Engineering Proceedings

Other

8 pages, 3984 KiB

Open AccessProceeding Paper

Defects and Ultrasonic Characterization of Scarf-Repaired Composite Structures

by Yalin Qu, Ning Ning and Ting Jiao

Eng. Proc. 2024, 80(1), 1; https://doi.org/10.3390/engproc2024080001 - 26 Dec 2024

Viewed by 463

Scarf repairs are the most common method of repairing composite structures. With the development of repair technology, the problems of strength evaluation and damage detection of repaired structures need to be solved urgently. Taking the repaired laminate structure as an example, the possible [...] Read more.

Scarf repairs are the most common method of repairing composite structures. With the development of repair technology, the problems of strength evaluation and damage detection of repaired structures need to be solved urgently. Taking the repaired laminate structure as an example, the possible types of defects and the ultrasonic characteristic signals are summarized and analyzed, which are then compared and verified with repair process characteristics to provide data accumulation for the establishment of the complete ultrasonic detection criteria for such structural defects. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

4 pages, 353 KiB

Open AccessProceeding Paper

The Impact of AI on the Aviation Industry: An Industry View of Opportunities and Challenges for a Sustainable Future

by Zhiqi Fang

Eng. Proc. 2024, 80(1), 2; https://doi.org/10.3390/engproc2024080002 - 26 Dec 2024

Viewed by 1408

Abstract

Artificial intelligence (AI) has been on the agenda worldwide for at least 10 years. As more evidence of industry applications becomes apparent, it continues to gain momentum. In aviation, AI is seen as a new generation of “stealth engines” that drive the industry. [...] Read more.

Artificial intelligence (AI) has been on the agenda worldwide for at least 10 years. As more evidence of industry applications becomes apparent, it continues to gain momentum. In aviation, AI is seen as a new generation of “stealth engines” that drive the industry. This paper explores the application of AI technology in the aviation industry and its impact on the sustainable development of the industry. Through the method of systematic literature review, it has been found that while AI contributes to making more informed decisions and optimizing operational efficiency, addressing challenges such as regulatory compliance, ethical considerations, and cyber security is crucial to realizing its full potential responsibly and sustainably. By examining current trends and future prospects, this paper provides an overview of AI’s role in shaping the future aviation, aiming to balance technological progress with industry resilience and sustainability. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

10 pages, 1189 KiB

Open AccessProceeding Paper

An Overview of the Sustainable Aviation Fuel: LCA, TEA, and the Sustainability Analysis

by Meiting Wang and Xiao Yu

Eng. Proc. 2024, 80(1), 3; https://doi.org/10.3390/engproc2024080003 - 27 Dec 2024

Viewed by 1171

Abstract

This paper investigates how the present paths support massive manufacturing by evaluating the existing state of sustainable aviation fuel (SAF) technologies, examining technology readiness levels (TRL), fuel readiness levels (FRL), costs, economic conditions, emissions, etc. This assessment summarizes major conclusions about bio-jet replacements [...] Read more.

This paper investigates how the present paths support massive manufacturing by evaluating the existing state of sustainable aviation fuel (SAF) technologies, examining technology readiness levels (TRL), fuel readiness levels (FRL), costs, economic conditions, emissions, etc. This assessment summarizes major conclusions about bio-jet replacements for conventional jet fuels. In order for SAF to play a sustainable role, a full life cycle emissions assessment, techno-economic analysis (TEA), and discussions about the sustainability of SAF materials are required. The life cycle assessment (LCA) discusses the capability of SAF in cutting down emissions, TEA argues for its economic viability, and the sustainable supply of SAF feedstock is a third critical factor determining the sustainability of the industry. With all the analyses, this overview provides recommendations for the sustainable development of the SAF industry and calls on industry stakeholders to enhance cooperation. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

12 pages, 1932 KiB

Open AccessProceeding Paper

Research on Text Information Extraction and Analysis of Civil Transport Aircraft Accidents Based on Large Language Model

by Jianzhong Yang, Tao Su and Xiyuan Chen

Eng. Proc. 2024, 80(1), 4; https://doi.org/10.3390/engproc2024080004 - 27 Dec 2024

Viewed by 3356

Abstract

Civil aviation safety is crucial to the airline transportation industry, and the effective prevention and analysis of accidents are essential. This paper delves into the mining of unstructured textual information within accident reports, tracing the evolution from manual rules to machine learning and [...] Read more.

Civil aviation safety is crucial to the airline transportation industry, and the effective prevention and analysis of accidents are essential. This paper delves into the mining of unstructured textual information within accident reports, tracing the evolution from manual rules to machine learning and then to advanced deep learning techniques. We particularly highlight the advantages of text extraction methods that leverage large language models. We propose an innovative approach that integrates TF-IDF keyword extraction with large language model prompted filtering to scrutinize the causes of accidents involving civil transport aircraft. By analyzing the keywords before and after filtering, this method significantly enhances the efficiency of information extraction, minimizes the need for manual annotation, and thus improves the overall effectiveness of accident prevention and analysis. This research is not only pivotal in preventing similar incidents in the future but also introduces new perspectives for conducting aviation accident investigations and promotes the sustainable development of the civil aviation industry. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

13 pages, 8454 KiB

Open AccessProceeding Paper

Theoretical Study and Verification of the Mechanical Properties of Concave Honeycomb Structures Based on Additive Manufacturing

by Yuchao Guo, Likai Wang, Sen Ai, Liang Chang and Xiaohua Nie

Eng. Proc. 2024, 80(1), 5; https://doi.org/10.3390/engproc2024080005 - 30 Dec 2024

Viewed by 446

Abstract

This paper focuses on the internal honeycomb structure of flexible skins for morphing aircraft, specifically targeting a unique concave honeycomb structure. By selecting specific honeycomb cells and simplifying their cell walls to beams, the equivalent elastic modulus and shear modulus were derived using [...] Read more.

This paper focuses on the internal honeycomb structure of flexible skins for morphing aircraft, specifically targeting a unique concave honeycomb structure. By selecting specific honeycomb cells and simplifying their cell walls to beams, the equivalent elastic modulus and shear modulus were derived using the principle of virtual work. The cell was also simplified to an orthotropic plate, and the equivalent bending stiffness was derived using the principle of equivalent deformation energy. Using additive manufacturing methods and photosensitive resin materials, a series of honeycomb structure test pieces were manufactured and subjected to mechanical performance tests. The stress–strain curves and load-deflection curves of the honeycomb structures were obtained, and the equivalent elastic modulus, equivalent shear modulus, and equivalent bending stiffness were calculated from the experimental data. The theoretical values of the equivalent mechanical properties were compared with the experimental values, with errors of 4.38%, 16.67%, and 15.47% for the equivalent elastic modulus, equivalent shear modulus, and equivalent bending stiffness, respectively. Finally, the causes of the errors were analyzed, and this method has significant value for the application of such honeycomb structures. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

9 pages, 718 KiB

Open AccessProceeding Paper

Analysis of Airworthiness Requirements for Commercial Aircraft Avionics System Design in Low Altitude Economy

by Jun Xiao and Wujie Li

Eng. Proc. 2024, 80(1), 6; https://doi.org/10.3390/engproc2024080006 - 26 Dec 2024

Viewed by 516

Abstract

This paper introduces the development history and process of low altitude economy, explains the characteristics and advantages of low altitude economy, and further discusses the development direction and trend of commercial low-altitude aircraft. By analyzing the current popular commercial aircraft avionics system design [...] Read more.

