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The International Conference on Aerospace and Aviation (ICASA 2018) was organized by and held at Institut Teknologi Bandung, Indonesia on October 23^rd – 25^th 2018. Highlighting on the current growth in aerospace field and aviation in South East Asia, ICASA 2018 conference themes was taken to be "Aerospace and Aviation for Regional Sustainable Development".

ICASA 2018 accomplished as a forum to exchange and to discuss information in the most advanced scientific fields related to aerospace and aviation and in recent cutting-edge technologies among participants from the world's academia, industries, and governments. The Conference also provides a platform for collaborations among professional societies and to enhance technical exchanges among participants.

We are committed on increasing the quality of the papers through a fruitful peer-review based on the originality, impact, novelty, and the relevance to the area of the conference. The published papers were selected from ICASA 2018 presented paper.

The committee would like to thank you all distinguished keynote speakers, authors, and reviewers for their contribution that have made this conference a forum of exchange, enlightening and network. Also, for all steering committee and organizing committee member and staff that plan and make the conference possible. In addition, ICASA 2018 is launched in a good collaboration with Faculty of Engineering, Universitas Lampung and Java Scientific Academy, Indonesia. We do hope that you would find this publication as an enjoyable and useful guide and reference.

Editorial board:

Taufiq Mulyanto, Faculty of Mechanical and Aerospace Engineering, Institut Teknologi Bandung Indonesia

Irza Sukmana, Faculty of Engineering, Universitas Lampung, Indonesia

Khairul Ummah, Faculty of Mechanical and Aerospace Engineering, Institut Teknologi Bandung Indonesia

All papers published in this volume of IOP Conference Series: Materials Science and Engineering have been peer reviewed through processes administered by the proceedings Editors. Reviews were conducted by expert referees to the professional and scientific standards expected of a proceedings journal published by IOP Publishing.

The use of star sensor, which is the most accurate attitude sensor on satellites, began to penetrate into micro satellites and nano satellites. Thus the need arises to research and develop star sensor independently to meet the specific design of micro satellites and nano satellites. There are mainly two aspects to be considered in star sensor: hardware and software (algorithm). Star sensor's algorithm is also known as star pattern recognition algorithm. This paper deals with development of star pattern recognition algorithm using ${C}_{3}^{n}$ combination of triangles pattern, that is when there are n stars to be used to do pattern recognition, then ${C}_{3}^{n}$ combination of triangles pattern would be generated. Success rate test are conducted in digital simulation approach using various number of stars that be used to do pattern recognition and various of star image resolution to test its robustness against star spot centroiding error. Results show that this algorithm has high level of success rate even on low resolution of star image, but has increased processing time when more stars are used to do pattern recognition.

In crime and falsification related to documents are often difficult to verify orauthenticated by the authorities. This is the basis of research to develop a system in assisting digital forensics to investigate and seek the truth of the evidence in the form of digital handwritten documents. The steps that being taken by researchers are collecting and digitizing the documents into image form, converting color from RGB to greyscale, separate the object through thresholding, color histogram, uniform quantization from 256 to 128 of greylevel, texture feature extraction ie variance, skew, relative smoothness, entropy and mean, normalize the feature value and similarity measures through Euclidean distance calculations. From the results of testing of 10 data that has been matched with 20 training data, 6 documents successfully recognized correctly the authenticity of the document owner. Thus, the system in this study produces an accuracy of 60% and can be used to assist digital forensics in analyzing the authenticity of handwritten documents.

The air traffic density at the Terminal Control Area can lead to several problems related to the safety and efficiency of flight operation if not adequately managed. These problems include the increased risk of crashes between aircraft, airborne and ground delays, waste of fuel and environmental problems caused by gas emission and noise. One of the analysis tools to solve these problems is the hybrid simulation model. The socio technic characteristics of the system can be observed more intact using a hybrid simulation model so that the results of the analysis more precise and comprehensive. This article describes the research framework and progress on the development of the hybrid simulation model of an ATM system in the Terminal Control Area. The final model will integrate of agent-based simulation, discrete event simulation, and system dynamics models. An agent-based simulation model that defines the movement of aircraft in the Terminal Control Area has been developed in this early research phase. The initial model can describe the rules for minimum separation between aircraft that are applied to ensure the safety of flight operations. The following aircraft will reduce its speed so that an adequate separation distance is obtained with the aircraft in front of it. The model then will be improved by integrating a discrete event simulation and system dynamics models on the initial model to obtain a complete hybrid simulation model.

