Aircraft Technology Research Articles

Research on Optimization Design of Intelligent Aircraft

Demand analysis and concept research of intelligent deform-able aircraft, overall and subsystem design technology of intelligent deform-able aircraft. From the perspective of basic scientific problems and bottleneck technologies, the main problems lie in two aspects, namely: aerodynamics, flight mechanics and flight control of deform-able aircraft, deform-able structure, drive and deformation control. The connotation of intelligent deform-able aircraft, deform-able technical indicators, deform-able materials and structures, and cost-effectiveness analysis. Technical difficulties for each performance indicator mentioned above, some novel technologies and methods are used to improve the performance of cross-medium aircraft, which are mainly divided into variable wing technology, variable blade technology, variable density technology and structural buffer technology.

Effect of ultra-high aspect ratio wings and distributed propulsion on the viability of fully electric regional aircraft

PurposeRevolutionary advances in aircraft technology and performance are needed for fuel-efficient and sustainable next-generation air transportation. This study aims to explore the influence of integrating distributed propulsion with ultra-high aspect ratio (AR) wings (UHARW) on the realization of fully electric regional aviation.Design/methodology/approachThe strut-braced wing (SBW) configuration is advantageous for UHARW due to its additional support. A conceptual design and analysis framework for UHARW aircraft with SBW and distributed propulsion configurations is developed by enhancing and integrating several methods and tools. Based on the mission profile and top-level requirements, a fully electric regional SBW aircraft with distributed propulsion is designed and analyzed.FindingsIntegrating distributed propulsion with a high AR SBW configuration in a fully electric regional aircraft results in notable energy efficiencies. The design achieves a 2.85% increase in the lift-to-drag ratio and a 2.62% reduction in drag during cruise. Sensitivity analysis indicates optimal performance with an AR up to 22, beyond which structural weight penalties diminish benefits. The aircraft’s energy efficiency improves by 9.9% during climb and 6% during cruise, highlighting the importance of propulsion integration.Practical implicationsThis research provides a viable framework for designing fully electric regional aircraft by integrating distributed propulsion with high AR SBW configurations. The findings provide practical guidance for enhancing energy efficiency and reducing structural weight, supporting the development of more sustainable and efficient aircraft designs.Social implicationsThe findings support the development of sustainable aviation technologies, potentially reducing the environmental footprint of regional air travel and contributing to global efforts toward greener transportation solutions.Originality/valueThis study presents a comprehensive methodology for designing and analyzing UHARW aircraft with SBW and distributed propulsion, contributing to the feasibility assessment of fully electric regional aviation.

Potential of Hydrogen Fuel Cell Aircraft for Commercial Applications with Advanced Airframe and Propulsion Technologies

The present work demonstrates a comparative study of hydrogen fuel cells and combustion aircraft to investigate the potential of fuel cells as a visionary propulsion system for radically more sustainable medium- to long-range commercial aircraft. The study, which considered future airframe and propulsion technologies under the Se2A project, was conducted to quantify potential emissions and costs associated with such aircraft and to determine the benefits and drawbacks of each energy system option for different market segments. Future technologies considered in the present work include laminar flow control, active load alleviation, new materials and structures, ultra-high bypass ratio turbofan engines, more efficient thermal management systems, and superconducting electric motors. A multi-fidelity initial sizing framework with coupled constraint and mission analysis blocks was used for parametric airplane sizing and calculations of all necessary characteristics. Analyses performed for three reference aircraft of different sizes and ranges concluded that fuel-cell aircraft could have operating cost increases in the order of 30% compared to hydrogen combustion configurations and were caused by substantial weight and fuel burn increases. In-flight changes in emissions of fuel cell configurations at high altitudes were progressively reduced from medium-range to long-range segments from being similar to hydrogen combustion for medium-range to 24% for large long-range aircraft, although fuel cell aircraft consume 22–30% more fuel than combustion aircraft. Results demonstrate a positive environmental impact of fuel cell propulsion for long-range applications, the possibilities of being a more emission-universal solution, if desired optimistic technology performance metrics are satisfied. The study also demonstrates progressively increasing technology requirements for larger aircraft, making the long-range application’s feasibility more challenging. Therefore, substantial development of fuel cell technologies for long-range aircraft is imperative. The article also emphasizes the importance of airframe and propulsion technologies and the necessity of green hydrogen production to achieve desired emissions.

