowtie-based case study is presented herein, applying the ICAO risk matrix and the ALARP (As Low As Reasonably Practicable) methodology to a representative loss-of-pressurization scenario in Blue Origin’s suborbital operations. This approach demonstrates that structured qualitative risk-management frameworks can effectively assess catastrophic hazards with limited empirical data and reduce risks to acceptable levels without imposing excessive costs on operators. To address existing safety and regulatory gaps, this study recommends: (1) establishing a defined regulatory framework with mandatory vehicle certification and legal protections for participants; (2) the adoption of risk-management methodologies such as ALARP and CBA by commercial operators; (3) developing FAA-AST– directed medical screening and training programs for spaceflight participants; (4) incorporating personal safety equipment, including breathing apparatus; and (5) fostering collaboration with established aerospace institutions such as NASA. Overall, the findings highlight the need for near-term policy action to support a safe, sustainable, and accountable evolution of suborbital space tourism.]]></description>
            <category>ARTICLE</category>
        </item>
        <item>
            <title><![CDATA[Numerical Investigation of a Nested Double Annular Combustion Chamber Configuration for Rotating Detonation Engine Applications]]></title>
            <link>https://reference-global.com/article/10.2478/tar-2026-0005</link>
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            <pubDate>Wed, 18 Mar 2026 00:00:00 GMT</pubDate>
            <description><![CDATA[Rotating Detonation Engines (RDEs) utilize supersonic combustion to enhance propulsion efficiency while enabling simplified engine architectures. However, in a conventional annular RDE, the central plug reduces thrust density compared to alternative propulsion concepts. To address this limitation, a nested double annular combustion chamber is proposed. This study evaluates the feasibility and performance of the configuration using two-dimensional axisymmetric computational fluid dynamics (CFD) simulations in ANSYS Fluent. Comparative numerical analyses of single- and double-chamber models were conducted under identical mass flux conditions. The results indicate that the proposed double-chamber configuration achieves comparable performance and can even outperform the single-chamber annular RDE by up to 2.26% in thrust per chamber area. These findings provide valuable insight into the potential of nested annular RDE configurations for improving thrust density and propulsion system compactness in future propulsion applications.]]></description>
            <category>ARTICLE</category>
        </item>
        <item>
            <title><![CDATA[Uncertainty-Aware Robustness Analysis of Blended-Wing-Body Cabin Evacuation Under the Faa 90-Second Requirement (14 CFR § 25.803)]]></title>
            <link>https://reference-global.com/article/10.2478/tar-2026-0006</link>
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            <pubDate>Wed, 18 Mar 2026 00:00:00 GMT</pubDate>
            <description><![CDATA[Blended-wing-body (BWB) aircraft are currently being explored for potential efficiency gains, but emergency evacuation remains a key certification feasibility requirement for wide, non-cylindrical cabins under the FAA 90 s rule (14 CFR §25.803). This study reframes evacuation compliance as a probabilistic safety assessment problem and develops an uncertainty-aware pipeline for certification-style robustness evidence. Evacuation is posed as a limit-state problem, g(θ) = 90 - T(θ), where T is evacuation time under uncertainty in behavioral and flow parameters. Monte Carlo simulation propagates bounded aleatory variability and evidence-tagged epistemic assumptions across a predefined stressor matrix (S0–S7) to estimate the distribution of T. Compliance is reported as PoC = P(T ≤ 90 s) with 95% confidence intervals and tail-risk metrics (T95,T99); Morris screening identifies dominant contributors to failure probability Pf = 1 - PoC and extreme delays. Baseline conditions meet the 90 s requirement, whereas topology/capacity disruptions – especially exit loss and compound stress – drive PoC toward zero and inflate upper-tail percentiles, indicating discharge-capacity limits. Reduced visibility and degraded crew effectiveness primarily thicken the right tail, yielding partial compliance but elevated Pf at 90 s. Robust layout screening (D1–D9) shows that exit-demand redistribution and capacity-preserving geometry recover safety margin with limited structural penalty growth‥]]></description>
            <category>ARTICLE</category>
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        <item>
            <title><![CDATA[Analytical Modelling and Parametric Optimization of Hybrid Hydrogen-Electric Propulsion for Long-Endurance UAVs]]></title>
            <link>https://reference-global.com/article/10.2478/tar-2026-0001</link>