Chamber with the controlled temperature is required in the energy efficiency test of a household product. Chamber wall plays an important role to keep the temperature inside the chamber so as not to be affected by the temperature from outside. Experiments were carried out to compare the thermal performance of two different material for chamber wall : 1) Acrylic and 2) expanded polystyrene. The boxes with dimension 40 x 40 x 40 cm were affected with fixed thermal loads in a climatic chamber. Meanwhile, temperature inside the box was monitored with data logger. The thermal loads for testing were 40°C, and 60°C. Based on the measurement, temperature in the acrylic box reach the load temperature from the outside and starts steady at 300 seconds, while the expanded polystyrene at 550 seconds. The result show that the insulating performance of expanded polystyrene is better than acrylic. The result of this study can be used not only for refrigerator manufacture, it can also use by another industry related to thermal dynamic. The industries include aeronautic industry related to aircraft wall coatings for external temperature protection, building industry in terms of building wall coatings to maintain temperature stability, and other related industries.

Sailplaning or gliding is one branch of aero sports activities in Indonesia under Federation of Aero Sport Indonesia (FASI). Until now, the most common sailplane used in Indonesia is still Schweitzer SGS 1-26, which is a single seated metal-fabric sailplane designed in 1955 and produced until 1979. The development of a new national glider to replace the Schweitzer SGS 1-26 had been conducted since 2013 and resulted in a design named GL-1. The EASA CS-22 had been chosen as certification basis for GL-1 as there is no equivalent yet in Indonesian CASR. A preliminary design of internal cockpit arrangement and control mechanism has been conducted. This study shows that the control mechanism using a combination of cable and push-pull rod arrangement satisfy the required control surface movement and limited sailplane interior space.

Glider GL-1 is designed as a national glider of Indonesia for aero sport gliding activity and fall into category of 15 meters class by FAI (world's air sport federation). In preliminary design phase, design requirements are derived from thermal updraft condition of Indonesia which lead to maximum rate of descent of 3 m/s and maximum turning radius of 150 m. GL-1 has wing area of 12 m² and wing aspect ratio of 17. Wing span of GL-1 is 14.283 m with length of fuselage is 6.795 m. Performance study in preliminary design gives two optimum flight conditions for GL-1 to glide, which is maximum range condition and maximum endurance condition. In maximum range condition, with maximum aerodynamics efficiency between 24 to 30, GL-1 has a velocity of 20 – 25 m/s with density of 1.225 kg/m3. In maximum endurance condition, GL-1 has a velocity of 17 – 20 m/s with the same density and minimum rate of descent between 0.66 – 1.1 m/s. Reynolds number is between 1 – 1.5 million. This paper present CFD simulation result for both optimum flight conditions predicted in preliminary design that carried out at velocity of 25 m/s for maximum range condition and 17.5 m/s for maximum endurance condition. By using full-glider meshing with total element of about 11 million, a maximum aerodynamics efficiency of 21 is obtained for maximum range condition with lift coefficient of 0.91. While minimum rate of descent for maximum endurance condition of 0.87 m/s is obtained.

