Progress in Aerospace and Aviation Technology
type: channel
description: The Progress in Aerospace and Aviation Technology (PAAT) is a peer-reviewed journal that publishes twice a year, in June and December. PAAT welcomes article submissions from local and international researchers and practitioners in various fields of aeronautics, flight, and aerospace engineering. From time to time, PAAT will publish review articles and bring out special issues on a specific sub-field of aeronautic, flight, and aerospace engineering. Authors are encouraged to contact the editors if they would like to submit a review article or bring out a special issue of the journal.
publisher: Penerbit UTHM
language: en
publication name: Progress in Aerospace and Aviation Technology
issn: 2821-2924
items: Analysis of Insulation Materials for Cryogenic Hydrogen Storage Tank for Light Aircraft
items: Simulation of Phase Change Material Solidification for High-Performance Aero-Thermal Energy Storage
items: Analysis of Flow Over Streamlined Body of High-Speed Train and Bus
items: Review on Passive, Active, and Hybrid Adaptive-Morphing Flapping Wing for Energy Efficient Bird Sized UAV
items: Design and Analysis of Nozzle Exit Area for Science Technology Engineering and Mathematics (STEM) Based Solid Rocket Propellant
items: Detection of Free Obstacle Region using Distance Transform and Image Subtraction Method for Monocular Camera Sensor
items: Aerodynamic Study of a Single Groove on The Upper and Lower Surfaces of an Airfoil at Low Angles of Attack
items: Aerodynamic Study of a Two Groove on the Upper Surface of an Airfoil at Low Angles of Attack
items: Dynamic Modelling and System Identification of a Quadrotor Unmanned Aerial Vehicle Using Gyroscopic Based Test Stand
items: Effect of Graphene on Pineapple Leaf Fibre (PALF)—Fiberglass Polymer Composite for Aerospace Application
items: System Identification Study for A Small-Scale Hybrid Unmanned Aerial Vehicle Using Differential Evolution Approach
items: The Effect of Moveable Fins on Trajectory and Aerodynamic Characteristics of Model Rockets
items: Development and Characterization of Pineapple Leaf Fibre Reinforced with Graphene and Fibre Glass Composites for Aerospace Application
items: Development of Two-Axis Rotational Small Ball Miller for Powder Metallurgy Applications
items: Investigating Aerodynamic Characteristics of a Fixed-Wing Hybrid UAV During Hover-Forward Transition Flight Phase
items: Design Optimization and Performance Enhancement of Small-Scale Vortex-Induced Turbines for Sustainable Energy Generation
items: Performance Evaluation of the Spiral Water Turbine
items: Proposed Design of Wind Turbine for Highway Energy Harvesting
items: Investigation of Different Windshield Designs for Aerodynamic Drag Force in Motorcycle
items: Flight Controller Design for a Helicopter Based Unmanned Aerial Vehicle (UAV) Using Differential Evolution-Based PID Tuning
items: The Fabrication and Testing of Unmanned Aerial Vehicle (UAV) Wing Structure Using 3D Printing and Carbon Fibre Skinning Method
items: Computational Fluid Dynamics (CFD) Analysis of Archimedes Wind Turbine
items: Investigation of Different Emissions Tax Calculation Methods for Kuala Lumpur International Airport
items: Mechanical Properties of Hybrid Pineapple Leaf and Kenaf Fibers Composite
items: Water Consumption Using Artificial Neural Network Modelling in Commercial Aircraft
items: The Comparative Study Between the Grid Size of Image Frame Using Image Subtraction and Pixel Expansion Cue for Free Obstacle Region Detection
items: Conceptual Design and Analysis of a Shrouded-Type Wind Turbine for Low Wind Speed Condition
items: Flight Control System Design and Dynamic Simulation for DJI F450 Quadcopter UAV using Pole Placement Tuning Method
items: Optimisation of Water Volume Consumption in Commercial Aircraft
items: A Study On Aircraft Air-Conditioning System Trainer Model AS-43 For Aeronautical Engineering Student Practice

Analysis of Insulation Materials for Cryogenic Hydrogen Storage Tank for Light Aircraft
type: item
description: This study investigates the influence of insulation material on the performance of a cryogenic hydrogen storage tank designed for a light aircraft. A cylindrical pressure tank with hemispherical end domes was sized for integration into the aft cabin of a Cessna 172 aircraft. The tank and insulation layers were modelled in SolidWorks 2022. Static structural and steady-state thermal analyses were performed for fiberglass and aerogel as the insulation materials. The mass characteristics, stress distribution and thermal behaviour of the two configurations were compared. For the same storage pressure and volume, the total mass of the fiberglass-insulated tank was about 38.9 kg, whereas the aerogel-insulated tank had a reduced total mass of approximately 15.9 kg, representing a reduction of more than 50% in the system mass. In both cases, the von Mises stress field was dominated by the cylindrical shell, with lower stresses in the domes, and no adverse stress concentrations were introduced by replacing the fiberglass with aerogel. Thermal analysis showed that the fiberglass configuration developed a higher heat flux and significant temperature gradients, leading to an estimated hydrogen boil-off rate of 2019.2 g/h. By contrast, the aerogel configuration maintained most of the internal surface close to the cryogenic temperature, with a much lower heat flux of 0.2223 W/m², a total heat transfer rate of 0.2223 W, and a boil-off rate of only 3.6 g/h. These findings indicate that aerogel offers substantial advantages over fiberglass for cryogenic hydrogen storage in light aircraft. Therefore, it merits further investigation in more detailed tank- and aircraft-level design studies.
subject: Articles
  topic: section
subject: hydrogen storage
  topic: keywords
subject: hydrogen tank
  topic: keywords
subject: cryogenic tank
  topic: keywords
subject: light aircraft
  topic: keywords
subject: aerogel
  topic: keywords
subject: fiberglass
  topic: keywords
creator: Muhammad Aiman Hakimi Nazri
creator: Siti Nur Mariani Mohd Yunos
rights: Copyright (c) 2025 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2025-12-17
publication date: 2025-12-17
starting page: 81
ending page: 87

Simulation of Phase Change Material Solidification for High-Performance Aero-Thermal Energy Storage
type: item
description: Phase Change Materials (PCM) can be used in aerospace thermal management systems due to their ability to absorb and release large amounts of latent heat during phase transitions, making them effective for controlling temperature fluctuations in high-performance aero components. The research paper examines the solidification of paraffin wax PCM in a rectangular enclosure through the computational fluid approach provided by ANSYS Fluent. These three geometrical regions comprised Geometry 1, whose size was 150 mm x 100 mm; Geometry 2, of 200 mm x 150 mm; and Geometry 3, of 250 mm x 200 mm, and were examined under three sets of thermal boundaries, which were 363 K-294 K, 380 K-300 K, and 400 K-310 K. The transient simulation with the enthalpy-porosity approach was run to assess the temperature distribution, the pressure profiles, and the phase change advancement. The findings indicate that increased geometry sizes and greater thermal differences favor a stronger natural convection and a rapid solidification. The numerical model demonstrates the correlation between design parameters and PCM behavior, allowing for the optimization of TES systems' thermal performance.
subject: Articles
  topic: section
subject: Thermal energy storage
  topic: keywords
subject: phase change material
  topic: keywords
subject: solidification
  topic: keywords
subject: enthalpy-porosity
  topic: keywords
subject: CFD simulation
  topic: keywords
creator: Izzul Nisa’ Muhamad Noor
creator: Ishkrizat Taib
creator: Mohd Syahir Abd Razak
creator: Mohammad Hasiff Mohamad Haniff
creator: Norhasikin Ismail
rights: Copyright (c) 2025 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2025-12-17
publication date: 2025-12-17
starting page: 73
ending page: 80