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            <pubDate>Sat, 14 Mar 2026 00:00:00 GMT</pubDate>
            <description><![CDATA[This study presents a clear and analytically explicit framework for exploring hybrid hydrogen–electric propulsion in micro-to-small fixed-wing unmanned aerial vehicles (UAVs). By combining classical lift–drag relationships with a first-principles energy balance, the model expresses flight endurance and range through simple, closed-form relations involving hydrogen mass, battery capacity, and cruise speed. Unlike approaches that rely on computationally intensive CFD simulations or extensive hardware testing, the framework is entirely physics-based, enabling fast, transparent, and reproducible performance estimation during early design stages. A parametric design-space analysis examines how mass allocation between hydrogen and battery storage influences endurance and range. Under idealized, constant-mass and constant-efficiency assumptions, the analytical model predicts that balanced hybrid configurations can yield theoretical endurance values approaching 70 hours and ranges on the order of 3700 km, representing a substantial improvement relative to battery-only operation. Contour-based visualization illustrates trade–offs associated with hybridization ratios and cruise conditions, providing intuitive insight into system-level behaviour. Owing to its simplicity, interpretability, and open analytical structure, the framework serves as a practical conceptual-design tool for UAV sizing, propulsion planning, and sustainable long-endurance flight studies. The model supports early-stage decision-making by offering a physics-grounded means of exploring hybrid UAV performance trends prior to more detailed analyses.]]></description>
            <category>ARTICLE</category>
        </item>
        <item>
            <title><![CDATA[Study of the Impact of Prolonged Operation on Residual Deformations in the Airframe Structure of an Aircraft]]></title>
            <link>https://reference-global.com/article/10.2478/tar-2025-0019</link>
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            <pubDate>Wed, 24 Dec 2025 00:00:00 GMT</pubDate>
            <description><![CDATA[PurposeThe study aims to quantitatively assess the accumulation of residual deformations in the aircraft airframe during long-term operation, using the An-24 regional aircraft as a representative case.MethodsLevelling data obtained during maintenance were statistically processed using regression and correlation analysis. Polynomial trend models were combined with probability distribution parameters (mean, standard deviation, skewness) to describe geometric deviations of wing control sections across different intervals of flight hours, service life, and landings.ResultsThe analysis revealed that 25–32% of wing geometry variations are explained by accumulated flight hours, while the remaining deviations result from other operational factors such as hard landings, turbulence, and maintenance practices. Residual deformations manifested as systematic changes in wing incidence and dihedral angles, with probability estimates showing a nonlinear increase in the risk of exceeding permissible limits.Practical implicationsThe findings improve monitoring of structural geometry through systematic levelling, enhance the reliability of residual life prediction, and support the development of preventive maintenance strategies aimed at ensuring long-term airworthiness and flight safety.]]></description>
            <category>ARTICLE</category>
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            <title><![CDATA[A Poisson-Process Model for Cumulative Delamination Damage in Composite Materials]]></title>
            <link>https://reference-global.com/article/10.2478/tar-2025-0022</link>
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            <pubDate>Wed, 24 Dec 2025 00:00:00 GMT</pubDate>
            <description><![CDATA[This study presents a probabilistic model for cumulative damage in composite materials undergoing delamination. The model assumes the presence of numerous weak microvolumes (WMVs) in which fatigue damage can initiate and accumulate. Defect nucleation is described as a Poisson process whose rate does not depend on specimen size. The cumulative distribution function of the fatigue life of each microvolume is obtained using the Poisson formulation, and the overall delamination behavior is interpreted as a brittle-type failure mechanism governed by nodal attachment points in honeycomb structures. Numerical implementation is demonstrated through Excel-based inverse comparison and R-based simulation methods. The results show that Poisson-driven damage evolution provides a viable approach for estimating residual undamaged area and for modelling avalanche-type delamination growth. The methodology offers a foundation for future experimental verification and refinement of stochastic models for composite damage propagation.]]></description>
            <category>ARTICLE</category>
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