Research on monocular vision-based reconstruction technology for aircraft fuel liquid surfaces

Research on monocular vision-based reconstruction technology for aircraft fuel liquid surfaces

Adaptive proportional integral derivative fault tolerant control for continuous-time switched systems: A highly maneuverable aircraft technology (HiMAT) vehicle application

This article presents an active fault-tolerant tracking control (FTTC) scheme for switched linear systems with unknown external disturbances and actuator faults. First, a switched adaptive observer (SAO) is designed to simultaneously achieve system state and actuator fault estimation. Second, an active fault-tolerant tracking controller with a reconfigurable adaptive proportional–integral–derivative architecture is proposed based on the results of these estimations. This FTTC technique aims to ensure the tracking of a predefined reference trajectory while also compensating for actuator fault effects. In terms of linear matrix inequalities, less conservatism design conditions for the SAO and fault-tolerant tracking controller are obtained by utilizing the average dwell time technique and multiple Lyapunov functions. Finally, an application to the highly maneuverable aircraft technology vehicle is used to prove the benefits of the presented scheme.

Revitalizing Diesel Technology in Aircraft: A Path Toward Fuel Efficiency and Sustainability

As the aviation industry seeks to reduce its environmental impact and improve fuel efficiency, diesel engines have re-emerged as a promising alternative to traditional aviation fuels. This paper explores the historical development, advantages, challenges, and current applications of diesel engines in aviation. With their superior fuel efficiency, lower emissions, and enhanced durability, diesel engines offer significant potential for reducing operational costs and contributing to the industry's sustainability goals. However, challenges related to engine weight, performance limitations, certification processes, and noise concerns have slowed their widespread adoption. Key advancements in turbocharging, direct fuel injection, and hybrid integration are poised to overcome these obstacles, making diesel engines increasingly viable for various aviation sectors. Current applications, such as the Diamond DA40 and DA62, the Aero Vodochody L-39 Albatros, and the Pipistrel Alpha Electro, demonstrate the adaptability and cost-saving potential of diesel engines. The paper concludes by discussing future prospects for diesel engine technology in aviation, highlighting ongoing technological innovations and the critical role of regulatory support in fostering sustainable aviation solutions.

Dynamic model adjustment of a honeycomb sandwich panel using response surface methods and parametric optimization algorithms

The aeronautical and aerospace industries have been evolving in technologies that improve the efficiency of their structures, where, in this context, sandwich panels with honeycomb cores are one of the frequently employed technologies in aircraft and nano satellites. This type of structure presents superior mechanical properties compared to traditional panels, as well as a low structural weight due to its porous core. However, they exhibit complex characteristics both geometrically and behaviorally, requiring the use of more sophisticated computational tools such as finite element analysis packages. Precise numerical models are required to allow for reliable analysis during the design process of aerospace structures. The most commonly employed approach is to create a numerical model and refine it through adjustments using experimental data. This study presents the modal numerical analysis of a sandwich panel with a honeycomb core using finite elements and proposes an adjustment of the obtained numerical model. The panel is composed of Aluminum 2024 skins and an Aluminum 5056 honeycomb core. This panel had its vibration modes and frequencies previously identified through experimental tests. Once the numerical and experimental values are compared, a numerical-experimental adjustment is proposed using the optimization algorithms NLPQL, MISQP, and Genetic, which are applied through two methodologies, with and without the use of a metamodel, where the metamodel is constructed using the kriging algorithm. The optimization problem was formulated considering the minimization of a function defined as the sum of squared differences between experimental and numerical frequencies. The ANSYS Workbench software package was utilized for the numerical modeling, which also provided the necessary optimization algorithms. The results demonstrate good agreement with the experimental data, and the numerical adjustments made using the optimization algorithms proved to be effective.