Analysis of Flow Over Streamlined Body of High-Speed Train and Bus
type: item
description: External aerodynamic flow is a key factor in determining the performance, energy efficiency, and stability of land-based vehicles such as trains and buses. Vehicles with streamlined shapes tend to experience less aerodynamic drag compared to blunt bodies, which are more prone to flow separation and larger wake regions. This study aims to investigate and compare the external flow behavior over a streamlined body and a blunt body using Computational Fluid Dynamics (CFD). The objective is to understand how shape influences boundary layer development, flow separation, wake formation, and overall drag characteristics. Two geometries are modeled: a high-speed train, representing the streamlined body, and a bus, representing the blunt body. The train model is scaled to a width of 0.3 m, height of 0.4 m, and length of 3.2 m, while the bus model has a width of 0.244 m, height of 0.37 m, and length of 1.127 m. The flow inlet is being compared under incompressible conditions at air flow speeds of 10 m/s, 20 m/s, and 30 m/s through the opening, using three different values. For an accurate representation of wall boundary layers, a mesh is organized with fewer elements near walls, and the k-ω model of turbulence is used. To see how the external flow works over every geometry, both velocity contours and pressure distributions are evaluated. It is shown that the train’s reduced geometric dimensions lead to less detached flow and a tighter wake, which then causes less drag. Conversely, the basic design of buses causes the flow to divide earlier and spread, which allows for more resistance. The results indicate that body shape has a big impact on airflow and support using streamlined designs for higher aerodynamic performance in vehicles.
subject: Articles
  topic: section
subject: External flow
  topic: keywords
subject: streamlined body
  topic: keywords
subject: pressure drags
  topic: keywords
subject: k-w SST model
  topic: keywords
subject: computational fluid dynamics
  topic: keywords
creator: Muhammad Afif Rifaie Aziz
creator: Ishkrizat Taib
rights: Copyright (c) 2025 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2025-12-17
publication date: 2025-12-17
starting page: 58
ending page: 72

Review on Passive, Active, and Hybrid Adaptive-Morphing Flapping Wing for Energy Efficient Bird Sized UAV
type: item
description: Unmanned aerial vehicles (UAVs) with flapping wings are a promising bio-inspired technology that offers special benefits like increased agility, energy efficiency, and adaptability for both natural and urban settings. Recent developments in flapping wing UAV development are examined in this review, with particular attention paid to material innovations, aerodynamic optimization, and passive and active morphing mechanisms. Quantitative evidence across multiple studies indicates that passive morphing such as elastic joints and borehole designs can reduce power consumption by 10–27% and enhance lift generation by 16–40%, while active morphing enabled by actuators and smart materials improves maneuverability, stability, and load adaptability in dynamic flight conditions. Aerodynamic interactions have been better understood thanks to computational tools like Computational Fluid Dynamics (CFD) and experimental techniques like wind tunnel testing, which have also yielded important insights into performance optimization. Despite these advances, persistent challenges remain in computational cost, structural complexity, and sustained energy efficiency during extended missions. Unlike previous reviews that focus mainly on kinematics or control, this work uniquely integrates a cross disciplinary synthesis of morphing mechanisms, materials, and aerodynamic modeling to identify performance tradeoffs and emerging trends. Future research directions include AI-assisted control architectures, adaptive composite materials, and hybrid morphing designs that can transform flapping wing UAVs from laboratory prototypes into field ready systems for environmental monitoring, surveillance, and confined space operations.
subject: Articles
  topic: section
subject: Flapping-wing UAVs
  topic: keywords
subject: passive morphing
  topic: keywords
subject: hybrid morphing
  topic: keywords
subject: aerodynamic performance
  topic: keywords
subject: energy efficiency
  topic: keywords
creator: Jiaqing Guo
creator: Ermira Junita Abdullah
creator: Mohd Faisal Abdul Hamid
rights: Copyright (c) 2025 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2025-12-17
publication date: 2025-12-17
starting page: 42
ending page: 57

Design and Analysis of Nozzle Exit Area for Science Technology Engineering and Mathematics (STEM) Based Solid Rocket Propellant
type: item
description: The performance of a solid rocket propulsion system depends strongly on the geometric characteristics of its convergent–divergent (C-D) nozzle, particularly the exit area that determines the expansion of exhaust gases and the resulting thrust. This study investigates three C-D nozzle configurations with identical inlet and throat diameters using Computational Fluid Dynamics (CFD) simulations in ANSYS Fluent. Each nozzle was analyzed in terms of static pressure, temperature distribution, and velocity magnitude under the same operating conditions. The results indicate that all designs achieve choked flow at the throat, with peak velocities entering the supersonic regime. However, significant differences were observed downstream. Design B exhibits the most favorable flow characteristics, including a smooth pressure reduction of approximately 60–70% from inlet to throat, a uniform temperature decrease of about 25–30% across the divergent region, and the highest, most uniform exit velocity with minimal backflow. Designs A and C, in contrast, display irregular pressure recovery and non-uniform temperature and velocity gradients, indicating potential inefficiencies and localized separation. Overall, the findings confirm that nozzle contour geometry has a substantial effect on expansion efficiency, and the optimized configuration demonstrates strong potential for improving thrust and specific impulse in STEM solid rocket applications.
subject: Articles
  topic: section
subject: rocket nozzle, C-d design
  topic: keywords
subject: ANSYS Fluent
  topic: keywords
subject: computational fluid dynamics
  topic: keywords
subject: flow analysis
  topic: keywords
creator: Muhammad Fadhli Hairi Rahim
creator: Ahmad Hamdan Ariffin
rights: Copyright (c) 2025 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2025-12-17
publication date: 2025-12-17
starting page: 8
ending page: 16

Detection of Free Obstacle Region using Distance Transform and Image Subtraction Method for Monocular Camera Sensor
type: item
description: An area that is free of any barriers is known as a free region. Prior studies have demonstrated that when textureless impediments are used, the pixel volume expansion approach has limitations in identifying free spaces. To address the shortcoming, an approach that combines distance transform and image subtraction techniques is suggested. This algorithm incorporates three primary image processing processes: distance transform, image subtraction, and k-means segmentation. An object that is 170 cm and another that is 200 cm from the camera serve as the algorithm's inputs. Following image processing, the output is separated into 12 sections, one of which is designated as a free region. Two distinct scenarios—a congested atmosphere and an uncluttered environment—were tested by the program. Four different types of obstacles are tested for each scenario. In this case, there are four types of obstacles: texture, textureless, textureless with one obstacle on the left, and textureless with one obstacle on the right. The outcome demonstrates that the technique can accurately identify free zones. Most importantly, it has a 100% success rate in detecting obstructions that lack texture. This demonstrates that the approach can get around the prior method's drawback. Additionally, each obstacle's success rate is compiled and shown in a table. Furthermore, a comparison is made between the proposed method and the pixel volume expansion method. Combining the image subtraction and distance transform method with the volume pixel expansion method yields the same success rate (100%) in texturing barriers for crowded situations.
subject: Articles
  topic: section
subject: Free region
  topic: keywords
subject: distance transform
  topic: keywords
subject: image subtraction
  topic: keywords
subject: k-means segmentation
  topic: keywords
subject: pixel volume expansion
  topic: keywords
creator: Muhammad Syazani Nabil Sobri
creator: Muhammad Faiz Ramli
creator: Muhamad Wafi Abdul Aziz
rights: Copyright (c) 2025 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2025-06-30
publication date: 2025-06-30
starting page: 1
ending page: 7