The test results of the removed aircraft components are classified into No Fault Found (NFF), Real Reason Conform (RRC) and Other Defect Found (ODF). Corrective actions will be taken on findings that are classified as RRC and ODF, while for the NFF category no action will be taken. In the MRO XYZ, for the NFF category, the age of the component during the removal is included into the failure data. Moreover, the reliability calculation in the MRO XYZ uses the 2-parameters Weibull distribution. These will result in unrepresentative reliability calculation. Therefore, it is necessary to evaluate the method. The research compares the results of the reliability calculation between the 2-parameters and the 3-parameters Weibull distributions by applying them to several part numbers data. Furthermore, the reliability calculation using the 3-parameters Weibull is also applied to the data where the NFF category is not included the failure data. The location parameter, γ, is calculated using the Muralidhar method. The research also develops an excel VBA macro-based tool for reliability calculation. The results of the reliability calculation show that there is a significant difference of the failure rate between using the 2-parameters and the 3-parameters Weibull distribution. The failure rate calculated by using the 3-parameters Weibull distribution for the data where NFF category is not included into the failure data show a significant different as compared to the method used by the MRO XYZ, where the difference is affected by the percentage of NFF items in the failure data.

Most aviation related academic programs in Malaysia were designed centred around the aerospace engineering and aircraft engineering technologies. However, the emergence of Industry 4.0 demands aviation talents especially the non-management aviation practitioners such as aircraft engineers and other technical personnel to equip themselves with certain management-related skills. Hence, there is a pressing need for an advanced industry-driven and practitioners-based academic program in aviation management suits for various categories of aviation practitioners. The aims of this study are to explore the employability prospective of aviation managers (first stage); to examine the Industry 4.0-related management skills needed by aviation companies (second stage); and to analyse the personal development intention of individual practitioners (third stage). This study employed multistage-multilevel analysis on a single-case market study in a Malaysian aviation technical training university. Findings from this study are segregated into three levels. At the industry level, it is concluded that there is a brighter employability prospect of aviation managers at least until 2030. At the organizational level, there is an urgent need for the aviation professionals to upgrade themselves with managerial skills relevant to the Industry 4.0 such as data driven scenario planning, big data analysis, and collaborative decision making. At the individual practitioner's level, finding indicates that there is an increasing awareness among the individual aviation professional in particular the technical and engineering professional to engage in personal development in aviation management at postgraduate level. The key contribution of this case study is that, through multistages and multilevels analysis, it not only expands the robustness of the market study on new postgraduate program development but also able to incorporate the perspectives of different aviation stakeholders group i.e. the aviation industry, aviation organizations, and individual aviation talents. This multistage-multilevel model can facilitate university's policy makers to design future industry-based and practitioners-driven development program meant for industry practitioners.

This Annular combustion Chamber is designed for micro turbo jet engine. Combustion chamber is positioned in between compressor and turbine of turbojet. Combustion chamber is designed to increase enthalpy without significant pressure loss. Existing combustion chamber is designed by conventional method of trial and error. To further increase its performance then a optimization is needed. The geometry of the combustion chamber is optimized to maximized efficiency, minimized Pattern Factor, minimized pressure loss and lower temperature on the combustion wall. Varying Parameter is chosen based on Sensitivity Analysis with Spearman Correlation method to choose influential changes on geometry. After sampling process with Latin Hypercube Sampling (LHS) method and followed by interpolation with Kriging method, the combustion chamber then optimized using Multi Objective Genetic-Algorithm (MOGA). Performance of the combustion chamber then evaluated by numerical simulation. The combustion chamber will be chosen if it fulfilled pressure loss and temperature on wall criteria. Final design give better performance with a little increase in efficiency and good Pattern Factor.

Knowledge enhancement is essential to support continuous sustainability of organization in a competitive environment. It is not an exception to an aviation industry. In facing up with future challenges of industrial revolution 4.0 (IR 4.0), studies have shown that one of the issues addressed in ensuring it success is the importance of knowledge among employees. Various activities can be done to enhance knowledge such as by enrolling to academic (undergraduate or postgraduate) programs, attending short courses/training or sitting for professional certification. Furthermore, obtaining postgraduate degrees offers wide exposure to academic and industry environment. Therefore, the purpose of this study is to gauge the understanding on practitioners' key reasons to further their education at the postgraduate level. Four major constructs established for this study to analyse the aviation practitioners' intention to further study that are personal needs for continuing education, organization needs, source of funding and teaching and learning facilities. Document review were conducted at the beginning of the study to explore fundamental issues of knowledge enhancement needs among practitioners, meanwhile survey performed were analysed by using Fuzzy Delphi method (FDM). Findings shows that six elements (items) for the whole survey fulfil the criteria of threshold value (d construct) less than 0.2 and achieved the percentage of expert group consensus more than 75%. This research provides objective and constructive input to university on the major factors influencing aviation practitioner's decision to further their study at the postgraduate level. The finding becomes avenues for university to draft a better postgraduate program to fulfil the requirement of industry and academic.