This paper introduces the development history and process of low altitude economy, explains the characteristics and advantages of low altitude economy, and further discusses the development direction and trend of commercial low-altitude aircraft. By analyzing the current popular commercial aircraft avionics system design features and considering the current low-altitude economic application scenarios, the characteristics of commercial low-altitude aircraft avionics systems design are described. Then, through the analysis of the design of low-altitude aircraft avionics systems, this paper puts forward the additional airworthiness requirements of commercial aircraft avionics system designs in low-altitude operation environments and explains the problems that should be paid attention to in the low-altitude operation application scenario. Through the research application of the airworthiness requirements of commercial aircraft avionics system design in the low-altitude economy, this paper provides guidance for the future development of low-altitude aircraft avionics systems. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

6 pages, 814 KiB

Open AccessProceeding Paper

Discussion of Speeding Up Fatigue Test of Full-Scale Aircraft

by Shuang Lv

Eng. Proc. 2024, 80(1), 7; https://doi.org/10.3390/engproc2024080007 - 2 Jan 2025

Viewed by 505

Abstract

The full-scale aircraft fatigue test is a critical assessment and validation of the fatigue and damage tolerance design of new aircraft models, and it is also a prerequisite for obtaining the type certification for an aircraft. The full-scale fatigue test is an extremely [...] Read more.

The full-scale aircraft fatigue test is a critical assessment and validation of the fatigue and damage tolerance design of new aircraft models, and it is also a prerequisite for obtaining the type certification for an aircraft. The full-scale fatigue test is an extremely complex and high-risk task that requires a lengthy period of time and significant financial investment. Therefore, there is an urgent need to shorten the test cycle and safely and efficiently complete the full-scale fatigue test during aircraft model development. Based on the experience and results of a nearly decade-long full-scale fatigue test conducted on a certain civil aircraft, and with reference to the full-scale fatigue test of the Boeing 777 in the United States, this article compares and contrasts the similarities and differences in aircraft configuration, test load spectrum, load application methods, and test detail control, as well as damage detection, monitoring, and maintenance. It analyzes the main reasons for the high time consumption and low efficiency of full-scale fatigue tests for domestic civil aircraft and proposes test acceleration schemes to further shorten the test cycle. The analysis results presented in this article provide valuable reference for the design of full-scale fatigue tests and relevant test personnel. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

10 pages, 3430 KiB

Open AccessProceeding Paper

Untethered Flight of a 5 cm Micro Vehicle Powered by an Onboard Capacitor

by Ruide Yun, Long Zhou, Ruiwen Wang, Junbo Bao and Jian Zhou

Eng. Proc. 2024, 80(1), 8; https://doi.org/10.3390/engproc2024080008 - 2 Jan 2025

Viewed by 2648

Abstract

Due to the small size of the micro aircraft, it has high permeability and concealability, holding promise in application in the military and civil fields, and it has become a domestic and international research frontier and hotspot in the past decade. However, caused [...] Read more.

Due to the small size of the micro aircraft, it has high permeability and concealability, holding promise in application in the military and civil fields, and it has become a domestic and international research frontier and hotspot in the past decade. However, caused by the heavy onboard power supply and the decline in the actuator’s operating power at micro sizes, untethered flight is still a development difficulty at present. In this paper, we introduce a new micro vehicle configuration which is driven by onboard capacitive energy and can realise off-line free flight under the drive of electrostatic actuators. In the overall design, this paper proposes structural capacitors as the energy supply unit and buoyancy unit of the vehicle, which can overcome part of the vehicle body’s weight by being filled with helium gas, while the capacitor can provide electrical energy for the propulsion unit. The micro vehicle has a wingspan of 5 cm, a total mass of 165 mg, a stable operating voltage between 1300 V and 2400 V, and a flight time of more than 60 s under the condition of an onboard capacitor power supply. The micro vehicle designed in this thesis has a small wingspan, light weight, and better concealment, and it has broad application prospects in the future in environmental reconnaissance, surveying, and other scenarios. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

4 pages, 428 KiB

Open AccessProceeding Paper

Quality Control and Management of Nondestructive Testing Process in Aircraft Fatigue Test

by Shuang Lv and Zhiwei Peng

Eng. Proc. 2024, 80(1), 9; https://doi.org/10.3390/engproc2024080009 - 2 Jan 2025

Viewed by 357

Abstract

Aircraft fatigue test is a critical step for new aircraft models to obtain certification. The primary task of fatigue test is to detect damage promptly and gather damage data. Therefore, to ensure the timeliness and effectiveness of non-destructive testing (NDT) data, it is [...] Read more.

Aircraft fatigue test is a critical step for new aircraft models to obtain certification. The primary task of fatigue test is to detect damage promptly and gather damage data. Therefore, to ensure the timeliness and effectiveness of non-destructive testing (NDT) data, it is essential to control and manage the quality of the NDT process in aircraft fatigue test. This paper, based on the characteristics and work features of NDT in aircraft fatigue test, aims to achieve the goal of timely damage detection by focusing on the five key aspects of NDT quality control, namely: personnel, equipment, materials, methods, and environment. It elaborates on the quality control process, identifies key aspects of quality management, and enhances the quality of NDT in aircraft fatigue test. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

11 pages, 5657 KiB

Open AccessProceeding Paper

Optimum Selection Analysis of Composite Cap Cone

by Jijun Liu, Yongping Jiang, Kaixiang Li and Yafeng Wang

Eng. Proc. 2024, 80(1), 10; https://doi.org/10.3390/engproc2024080010 - 3 Jan 2025

Viewed by 401

Abstract

An in-depth analysis was conducted on the dynamic strength design optimization of carbon fiber composite cap cones in aircraft engines subjected to bird body impacts. Initially, the top, 1/4, 1/2, 3/4, and root positions of the cap cone’s generatrix were designated as the [...] Read more.

An in-depth analysis was conducted on the dynamic strength design optimization of carbon fiber composite cap cones in aircraft engines subjected to bird body impacts. Initially, the top, 1/4, 1/2, 3/4, and root positions of the cap cone’s generatrix were designated as the impact sites. The analysis of bird impacts revealed that the 1/2 position along the generatrix is the most hazardous impact location. Subsequently, considering the thickness of the composite material cap cone as a variable and accounting for its high-speed rotational state, a bird impact analysis was performed at the most critical impact location. Additionally, a comparative study on the bird impact performance of the composite material cap cone under rotating and non-rotating conditions was conducted. The study indicates that, under identical conditions, the cap cone in rotation experiences more severe damage than in a non-rotating state, necessitating a cone thickness of 7 mm or greater; Subsequently, a bolt strength analysis model was established to thoroughly examine the impact of varying cone side thicknesses on the load applied to connecting bolts, and to assess bolt strength. The findings suggest that excessive bolt loads can also constrain the optimization of the cap cone; hence, finding the optimal balance between bolt quantity and strength is essential in design. Lastly, the study discussed the weakening of local stiffness in the composite material cap cone post-impact, noting a 12% decrease in its elastic mode frequency and the emergence of asymmetric vibration modes. This phenomenon could potentially lead to dynamic unbalanced loads, thus necessitating further evaluation in the optimization process of the cap cone. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

6 pages, 992 KiB

Open AccessProceeding Paper

Research on the Application of Additive Manufacturing Technology in Pilot Control Unit Design

by Liyang Yao, Zhongrui Zhao and Jinlei Zheng

Eng. Proc. 2024, 80(1), 11; https://doi.org/10.3390/engproc2024080011 - 6 Jan 2025

Viewed by 473

Abstract

Additive manufacturing technology can realize the rapid integrated manufacturing of complex shape models, and has become a new method for integrated design and manufacturing of complex components of high performance weapons and equipment. This article summarizes the current application status of additive manufacturing [...] Read more.

Additive manufacturing technology can realize the rapid integrated manufacturing of complex shape models, and has become a new method for integrated design and manufacturing of complex components of high performance weapons and equipment. This article summarizes the current application status of additive manufacturing technology in various aspects of pilot control unit design, such as the layout design of the control stick switch for demand analysis, the evaluation of the control stick length and grip diameter size for selection tests, and the cost control of different test types for ground tests. Research was conducted on material costs, manufacturing time, model strength, and other aspects. Additive manufacturing technology can reduce the design and testing cycle of pilot control units, which is conducive for comparing the parameters and design effects of different models of units, and can lead to better detailed design from the perspective of human engineering in the scheme design stage. Meanwhile, the integrated design effectively reduces the weight of the system, with a preliminary estimated weight reduction effect of 19.7%. Finally, the potential risks of additive manufacturing technology in practical applications were analyzed, and further considerations and prospects were proposed for its application in the design of pilot control units in the future. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

14 pages, 9339 KiB

Open AccessProceeding Paper

Design of an Autonomous Drone

by Wendi Yu

Eng. Proc. 2024, 80(1), 12; https://doi.org/10.3390/engproc2024080012 - 6 Jan 2025

Viewed by 749

Abstract

This project mainly focuses on the design of an Autonomous Drone, which consist of the control system, a simulation, and the aerodynamic properties. eVTOL aircraft constitute a large family with various configurations. In this project, the object of discussion is a quadrotor drone. [...] Read more.