Aerodynamic Study of a Single Groove on The Upper and Lower Surfaces of an Airfoil at Low Angles of Attack
type: item
description: This project investigates the aerodynamic effects of introducing a single groove on both the upper and lower surfaces of a NACA 0012 airfoil at low angles of attack, ranging from 0° to 10°. Each simulation features two grooves, one on the upper surface and one on the lower surface, to evaluate their combined influence on lift and drag performance. The objective is to determine whether passive flow control via surface grooves can enhance aerodynamic efficiency in low-speed conditions. The study was conducted using computational fluid dynamics (CFD) simulations in ANSYS Fluent. Several groove configurations were analyzed, including parallel grooves at 0.20C, 0.25C, and 0.30C, as well as fixed upper grooves at 0.25C and 0.30C combined with variable lower groove positions at 0.25C to 0.40C. A mesh independence test and validation against experimental data were performed to ensure simulation accuracy. A groove diameter of 1.0 cm was selected based on its favorable aerodynamic performance across the tested angles of attack. Results indicate that the configuration with a fixed upper groove at 0.25C and a lower groove at 0.40C yields the most significant lift improvement and slight drag reduction compared to the baseline airfoil. The study demonstrates that using two grooves in a dual-surface configuration can effectively delay flow separation and enhance the lift-to-drag ratio. These findings support the advancement of passive aerodynamic control strategies in low-speed airfoil applications.
subject: Articles
  topic: section
subject: Angle of Attack, lift coefficient, drag coefficient, simulation, aerodynamics, groove, airfoil
  topic: keywords
creator: MUHAMMAD AIDEED AZMAN
creator: Mohd Fauzi Yaakub
creator: Esmail Abdullah
creator: Wan Muhammad Aqil Wan Nawang
rights: Copyright (c) 2025 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2025-06-30
publication date: 2025-06-30
starting page: 55
ending page: 84

Aerodynamic Study of a Two Groove on the Upper Surface of an Airfoil at Low Angles of Attack
type: item
description: This study investigates the aerodynamic effects of introducing two semicircular grooves on the upper surface of a NACA 0012 airfoil at low angles of attack using computational fluid dynamics (CFD). The purpose of this research is to evaluate how groove geometry, depth, and spacing influence the lift and drag characteristics and to determine the optimal groove configuration that enhances aerodynamic performance. ANSYS Fluent was utilized to simulate the airflow over a baseline smooth airfoil and modified versions featuring grooves of varying sizes and positions. A grid independence test was conducted to ensure the accuracy and numerical reliability of the simulation. The baseline airfoil simulation was validated against experimental data, showing good agreement with a maximum relative error of less than 10%. The results revealed that a single groove of 0.01c depth provided an increase in lift and a notable drag reduction, particularly at a 10° angle of attack. Further investigations with two grooves, where the first groove was fixed at 0.25c and the second varied between 0.239c and 0.45c, showed that the optimal configuration was with the second groove placed at 0.35c. The study concludes that proper groove positioning and sizing can effectively delay flow separation, enhance lift, and reduce drag in low-speed aerodynamic applications. These findings suggest potential benefits for UAVs, gliders, and other airfoil-based systems operating at low angles of attack.
subject: Articles
  topic: section
subject: airfoil
  topic: keywords
subject: aerodynamic
  topic: keywords
subject: lift
  topic: keywords
subject: drag
  topic: keywords
subject: groove
  topic: keywords
creator: Esmail Abdullah
creator: Mohd Fauzi Yaakub
creator: Muhammad Aideed Azman
creator: Wan Muhammad Aqil Wan Nawang
rights: Copyright (c) 2025 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2025-06-30
publication date: 2025-06-30
starting page: 41
ending page: 54

Dynamic Modelling and System Identification of a Quadrotor Unmanned Aerial Vehicle Using Gyroscopic Based Test Stand
type: item
description: System identification plays a crucial role in developing accurate mathematical models for dynamic systems, which are essential for designing high-performance controllers. This study presents a novel gyroscope-based dynamic test rig developed specifically for quadrotor-type unmanned aerial vehicle (UAV) system identification. Unlike conventional outdoor testing, the proposed platform provides a controlled, repeatable, and vibration-minimized environment for capturing roll, pitch, and yaw dynamics, ensuring high data fidelity and safety. Using Mission Planner and LabVIEW grey box optimization, the research successfully identified continuous-time state space models that accurately characterize the UAV attitude behavior. The identified models achieved a mean squared error (MSE) below 0.002, indicating strong agreement between predicted and measured responses. These validated models formed the basis for tuning a PID controller, significantly enhancing flight stability and responsiveness. The proposed framework, which combines rig design, precise data acquisition, and data-driven modeling, provides a practical and scalable solution for UAV developers to perform pre-flight validation, reduce tuning time, and improve operational safety and control performance.
subject: Articles
  topic: section
subject: Test rigs
  topic: keywords
subject: State Space
  topic: keywords
subject: quadcopter UAV
  topic: keywords
subject: System identification
  topic: keywords
subject: state space modeling
  topic: keywords
subject: quadrotor
  topic: keywords
subject: unmanned aerial vehicles
  topic: keywords
creator: Haziqah Khudairi
creator: Syariful Syafiq Shamsudin
creator: Mohammad Fahmi Pairan
creator: Nik Ahmad Ridhwan Nik Mohd
creator: Mohd Shazlan Mohd Anwar
rights: Copyright (c) 2025 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2025-12-17
publication date: 2025-12-17
starting page: 30
ending page: 41

Effect of Graphene on Pineapple Leaf Fibre (PALF)—Fiberglass Polymer Composite for Aerospace Application
type: item
description: This study investigates the impact of incorporating graphene into a hybrid composite of pineapple leaf fibre (PALF) and fibreglass, specifically targeting aerospace applications. PALF, a natural and sustainable fibre, offers desirable mechanical properties but faces limitations in tensile and flexural strength, moisture resistance, and bonding efficiency with polymer matrices. To overcome these challenges, graphene and fibreglass are introduced as reinforcements. Graphene, known for its exceptional tensile strength, flexibility, and thermal conductivity, enhances the composite's mechanical properties, while fibreglass provides additional structural integrity due to its lightweight and durability. A sandwich layup method was employed for composite fabrication, and comprehensive mechanical testing, including tensile, flexural, and scanning electron microscopy (SEM) analyses, was conducted to evaluate their performance. Results from the tensile tests consistently demonstrated significant improvements in maximum stress, breaking stress, and strain as graphene content increased from 1% to 4%. For flexural tests, while the trends were less consistent across all percentages, a notable increase in maximum stress was observed at 4% graphene oxide. SEM analysis further revealed enhanced fibre-matrix interfacial bonding, with fibre breakage observed more frequently than pullout, particularly with increased graphene content, indicating a tougher and more resilient interface. This research highlights the significant potential of PALF/graphene/fibreglass composites as sustainable alternatives for advanced aerospace materials, offering eco-friendly and high-performance solutions capable of meeting demanding structural requirements.
subject: Articles
  topic: section
subject: PALF, graphene, fibreglass, reinforcement, tensile test, SEM test, flexural test
  topic: keywords
subject: morphological analysis
  topic: keywords
creator: Muhammad Hafizuddin Baderillah
creator: Mohd Fadhli Zulkafli
rights: Copyright (c) 2025 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2025-12-17
publication date: 2025-12-17
starting page: 17
ending page: 29