Springback is a critical phenomenon in design and analysis of sheet metal forming process of metallic sheets. An accurate prediction of elastic recovery of material allows to design forming tools which take into account springback compensation. Springback is influenced by many factors including mechanical properties of material, friction conditions, temperature and geometry of bending die. In this paper, the investigations are focused on the analysis of an intelligent air bending process using an artificial neural network (ANN). The air bending experiments were carried out in a designed semi closed 90° V-shaped die. The tests were conducted on three grades of sheet metals: aluminium 1070, brass CuZn37 and deep-drawing quality steel sheet DC04. The results of experimental tests were used as a training set for back-propagation learning of a multilayer artificial network built in Statistica Neural Network program. For all materials tested, an increase of the springback coefficient is observed when the bend angle increases. The results of neural prediction are in a good agreement with the experiments. The correlation coefficient of ANN prediction to the experimental results is equal to about 0.99.

The application of PID to perform position control in the presence of Stribeck friction is believed to provoke the system trapped in limit cycle oscillation. This research aims to investigates the formulation of PID that will stabilize the position control of DC motor in the presence of Stribeck friction. In order to diminish the limit cycle oscillation, the PID gain is set to meet global asymptotic stability in Lyapunov sense as Kalman conjecture is fully applied. The analysis shows that the stability of the system depends on the friction properties near Stribeck velocity. Furthermore, the proposed PID formulation is found to be easy to be applied as the maximum integrator gain applied to the system is directly proportional to the given proportional gain.

Nowadays, awareness of global society to the green concept where life should be in harmony with nature has been increasing. One of the ideas in the green concept is to reduce excessive sound exposures or noise. Within this context, gas turbine GTS 22 engine is one of mechanical system that generates a very high sound pressure level. Hence, it is instructive to develop noise controls for the gas turbine in order to have acceptable sound pressure level. This research is focused on the design of muffler as noise control treatment after carefully analyzing the dominant noise spectrum of the gas turbine. In this paper, numerical approach is employed to design the muffler. The results are then validated by experimental ones. Moreover, noise reduction (NR) is used to assess the muffler performances. The design of muffler in this research contains all of combination treatment: area cross section expansion chamber, perforated system (micro perforated panel), porous material, partition chamber and concentric tube. The chosen final design of muffler is combination treatment design where NR 38.77 dB is present. This NR leads to sound pressure level of 80.82 dB or 68.95 dBA exist after the muffler applied on the exhaust of gas turbine. The deviation of experimental results compared to numerical ones is 7.14% in average. Moreover, the pressure drop (ΔP) of the muffler is only 0.4042% which is acceptable to keep the mechanical performance.

Remotely Operated Vehicle (ROV) is a small marine craft used for underwater observation. Hence, the analysis of hydrodynamic characteristics is important. Hydrodynamic characteristics can be obtained by fluid dynamic visualization and simulation of Computational Fluid Dynamic (CFD). In this paper, ROV Hydrodynamic characteristics begin by forming a three-dimensional (3D) ROV model, forming link elements (mesh) from the 3D ROV model, and forming the computational domain used for CFD simulations. CFD simulations were conducted by analyzing the fluid flow angle variations that represent motion of the ROV, namely translational motion and rotational motion towards the vertical axis (yaw). The simulation results obtained were compared with the previous ROV design that had been developed, so as to obtain an evaluation of the results of the design optimization. The results showed an increase in the hydrodynamic characteristics of the optimal ROV design indicated by the value of drag, pressure distribution, and fluid flow contour.