This project mainly focuses on the design of an Autonomous Drone, which consist of the control system, a simulation, and the aerodynamic properties. eVTOL aircraft constitute a large family with various configurations. In this project, the object of discussion is a quadrotor drone. The control system is the central part of the autonomous drone, and so that is the main point of discussion. The control system includes the PID controllers, LQR controllers, and some other relative control methods. In this sense, the main difficulty involves building the systems and performing correct operation. MATLAB and SOLIDWORKS are applied to assess and discuss the system and it properties. In this project, the drone is first designed by using SOLIDWORKS. After that, the model is utilized to perform the analysis and simulation. The results show that the system can achieve the target value in a short timeframe. Also, the flight trajectory largely conforms to the projected expectations. The simulation results from MATLAB show that the control accuracy and stability of the PID controllers can meet the needs of a simple autonomous drone control system. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

8 pages, 181 KiB

Open AccessProceeding Paper

Comparative Study on the Legal Supervision System of Low-Altitude Aircraft in China and Europe Based on Key Risks

by Mingming Liu and Shuang Liu

Eng. Proc. 2024, 80(1), 13; https://doi.org/10.3390/engproc2024080013 - 6 Jan 2025

Viewed by 1253

Abstract

In order to further ensure the safety of low-altitude activities, this paper takes the low-altitude aircraft regulatory systems that have been issued by the European Union and China as the research object and compares and analyzes the regulatory measures taken by the two [...] Read more.

In order to further ensure the safety of low-altitude activities, this paper takes the low-altitude aircraft regulatory systems that have been issued by the European Union and China as the research object and compares and analyzes the regulatory measures taken by the two regions for key risks and hidden dangers during low-altitude aircraft activities. Based on the analysis results, three improvement suggestions are put forward for China’s future low-altitude aircraft regulatory measures: 1. Establish a complete risk assessment mechanism for the entire operation process of low-altitude aircraft, confirm flight activity authorization based on risks, and reduce operational risks; 2. Equip observers for special flight activities to reduce the workload of operators; 3. Establish a complete low-altitude aircraft information registration and monitoring system, monitor the entire process from production and sales to use, and avoid the phenomenon of “illegal flying”. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

16 pages, 1030 KiB

Open AccessProceeding Paper

Research on the Security Risk Governance Roadmap in Low-Altitude Economic Field Based on the Economic Externality Theory

by Shuang Liu and Mingming Liu

Eng. Proc. 2024, 80(1), 14; https://doi.org/10.3390/engproc2024080014 - 6 Jan 2025

Viewed by 1213

Abstract

In 2024, the low-altitude economy, as a representative of strategic emerging industries, was written into the government work report for the first time, becoming an important engine for the development of new-quality productive forces. China’s low-altitude economic development market is huge, but opportunities [...] Read more.

In 2024, the low-altitude economy, as a representative of strategic emerging industries, was written into the government work report for the first time, becoming an important engine for the development of new-quality productive forces. China’s low-altitude economic development market is huge, but opportunities and risks coexist. With the rapid development of the low-altitude economy, all kinds of safety risks contained within it have not received enough attention, and the relevant policies and regulations of safety risk management need to be improved. Therefore, the concept of the low-altitude economy is defined and considers that the low-altitude economy belongs to the “economic field”. Secondly, the types of low-altitude economic security risks are summarized based on the theory of economic externalities, which shows that the management of low-altitude economic security risk of the national team is important and necessary. Thirdly, we comprehensively summarize the policies, laws, and regulations of a low-altitude economy and give a description of low-altitude economic security risk management. Finally, the practical path of low-altitude economic security risk management is given as establishing top-level design, establishing and perfecting regulations and standards, collaborative governance of multiple subjects, and strengthening safety knowledge. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

20 pages, 1952 KiB

Open AccessProceeding Paper

Energy-Efficient Path Planning for Commercial Aircraft Formation Flights

by Olivia Curtis, Yibing Xie, Man Liang and Cees Bil

Eng. Proc. 2024, 80(1), 15; https://doi.org/10.3390/engproc2024080015 - 6 Jan 2025

Viewed by 593

Abstract

The increasing global demand for air travel over the past three decades has led to heightened congestion, environmental concerns, and operational inefficiencies. This study explores the potential of commercial aircraft formation flight, inspired by the energy-saving flight patterns of migratory birds, to enhance [...] Read more.

The increasing global demand for air travel over the past three decades has led to heightened congestion, environmental concerns, and operational inefficiencies. This study explores the potential of commercial aircraft formation flight, inspired by the energy-saving flight patterns of migratory birds, to enhance fuel efficiency on the busy Melbourne to Sydney city-pair route. The methodology is divided into macroscopic and microscopic levels, addressing both strategic planning and detailed flight optimisation. The macroscopic level focuses on route optimisation, formation flight planning, air traffic management integration, and environmental impact. The microscopic level involves adjustments to individual aircraft flight profiles to ensure minimum separation, flight safety, and efficiency. Using a gradient-based optimisation algorithm applied to a constrained nonlinear multivariable function, this study aims to minimise fuel consumption and travel time while maintaining the required separation distances. The mathematical formulation and algorithm pseudocode provides a clear framework for implementation. The experimental results demonstrate the potential of formation flight to optimise fuel efficiency and resolve path conflicts on the Melbourne to Sydney route; despite a conservative 5% fuel efficiency improvement for the follower aircraft, the total fuel consumption decreased by 2.5–2.65% compared to the non-formation flight. These findings support the feasibility of applying formation flight principles to commercial aviation in Australia for improved fuel efficiency and operation performance of busy short-haul routes. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

5 pages, 177 KiB

Open AccessProceeding Paper

Research on the Requirement Validation Process of an eVTOL Aircraft

by Haiyun Yang, Yiheng Li and Jing Hu

Eng. Proc. 2024, 80(1), 16; https://doi.org/10.3390/engproc2024080016 - 7 Jan 2025

Viewed by 347

Abstract

According to the SAEARP4754B standard, the positive development of electric vertical takeoff and landing (eVTOL) aircraft must carry out requirement management in order to ensure the traceability of requirements. The requirement validation process plays a key role in the requirement traceability process, and [...] Read more.

According to the SAEARP4754B standard, the positive development of electric vertical takeoff and landing (eVTOL) aircraft must carry out requirement management in order to ensure the traceability of requirements. The requirement validation process plays a key role in the requirement traceability process, and this paper is mainly about the research on the requirement validation process. The steps of optimizing the requirement validation process are to formulate validation plans, define the initial validation matrix template, select the validation approach, implement requirement validation, and notify the relevant parties of the problems found in validation. The implementation of the optimized requirement validation process avoids human error to some extent. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

11 pages, 2327 KiB

Open AccessProceeding Paper

An Initial Sizing Method of Large-Scale Electric Cargo Unmanned Aeiral Vehicles for Conceptual Design

by Chang-Zhou Wang and Fu-Hu Liu

Eng. Proc. 2024, 80(1), 17; https://doi.org/10.3390/engproc2024080017 - 7 Jan 2025

Viewed by 420

Abstract

In order to accurately evaluate the preliminary parameters of the large-scale electric cargo UAV for conceptual design, combined with its own characteristics and payload requirements, a total weight assessment procedure of a traditional fixed-wing electric propeller cargo UAV was established. According to the [...] Read more.