System Identification Study for A Small-Scale Hybrid Unmanned Aerial Vehicle Using Differential Evolution Approach
type: item
description: This research develops a dynamic model for a small-scale hybrid unmanned aerial vehicle (UAV) using the system identification approach, optimized by the Differential Evolution (DE) method, aiming to enhance the performance, stability, and controllability characteristics of this complex type of UAV. The methodology involved gathering data from simulated tests using LabVIEW and X-Plane 9, establishing the model structure, and then refining and training the model parameters. The differential evolution algorithm was applied in the tuning phase, comprising initialization, mutation, crossover, and selection, to efficiently optimize parameters for precision and performance. Flight data was collected from simulated hover and forward flight tests. The training dataset employed frequency-swept excitation, while the test dataset utilized doublet excitation for validation. Model validation was conducted through statistical analysis, demonstrating high prediction accuracy. The dynamic models demonstrated low mean square error with minimal standard deviation, and the predicted responses aligned closely with measured data, confirming robustness and accuracy. This study successfully applied the DE algorithm based on the system identification approach to develop and validate accurate dynamic models for a small hybrid UAV. The results establish a valuable framework for improving UAV performance and inspiring further advancements in system identification.
subject: Articles
  topic: section
subject: System Identification, Unmanned Aerial Vehicle, Hybrid UAV, Dynamic Model, Differential Evolution
  topic: keywords
creator: Abdul Malek Akalil Malek Razak
creator: Syariful Syafiq Shamsudin
creator: Mohamad Fahmi Pairan
rights: Copyright (c) 2025 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2025-06-30
publication date: 2025-06-30
starting page: 28
ending page: 40

The Effect of Moveable Fins on Trajectory and Aerodynamic Characteristics of Model Rockets
type: item
description: The application of the fins on the rocket are necessary to achieve optimal flight performance. However, the appearance of gust wind can affect the stability of the rocket during flight. To minimize instability, the fins are designed to be adjustable by changing the fin cant angles. This study aims to investigate the effect of different cant angles on rocket’s trajectory and aerodynamic characteristics through computer simulation. The Open Rocket software is used to conduct the simulations. The range of cant angle in this study is from 0° to 15° and the Clipped Delta fin design is chosen for this study. The launch condition is all the same for all the model rockets and the launch site’s latitude and longitude was based on Parit Raja location. The trajectory characteristics were evaluated through simulations of altitude versus position east of launch, altitude versus position north of launch, and altitude versus lateral distance. Meanwhile, the aerodynamic characteristics were evaluated through simulations of stability margin and drag force over time. This study found that the maximum altitude for each model rocket is decreasing as the cant angle increases. Different fin’s cant angles slightly alter the trajectory characteristic of model rockets, but they do not significantly impact the overall stability and drag characteristics during critical phases of flight. Higher cant angles resulted in shorter horizontal and lateral distances from the launch site to the apogee, suggesting a more vertical trajectory.
subject: Articles
  topic: section
subject: Fins
  topic: keywords
subject: aerodynamic
  topic: keywords
subject: cant angle
  topic: keywords
subject: Open Rocket
  topic: keywords
subject: Trajectory
  topic: keywords
creator: Nicholas Bawing Jampi
creator: Mohd Fadhli Zulkafli
rights: Copyright (c) 2024 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2024-08-15
publication date: 2024-08-15
starting page: 72
ending page: 81

Development and Characterization of Pineapple Leaf Fibre Reinforced with Graphene and Fibre Glass Composites for Aerospace Application
type: item
description: Natural fibre-based composites such as Pineapple leaf fibre (PALF) are valued for their environmental friendliness and unique properties, can be combined with graphene and glass fibres to create advanced aerospace composites. This study investigates the effects of graphene content and PALF composition on the mechanical properties of the composite. PALF is made using environmentally friendly methods, with graphene treated for better integration and fibre glass added through layering. This study compares the strength and flexibility of two samples with different PALF-to-fibreglass ratios: 50:50 and 70:30, and one sample with a 70:30 PALF-to-fibreglass ratio reinforced with 1% graphene, using tensile and flexural tests. The 70:30 composition ratio results in a lower maximum tensile strength and Young’s modulus, but a higher bending stress than the 50:50 ratio due to the higher volume of PALF in the sample. 70:30 PALF/fibreglass reinforced with 1% graphene is stiffer, resulting in a higher Young’s modulus compared to the sample without graphene. There is a slight decrease in flexural strength for the 70:30 PALF/fibreglass ratio reinforced with 1% graphene, while still maintaining superior bending stress strength compared to 50:50 ratio compositions. From the SEM test, PALF/fibreglass samples exhibited fibre pull-out, while 70:30 samples reinforced with graphene showed fibre breakage. Graphene enhanced the bonding between fibres and resins, leading to the breakage. Without graphene, weaker bonding led to fibre pull-out. Therefore, the PALF/fibreglass reinforced with graphene has the potential for aerospace applications, particularly in components subjected to high bending stress, such as aircraft wings or the horizontal tail.
subject: Articles
  topic: section
subject: PALF, graphene, fibreglass, reinforcement, tensile test, SEM test, flexural test
  topic: keywords
creator: Noor Ezzat Nafie Noor Azman
creator: Mohd Fadhli Zulkafli
creator: Syafiqah Nur Azrie Safri
rights: Copyright (c) 2024 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2024-08-15
publication date: 2024-08-15
starting page: 82
ending page: 91

Development of Two-Axis Rotational Small Ball Miller for Powder Metallurgy Applications
type: item
description: In powder metallurgy, milling involves reducing solid metal into fine particles through grinding or crushing, which enhances its properties and applications. This study aims to fabricate a two-axis small milling machine for powder milling and to investigate the relationship between rotational speed and milling time effectiveness. The research begins with analyzing the requirements for powder metallurgy processes, focusing on factors like particle size distribution and homogeneity. SolidWorks software designs the milling machine, emphasizing optimal functionality for powder milling. The machine tests use aluminum chips, and an optical microscope assesses the post-milling particle sizes at various time intervals. The study employs two motors: a 12V DC motor and a 24V DC motor, each capable of reaching up to 1500 rpm. A potentiometer is used for user control and automation. After adding a fixed bar, particle sizes are measured at 1.02 mm for 500 rpm and 1.08 mm for 1500 rpm after two hours of milling. After an additional two hours, sizes decrease to 0.50 mm for 500 rpm and 0.56 mm for 1500 rpm, indicating effective particle size reduction with extended milling time. Results demonstrate that integrating a fixed bar into the two-axis small milling machine enhances particle size distribution and milling efficiency. Additionally, critical speed analysis underscores the importance of maximizing mill rotation for efficient milling operations. In conclusion, the two-axis small milling machine is successfully fabricated, demonstrating high quality and efficiency in powder metallurgy milling processes.
subject: Articles
  topic: section
subject: Powder Metallurgy
  topic: keywords
subject: Conventional ball mills
  topic: keywords
subject: Two-axis rotation small ball miller
  topic: keywords
subject: Small-scale applications
  topic: keywords
subject: Mixing and grinding control
  topic: keywords
creator: Ahmad Syakir Fisal
creator: Wan Nur Azrina Wan Muhammad
creator: Md. Nor Anuar Mohamad
rights: Copyright (c) 2024 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2024-12-24
publication date: 2024-12-24
starting page: 1
ending page: 9