Research on manufacturing process control and analysis technology of civil aircraft

Abstract The manufacturing stage is the core link of product reliability, and the manufacturing process control is the bridge between design reliability and product reliability. In the manufacturing process, the influence of various factors on the formation of product reliability is considered and controlled. Meanwhile, the process failure mode and impact analysis (PEMEA) method is introduced to clarify its principle and method. The key processes of the manufacturing and assembly process are identified by taking the RAT system of certain aircraft as an example. Effective measures are proposed to improve the manufacturing and assembly process, ensure the manufacturing reliability of products, and provide strong support for improving the quality and reliability of civil aircraft.

Economic Feasibility Study of Deploying Green H2 Infrastructure at Los Angeles International Airport (LAX)

Air transportation is among the critically debated subjects, contributing to approximately 2.5% of global CO2 emissions 1. The main strategy for addressing environmental concerns related to aviation emissions is the shift to low-carbon propulsion technologies for aircraft. Hydrogen could be introduced to the aviation sector as a fuel for fuel cell-powered aircraft or for direct combustion jet engines, with anticipated zero- to low-carbon emissions 2. Moreover, the universe lightest element possesses a very high gravimetric energy density of 120 MJ/kg, which will be higher when stored in cryogenic hydrogen form3, making it an ideal alternative to conventional aviation fuels (for example, jet fuel). This study provides a techno-economic analysis of introducing green hydrogen infrastructure to Los Angeles International Airport (LAX) to promote its transition towards sustainability. Preliminary research showed that the largest uncertainty in economic projections for H2-powered aviation hinges on future H2 supply costs, rather than aircraft modifications4. Therefore, the costs of potential hydrogen implementation routes, including off-site production supplied by road tankers or pipelines to the airport, and on-site production, will be assessed. In summary, the implementation of a hydrogen infrastructure at LAX is not only an initiative to reduce its associated carbon footprint but also suggests a practical and environmentally sustainable paradigm for future upgrades to aviation fuel infrastructure.

Sensitivities of Ozone and Radiative Forcing to Supersonic Aircraft Emissions Across Two Flight Corridors

AbstractCivil supersonic aviation may return in the near future. Their emissions have been found to lead to changes in the composition of the stratosphere, affecting the ozone layer and climate. To keep up with the rapid developments in supersonic aircraft technology and alternative fuels there is an increasing need for the development of surrogate modeling methods, which requires knowledge of the sensitivities to these emissions. We present a parametric study which evaluates the first‐ and second‐order sensitivities of the ozone column and radiative forcing (RF) to supersonic emissions across two flight corridors and three altitudes. For a given increase in global fuel burn, we find that the increase in emission of is the main driver of both the changes in the global ozone column and RF, the latter of which is linked through changes in the ozone distribution. Followed by the increase in the emission of , which leads to loss and has a cooling effect. The ozone column and climate are least sensitive to increases in emissions. We also show that interactions between , , and emissions lead to non‐linear behavior in the atmospheric response. The effect of these interactions can lead to 5% differences in the ozone column impacts and up to 7.3% increases in RF. Our results demonstrate that the majority of second‐order sensitivities may be neglected in surrogate models for small errors, which could greatly simplify their development. Our results also indicate that reductions in flight altitude and fleetwide emissions may effectively reduce the environmental footprint of supersonic aviation emissions.

Aeropropulsive Shape Optimization of an Airfoil System in the Transonic Regime

Boundary-layer ingestion and distributed propulsion are important concepts for future aircraft systems and technologies. Both concepts have the potential to increase aerodynamic efficiency and improve aircraft design in various other ways. The present study aims to address design implications and challenges of configuring a highly integrated and distributed propulsion system into wing sections within the compressible flow environment, which is the aerodynamic regime associated with large, commercial transport aircraft. To this end, a design and optimization framework was established to facilitate two-dimensional aeropropulsive optimization with strict, complex geometric constraints. A bi-objective, multipoint aeropropulsive shape optimization problem was solved using this package for an underwing-propulsor airfoil system to demonstrate the performance improvements achievable for a highly integrated aeropropulsive system. The results of this optimization indicate that an aerodynamic drag reduction of 11% and required mechanical flow power reduction of 35% are achievable relative to a baseline configuration.

