Asrel Aerospace Research Letters Archive

In this study, the flight data recording system used in today's passenger planes and the connections between the elements that make up the system were investigated. Flight data recording system started to be used in airplanes later, but today it has become a necessity. Accidents in aviation, the cause and manner of which could not be clarified, caused a loss of confidence in the sector. In order to learn the cause of the accidents, to produce technical solutions, if any, and to reduce commercial costs, international civil aviation authorities have requested the recording of flight data. Flight data loggers were used as simple systems when they were first used on airplanes. In line with the development of technology and needs, it has become complex and has become a system that includes many components. Boeing 737, one of the most used passenger aircraft in the world, was chosen for the study. Although the system to be explained in the study is a Boeing 737 system, since a similar system is used in all passenger aircraft, the information given is generally basic information for all passenger aircraft.

In this study, a low-weight unmanned aerial vehicle design and flow analyzes were carried out. The ability of the aircraft, which can stay in the air for 15 minutes with a cruising speed of 15 m/s and a maximum flight altitude of 1000 meters, can provide the necessary aerodynamic forces has also been supported by OpenVSP analysis. Thanks to these aerodynamic forces, the aircraft has a range of 13.5 km and can perform its mission by displaying a stable flight at all points of this diameter.

The essence of this study is the broadband microstrip that can be integrated into devices, whether it is 4G (LTE) mobile network or WiFi wireless internet connection, at the same time, since today's mobile phones are not ready for 5G infrastructure, during airplane journeys, which have become an indispensable means of transportation in daily life, includes antenna design details and simulation results with High Frequency Structural Simulator (HFSS) program. It is aimed to design a microstrip patch antenna that can communicate with both 4G (LTE) and 2.4GHz WiFi wireless communication bands at the same time, by integrating it into mobile personal devices such as mobile phone, tablet, laptop, etc. The related microstrip patch antenna design was designed with the microstrip feeding method and the material selection was in favor of the FR-4 dielectric material. In order to increase the bandwidth, measurement differences were made on the ground floor of the design. According to the microstrip patch antenna design and simulation results made with the HFSS program; antenna center frequency is 2.57 GHz and S₁₁ value is measured as -24.18 dB. The bandwidth of the system is at 250 MHz. In addition, the antenna gain value is simulated as 3.08 dBm. Due to the large size of the designed antenna gain and broadband, it has been seen that it can be used efficiently in both 4G (LTE) and 2.4 GHz WiFi (between 9-14 channels) wireless communication systems in today's existing mobile phones.

Solid propellant rocket design for air-to-air missiles is the subject of this study. The most important design objective for an air-to-air missile is known to be maneuverability. It is known that there are many design parameters that affect maneuverability, but it is accepted in this study that maneuverability is a parameter related to the propulsion system of the missile, namely the thrust-to-weight ratio. Other design objectives are range and Mach number of flight. The cigarette type fuel core design was chosen for this study. Fuel rod diameter, fuel rod length and combustion chamber pressure were determined as the design parameters that will be effective in achieving these design objectives. The composite fuel type design was deemed appropriate to achieve the design objectives. PBAN/AP/AL, CTPB/AP/AL and HTPB/AP/AL fuel types were determined as design options. Determining the design parameters in line with the design objectives is carried out in this study.  For this purpose, the change of design objectives depending on the design parameters is expressed graphically. The thrust-to-weight ratio is taken as the primary design objective and Mach number and range are taken as the lower priority design objectives. An optimization study was carried out to determine the design parameters that will achieve the design objectives. Meta-heuristic algorithms were selected as the optimization method. To determine the speed design objective, the drag model is obtained from the literature. Depending on this model, the flight Mach number is determined. Rocket materials in the literature are identified and tabulated. Fuel type and material selection are made based on the optimization results in line with the design objectives. Design choices and design parameters are determined by optimization method and conceptual design of solid fuel rocket for air-to-air missile is realized. In line with the studies, a missile with a maximum speed of Mach 4.6 and a range of 12.68 kilometers is designed. The thrust-to-weight ratio of the optimum designed missile is obtained above 16.

The aviation sector is constantly developing and changing with the effect of globalization and technological innovations. Organizations need their employees, who are the most valuable resources, in order to keep up with this change and development, to achieve sustainable competitive advantage and especially to survive. In this context, the concept of organizational support comes to the fore in order for organizations to reach their goals by increasing the motivation, performance, commitment and job satisfaction of their employees. The aim of this study is to examine whether the organizational support perceptions of aviation employees differ according to their demographic characteristics. The data of the research were collected by the survey method with the participation of 410 employees working at İGA Istanbul Airport. The questionnaire consists of two parts, in the first part there are questions about the demographic characteristics of the participants, and in the second part there are questions about the levels of perceived organizational support. “Perceived Organizational Support Scale” was used in the study. Analysis of variance and t-test were used to determine how the organizational support perceptions of aviation employees differ according to their demographic characteristics. According to the findings, employees' perceptions of organizational support differ according to their age, education and marital status, and there is no difference in terms of gender, seniority in the enterprise and total seniority.