Investigating Aerodynamic Characteristics of a Fixed-Wing Hybrid UAV During Hover-Forward Transition Flight Phase
type: item
description: In the past few years, unmanned aerial vehicles (UAVs) have been employed extensively in agricultural observation, wildlife protection, and traffic monitoring sectors. Hybrid UAVs combine the advantages of both multirotor and fixed-wing types, which can take off and land vertically. The key objective of the present work is to investigate the aerodynamic characteristics of a vertical takeoff and landing (VTOL) fixed-wing Tricopter (VFW tricopter) UAV by creating a 3D model in Plane-Maker and simulating that model to get thrust, lift force, drag force, and static pitch stability. X-Plane 12 was used to design and study the aerodynamic characteristics of a VTOL Tricopter UAV during the hover-forward transition flight phase. It has been found that the value of thrust force was high before transition, which is suitable for vertical takeoff and maneuvering. During the transition, it starts decreasing. After the transition, the thrust goes down and then stabilizes at lower values to sustain forward motion. This thrust reduction enables the plane to glide. In terms of pitch stability, at the beginning of the transition phase, the VFW tricopter UAV was unstable. Afterwards, the pitch stability stabilizes, indicating that the UAV has adjusted to a stable forward flight. Transition thrust vector changes may cause instability at the start of the transition phase. Lift force was high and stable during hover, decreased during transition, and showed fluctuations as the tricopter UAV adjusted to forward flight. Drag force was relatively high during hover and decreased during transition, stabilizing at lower values during forward flight. The frontal area of the tricopter UAV decreased, which caused the plane to produce less drag. This study aids in designing and understanding the aerodynamic characteristics of a VFW tricopter UAV during the hover-forward transition flight phase.
subject: Articles
  topic: section
subject: UAV
  topic: keywords
subject: Fixed-Wing UAV
  topic: keywords
subject: VTOL
  topic: keywords
subject: hybrid UAV
  topic: keywords
subject: simulation
  topic: keywords
subject: tricopter
  topic: keywords
creator: Muhammad Munib Abid Aqeel
creator: Mohd Fadhli Zulkafli
creator: Mohammad Fahmi Pairan
rights: Copyright (c) 2024 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2024-12-24
publication date: 2024-12-24
starting page: 76
ending page: 87

Design Optimization and Performance Enhancement of Small-Scale Vortex-Induced Turbines for Sustainable Energy Generation
type: item
description: This study presents the development and evaluation of a vortex bladeless wind turbine prototype designed to harness wind energy in low wind speed conditions, making it suitable for regions such as Malaysia. The prototype consists of a 2-meter-tall, 0.2-meter-diameter cylindrical structure mounted on a flexible shaft, which utilizes vortex-induced vibrations to generate mechanical energy. Testing was conducted in a wind tunnel with airflow ranging from 1 m/s to 10 m/s, as well as in outdoor field locations around UTHM. Results demonstrated the turbine’s effectiveness at low to moderate wind speeds. Vibrations were converted into electrical energy using an electromagnetic induction system. Analysis of oscillation frequency, voltage output, and efficiency indicated promising performance under conditions where traditional turbines are less effective. Design enhancements further improved the turbine’s performance.
subject: Articles
  topic: section
subject: Bladeless wind turbine (BWT)
  topic: keywords
subject: Vortex induces turbine (VIWT)
  topic: keywords
creator: Sheikh Alif Habibullah Sheikh Hassan
creator: Sofian Mohd
rights: Copyright (c) 2025 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2025-12-17
publication date: 2025-12-17
starting page: 1
ending page: 7

Performance Evaluation of the Spiral Water Turbine
type: item
description: Water is a fundamental component of renewable energy and may produce power through the utilization of a water turbine. These turbines utilize electromechanical energy converters to harness the kinetic energy of flowing water. The research seeks to enhance and evaluate the existing spiral water turbine design, in addition to assessing the turbine's power production via testing. The mechanism and control system were analyzed, and a comprehensive design of the water turbine was created in SolidWorks. The testing was conducted at the Sungat Bantang waterfall, with evaluations performed at heights of 0.21m, 0.51m, and 0.87m. The turbine experienced two modes of operation: half-submerged and fully submerged. The analysis of the findings is based on data collected during testing, which includes water velocity, current, voltage, and power output. The findings indicated that power output increases with water velocity as a result of increased kinetic energy in the flow. In the trials, the turbine's power output reached 28.99 W, 176.77 W, and 357.11 W under partially submerged conditions, corresponding to water velocities of 2.03 m/s, 3.16 m/s, and 4.13 m/s, respectively. Simultaneously, fully submerged conditions produced power outputs of 29.74 W, 132.34 W, and 312.34 W, respectively. Consequently, higher velocity results in increased power. In conclusion, although it was tested just at the rapid's minimal height of one meter, the turbine effectively generated energy.
subject: Articles
  topic: section
subject: Spiral Water Turbine
  topic: keywords
subject: Electricity
  topic: keywords
subject: Power generation
  topic: keywords
creator: Siti Nurhajar Bahtiyar
creator: Sofian Mohd
rights: Copyright (c) 2024 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2024-12-24
publication date: 2024-12-24
starting page: 70
ending page: 75

Proposed Design of Wind Turbine for Highway Energy Harvesting
type: item
description: This study explores the feasibility of deploying wind turbines alongside highways to harvest untapped wind energy generated by vehicular traffic, with a focus on Malaysia's North-South Highway. The research aims to analyze local wind meteorology data, identify suitable wind turbine designs for roadside applications, and propose mechanically optimized configurations to enhance energy harvesting efficiency and safety. The methodology involves a comprehensive literature review on wind patterns, structural considerations, and turbine types from international contexts, followed by the simplification and design of vertical axis wind turbines (VAWTs), specifically Darrieus and Savonius models, using SolidWorks software. Computational fluid dynamics (CFD) simulations were conducted at a wind speed of 30.56 m/s (equivalent to Malaysia's highway speed limit of 110 km/h), evaluating parameters such as blade count, materials (e.g., high-grade steel alloys), airflow density, pressure, velocity, and power output. Data from the Malaysian Meteorological Department (2019–2022) informed site-specific assessments, particularly for the Pagoh to Yong Peng section. Findings indicate that VAWTs are most appropriate for highway installations due to their adaptability to turbulent, low-speed winds. The Darrieus turbine outperformed the Savonius and a previous design, achieving an average velocity of 27.460 m/s, a pressure of 101797.48 Pa, and a power output of 3.163 kW, exceeding the Betz limit of 1.875 kW and demonstrating superior energy capture efficiency. This research contributes to renewable energy integration in transportation infrastructure by providing evidence-based recommendations for VAWT deployment, highlighting mechanical optimizations for safety and performance. It informs policymakers, engineers, and developers on sustainable practices, potentially reducing reliance on fossil fuels while enhancing highway energy self-sufficiency.
subject: Articles
  topic: section
subject: Savonius wind turbine
  topic: keywords
subject: Wind Turbine
  topic: keywords
subject: Highway energy harvesting
  topic: keywords
subject: Vertical Axis Wind Turbine
  topic: keywords
subject: Horizontal Axis Wind Turbine
  topic: keywords
subject: Darrieus wind turbine
  topic: keywords
creator: Ahmad Danial Ezman Bin Azhar
creator: Nurhayati Rosly
rights: Copyright (c) 2025 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2025-06-30
publication date: 2025-06-30
starting page: 18
ending page: 27