The Overview of Vertical Take-Off and Landing Technology

Vertical takeoff and landing (VTOL) technology is garnering significant attention in the aviation industry due to its distinct benefits and wide range of potential applications. A long runway is not necessary when using VTOL technology, which allows aircraft to take off and land vertically straight from the ground. Air mobility in cities, military activities, and emergency response are just a few of the areas where this technology is beneficial. This essay will provide an overview of the development, application, and future of vertical takeoff and landing technology. The technologys operating principles, advantages and limitations will also be explored. Overall, VTOL technology offers a tremendous leap in aircraft technology, with numerous possible uses. Even though there are still difficulties, more research and development will probably result in improvements and broader use.

An Examination of the Sustainability Activities of Global Airline Collaborations within the Scope of IATA's Sustainability Goals

This study aims to evaluate the sustainability activities of the global airline alliances Star Alliance, SkyTeam, and OneWorld within the framework of the International Air Transport Association's (IATA) sustainability goals. Specifically, it focuses on key areas such as achieving net-zero carbon emissions by 2050, promoting new aircraft technologies, enabling greener travel (in terms of noise and air quality), enhancing energy, resource, and operational efficiency, managing cabin waste and recycling, adopting sustainable aviation fuels (SAF), and protecting biodiversity. Using a content analysis methodology, data were gathered from publicly available sources, including airline sustainability reports, annual reports, and information from the IATA website. This systematic analysis provides an objective evaluation of how well these airline alliances are aligning their strategies with IATA’s sustainability goals. The findings reveal significant disparities in the alliances’ commitments. For instance, Star Alliance and OneWorld members exhibit deficiencies in biodiversity conservation, while SkyTeam members show slower progress towards achieving the net-zero carbon emissions target. Additionally, all three alliances demonstrate varying degrees of success in adopting SAF and implementing other sustainable practices, such as waste management and the promotion of new aircraft technologies. By identifying the strengths and weaknesses across the alliances, this research offers critical insights into how the aviation sector can more effectively contribute to global sustainability efforts.

Flow and heat transfer characteristics of low water content jet fuel in U-bend tubes: A numerical study using LES and DPM approaches

This study provides an in-depth analysis of the flow and heat transfer behavior of low-water-content jet fuel (α ≤ 2 %) in U-bend tubes, utilizing Large Eddy Simulations (LES) and Discrete Phase Models (DPM). The research focus on the influence of radii of curvature ratio (r/D), flow rates (Qtp) and α on flow dynamics and heat transfer mechanisms. Flow fields for r/D = 1 and r/D ≥ 2.5, where distinct secondary flow structures, play a critical role in shaping internal flow behavior. These vortices significantly enhance flow mixing and heat transfer, especially on the inner wall, through complex multi-level vortex interactions. The local wall Nusselt number shows a close correlation with vorticity trends, initially increasing and then decreasing, with notable deviations near the inlet and outlet regions. This non-uniform heat transfer is primarily driven by the interaction of secondary flow structures and adverse pressure gradients near the inner wall, while higher Qtp and smaller r/D can improve heat transfer uniformity under certain flow conditions. The presence of droplets increases the total wall Nusselt number by 4 % to 60 % compared to single-phase jet fuel flow, due to two-phase interaction and boundary layer disruption. Finally, the study proposes modified correlations for pressure drop gradients and total wall Nusselt numbers, accounting for effects of r/D and multiphase heat transfer processes. These correlations, validated with RRMSEs of 3.54 % and 6.80 % respectively, provide valuable insights for improving heat transfer efficiency in fuel systems and form a theoretical foundation for real-time monitoring technologies in aircraft fuel lines.