Propulsion system development involved aircraft manufacturer and engine or propeller manufacturer to perform test and evaluation. The main of this research was propulsion testing for unmanned aerial vehicle by evaluating thrust in static condition. Static thrust testing was conducted by force measurement using load cell and data acquisition systems. Thrust measurement result was compared with analytical method and computer fluid dynamic simulation. Analytical method in this paper used vortex blade element theory to calculated static thrust meanwhile Computational fluid dynamic was running both 2 dimension and 3 dimension simulation. Vortex blade element theory analysis combined with computational flight dynamic simulation for propeller aerofoil at 70% location. Test result compared with analytical and CFD calculation using non dimensional parameter. Analytical calculation deviated 5.08% from experiment meanwhile CFD calculation give 13.56% but still in error tolerances. Error tolerances considered from friction force, sensor accuracy and air density correction with total 6.33 kgf.

This paper reports a design of flight control system mechanism which will be implemented in the national glider GL-1. The flight control system in the glider GL-1 includes the following control surfaces: elevator, ailerons, and rudder for primary flight control system as well as flaps and airbrakes for secondary one. In designing the components of flight control system, selections of type, material, and dimension of components are based on loads computation as well as benchmarking to some modern gliders. Mechanism and kinematics of flight control system are designed to comply with regulation as well as space availability. Fully-mechanical flight control system is selected for the aircraft since the aerodynamic forces acting on the glider are not excessive. The aircraft uses a centre-stick as manipulator for pilot to control longitudinal and lateral movements, which is linked to elevator and ailerons by push-pull rods with coupled mechanism. Meanwhile, for directional control, an adjustable pedal is used. The pedal is linked to the rudder by tension cables. Plain flaps and flat-plat panel airbrakes are selected as flap and airbrake types in this glider. The flaps and airbrakes are controlled by mechanical levers, which are linked by push-pull rods.

A set of performance analysis was performed on Master Airscrew 10X7 Electric propeller. The airfoil geometry was extracted by cutting and scanning a number of blade cross-sections. Experimentally, the test was performed at Institut Teknologi Bandung using 40 cm x 40 cm rectangular test section wind tunnel. The experimental rig was built using 3 load cells designed to measure thrust and torque. For data comparison, theoretical and numerical analysis were also done using Momentum-Blade Element method and Computational Fluid Dynamics. Compared with the previous study, the experimental data shows good agreement with most of the reference data. The theoretical data overestimated the thrust value by around 20% and underestimated the torque value by 30% at max, but the performance curve follows the similar trend with the experimental data. Both the thrust and torque value of the numerical data shows better agreement when fitted to experimental data by around 10%. While it may need more propeller samples analyzed to draw general conclusion, the three methods performed in this research showed analogous results and could be used for a particular stage of research depending on the level of accuracy needed.

One of important aspect in designing a good quality product is on the method of how to manufacture it. In the world of aviation, products are required to meet several design criteria namely, strength, weight, and cost. Based on these design criteria, a study was carried out to manufacture LSU-03 propeller product sample using two manufacturing methods, i.e. hand lay-up and vacuum assisted resin transfer molding (VARTM). The objective is to design the manufacturing processes and to compare the quality of the propellers. The material used in this study are E-glass fiber cloth 135 and Epoxy "Lycal" resin. Prior to the propeller manufacturing process, several testing based on ASTM of manufactured composite plate was carried out to determine important parameters, i.e. thickness distribution, fiber volume fraction and voids content. A total of 3 propellers were manufactured. In order to determine the conformity of the product, propeller geometry is then measured and compared to the design mold. Finally, the comparison of the quality was made between the products of two methods. The quality of propeller products is measured based on calculated mass, thickness, void, fiber volume fraction, cost, surface quality and geometry conformity. It was concluded that VARTM is better than standard HLU and therefore more suitable for LSU-03 aircraft propeller production.