Investigation of Different Windshield Designs for Aerodynamic Drag Force in Motorcycle
type: item
description: This research investigates the aerodynamic performance of different windshield designs for the Honda CB500X motorcycle at 140 km/h, focusing on drag force, drag coefficient, and pressure distribution. Three aftermarket windshields and one original equipment manufacturer (OEM) windshield were developed in SolidWorks and simulated using computational fluid dynamics (CFD) in ANSYS Fluent. The OEM windshield outperformed the aftermarket designs in terms of aerodynamic efficiency, with a lower drag force (735.65991 N) and drag coefficient (0.3951). However, a pressure distribution study found that aftermarket windshields provided better deflection of airflow, resulting in less direct wind effect on the rider, potentially improving rider comfort and safety. These findings highlight the trade-off between aerodynamic efficiency and rider comfort in windshield design.
subject: Articles
  topic: section
subject: Drag force
  topic: keywords
subject: aerodynamic performance
  topic: keywords
subject: drag coefficient
  topic: keywords
creator: Farid Ghazali
creator: Mohammad Fahmi Abdul Ghafir
rights: Copyright (c) 2024 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2024-08-15
publication date: 2024-08-15
starting page: 49
ending page: 56

Flight Controller Design for a Helicopter Based Unmanned Aerial Vehicle (UAV) Using Differential Evolution-Based PID Tuning
type: item
description: Helicopters possess the ability to perform a range of maneuvers, including vertical takeoff, hovering, forward or sideways movement, spinning, and turning. Helicopter UAVs are highly advantageous for both military and civilian applications due to their exceptional agility, particularly in hazardous environments. It is critical to evaluate the control system's performance and safety through simulation before using it on actual flights. This helps to reduce risks and minimize the need for extensive flight testing using complex aeronautical systems. The objective of this study is to develop an autonomous flight control system (AFCS) specifically designed for a helicopter-based unmanned aerial vehicle (UAV). This system will control and regulate the helicopter's altitude, attitude, velocity, and heading. The purpose of the study is to determine the optimal gains for a PID controller using the Differential Evolution methodology. Differential evolution is a heuristic method that operates on a population of vectors. To minimize cost functions, it replaces the existing vectors with trial vectors derived from mutant vectors. The optimization process consists of four distinct phases: initialization, mutation, crossover, and selection. The method is a simple and efficient search approach for finding the global optimum. It employs population model functions with real-valued arguments, as well as those defined on completely ordered spaces. The control algorithm underwent testing and simulation using the X-Plane 9 flying simulator and LabVIEW software. A sequence of simulated flight tests validates the performance and effectiveness of the proposed controller. Therefore, it can be inferred that the controller gain obtained by the Differential Evolution (DE) approach in the AFCS design is suitable for hovering and circular trajectory tracking. This is achieved by adjusting the PID gain values based on the Q matrix variations in a multi-objective cost function. The accuracy of posit…
subject: Articles
  topic: section
subject: Helicopter UAV
  topic: keywords
subject: Differential Evolution
  topic: keywords
subject: PID
  topic: keywords
subject: LQR cost function
  topic: keywords
subject: Multi-Objective cost function
  topic: keywords
subject: Tuning method of PID controller
  topic: keywords
subject: X-plane
  topic: keywords
subject: Software-in-the-loop simulation
  topic: keywords
subject: LabVIEW
  topic: keywords
creator: Illia Mohammed Shukor
creator: Syariful Syafiq Shamsudin
creator: Mohammad Fahmi Pairan
rights: Copyright (c) 2024 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2024-12-24
publication date: 2024-12-24
starting page: 36
ending page: 50

The Fabrication and Testing of Unmanned Aerial Vehicle (UAV) Wing Structure Using 3D Printing and Carbon Fibre Skinning Method
type: item
description: This study examines the efficacy of integrating 3D printing with carbon fibre skinning to construct wing structures for Unmanned Aerial Vehicles (UAVs). The primary objective is to enhance the structural integrity and material characteristics. The study performs static load tests, which demonstrate that wings reinforced with carbon fibre lamination can endure a substantially greater maximum stress of 29.43 N, in contrast to 14.391 N for wings produced only by 3D printing. The carbon fibre laminated wings have a greater load-bearing capability, as evidenced by the safety factor study. This analysis reveals that the permitted loads for carbon fibre laminated wings (19.61 N) are higher compared to 3D printed wings (9.594 N). The tensile testing of the specimens reveals that carbon fibre laminated wings demonstrate enhanced ductility, stiffness, and yield strength. Additionally, they withstand greater levels of maximum stress and strain, except for a slightly higher stiffness seen in 3D printed wings. This research highlights that carbon fibre laminated wings are typically more durable and versatile for many uses, although 3D printed wings may be favoured in situations when greater rigidity is necessary. In conclusion, the study effectively showcases the advantages of combining 3D printing with carbon fibre skinning in the construction of UAV wings. This research significantly contributes to the progress of UAV design and provides fresh insights in the fields of aeronautical engineering and materials science. It is particularly valuable for applications that require UAVs with exceptional performance, durability, and reliability.
subject: Articles
  topic: section
subject: Unmanned Aerial Vehicle (UAV)
  topic: keywords
subject: Carbon Fibre Skinning
  topic: keywords
subject: Tensile Testing
  topic: keywords
subject: Vertical Take-Off, and Landing (UAV)
  topic: keywords
subject: Wing Structure
  topic: keywords
creator: Muhammad Ariff Nazrin Mohd Kamarulnizam
creator: Mohd Fauzi Yaakub
rights: Copyright (c) 2024 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2024-08-15
publication date: 2024-08-15
starting page: 16
ending page: 27

Computational Fluid Dynamics (CFD) Analysis of Archimedes Wind Turbine
type: item
description: Windmills, or wind turbines, generate wind energy and serve as a viable substitute for fossil fuels. This study mainly focuses on the Archimedes wind turbine, a novel horizontal-axis wind turbine design inspired by Archimedes' screw pump. Computational Fluid Dynamics (CFD) analysis plays a crucial role in enhancing the turbine's effectiveness, providing insights into its performance. This study investigated the performance of the Archimedes wind turbine with respect to pitch, opening angle, and wind speed variation, utilizing SolidWorks for three-dimensional modeling and ANSYS Fluent for CFD analysis. Additionally, wind turbine comparative analysis was conducted to evaluate the power and torque coefficients of the Archimedes wind turbine against the Savonius and Helical Savonius wind turbines at various wind speeds. Essentially, the study's results showed that increasing the pitch and opening angle of the Archimedes wind turbine positively impacted the power coefficient and torque coefficient, resulting in improved turbine performance. When increasing the pitch from 600 mm to 2000 mm, the maximum C_p and C_t achieved were 0.2013 and 0.2577, respectively, at 1400 mm pitch. Furthermore, when increasing the opening angle from 15° to 75°, the maximum C_p and C_t achieved were 0.2290 and 0.2937, respectively, at a 60° opening angle. The Archimedes turbine consistently outperformed the Savonius and Helical Savonius wind turbines, indicating its potential for wind energy applications. However, the Helical Savonius has approximately similar performance to the Archimedes wind turbine. Therefore, this study provided valuable insights into the performance of the Archimedes wind turbine through CFD analysis. The findings contributed to the development of more efficient wind energy technology, addressing environmental concerns and promoting sustainable energy solutions.
subject: Articles
  topic: section
subject: Archimedes wind turbine
  topic: keywords
subject: Computational Fluid Dynamics
  topic: keywords
subject: pitch
  topic: keywords
subject: opening angle
  topic: keywords
subject: wind speed
  topic: keywords
subject: Savonius wind turbine
  topic: keywords
subject: Helical Savonius wind turbine
  topic: keywords
subject: power coefficient
  topic: keywords
subject: torque coefficient
  topic: keywords
creator: Mohamad Faizal Mohamad Raffi
creator: Sofian Mohd
rights: Copyright (c) 2024 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2024-12-24
publication date: 2024-12-24
starting page: 60
ending page: 69

