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International Journal of Aviation Science and Engineering
Published by Institut Teknologi Bandung
ISSN : 27215342     EISSN : 27156958     DOI : https://doi.org/10.47355/avia.v1i1.6
Core Subject : Engineering,
Aerospace Engineering Automotive Engineering Electrical & Electronics Engineering Mechanical Engineering Transportation
AVIA : International Journal of Aviation Science and Engineering is published by Faculty of Mechanical and Aerospace Engineering, FTMD Institut Teknologi Bandung, Indonesia - in cooperation with Faculty of Engineering, Universitas Lampung and Java Scientific Academy, Indonesia. International Journal of Aviation Science and Engineering aims to publish original research articles and critical review manuscript in the field of Aviation Science and Engineering as well as Aerospace and applied Mechanical Engineering. The topics are including, but limited to: aviation sciences and technology, aerospace engineering, aeronautics, defense system and engineering, safety and energy, mechanical engineering, aeronautics education and training, interdisciplinary engineering and applied sciences.
Arjuna Subject : Teknik (semua kategori) - Teknik Ruang Angkasa
Articles 66 Documents
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Fibrin Gel Properties and Gelation Structures for Tissue Engineering Scaffold and Biomedical Engineering Applications Vadival, G N; Sukmana, Irza; Risano, A Yudi Eka; Sugiri, Agus; Hamdani, Fadil
International Journal of Aviation Science and Engineering - AVIA Vol. 5 No. 1: (June 2023)
Publisher : FTMD Institut Teknologi Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.47355/avia.v5i1.85

Abstract

Fibrin 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 properties
The Role Of Flight Test Data Analysis In Development Flight Testing Khasyofi, M
International Journal of Aviation Science and Engineering - AVIA Vol. 5 No. 2: (December,2023)
Publisher : FTMD Institut Teknologi Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.47355/avia.v5i2.86

Abstract

Flight test purposes is to evaluate aircraft design and performance. Nature of flight test are hazardous and expensive so that it have to be planned well to ensure safety and effectiveness of the mission. Any data obtained from flight test must be utilized to get comprehensive evaluation of the aircraft characteristic. Flight test data play central role in aircraft development. As part of flight test team and flight test program, data analysis support aircraft designer to evaluate flight test data, data reduction, and determine the quality of flight test data. This paper described flight test data processing and flight test data analysis role duringflight test program from industry perspective. Flight test activity or flight test program start with the purpose whether for experimental, development and certification or production. Flight test program activity can be divided 3 phase: flight planning and preparation, flight test execution and flight test reporting. During flight test execution and flight test reporting, test data have to be process, distribute, and use properly. Data from aircraft and flight instrumentation wereprocess from raw data format to engineering unit. Data noise and error during flight test influenced by atmosphere condition, instrumentation, experience etc. Using several method in data reduction process, this error could be minimized as possible. Technology information make data processing and analysis process faster and more efficient. Some example in this paper came from industrial perspective during development new type design aircraft in IndonesianAerospace. Case example from this paper based on experiences during development and certification N219. For other aircraft case it may be more complicated or simple. Development of technology such as computation, electronic, and communication bring new method in data analysis. As digital technology increase amount of data and sensor capability to produce highresolution data make big data analytic should be considered as solution to improving data analytic capability in flight testing. 
Analysis of Star Catalog Model Based on The Nearest Star Composition and Brightest Star as Guide Star Ramadhana, Alif; Saifudin, M A; Poetro, Ridanto E; Fathurahim, L
International Journal of Aviation Science and Engineering - AVIA Vol. 6 No. 1: (June, 2024)
Publisher : FTMD Institut Teknologi Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.47355/avia.v6i1.88

Abstract

Star sensor is the most advanced attitude determining instrument for spacecraft with very high accuracy, and it is independent of other attitude sensors. However, the star sensor's accuracy and processing time depend on selecting the algorithm, which starts from detecting the star pattern until the matching process with the star catalog. The star catalog consists of the right ascension and declination of stars' position and magnitude for 250.000 stars which need a large memory size. Therefore, modifying a new star catalog consisting of guide stars' position,magnitude, and nearest star composition can reduce the required memory and processing time without losing accuracy. T he nearest star catalog model in this paper used radial based featurewhere for each guide star candidate, the number of stars in each binary (bin) layer around the guide star will be calculated. This paper focuses on determining the best architecture for the nearest star catalog model, such as the number of bin layers and bin ranges, and the influence ofstar sensor field of view and guide star limitation with the model's accuracy. The proposed star catalog provides excellent performance in low-cost star sensors with a high and medium field of view.
Clustering and BiLSTM Network for Aircraft Trajectory Prediction Model Sembiring, Javen; Fauzan, M Ariq; Ummah, Khairul; Hamdani, Fadil; Djuansjah, Joy R P
International Journal of Aviation Science and Engineering - AVIA Vol. 5 No. 2: (December,2023)
Publisher : FTMD Institut Teknologi Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.47355/avia.v5i2.89

Abstract

The 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 kevin, alexander; Ramadhana, A; Pardede, D C X; Koswara, S F; Abednego, J; Poetro, R E; Fathurrohim, L
International Journal of Aviation Science and Engineering - AVIA Vol. 5 No. 2: (December,2023)
Publisher : FTMD Institut Teknologi Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.47355/avia.v5i2.92

Abstract

Space 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.
Preliminary Design of a 6-Seater Electric Aircraft Chandra, C; Khan, M; Putri, T; Alexsoh, W; Moelyadi, M A; Amalia, E
International Journal of Aviation Science and Engineering - AVIA Vol. 5 No. 2: (December,2023)
Publisher : FTMD Institut Teknologi Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.47355/avia.v5i2.93

Abstract

A 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.
Conceptual Design of a 10-Seater Electric Aircraft Marcell, A; Limor, F; Humairah, J F; Baniz, M D T Z; Mulyanto, Taufiq
International Journal of Aviation Science and Engineering - AVIA Vol. 5 No. 2: (December,2023)
Publisher : FTMD Institut Teknologi Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.47355/avia.v5i2.94

Abstract

With 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 kg
Æ-6 eLena; Conceptual Design of 6-Seater Electric Aircraft Aini, F N; Prastawa, H; Permana, J I; Dara, K; Ummah, K; Arief, Yanuar Zulardiansyah
International Journal of Aviation Science and Engineering - AVIA Vol. 6 No. 1: (June, 2024)
Publisher : FTMD Institut Teknologi Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.47355/avia.v6i1.95

Abstract

Globalization 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.
Load Cell Design for Measurement of Propeller Thrust Rosli, N A N; Wahid, M A; Othman, N; Zain, M Z Md; Ali, W K Wan
International Journal of Aviation Science and Engineering - AVIA Vol. 6 No. 1: (June, 2024)
Publisher : FTMD Institut Teknologi Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.47355/avia.v6i1.96

Abstract

The 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.
Effects of Transition Strip on Aerodynamic Yaw Derivatives of MULDICON Wing using an Oscillating Rig at Various Angle of Attack Haider, Bilal; Mansor, Shuhaimi; Mat, Shabudin; Wan Omar, Wan Zaidi; Nasir, Nazri
International Journal of Aviation Science and Engineering - AVIA Vol. 6 No. 1: (June, 2024)
Publisher : FTMD Institut Teknologi Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.47355/avia.v6i1.97

Abstract

This 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.

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