In order to accurately evaluate the preliminary parameters of the large-scale electric cargo UAV for conceptual design, combined with its own characteristics and payload requirements, a total weight assessment procedure of a traditional fixed-wing electric propeller cargo UAV was established. According to the demand of different flight conditions, a constraint analysis method that meets the flight performance was established. Considering long-distance transportation requirements, a method of evaluating the range was obtained, as well as the relationship between the following three parameters: range, preliminary parameters, and battery energy density. These methods can form a design system to evaluate the total weight, power load, wing load, range, and some crucial sizing parameters. Based on this system, the parameter design and iterations of ton-level electrical cargo UAV were analyzed, whose values basically met the design requirements. The results show that the design method can be used for the preliminary parameter analysis and performance evaluation of large-scale electric cargo UAVs, which are a kind of traditional fixed-wing propeller aircraft. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

7 pages, 1556 KiB

Open AccessProceeding Paper

Geometrically Nonlinear Static Analysis of High-Aspect-Ratio Truss-Braced Wing

by Yanxin Huang, Jinchi Chen and Qingyuan Ma

Eng. Proc. 2024, 80(1), 18; https://doi.org/10.3390/engproc2024080018 - 7 Jan 2025

Viewed by 331

Abstract

Truss-braced wings (TBWs) feature higher aspect ratios with a lighter weight and lower bending moment than conventional wings. These wings show significant potential for performance improvements in terms of fuel efficiency. However, additional configurations of these wings also present nonlinear problems and challenges [...] Read more.

Truss-braced wings (TBWs) feature higher aspect ratios with a lighter weight and lower bending moment than conventional wings. These wings show significant potential for performance improvements in terms of fuel efficiency. However, additional configurations of these wings also present nonlinear problems and challenges in aeroelastic designs. This paper investigates the static response of a TBW with a high aspect ratio, specifically focusing on the impact of the spanwise joint location on aeroelastic characteristics. The TBW is modeled by nonlinear beam elements and the unsteady vortex-lattice method (UVLM). The results show that the bending deformation is effectively reduced by the truss member and the deformation is impacted by the location of the spanwise joint connected to the main body. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

5 pages, 1023 KiB

Open AccessProceeding Paper

The Influence of Boundary Constraint Viscoelasticity on the Nonlinear Forced Vibration of Fluid-Conveying Layered Pipes

by Zhoumi Wang and Qingchun Meng

Eng. Proc. 2024, 80(1), 19; https://doi.org/10.3390/engproc2024080019 - 8 Jan 2025

Viewed by 319

Abstract

In this paper, the influence of the viscoelasticity of boundary constraints on the forced vibration of the nonlinear forced resonance of a fluid-conveying layered pipe under an external forced excitation is studied. The pipe lays on viscoelastic foundations and is simply supported at [...] Read more.

In this paper, the influence of the viscoelasticity of boundary constraints on the forced vibration of the nonlinear forced resonance of a fluid-conveying layered pipe under an external forced excitation is studied. The pipe lays on viscoelastic foundations and is simply supported at both ends, and one end is subject to a viscoelastic boundary constraint. The Kelvin–Voight model was employed to describe the viscoelasticity provided by the foundation and boundary constraint. Hamilton’s variational principle was used to obtain the governing equations, during which geometric nonlinear factors including curvature nonlinearity and inertia nonlinearity were considered. By employing a perturbation-incremental harmonic balance method (IHBM), amplitude–frequency bifurcation diagrams of the pipe were obtained. The results show that the viscoelastic constraints from the boundary and foundation have significant influence on the linear and nonlinear dynamic behavior of the pipe system. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

12 pages, 12962 KiB

Open AccessProceeding Paper

One Kind of Green New Method for Detection of Inside Layer Cracks of Aircraft Multilayer Structures

by Huabin Huang, Zhiwei Peng and Mao Xu

Eng. Proc. 2024, 80(1), 20; https://doi.org/10.3390/engproc2024080020 - 10 Jan 2025

Viewed by 393

Abstract

To address the technical challenges in detecting internal cracks within aircraft metallic multilayer structures, we have employed the environmentally friendly detection technique of remote-field eddy current (RFEC). Through theoretical analysis and experimental research, we have analyzed influencing factors such as frequency and phase, [...] Read more.

To address the technical challenges in detecting internal cracks within aircraft metallic multilayer structures, we have employed the environmentally friendly detection technique of remote-field eddy current (RFEC). Through theoretical analysis and experimental research, we have analyzed influencing factors such as frequency and phase, designed detection probes and reference blocks, and conducted research on the capability of detecting concealed defects within thick structures (greater than 10 mm). By testing the reference blocks, we have studied the changes in phase and amplitude caused by variations in frequency and damage, gaining insights into the detection capabilities and applicable scope of this method. Ultimately, we have obtained an effective method for detecting internal cracks within different thickness layers of metallic multilayer structures. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

8 pages, 2093 KiB

Open AccessProceeding Paper

Technology for eVTOL Cementing and Co-Curing Composite Wing Box Segment

by Shutao Qi, Jiannan Cheng, Jichuan Ma and Jun Wang

Eng. Proc. 2024, 80(1), 21; https://doi.org/10.3390/engproc2024080021 - 10 Jan 2025

Viewed by 392

Abstract

In this paper, the status quo of manufacturing technology of the wing structures of large and small general aircraft at home and abroad is reported. The existing problems in the manufacturing technology of double-beam, multi-rib composite wing structures are analyzed. The application of [...] Read more.

In this paper, the status quo of manufacturing technology of the wing structures of large and small general aircraft at home and abroad is reported. The existing problems in the manufacturing technology of double-beam, multi-rib composite wing structures are analyzed. The application of adhesive co-curing technology to manufacture eVTOL double-beam, multi-rib integral composite wing box segment structures is proposed. Composite-material wing box segment adhesive co-curing manufacturing technology realizes the high-quality manufacturing of double-beam, multi-rib integral wing box segment structures and the optimal lightweight design of such structures. It can be applied to the manufacture of this type of integral wing box segment structure or the manufacture of other complex integral composite components. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

5 pages, 874 KiB

Open AccessProceeding Paper

Study on the Influence of Preload in a Rubber Vibration Isolator on Its Buffering Performance

by Ke Duan and Feng Hou

Eng. Proc. 2024, 80(1), 22; https://doi.org/10.3390/engproc2024080022 - 15 Jan 2025

Viewed by 356

Abstract

In this paper, by studying the basic principle of buffering, it was analyzed that damping and natural frequency have a great influence on the buffering effect. In order to obtain the influence of rubber preload on structural damping and natural frequency, a series [...] Read more.

In this paper, by studying the basic principle of buffering, it was analyzed that damping and natural frequency have a great influence on the buffering effect. In order to obtain the influence of rubber preload on structural damping and natural frequency, a series of impact tests were carried out. The test data show that when the diameter of the smooth rod is increased by 0.2 mm, the buffering rate in a horizontal direction is reduced from 96.59% to 81.74%. The buffer ratio in the other direction is reduced from 97.37% to 85.81%. When the length is increased by 0.2 mm, the vertical buffer ratio is increased from 85.52% to 93.26%. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

8 pages, 3116 KiB

Open AccessProceeding Paper

Co-Simulation and Platform Design of Airfoil Actuator Performance

by Mengyi Liu

Eng. Proc. 2024, 80(1), 23; https://doi.org/10.3390/engproc2024080023 - 2 Jan 2025

Viewed by 216

Abstract

The airfoil actuator is a necessary general component of modern aircraft, and the design of the airfoil actuator is a process that needs to be iterated repeatedly. It is difficult for a single modeling simulation to meet the requirements of multi-dimensional design. By [...] Read more.

The airfoil actuator is a necessary general component of modern aircraft, and the design of the airfoil actuator is a process that needs to be iterated repeatedly. It is difficult for a single modeling simulation to meet the requirements of multi-dimensional design. By designing a platform software to meet the requirements of multi-model co-simulation, the co-simulation can more accurately describe the detailed situation of a system through comparative analysis of simulation results. This paper provides a set of systematic and complete methods for the performance co-simulation of the airfoil actuator, and the data obtained from the analysis provide a reference for the design of the airfoil actuator. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

9 pages, 3416 KiB

Open AccessProceeding Paper

A Convenient Method for Simulating Crack Propagation in Panel Structures Based on the Secondary Development of ABAQUS

by Wendong Zhang, Xianmin Chen and Jun Yang

Eng. Proc. 2024, 80(1), 24; https://doi.org/10.3390/engproc2024080024 - 20 Jan 2025

Viewed by 405

Abstract

In the damage tolerance analysis of aircraft panels, it was necessary to frequently apply complex boundaries and loads to simulate crack propagation. It was difficult to simulate crack propagation with the conventional finite element method. In this paper, a convenient method for crack [...] Read more.