Investigation of Different Emissions Tax Calculation Methods for Kuala Lumpur International Airport
type: item
description: The aviation sector is among the most active industries globally and has been evolving for over a century. Aviation's rapid expansion significantly contributes to emissions. This study aims to propose a methodology for calculating nitrogen oxide (NOx) emission taxes for Kuala Lumpur International Airport (KLIA) while concurrently analyzing the departure traffic in the vicinity. This study attempts to identify the airline and differentiate the engine type that contributes to NOx emissions at KLIA. Departure information and aircraft statistics at the specified airport were acquired via FlightRadar 24 and Airfleets.net. The data was collected over a three-month period from September to November 2023. Upon compilation of the collected data, the tax prices are calculated and analyzed using three distinct methodologies. The NOx emission index is derived from the latest version of the ICAO databank. The peak departure hours at KLIA are 9:00 am and 1:00 pm. AirAsia is the airline with the largest daily departure activity, and CFM engines are likely the primary contributors to NOx emissions. Finally, the Copenhagen method is recommended for implementation at KLIA due to its fair and efficient NOx emission tax system, which accurately represents the environmental consequences of its operations and promotes more sustainable behaviors within the aviation sector.
subject: Articles
  topic: section
subject: NOx emissions
  topic: keywords
subject: Tax calculation method
  topic: keywords
subject: Tax emissions
  topic: keywords
subject: Data of airlines
  topic: keywords
subject: Data of engine
  topic: keywords
subject: Departure activity
  topic: keywords
creator: Alif Izzuddin Azrin
creator: Mohammad Fahmi Abdul Ghafir
rights: Copyright (c) 2024 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2024-12-24
publication date: 2024-12-24
starting page: 51
ending page: 59

Mechanical Properties of Hybrid Pineapple Leaf and Kenaf Fibers Composite
type: item
description: The use of natural fibers such as pineapple leaf (PALF) and kenaf fibers in composite materials has gained attention due to their potential to provide improved mechanical properties over traditional materials. Furthermore, there is significant opportunity for this idea to be employed in high-value sectors like building, aircraft, and automobiles. Therefore, the study aims to investigate the mechanical properties of hybrid kenaf fibers and PALF composite material for aircraft applications. The hybrid composite ratio between kenaf fiber and PALF varies into three different ratios. The kenaf fiber:PALF ratio is 60:40, 40:60, and 50:50, respectively. The samples were fabricated via a hand-layup process. Tensile and flexural testing were conducted to analyze the mechanical properties of the hybrid composite. The Scanning Electron Microscope (SEM) was employed to investigate the structure morphology. The tensile testing shows that the 40:60 ratio composite has the highest maximum stress (69.14 MPa). Besides that, the 60:40 ratio composite has the maximum flexural strength (129.35 MPa). The SEM investigation reveals that the failure occurs due to matrix deformation, fiber breaking, and fiber pullout. The results show that the hybrid composite has good performance as compared to the existing material in aviation, such as for food trays, inner walls, and low-critical composite parts. Hence, it has a big potential for further enhancement with regards to weight reduction, increasing fuel efficiency, and lowering carbon emissions in the aviation sector.
subject: Articles
  topic: section
subject: hybrid composite material
  topic: keywords
subject: tray tables
  topic: keywords
subject: aircraft
  topic: keywords
creator: Wan Amin Khalili Wan Hashim
creator: Ahmad Hamdan Ariffin
creator: Mohd Fadhli Zulkafli
rights: Copyright (c) 2024 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2024-12-24
publication date: 2024-12-24
starting page: 10
ending page: 16

Water Consumption Using Artificial Neural Network Modelling in Commercial Aircraft
type: item
description: Amidst the current period of increased environmental consciousness and the aviation industry's dedication to sustainability, the delicate balance between water-carrying and fuel usage in commercial aircraft has become a crucial issue due to the rapid development of aviation technology. The primary purpose of this study is to evaluate the water usage of commercial aeroplanes and to optimise the aeroplanes' usage of water. Moreover, the study focuses on analysing the comparison between water consumption estimated using the Artificial Neural Networks (ANN) and historical data collected precisely. By referring to the actual operational data of water tank usage of the Boeing 787-9 fleet in a commercial airline, the flight hours, total passengers, and also actual portable water tank were obtained. The data were gathered over two years, starting from January 2022 until December 2023, for day and night flight time. After all the collected data were completed, the optimisation of the water consumption was conducted and analysed using ANN. The optimised results were then compared using two conventional methods, IATA and Boeing. In conclusion, the ANN method has the least errors compared to IATA and Boeing. The ANN method is suggested as a method to optimise the water tank volume for commercial aircraft.
subject: Articles
  topic: section
subject: Water volume optimization
  topic: keywords
subject: , Fuel consumption
  topic: keywords
subject: Sustainability
  topic: keywords
subject: Artificial Neural Network
  topic: keywords
subject: Mean Square Error
  topic: keywords
subject: Flight duration
  topic: keywords
subject: Portable water tank
  topic: keywords
creator: Muhammad Aieman Muhamed Suhan
creator: Mohammad Fahmi Abdul Ghafir
rights: Copyright (c) 2024 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2024-08-15
publication date: 2024-08-15
starting page: 28
ending page: 34

The Comparative Study Between the Grid Size of Image Frame Using Image Subtraction and Pixel Expansion Cue for Free Obstacle Region Detection
type: item
description: This research investigates optimizing grid sizes for obstacle detection in Unmanned Aerial Vehicles (UAVs) using vision-based approaches. There were many proper computer visions algorithm that can be used to detect free obstacle region. One of it is by using grid-based approach. By dividing the image that taken by camera, the algorithm can choose the best path to go through. This study will explore various grid sizes, from 3x4 to 24x32, to determine their effectiveness in detecting free obstacle regions in different environments. The methodology combines image subtraction, pixel expansion cues, and k-means segmentation, with images resized to 640x360 pixels and processed to display only two colors for simplification. The experiments, conducted using an iPhone 12 camera and analyzed with Spyder software and OpenCV, reveal that larger grids are more accurate in complex environments, albeit with higher computational time, whereas smaller grids are more efficient in simpler settings. The research identifies a grid size range of 12x16 to 16x24 as a balanced solution for various scenarios, highlighting the need for adaptive sizing and sophisticated algorithms in UAV obstacle detection.
subject: Articles
  topic: section
subject: Free region detection
  topic: keywords
subject: grid size
  topic: keywords
subject: number of grid
  topic: keywords
subject: computational time
  topic: keywords
creator: Mohammad Anwaar Badrol
creator: Muhammad Faiz Ramli
rights: Copyright (c) 2024 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2024-08-15
publication date: 2024-08-15
starting page: 57
ending page: 71