UCAV as one of the UAV application needs to have good maneuverability to be able to carry out missions. For this reason, an Automatic Flight Control System (AFCS) is needed to facilitate the operator in controlling the maneuvering motion. This study aims to design an automatic flight control system that is able to track the given maneuver control commands so that the aircraft can maneuver according to the control command. First, an analysis of the open loop system is conducted to determine the characteristics of the UCAV to be controlled. The stability augmentation system is then designed to improve the dynamic stability characteristics of UCAV. Finally, a command augmentation system is created that uses the tracking controller principle. This principle aims to track control commands (attitude and flight path variables to control maneuvers) so that the aircraft is able to maneuver according to the given control command. The simulation results show that the automatic flight control system that is being made has been successful in tracking the maneuver control command with the optimal method.

UCAV (Unmanned Combat Aerial Vehicle) is a unmanned flying vehicle designed to carry out combat missions by carrying weapons. In the UCAV mission profile there is usually a cruise mission. In this cruise phase the vehicle must have a good control system and control altitude. In this paper, the UCAV altitude control system is designed to use the TECS (Total Energy Control System). TECS coordinates changes in speed and change in altitude by considering the total energy contained in the flying vehicle. The UCAV dynamic model that is used as the basis of the development is the fixed wing UCAV model which is equivalent to one of the UCAVs that are currently operating. As a comparison, a conventional control system (speed hold system and altitude hold system) was developed. The results showed that the altitude control system with TECS can adjust flight altitude and speed in a more coordinated manner, so that there is no change in the drastic and sudden variable values of flying when maneuvering. change in height begins.

In the past few years, the usage of Unmanned Aerial Vehicles (UAVs) aircraft has increased significantly, but the need for UAVs with higher performance is increasing also. Therefore, all systems of the UAVs must be developed to have high efficiency, including the propulsion system. It is necessary to perform some design and analysis tasks on low Reynolds number propeller, which is a commonly used propulsion system on UAVs, to have higher efficiency and improve the overall UAVs performance. In this paper, low Reynolds number propellers are designed using the Larrabee Design analytical method by referring to the "Master AirScrew 10x7E" propeller. Meanwhile, performance of the designed propellers is analysed by using analytical method of Inversing Larrabee Design method. At the design stage of low Reynolds number propeller, 42 variations of alpha design (α_des) was inputted along the blades with uniform, linear, and quadratic distributions. Furthermore, the best design from these 42 variations was selected by performing two-stage scoring. At first stage scoring, 42 designs are selected to obtain 5 designs with the highest on-design efficiency. Then, performance of these 5 selected designs are analysed analytically along a certain range of advance ratio. Finally, second stage scoring is performed to obtain 1 design with the best overall performance.

Aviation industry growth has increased continuously over the years. Air transport demand continues to increase due to the reliability, time saving and efficiency. Aviation industry has impact on environment as a source of pollutant emissions. The estimation of pollutant emissions at taxi/idle, approach, climb out and take off of Carbon dioxide (CO₂) and Nitrogen dioxide (NO_x) at Juanda International Airport Indonesia was calculated using Advanced ICAO landing and take-off (LTO) cycle method. The CO₂ emissions were 23.02 tons, 10.52 tons, 17.27 tons and 6.73 tons during taxi/idle, approach, climb out, take off respectively while NOx emissions were 0.03 tons, 0.03 tons, 0.12 tons and 0.06 tons for taxi/idle, approach, climb out and take-off respectively. Based on the results of the discussion it can be concluded that pollutant emissions and fuel consumption are positively related to amount of flight operation. The aircraft emissions affect the air quality around the vicinity of airport and lead to climate change.

A Friction is inevitable in a hydraulic actuator due to the presence of seal. Unfortunately, the existence of friction makes the system prone to limit cycle oscillation as PI controller is applied. This research investigates the maximum integrator constant of PI controller that can be introduced to the system while maintaining global asymptotic stability in Lyapunov sense. This condition is achieved as the system complies with circle criterion. In this research, a simplified hydraulic system which behaves linearly is adopted. Thus, the only source of nonlinearity is the Stribeck friction. The main contribution of this research is a formulation of stable PI strategy that is free from the effect of inertia. The PI strategy is suitable for a hydraulic testing machine of which the mass of device under the test is varying.