In the damage tolerance analysis of aircraft panels, it was necessary to frequently apply complex boundaries and loads to simulate crack propagation. It was difficult to simulate crack propagation with the conventional finite element method. In this paper, a convenient method for crack propagation simulation in thin-walled structures was proposed. This method combined the extended finite element method (XFEM) and level-set method (LSM). Crack insertion, analysis, result extraction and automatic propagation were realized through the secondary development script in the ABAQUS platform. A specimen with a single center crack was simulated to study the crack propagation behavior under tensile and bending conditions. Also, multiple-crack propagation was simulated. The present work shows that the developed method can not only take the complex loading and boundary conditions into account, but also can give good predictions on the crack analysis. This method provided a convenient and effective secondary development of ABAQUS to solve complex crack problems. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

18 pages, 11030 KiB

Open AccessProceeding Paper

Numerical Simulation Research on Separation Process of Jettisoned FDR from Civil Aircraft

by Feifan Zhang and Zhaoke Xu

Eng. Proc. 2024, 80(1), 25; https://doi.org/10.3390/engproc2024080025 - 2 Jan 2025

Viewed by 230

Abstract

The safety of Jettisoned FDRS in the process of separation from an aircraft is a key factor in designing Jettisoned FDRs and enabling them to pass airworthiness certification and be widely used in civil aircraft. The separation process of Jettisoned FDR installed on [...] Read more.

The safety of Jettisoned FDRS in the process of separation from an aircraft is a key factor in designing Jettisoned FDRs and enabling them to pass airworthiness certification and be widely used in civil aircraft. The separation process of Jettisoned FDR installed on NASA Common Research Model is studied by the simulation method based on anisotropic unstructured hybrid grid and overset grid technology coupled with the rigid body 6-DOF equation. First, the numerical simulation accuracy of software under same simulation method is verified by WPFS standard model. Then, according to the three main aerodynamic parameters, including incoming Mach number, angle of attack α and sideslip angle β, 10 conditions including standard condition are designed and the separation process of recorder is simulated numerically. The simulation obtained the movement of Jettisoned FDRs in 6 degrees of freedom relative to the body coordinate system in different operating conditions during the separation process and confirmed that Jettisoned FDRs can be safely separated under these operating conditions. Finally, combined with the standard operating condition, the impact of three parameters’ changes on recorder’s 6 degrees of freedom motion and the time required to complete separation are analyzed, and conditions to ensure the safe separation of Jettisoned FDRs are summarized according to the requirements of airworthiness terms. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Graphical abstract

8 pages, 1934 KiB

Open AccessProceeding Paper

A Simulation Method for Fluid–Solid Coupling in the Flexible Wings of MAVs Based on the LBM

by Liansong Peng and Chen Wang

Eng. Proc. 2024, 80(1), 26; https://doi.org/10.3390/engproc2024080026 - 22 Jan 2025

Viewed by 504

Abstract

In this paper, a fast and accurate simulation method for the large deformation motion of anisotropic complex models is proposed. By establishing a fluid–structure interaction (FSI) coupling model based on the Lattice Boltzmann Method (LBM) and the Central Difference Method, the effect of [...] Read more.

In this paper, a fast and accurate simulation method for the large deformation motion of anisotropic complex models is proposed. By establishing a fluid–structure interaction (FSI) coupling model based on the Lattice Boltzmann Method (LBM) and the Central Difference Method, the effect of flexible deformation on the aerodynamic performance of anisotropic wings during flapping is analyzed. The method can provide theoretical guidance and data support for the fluid–solid coupling study and the aerodynamic optimization of Micro Aerial Vehicles (MAVs). Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

12 pages, 3314 KiB

Open AccessProceeding Paper

Multiphysics-Based Study of Thermal Temperature Rise of Aircraft Wiring Harness

by Tao Cao, Shumei Cui, Wei Li and Tianxu Zhao

Eng. Proc. 2024, 80(1), 27; https://doi.org/10.3390/engproc2024080027 - 26 Jan 2025

Viewed by 383

Abstract

The wide application of all-electric aircraft and multi-electric technology has made the design of aircraft EWIS more and more complex, and the integration of wiring harnesses is becoming higher and higher. Aircraft wiring harness thermal temperature rise design is the key technology of [...] Read more.

The wide application of all-electric aircraft and multi-electric technology has made the design of aircraft EWIS more and more complex, and the integration of wiring harnesses is becoming higher and higher. Aircraft wiring harness thermal temperature rise design is the key technology of aircraft EWIS design, which directly affects the safety, reliability and economy of aircraft EWIS design. Based on the multiphysics research on the thermal temperature rise of the aircraft wiring harness, it is found that there is a large difference between the thermal temperature rise of the wiring harness in the exposed area of the aircraft and the airtight area, and the optimization of the wire harness wire can realize the weight and cost reduction design of the wire harness for these differences and provide aircraft economy under the premise of ensuring the safety and reliability of the aircraft. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

12 pages, 5041 KiB

Open AccessProceeding Paper

Experimental Study on Fire Resistance of Electric Vertical Take-Off and Landing Electrical Connector

by Tai Zeng, Bin Wu, Kai Wang, Zhengliang Su, Fei Xie and Tianming Wang

Eng. Proc. 2024, 80(1), 28; https://doi.org/10.3390/engproc2024080028 - 5 Feb 2025

Viewed by 288

Abstract

As a core technology in the future of aviation transportation, the safety and reliability of electric vertical take-off and landing (eVTOL) aircraft are of paramount importance. Electrical connectors, being critical components of eVTOL systems, play a significant role in ensuring overall aircraft safety. [...] Read more.

As a core technology in the future of aviation transportation, the safety and reliability of electric vertical take-off and landing (eVTOL) aircraft are of paramount importance. Electrical connectors, being critical components of eVTOL systems, play a significant role in ensuring overall aircraft safety. This paper presents a systematic experimental investigation into the fire resistance performance of electrical connectors used in eVTOL systems. The study examines the behavior of various connector materials and designs under high-temperature and flame exposure conditions, as well as their fire endurance in practical applications. A series of standardized fire resistance tests were conducted to analyze the electrical performance, mechanical strength, and signal transmission stability of the connectors under fire scenarios. The results indicate that certain high-performance materials and optimized designs can substantially enhance the fire resistance of electrical connectors, thereby improving the overall safety of eVTOL systems. This research provides crucial experimental data and theoretical insights for the design and selection of eVTOL electrical connectors, contributing significantly to the enhancement of safety standards in eVTOL aircraft. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

23 pages, 3332 KiB

Open AccessProceeding Paper

A Review of Heat Transfer and Structural Failure Mathematical Models of Carbon Fiber Composites Under Fires

by Bin Wu, Wenguo Weng, Tai Zeng, Zuxi Xia, Zhengliang Su and Fei Xie

Eng. Proc. 2024, 80(1), 29; https://doi.org/10.3390/engproc2024080029 - 6 Feb 2025

Viewed by 310

Abstract

This paper reviews the heat transfer mechanism and structural failure model of carbon fiber-reinforced polymers (CFRP) under the action of external flames. It introduces the extensive application of CFRP in aviation and the associated fire safety challenges, emphasizing the importance of studying its [...] Read more.