Conceptual Design and Analysis of a Shrouded-Type Wind Turbine for Low Wind Speed Condition
type: item
description: Wind energy represents a valuable renewable resource with significant potential for electrical power generation. While conventional wind turbines have been well-developed for electricity generation, they suffer from reduced efficiency and limited power output in remote areas with low wind speeds (typically below 7 m/s), where wind energy extraction becomes economically unviable. The central research question addressed in this study is: Can shrouded wind turbine technology significantly improve power generation efficiency compared to conventional open rotor designs under low wind speed conditions? This study aimed to propose a conceptual design of a shrouded wind turbine and analyze its performance under low wind speed conditions ranging from 4 to 7 m/s. The proposed wind turbine's performance was analyzed through extensive computational fluid dynamics (CFD) simulations using ANSYS Fluent. Key performance parameters, including power coefficient (Cp), tip speed ratio (TSR), velocity distribution, pressure characteristics, torque generation, and power output capabilities, were investigated. Results demonstrated that the shrouded wind turbine achieved higher Cp values at elevated tip speed ratios compared to conventional open rotor configurations. Specifically, the shrouded design generated 17.1% more power at 4 m/s and 5.0% more power at 7 m/s wind speeds. The shrouded configuration increased air velocity by 11.6% at 4 m/s and 7.5% at 7 m/s compared to the open rotor design, demonstrating enhanced wind energy capture efficiency in low wind speed environments.
subject: Articles
  topic: section
subject: Shrouded Wind Turbine
  topic: keywords
subject: Horizontal Axis Wind Turbine
  topic: keywords
subject: Tip Speed Ratio,
  topic: keywords
subject: Power,
  topic: keywords
subject: Power Coefficient
  topic: keywords
subject: Torque Coefficient
  topic: keywords
creator: Syed Nazim Syed Ahmad
creator: Nurhayati Rosly
rights: Copyright (c) 2025 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2025-06-30
publication date: 2025-06-30
starting page: 8
ending page: 17

Flight Control System Design and Dynamic Simulation for DJI F450 Quadcopter UAV using Pole Placement Tuning Method
type: item
description: This paper presents the flight control design of a quadcopter-based unmanned aerial vehicle using an improved PID tuning method based on pole placement (PP) to achieve the desired time response specification. The flight of a quadcopter UAV presents a difficult control problem because it is a fast-responsive and unstable nonlinear system. This study employed the X-Plane flight simulator to assess the control gain values of the autopilot system. The autopilot system was developed using the PID controller in the LabVIEW environment, utilizing the Software in the Loop (SIL) approach. A series of simulated flight experiments were carried out to verify the performance of the proposed controllers and assess the effectiveness of the control systems. The findings suggest that PID controllers, when tuned using the pole placement (PP) technique, can achieve satisfactory position tracking performance during hovering movements, with x and y positions staying within ±0.5 m limits. The controller demonstrated sufficient resilience in handling wind turbulence of 4.5 m/s during a circular path tracking simulation. It achieved position errors of 0.1306 m, 0.0832 m, and 0.2881 m in the x, y, and z positions, respectively, while maintaining a heading error accuracy of less than 3º as per the intended specification.
subject: Articles
  topic: section
subject: PID
  topic: keywords
subject: quadcopter UAV
  topic: keywords
subject: pole placement (PP) tuning
  topic: keywords
subject: software in the loop (SIL)
  topic: keywords
creator: Annis Syahirah Jemsa
creator: Syariful Syafiq Shamsudin
creator: Mohammad Fahmi Pairan
rights: Copyright (c) 2024 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2024-12-24
publication date: 2024-12-24
starting page: 17
ending page: 35

Optimisation of Water Volume Consumption in Commercial Aircraft
type: item
description: This research paper focuses on optimising water volumes consumed in commercial aircraft water tanks during flying to reduce fuel consumption and promote sustainability. The study employs a methodology that includes real data collection, statistical analysis, and optimisation using the Response Surface Methodology (RSM). The data obtained from Boeing 787-9 and 787-10 fleets used in this study spans from December 2022 to March 2023. The findings and analyses are based on various parameters such as water usage, flight duration, and passenger count. Statistical comparisons between the water usage optimised by RSM and the present estimation model developed by the International Air Transport Association (IATA) and Boeing methods are conducted, highlighting the superior performance of RSM in terms of lower percentage errors and better optimisation. The frequency distributions of percentage errors provide further support for the effectiveness of RSM. This research significantly contributes to our understanding of optimising aircraft water usage for improved fuel efficiency and sustainability. The findings have important implications for the aviation industry and environmental preservation. By reducing fuel consumption through optimised water volumes, airlines can enhance operational efficiency while minimising environmental impact.
subject: Articles
  topic: section
subject: Water volume optimisation
  topic: keywords
subject: fuel consumption
  topic: keywords
subject: sustainability
  topic: keywords
creator: Muhmaammad Naqiuddin Bin Samsudin
creator: Mohammad Fahmi bin Abdul Ghafir
rights: Copyright (c) 2024 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2024-08-15
publication date: 2024-08-15
starting page: 1
ending page: 7

A Study On Aircraft Air-Conditioning System Trainer Model AS-43 For Aeronautical Engineering Student Practice
type: item
description: Aircraft air conditioning systems are crucial for ensuring a comfortable and safe environment for occupants during flight. These systems regulate temperature, humidity, and air pressure within the cabin and are found in various aircraft types, including commercial airliners, business jets, military aircraft, and helicopters. The objectives of the research are to identify suitable standard operating procedures (SOPs) and safety protocols for the trainer system, and to determine temperature, relative humidity, pressure, and enthalpy changes within the AS-43 system. A varying parameter is temperatures, pressure, relative humidity and the enthalpy can be obtained. Manual Cool and Auto cool mode of the AS-43 trainer are evaluated. The experimental results show the Manual Cool and Auto Cool gives a slightly different enthalpy values and COP for the system. The enthalpy obtained from the Manual cool are between 240 kJ/kg to 450 kJ/kg while Auto Cool enthalpy is between 240 kJ/kg to 440 kJ/kg. The relative humidity of both modes is in average range suggested by ASHRAE. P-h diagram of both experiments can be obtained based on the data collected. Finally, the study focuses on the AS-43 Aircraft Air Conditioning System Trainer Model, which serves as a valuable educational tool for teaching students about aircraft air conditioning systems. Hence, a significant recommendation is suggested discussed at the end of the research.
subject: Articles
  topic: section
subject: Aircraft air conditioning system
  topic: keywords
subject: AS-43 Trainer Model
  topic: keywords
subject: Enthalpy
  topic: keywords
subject: Standard Operating Procedure
  topic: keywords
subject: Educational tool
  topic: keywords
creator: Amirah Eitqan Ezaiyuddin
creator: Nor Adrian Nor Salim
rights: Copyright (c) 2023 Progress in Aerospace and Aviation Technology https://creativecommons.org/licenses/by-nc-sa/4.0
date: 2023-12-14
publication date: 2023-12-14
starting page: 8
ending page: 16