AVIA - International Journal of Aviation Science and Engineering
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Flight Test Evaluation for Tilt Rotor Unmanned Aerial Vehicle Development
Get PDFTiltrotor Unmanned Aerial Vehicle (UAV) is type of UAV that combine fixed wing (FW) and multirotor (VTOL) configuration in order to be able to perform instant transition from one configuration to another. Tiltrotor UAV has advantage to perform takeoff and landing from limited space such as plantation farm, forest, and residential area. Tiltrotor also can carry various mission since it has 2 configuration such as cargo drone, safer payload dropping, and mapping. In this research tiltrotor UAV designed with ruddervator (V-Tail) configuration with 3 motors in total, 2 motors placed on main wing with tilting capability and 1 motor placed at the end of fuselage as pitch controller in VTOL mode. Test flight will be conducted and evaluated to test UAV capability in hovering and transition from one mode to anothe
Conceptual Design of a 10-Seater Electric Aircraft
Get PDFWith the increase in population, an increase of transportation needs is inevitable, especially in air travel. There is an underlying problem in this matter that is carbon pollutions. Air travel contributes around 2% of the global emissions. This paper contains the conceptual design of 10- seater electric aircraft that can serve as a cleaner alternative for air travel. The paper will discuss about our objectives and the results of configurations, backed with calculations of proof in all aspects that is needed. In conclusions, this paper presents a conceptual design of 10-seater electric aircraft that have range more than 450 km. The aircraft being designed has a mid-wing three surface configuration with a MTOW of 7250 k
Æ-6 eLena; Conceptual Design of 6-Seater Electric Aircraft
Get PDFGlobalization has made a huge impact on worldwide interaction and integration in our lives. Traveling between locations, for instance, has become easier with the advancement of transportation modes such as aircraft. However due to the ever-increasing environmental concerns, alternatives of conventional aviation fuels have become necessary in order to provide more eco-friendly flights. Fortunately, alternatives such as aircraft batteries have become feasible with technology improvements, allowing an idea for resolving the issue, namely the development of an electric aircraft. This paper will be focused on designing a six-seater electric aircraft through parametric studies on several aspects such as aircraft configurations, weight and balance, stability, performance, structures, aerodynamics, and cost analysis while also aiming to meeting the given DRO. The designed aircraft, Æ-6 eLena, has a range of 540 km, a takeoff weight of 3003 kg, a cruising speed of 300 km/hr, and a lift-to-drag ratio of 13.5. The conceptual design of this aircraft is intended to be certified under current CASR 23 regulations, with production beginning in 2026
Effects of Transition Strip on Aerodynamic Yaw Derivatives of MULDICON Wing using an Oscillating Rig at Various Angle of Attack
Get PDFThis paper presents the effects of the passive flow control technique using transition strips on the transient aerodynamic stability derivative measured on the MULDICON AVT251 wing. The experiments were performed at two configurations; clean wing configuration and the transition strips attached to wing leading edge. MULDICON wind tunnel model was designed and fabricated in UTM based on the AVT251 design. The dynamic measurements were carried out in the Universiti Teknologi Malaysia Aerolab wind tunnel for Reynolds number of 0.3x106 & 0.475x106. MULDICON model was confined to oscillate with a single degree of freedom in yawing motion. The aerodynamic stability derivatives & are measured as aerodynamic stiffness and damping by extracting the stiffness and damping of the dynamic oscillating rig system. Springs of different stiffness are used to vary the oscillation frequencies with the reduced frequency range of 0.004-0.08. The unsteady aerodynamics effects are examined for both wing configurations. The angle of attack varies from α = 0° to 20° by comparing the transient measurements from the dynamic UTM-LST to the steady-state wind tunnel measurements. The dynamic results indicate that the aerodynamic stiffness derivative is not constant and exceeds the static values and strongly correlates with reduced frequency. The aerodynamic damping derivative is a function of reduced frequency as the damping derivatives become more negative with the increase of the reduced frequency. The amplification factor for the stiffness derivative is above unity which indicates that the steady-state derivative is under-predicted
Preliminary Design of a 6-Seater Electric Aircraft
Get PDFA more sustainable and eco-friendly aircraft is needed for the near future, but current electric aircraft technology (e.g., electric motors and batteries) is still lacking compared to its fossil-fuel- based counterparts. To support the effort for fully electric aircraft maturity, an electric aircraft up to its preliminary design stage is developed using various analytical and software-based analyses with the target of fulfilling a set of design requirements and objectives for a 5000 kg MTOW 6-seater fully electric aircraft. The results of the aircraft preliminary design yield that overall, the aircraft fulfills all the requirements and most of the objectives. The design itself can still be further developed through optimization, re-evaluation, future studies, and upcoming technologies
Load Cell Design for Measurement of Propeller Thrust