This paper reviews the heat transfer mechanism and structural failure model of carbon fiber-reinforced polymers (CFRP) under the action of external flames. It introduces the extensive application of CFRP in aviation and the associated fire safety challenges, emphasizing the importance of studying its heat transfer and failure mechanisms. The paper elaborates on the heat transfer model of CFRP in fire, including the formulation of energy equations, the variation in physical property parameters (such as density, thermal conductivity, and specific heat capacity), and the determination of boundary conditions, providing a theoretical basis for simulating the material’s dynamic response to fire. Furthermore, the thermal damage model of CFRP in fire is analyzed, discussing key damage mechanisms, such as porosity formation, stratified damage, decomposition, and carbon formation, and evaluating their impact on the material’s mechanical properties. The paper compares the accuracy and limitations of different models in predicting fire response, identifies the shortcomings of current research, and suggests future development directions. Finally, the importance of developing a unified model that can comprehensively consider multiple damage mechanisms is emphasized. This includes improving the predictive ability of thermal models in complex fire scenarios and enhancing the application of mechanical models under complex loading conditions, thereby providing theoretical support for the safe application of CFRP in aviation and other fields with high safety requirements. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

10 pages, 6436 KiB

Open AccessProceeding Paper

A Low-Cost Voltage Surge Monitor with Temperature Compensation for Electrified Aircrafts

by Zhao Song, Jiarui Han, Qiang Shao and Yang Ma

Eng. Proc. 2024, 80(1), 30; https://doi.org/10.3390/engproc2024080030 - 8 Feb 2025

Viewed by 125

Abstract

Along with the trend of aircraft electrification, the penetration of power electronics converters in aircraft energy systems is gradually deepening. Due to the nonlinear behavior and low inertia of aircraft power grids, voltage overshooting and oscillation may occur. Therefore, a voltage surge monitor [...] Read more.

Along with the trend of aircraft electrification, the penetration of power electronics converters in aircraft energy systems is gradually deepening. Due to the nonlinear behavior and low inertia of aircraft power grids, voltage overshooting and oscillation may occur. Therefore, a voltage surge monitor (VSM) is a safety-critical part in more-electric and electric propulsion aircrafts. VSMs often need a time delay response, so a stable delay time is important. Microprocessors and timer chips can realize accurate time delays but are relatively expensive. Having an extremely low cost and simple structure, RC filters with a discharge diode are popular in consumer electronics operating under narrow temperature ranges (0 °C~70 °C). However, it is unsuitable for aircrafts because of its severe temperature drift cause by the discharge diode. In this paper, a low-cost VSM with temperature compensation is proposed. A detailed mathematical model, simulation, and hardware experiments are conducted for demonstration and verification. Results have shown that the delay time of our VSM circuit has low temperature drift (<0.15%) and accuracy comparable to the typical timer chip LTC6994. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

8 pages, 199 KiB

Open AccessProceeding Paper

The Application of Digital Technology in the Field of Civil Aircraft Fireproof

by Bin Wu and Zhengliang Su

Eng. Proc. 2024, 80(1), 31; https://doi.org/10.3390/engproc2024080031 - 6 Feb 2025

Viewed by 238

Abstract

Civil aviation flight safety has always been a core concern of the air transport industry, with aircraft fire prevention technology being crucial for ensuring the safety of passengers and crew members. This paper reviews the types of aircraft fires and the historical lessons [...] Read more.

Civil aviation flight safety has always been a core concern of the air transport industry, with aircraft fire prevention technology being crucial for ensuring the safety of passengers and crew members. This paper reviews the types of aircraft fires and the historical lessons learned from past incidents, emphasizing the importance and urgency of advancing aircraft fire prevention technology. It details the development process and current application of fire prevention technologies, with a particular focus on the role of digital twin technology, numerical simulation techniques, and multi-objective optimization algorithms in enhancing aircraft fire safety. Finally, the paper explores the future prospects of aircraft fire protection technology, suggesting that as digital technologies continue to evolve and expand, they are expected to play an increasingly vital role in building smarter civil aviation systems, thereby contributing to the high-quality development of aircraft fire prevention. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

12 pages, 4065 KiB

Open AccessProceeding Paper

Research on an Embedded Intelligent Computing Technology

by Pengtao Su and Yihan Liu

Eng. Proc. 2024, 80(1), 32; https://doi.org/10.3390/engproc2024080032 - 18 Feb 2025

Viewed by 147

Abstract

In this paper, we study the realization in the embedded platform of an Artificial Neural Network (ANN) to explore the feasibility of a lightweight neural network. The purpose is to provide theoretical support for the intelligent information processing system based on a neural [...] Read more.

In this paper, we study the realization in the embedded platform of an Artificial Neural Network (ANN) to explore the feasibility of a lightweight neural network. The purpose is to provide theoretical support for the intelligent information processing system based on a neural network under the airborne embedded environment, and then to support the intelligent demand of the airborne system in the future complex battlefield. By analyzing the application prospect of ANN in the aviation field, this paper will design an embedded hardware platform for UAV autonomous intelligence information processing tasks, and realize a convolution neural network (CNN) on it, using an image recognition task to train and test. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

8 pages, 8876 KiB

Open AccessProceeding Paper

Configuration Design and Analysis of Tilt-Rotor-Type Flying Car

by Changlong Chen, Zhiming Tian, Aojie Li, Mengyu Xiong, Yuanshuo Wang, Fei Chen and Shichun Yang

Eng. Proc. 2024, 80(1), 33; https://doi.org/10.3390/engproc2024080033 - 25 Feb 2025

Viewed by 301

Abstract

Flying cars are envisioned as key components of the Future Comprehensive Transport Network System. Current flying car designs struggle to balance ground maneuverability with aerial agility, which means they cannot operate on standard roads (3.5 m width). Additionally, the low energy density of [...] Read more.

Flying cars are envisioned as key components of the Future Comprehensive Transport Network System. Current flying car designs struggle to balance ground maneuverability with aerial agility, which means they cannot operate on standard roads (3.5 m width). Additionally, the low energy density of existing aviation batteries limits their operational range. Therefore, a high lift-to-drag ratio (L/D) improves efficiency by reducing drag and extending the operational range. This leads to more economical and efficient flight performance, making it particularly beneficial for flying cars. This paper addresses the challenges of the land–air amphibious design and high-L/D configuration design of flying cars, and Computational Fluid Dynamics (CFD) simulations were conducted to optimize the overall configuration of a flying car, followed by creating a 1:4-scale model and validating its aerial posture. The results confirmed the structural integrity of the tilting and folding wing design for amphibious flying cars, achieving a fixed-wing mode L/D of 11. This design effectively addresses the traditional flying car issue of neglecting ground travel requirements by focusing solely on the flight capabilities of simulated aircraft or drones. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

18 pages, 9674 KiB

Open AccessProceeding Paper

Research on the Evaluation of the Architectural Design Objectives and Operation Effect of Terminals

by Pingli Xu, Qing Zhang and Ye Yuan

Eng. Proc. 2024, 80(1), 34; https://doi.org/10.3390/engproc2024080034 - 25 Feb 2025

Viewed by 201

Abstract

Through on-site research and the measurement of typical airport terminals, first-hand data are obtained. Based on actual operation data verification, the comprehensive use of measured data, and refined simulation research methods, we summarize the problems in the operation of typical airport buildings, find [...] Read more.

Through on-site research and the measurement of typical airport terminals, first-hand data are obtained. Based on actual operation data verification, the comprehensive use of measured data, and refined simulation research methods, we summarize the problems in the operation of typical airport buildings, find the reasons for the deviation between the goal and effect of “space quality and power supply” in the design, and establish a post-evaluation method. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

8 pages, 1915 KiB

Open AccessProceeding Paper

Intelligent Process Design System for Human–Robot Collaboration in Helicopter Assembly

by Xin Zhang, Guoqiang Zhang, Qingwen Yun and Jun Xiong

Eng. Proc. 2024, 80(1), 35; https://doi.org/10.3390/engproc2024080035 - 25 Feb 2025

Viewed by 151

Abstract

Traditional manual assembly is limited in terms of both efficiency and quality. In contrast, robots are characterized by rapidness and accuracy and can cooperate with humans to perform complex tasks. Human–robot collaboration may hold the potential to enhance the manufacturing capacity of the [...] Read more.