Navigating Technological Risks: An Uncertainty Analysis of Powertrain Technology in Hybrid-Electric Commuter Aircraft

Abstract This study addresses the uncertainties in hybrid-electric powertrain technology for a 19-passenger commuter aircraft, focusing on two future Entry-Into-Service timeframes: 2030 and 2040. The methodology is split into a preliminary optimization of aircraft design based on nominal technology scenarios followed by Monte Carlo simulations to investigate the impact of diverse technology projections and distribution types. Advanced surrogate modeling techniques, leveraging deep neural networks (DNN) trained on a dataset from an aircraft design framework, are employed. Key outcomes from this work reveal a marked increase in computational efficiency, with a speed-up factor of approximately 500 times when utilizing surrogate models. The results indicate that the 2040 entry-into-service (EIS) scenario could achieve larger reductions in fuel and total energy consumption—20.4% and 15.8% respectively—relative to the 2030 scenario, but with higher uncertainty. Across all scenarios examined, the hybrid-electric model showcased superior performance compared to its conventional counterpart. The battery-specific energy density is proved to be a critical parameter of the aircraft’s performance across both timeframes. The findings emphasize the importance of continuous innovation in battery and motor technologies to target toward greater system-level efficiency and reduced environmental impact.

Research on Large Hybrid Electric Aircraft Based on Battery and Turbine-Electric

Hybrid electric aircraft use traditional engine and electric propulsion combinations to optimize aircraft architecture, improve propulsion efficiency, and reduce fuel consumption. As a new technology, the fuel and energy consumption calculation of hybrid electric aircraft is more complicated than traditional aircraft due to the usage of different energy forms. The purpose of this paper is to develop the analytical method for fuel and energy consumption for hybrid electric aircraft. This paper summarizes the working principle of hybrid electric aircraft, including the system architecture and power conversion mechanism. The calculation of fuel and energy consumption for hybrid electric aircraft is carried out in detail. In order to evaluate large hybrid electric aircraft, the architecture, based on energy flow, is established, and turbofan engine, electrical system, electric duct fan, and aerodynamic model characteristics are established. With a single-aisle aircraft as an example, the fuel and energy consumption under the 800 nautical mile range is performed. It shows that fuel consumption can be reduced by 10% and energy consumption by 4.7% compared with a traditional aircraft. The effects of different range and battery ratios are analyzed. The payload range for the hybrid electric aircraft is analyzed. The results show that even though the hybrid electric aircraft reduces the payload and range, it can significantly reduce fuel and energy consumption.

Integrated Technologies for Anti-Deicing Functions and Structures of Aircraft: Current Status and Development Trends

With the increasing adoption of composite materials in aircraft construction, traditional anti-icing technologies face significant challenges due to the low thermal conductivity and heat resistance of composite resins. These limitations have spurred the development of lightweight, efficient, durable, and cost-effective integrated anti-icing technologies as a critical area of research. This paper begins with an overview of advancements in electrothermal anti-icing and de-icing technologies for aircraft. It then explores the configurations and applications of functional-structural integration technology for anti-icing and de-icing, emphasizing pivotal technologies and current challenges in this field. Finally, the study forecasts the development trends in the multifunctional integration of thermal conductivity/insulation, anti-icing, and electromagnetic wave transparency/wave-absorbing properties. These advancements are driven by the evolution of composite materialization in aircraft and the progression of multi-electrical/all-electrical technologies. The objective is to provide a comprehensive guide for technological development in anti-icing, aiding researchers and relevant departments to further enhance the application of anti-icing technology in composite material aircraft.