Get PDFThe design, analysis, and prototype testing of a load cell for measuring propeller thrust generated by propeller rotation in this study. Design concepts factors of safety, yield strength, stress, and strain values were evaluated using Solidworks simulation to ensure that the load cell would not fail. The force applied to the load cell is measured by four strain gauges connected in a Wheatstone bridge connection and amplified by HX711 amplifier. These instruments is then connected to Arduino and 16x2 LCD. A static testing was carried out to measure the thrust from an APC 6x4E propeller and compared with validated results to validate the accuracy of the load cell. The built-in load cell experimental results were compared to a commercialised load cell, manufacturer data and blade element momentum theory from other studies. A graph of thrust against propeller rotational speed was constructed. The rotational speed that starts to detect the thrust is about 2000RPM. The error between prototype load cell to the manufacturer, RC benchmark and BEMT is less than 1%, 0.05% and 0.05%, respectively
Development of Anti-UAV System Using Visual Artificial Intelligence
Get PDFUnmanned Aerial Vehicles (UAV) was first developed as a tool for military purposes. Due to the rapid growth in technology, UAVs are now used in various applications including civil needs. Of course, there are consequences for this where UAVs can be misused by irresponsible parties. One example is the use of UAVs in airport fields which can disrupt the airport operations and possibly become a serious threat towards security and safety of flights in the airport. This paper will discuss the artificial intelligence (AI) modeling to detect UAVs. This AI modeling is the first step in designing counter unmanned aerial system (C-UAS). UAV detection will use deep learning using YOLOv4 (single-stage detection) for optimal detection speed and accuracy. There are a total of 500 image data processed and used in two AI modeling experiments in this study. Gaussian blur filter is used to create dataset variations so that the training can be processed more efficiently and the model can detect better. The results shows that the training dataset that has been processed with gaussian blur (filtered dataset) increases the AI model’s detection performance in rainy and clear conditions. Therefore, the model trained using filtered datasets is more suitable for use in detecting UAV objects in anti-UAV systems
Fibrin Gel Properties and Gelation Structures for Tissue Engineering Scaffold and Biomedical Engineering Applications
Get PDFFibrin gel is utilized in a wide range of medical applications, such as hemostatic agents, wound healing, drug delivery, cell delivery, cell differentiation, and tissue engineering. Notably, fibrin gel exhibits exceptional extensibility compared to other filamentous biopolymers, capable of stretching over five times its original length without breaking. Remarkably, it can fully recover from elongations exceeding 100% once the applied stress is removed. This paper presents an optimized formulation of fibrinogen and thrombin tailored for culturing human umbilical vein endothelial cells (HUVEC). We explore the mechanical and physical properties of the fibrin gel, aiming to identify ways to enhance its medical applications. The gel is synthesized in vitro through the combination of fibrinogen and thrombin, allowing us to assess how varying the proportions of these components affects the gel structures and propertie
Clustering and BiLSTM Network for Aircraft Trajectory Prediction Model
Get PDFThe increasing demand for air travel requires the development of more accurate aircraft trajectory prediction methods to optimize airspace utilization and enhance safety. This paper presents a hybrid approach for single-flight-route trajectory prediction that employs the K-means clustering and Bidirectional Long Short-Term Memory (BiLSTM) networks. The primary objective is to develop a deep learning model that effectively predicts aircraft trajectories. Additionally, this research investigates the influence of trajectory clustering on prediction accuracy. To fulfill the objectives, a four-step methodology: data preprocessing, model construction, validation testing, and analysis is employed. Real-world historical flight data is used to train the BiLSTM model after being clustered with K-means. The model's performance is evaluated using randomized enroute flight data and various metrics like mean squared error and root mean squared error. This research is successful in accurately predicting the flight and the clustering process was proven to increase prediction accuracy by 15 percent in latitude, and 10 percent in longitude
Conceptual Design of Moon Lander Spacecraft
Get PDFSpace exploration is important for the development of humankind such as for exploiting unlimited resources from the celestial body or making a new colony on outer space. The Moon exploration is chosen because it can be made as a base for outer space exploration. In this study, the main objective is to design a Moon lander spacecraft with a mission to take a photograph of the Indonesian flag with Earth’s globe as the background and transmit it to the ITB ground station. Designing a Moon lander spacecraft involves many engineering fields, such as aerospace, astronautics, electrical, telecommunication, etc. In this study, the design process is based on the DRO and consists of trajectory analysis, landing site and scenario, determination of launch vehicle, subsystems analysis, and cost analysis. The subsystems are limited to propulsion, payload, power, communication, and structure. The design generates a 500-kg Moon cargo lander spacecraft with a landing site on 28° latitude. The mission will take 6 days to reach the low lunar orbit of the Moon. The propulsion analysis shows that the propellant needed is 200 kg N2O4/UDMH. The resolution of the Earth’s globe is 134.3 arcseconds/pixel. The power system can provide power for 5.69 years. The spacecraft also provides 3 links to communicate between the spacecraft on the Moon and the ITB ground station. The structure’s minimum factor of safety is 1.6 with its first natural frequency in the launch vehicle being 63.66 Hz. The spacecraft’s expected cost is 220M USD. The results show that the Moon lander spacecraft can conduct such a mission based on the DRO. However, the payload subsystem needs to be re-evaluated