Traditional manual assembly is limited in terms of both efficiency and quality. In contrast, robots are characterized by rapidness and accuracy and can cooperate with humans to perform complex tasks. Human–robot collaboration may hold the potential to enhance the manufacturing capacity of the helicopter industry. However, the traditional assembly process design methods based on personal experience can hardly adapt to the transformation of manufacturing mode, which makes deploying human–robot collaborative assembly inefficient. In this paper, we systematically analyze applications of human–robot collaboration in helicopter fuselage assembly. Concretely, an automatic drilling and riveting process based on human–robot collaboration is designed and verified. Moreover, we develop an intelligent process design prototype system that is specifically designed for human–robot collaborative assembly by modeling and integrating process knowledge. It can effectively assist human designers by means of recommending equipment selection, process parameters, and numerical control programs. Taking a fuselage assembly process design as an example, we verify that the prototype system can improve both the management of process knowledge and the efficiency of process design. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

11 pages, 3378 KiB

Open AccessProceeding Paper

Variable Pitch Propeller: Multi-Objective Optimization Design and Performance Analysis

by Zijun Zhang, Yudong Zhang, Jingbo Yu, Pengcheng Du and Junbo Zhao

Eng. Proc. 2024, 80(1), 36; https://doi.org/10.3390/engproc2024080036 - 26 Feb 2025

Viewed by 270

Abstract

Considering the principles of green and low-carbon development, practitioners strive to continuously improve propeller performance as a primary goal for propeller-powered aircraft. Specially, medium and high-altitude UAVs require propellers that possess sufficient thrust and high efficiency across the entire flight envelope to improve [...] Read more.

Considering the principles of green and low-carbon development, practitioners strive to continuously improve propeller performance as a primary goal for propeller-powered aircraft. Specially, medium and high-altitude UAVs require propellers that possess sufficient thrust and high efficiency across the entire flight envelope to improve the UAV’s endurance and mission capability. However, given the constraints imposed by flight altitude, speed, and power system capacity, attaining optimal matching of rotational speed and torque for fixed-pitch propellers across different operating scenarios remains a significant challenge. To ensure optimal aerodynamic performance across diverse design points, variable pitch technology is adopted, and a multi-objective propeller optimization design method is proposed that adapts to the varying pitch angle strategy. Based on the standard strip analysis, with different profile chord lengths and twist angle distributions of the propeller blade as the control parameters, we establish a multi-objective propeller aerodynamic shape optimization model using a genetic optimization algorithm. The newly designed electrically variable pitch propeller, employing this method, exhibits good aerodynamic performance throughout the flight envelope. Its design has been validated through high-precision CFD analysis and wind tunnel testing, achieving a cruising efficiency of up to 84.5%. The results show that the propeller performance calculation has good consistency with the test and can meet the requirements of unmanned aircraft. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

9 pages, 875 KiB

Open AccessProceeding Paper

Research on Real-Time Mission Planning for Multi-UAV

by Jingzhi Bi, Wei Huang and Maihui Cui

Eng. Proc. 2024, 80(1), 37; https://doi.org/10.3390/engproc2024080037 - 28 Feb 2025

Viewed by 242

Abstract

With the wide application of UAVs in various industries, solving the complex multi-UAV multi-target problem becomes crucial. The assignment and task planning of multi-UAV and multi-target usually need to consider two scenarios. First, before the UAV executes the task, the number and location [...] Read more.

With the wide application of UAVs in various industries, solving the complex multi-UAV multi-target problem becomes crucial. The assignment and task planning of multi-UAV and multi-target usually need to consider two scenarios. First, before the UAV executes the task, the number and location of the target points need to be determined. It is equivalent to matching UAVs in a situation where the need is determined. Second, in the process of UAV flight, it is necessary to take into account the existing range of the UAV, the number and position of the changed mission points and carry out real-time UAV mission planning. This paper presents a multi-UAV multi-target collaborative task planning algorithm that takes into account these two scenarios. An integer programming algorithm is used to assign target points, and the constraint condition is the shortest range of UAV. The ant colony algorithm is used to plan the path of a single UAV. In this paper, the UAV delivery of disaster relief materials is taken as an example to carry out mathematical modeling and calculate the algorithm. The simulation process starts from the initial location of the UAV at the airport. After a period of flight, the UAV’s voyage information and target location information are updated to carry out real-time mission planning for the UAV. The maximum range of a single UAV is set at 30,000. The simulation results show that the total path length of four UAVs in pre-mission planning is 70,006.49, and the longest path of a single UAVs is 20645.15. In real-time mission planning, the total path length of four UAVs is 43,633.44, and the longest path of a single UAVs is 14,413.56. Over the course of the entire mission, the total path length of the four UAVs is 54,504.00, and the longest path of a single UAV is 16,434.74. The simulation results show that the solution method designed in this paper is efficient and can realize the real-time path dynamic planning of multi-UAV. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

10 pages, 892 KiB

Open AccessProceeding Paper

Understanding Public Perceptions of Artificial Intelligence in China in Relation to Advanced Air Mobility

by Hong Guan, Hao Liu, Bo Li, Jialin Li, Xinyue Jiang, Jihan Zhang, Yangruijie Yu and Shuyuan Shi

Eng. Proc. 2024, 80(1), 38; https://doi.org/10.3390/engproc2024080038 - 3 Mar 2025

Viewed by 272

Abstract

This study explored the public perceptions of advanced air mobility (AAM) in relation to artificial intelligence (AI), focusing on openness, usefulness, practical use, and trust. A survey of 93 participants was conducted using a five-point Likert scale to assess these dimensions. The results [...] Read more.

This study explored the public perceptions of advanced air mobility (AAM) in relation to artificial intelligence (AI), focusing on openness, usefulness, practical use, and trust. A survey of 93 participants was conducted using a five-point Likert scale to assess these dimensions. The results show that, while the respondents viewed AI Use favorably, openness and usefulness were rated lower, indicating hesitancy about adopting AI technologies in AAM. Trust in AI was moderate, with diverse opinions regarding fully autonomous versus human-assisted AI systems. A factor analysis using a principal components approach was conducted to further investigate these variables, but the results did not yield clear or distinct factors with trust, openness, and usefulness. This suggests that public perceptions of AI in AAM are complex and interconnected, with trust playing a key role, highlighting the need for further research to address these concerns and promote the broader acceptance of AI in AAM. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

10 pages, 7745 KiB

Open AccessProceeding Paper

Design and Implementation of a Novel Tilt-Rotor Tri-Copter UAV Configuration

by Zishi Shen and Fan Liu

Eng. Proc. 2024, 80(1), 39; https://doi.org/10.3390/engproc2024080039 - 4 Mar 2025

Viewed by 417

Abstract

Hover-capable unmanned aerial vehicles (UAVs), including rotary-wing UAVs such as unmanned helicopters, multi-rotor drones, and tilt-rotor UAVs, are widely employed due to their hovering capabilities. In recent years, tilt-rotor aircraft, which offer both vertical takeoff and landing as well as rapid maneuverability, have [...] Read more.

Hover-capable unmanned aerial vehicles (UAVs), including rotary-wing UAVs such as unmanned helicopters, multi-rotor drones, and tilt-rotor UAVs, are widely employed due to their hovering capabilities. In recent years, tilt-rotor aircraft, which offer both vertical takeoff and landing as well as rapid maneuverability, have increasingly become a research focus. This paper first proposes a design concept for a flying-wing configuration tilt-rotor tri-rotor UAV, detailing the selection of airfoils and the calculation of aerodynamic parameters. To address the specific operational requirements and flight characteristics of this UAV, a specialized tilting mechanism was developed, and a flight control system was designed and implemented using classical PID control methods. Finally, a prototype of the tilt-rotor tri-rotor UAV was fabricated and subjected to flight tests. The results from both simulations and flight tests confirmed that the UAV met the design performance criteria and that the control method was effective. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

11 pages, 4219 KiB

Open AccessProceeding Paper

Green Maintenance Technology for Large Area Damage of Composite Tail Rotor Blade

by Miao Ren, Qidi Liu, Nan Lv and Lili Li

Eng. Proc. 2024, 80(1), 40; https://doi.org/10.3390/engproc2024080040 - 17 Mar 2025

Viewed by 69

Abstract

Based on the analysis of the damage location, damage size, product layering structure, and internal filling structure of the composite tail rotor blade, the damage maintenance technical scheme was initially determined. Combined with the comprehensive performance test after maintenance, to determine the use [...] Read more.