The future of airport noise: a comprehensive analysis of population exposure at Dublin airport 2023 to 2030

There are conflicting trends in the impact of aircraft noise as increased air traffic is offset by advancements in low noise aircraft technology. This paper considers the case of Dublin Airport and projects the noise impact of operations over the timeline to 2030. The airport projects an (Average Annual Growth Rate) of 1.2 %, translating to an estimated rise in annual air traffic movements from over 212736 flights in 2023 to around 244635 flights in 2030. This estimated increase poses not only logistical challenges for airports but also an escalation in noise pollution in the surrounding areas. The most significant challenge in predicting future airport noise exposure lies in the shifts in aircraft fleet distribution and the adoption of technology in newer generations of aircraft. This paper evaluates the most likely combination of fleet distribution and technology uptake. In 2023, the noise footprint is projected to affect a population of approximately 105762 people with Lden ≥ 55 dB. By 2030, this exposure increases to 168267 people. The increase in air traffic numbers also leads to a notable increase in nighttime flights, bringing nighttime noise exposure Ln ≥ 50 dB from 127720 in 2023 to 189376 in 2030.

Aviation aspects of engine oil conveying copper tiny particles embedded in a rotating disk with a binary chemical reaction

Nanofluids have significant industrial applications and motivating heat transfer characteristics for various factors that contribute to the movement of nanofluids are essential significance. The aim of the present study focused on importance of heat transfer analysis on engine oil conveying copper nano particles embedded in a porous rotating disk with potential application in aerospace technology. In this model we considered magnetohydrodynamics, non-linear thermal radiation, thermophoresis and Brownian motion. The present investigation utilized copper nanoparticle and engine oil as a base fluid. The mathematical flow equations are transformed into ordinary differential equations (ODEs) by employing suitable self-similarity variables. The resultant ordinary differential equations are solved numerically by using the Midrich technique in the Maple software. The results are calculated to measure the impact of active parameters on velocity, temperature, concentration equations are presented graphically and in tabular form. Higher values of the magnetic field parameter the velocity profile decreased while the opposite tendency we noticed on energy profile. When increasing the radiation parameter values the energy profile increased. In both cases when increasing the magnetic field and radiation parameter values the Nusselt number profile increased. The research has important implications in a number of real-world situations. In particularly, the advancement of aircraft technology has presented manufacturers with new criteria and problems for the functioning of their devices. It is essential that, in order to guarantee the secure operation of aerospace machinery, the failure mechanisms be identified and the operational durability of critical structural components be improved as quickly as possible.

Robust and Density Tunable Kevlar/Hexagonal Boron Nitride Microribbon Aerogels with Excellent Thermal, Mechanical, and Oil-Absorption Properties.

With rapid advancements in aerospace and supersonic aircraft technology, there is a growing demand for multifunctional thermal protective materials. Aerogels, known for their low density and high porosity, have garnered significant attention in this regard. However, developing a lightweight multifunctional aerogel that combines exceptional thermal and mechanical properties through a straightforward and time-efficient method remains a significant challenge. Herein, a facile and universal approach is developed for the preparation of Kevlar/hexagonal boron nitride (h-BN) aerogels, in which a spin-assisted method is applied to create robust microribbons and further accelerate solvent displacement. The resulting microribbon scaffold, with its entangled nanofiber-nanosheet morphologies, exhibits sufficient strength to prevent volume shrinkage during drying, thereby allowing precise control over aerogel density. The porous hybrid aerogels, featuring controllable geometric characteristics and tailored densities ranging from 6.9 to 100 mg cm-3, can be successfully fabricated. These aerogels exhibit excellent thermal insulation properties, and the thermal conductivities of the as-prepared KBX aerogels have a wide distribution in the range of 0.0269-0.0450 W m-1 k-1. The thermal stability of the hybrid aerogels is enhanced to 566 °C. Moreover, the resulting hybrid aerogels exhibit an ultrahigh bearing ratio, supporting more than 2000 times their own weight while maintaining stable structural integrity. These aerogels also demonstrate high compressive strength, hydrophobicity, and excellent sorption performance for various oils and solvents. Additionally, the oil-saturated aerogels can be easily recovered through heat treatment or combustion in air. The features endow hybrid Kevlar/h-BN aerogels with significant potential for applications in thermal management, environmental protection, and neutron protection.