Based on the analysis of the damage location, damage size, product layering structure, and internal filling structure of the composite tail rotor blade, the damage maintenance technical scheme was initially determined. Combined with the comprehensive performance test after maintenance, to determine the use of an enhanced repair method, special repair tooling was used to repair the product, which can repair the product fault, and the fatigue life of the product can be restored to the initial state of the product. The repair cost is low, the product performance after repair is excellent, and the repair pass rate for this kind of failure is 100%, enabling the green composite tail rotor blade repair to solve the bottleneck problem in composite blade maintenance. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

12 pages, 6680 KiB

Open AccessProceeding Paper

Aerodynamic Research on the Wing Design of a 3000 kg Hexa Tiltrotor eVTOL

by Yafei Zheng, Wei Qiao and Xinlei Wang

Eng. Proc. 2024, 80(1), 41; https://doi.org/10.3390/engproc2024080041 - 17 Mar 2025

Viewed by 110

Abstract

This paper describes a design method for 3000 kg hexa tiltrotor eVTOL wings. According to this design method, this paper designs and optimizes the wing area and incidence angle using CFD technology, provides the optimal wing design scheme, and estimates the range of [...] Read more.

This paper describes a design method for 3000 kg hexa tiltrotor eVTOL wings. According to this design method, this paper designs and optimizes the wing area and incidence angle using CFD technology, provides the optimal wing design scheme, and estimates the range of eVTOL based on CFD results. The results of the estimated range indicate that the wing designed according to the method in this paper can meet the requirements of eVTOL. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

5 pages, 1824 KiB

Open AccessProceeding Paper

The Design and Application of a Rubber Vibration Isolator for Aerospace Equipment

by Ke Duan and Feng Hou

Eng. Proc. 2024, 80(1), 42; https://doi.org/10.3390/engproc2024080042 - 28 Mar 2025

Viewed by 134

Abstract

In this study, a rubber vibration isolator is designed for certain aerospace equipment, and a finite element simulation is carried out to obtain the modal frequency and random vibration response, and to verify the accuracy of the design. The test verifies that there [...] Read more.

In this study, a rubber vibration isolator is designed for certain aerospace equipment, and a finite element simulation is carried out to obtain the modal frequency and random vibration response, and to verify the accuracy of the design. The test verifies that there is no amplification of vibration within 100 Hz; the damping efficiency values of vertical and horizontal random vibration are, respectively, 42.12% and 40.54%; and the impact isolation rate is more than 80%. The test results show that the vibration isolation buffer effect of the isolator is satisfactory and meets the design requirements. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

11 pages, 1705 KiB

Open AccessProceeding Paper

A Study on the Measurement and Prediction of Airport Carbon Emissions Under the Perspective of Carbon Peak

by Haitao Yu, Suiyi Bao, Qingpeng Man, Haifeng Xie and Jinliang Guo

Eng. Proc. 2024, 80(1), 43; https://doi.org/10.3390/engproc2024080043 - 8 Apr 2025

Viewed by 78

Abstract

Against the dual-carbon background, civil aviation is in urgent need of low-carbon and green transformation. Carbon emissions from airports are one of the main environmental concerns in civil aviation, so the early realization of airport carbon peak and carbon neutrality will help accelerate [...] Read more.

Against the dual-carbon background, civil aviation is in urgent need of low-carbon and green transformation. Carbon emissions from airports are one of the main environmental concerns in civil aviation, so the early realization of airport carbon peak and carbon neutrality will help accelerate the construction of green civil aviation and assist in the low-carbon transformation and upgrading of civil aviation. According to research, the terminal building, aircraft, and ramp area are the main sources of airport carbon emissions. Taking Harbin Taiping International Airport as an example, this study first measured the carbon emissions from the terminal building and ramp area of the airport in the past five years by using the emission factor method; then, we measured the carbon emissions from aircraft in the airport in the past five years by using the ICAO method and finally predicted the trend of carbon emissions from aircraft and the possibility of reaching the peak carbon emissions of the airport in the coming years by using scenario analysis and the Monte Carlo simulation method. The results show that the total carbon emissions of Harbin Taiping International Airport will be 458,800 tonnes in 2023 and up to 581,100 tonnes in 2035; under the scenarios of green development and technological innovation, the airport’s carbon emissions can reach their peak by 2035, which will be lower and reached earlier under the scenario of technological innovation; the airport can improve energy use efficiency, increase the utilization of renewable energy sources, establish a carbon emission monitoring system, and actively participate in the market for carbon emission monitoring systems. Airports can systematically build a development path for airport carbon peaking by improving energy efficiency, increasing the utilization rate of renewable energy, establishing a carbon emission monitoring system, actively participating in carbon trading in the market, etc., so as to reduce carbon emissions from airports and promote the transformation and upgrading of civil aviation into a green and low-carbon sector. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

12 pages, 2461 KiB

Open AccessProceeding Paper

Research on Damage Identification Method and Application for Key Aircraft Components Based on Digital Twin Technology

by Liang Chen, Fanxing Meng and Yuxuan Gu

Eng. Proc. 2024, 80(1), 44; https://doi.org/10.3390/engproc2024080044 - 9 Apr 2025

Viewed by 99

Abstract

According to high-precision damage identification of aircraft complex configuration fatigue key structures, a high-precision mathematical model of complex configuration structure is established with the use of digital twin technology to realize the real-time and accurate characterization of a physical entity from the macro [...] Read more.

According to high-precision damage identification of aircraft complex configuration fatigue key structures, a high-precision mathematical model of complex configuration structure is established with the use of digital twin technology to realize the real-time and accurate characterization of a physical entity from the macro to the micro state. Meanwhile, the damage identification information obtained by different sensor technologies and systems is used to deduce the exact state of the damage or crack. In other words, the advantage of a multi-source data drive is used to improve the effectiveness of the overall monitoring system and eliminate the limitations of single-sensor monitoring technology. Each sensor system directly transmits their filtered data information to the fusion center (digital twin system). There is no influence between each sensor; the digital twin carries out comprehensive processing and fusion analysis of each piece of information in an appropriate manner, according to the built-in algorithm and mechanism, and then outputs the final damage identification and fault diagnosis results. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

6 pages, 2226 KiB

Open AccessProceeding Paper

Design and Verification of Multi-Mode Variable Camber Wing Trailing Edge

by Yifei Lu, Zhigang Wang, Qi Wu, Yu Yang and Gang Liu

Eng. Proc. 2024, 80(1), 45; https://doi.org/10.3390/engproc2024080045 - 16 Apr 2025

Abstract

By changing the aerodynamic shape of the trailing edge of its wing, an aircraft can achieve lift and drag reduction during takeoff and landing and continuously achieve better aerodynamic efficiency while cruising, which plays an important role in the whole flight process and [...] Read more.

By changing the aerodynamic shape of the trailing edge of its wing, an aircraft can achieve lift and drag reduction during takeoff and landing and continuously achieve better aerodynamic efficiency while cruising, which plays an important role in the whole flight process and has always been a research hotspot in the field of aviation structure. Firstly, the principle scheme of wing trailing edge deformation based on a two-stage multi-link mechanism was designed and realized, and then the mechanical structure was designed in a way that ensured the machining feasibility of the prototype. Secondly, a control system scheme was designed to realize synchronous and differential deformation movement of single and double mechanisms. Finally, power drive device selection and prototype manufacturing verification were carried out. The experiments show that the designed and manufactured variable camber wing trailing edge prototype can achieve two modes of wing trailing edge deformation, namely the overall deflection of the variable camber wing trailing edge +5°~−20° and the wing tip deflection +10°~−10°. The deformation error is measured within 5%. Full article

(This article belongs to the Proceedings of 2nd International Conference on Green Aviation (ICGA 2024))

► Show Figures

Figure 1

Journal Menu

Journal Browser

Eng. Proc., 2024, ICGA 2024

Other

Further Information

Guidelines

MDPI Initiatives

Follow MDPI