Asrel Aerospace Research Letters Archive

In order to gain weight in aerospace vehicles, the tendency to materials with high specific strength has increased. As a result, composite materials quickly took its place in aviation industry and have replaced metals at most points. Studies on impact tests on these composites have gained importance. The time required and the cost to be incurred for the experiments to be performed increase exponentially depending on the number of parameters selected for the experiments. Money and time are saved by performing numerical analysis. In this study, a low velocity impact test was simulated on E-Glass/Epoxy laminates with 6 mm thickness and 50x100 mm dimensions placed in [0, 90, 0, 90, 0, 90] orientation with LS-DYNA software. Impact was applied on the laminates at 2.0, 2.5 and 3.0 m/s velocities with a 12 mm diameter and 30 kg impactor. As a result of the low-speed impact simulation, force-time, acceleration-time, velocity-time and energy-time changes were obtained. These changes were compared among themselves, and the impact behavior of the composite plate was revealed.

In the study, detailed researches were made about Hoshin Kanri, Hoshin
Kanri's history, model and various branches were given, and the relationship between the PDCA Cycle was mentioned. The Hoshin Kanri practice covers the practices of the PDCA cycle, and they benefit from each other in a relationship and exchange. In addition to PDCA, two other simple but effective and valuable applications used in the Hoshin Kanri Method, Cathball and Self-diagnosis, were also included in the study. Hoshin Kanri is associated with many applications and models. The Fair Model is an example of this. The prepared study is an application made on behalf of the aviation industry. With this application, it is thought that Hoshin Kanri will be used more efficiently in the aforementioned sector.

The air drawn from the compressor section to be used in different systems and places in turbojet engines of airplanes is called “bleed air”. In this study, the effect of the bleed air on the engine performance was examined. While the effect of bleed air on engine performance was examined, both the compressor splitting method and the method based on the assumption that all air is removed from the end of the compressor was compared with each other. Additionally, an analytical calculation-based interface was designed. It was aimed that the user could get results quickly and easily carry out the evaluation from the graphs. If it is required, the user can also do component level examination instead of graphical examination. Using the interface created in the MATLAB environment, the relationship of the bleed air with the engine's performance, jet outlet pressure, and specific fuel consumption is presented to the user as graphical and component-level information on the Mach number, altitude, and compressor compression ratio determined by the user. If the results from both methods were compared with the literature, it was determined that the maximum error rate was approximately 1.1%. It has been observed that as the amount of bleed air removed from the compressor increases, the engine's performance and the outlet pressure decrease, while the specific fuel consumption increases.

Simulation tools offer many advantages to their users, such as avoiding large costs before the production and/or management of a real system, performing R&D work with rapid prototyping, and providing unlimited testing in different scenarios. In this study, a flight from Istanbul to Cairo was planned within the scope of flight mechanics using the MATLAB/Simulink simulation environment. Before the calculations of the flight plan, Euler's differential equation solver method (ode1) and its use in the simulation tool are mentioned. Then, by talking about the variables of the aircraft (horizontal position on the X and Y axes, altitude, true airspeed, head angle, mass of the aircraft), control signals (engine thrust, yaw angle, flight path angle), air traffic rules and the route of a real aircraft, the simulation tool will be used. Scope is revealed. After specifying the scope of the study, the flight route and movement changes such as takeoff, climb, cruise flight, turn, and landing on this route are indicated by using the aircraft performance operational data of a real Boeing 737-700 aircraft from Istanbul Airport (IST) to Cairo Airport (CAI). During the simulation phase of the entire flight, the variables, 3D route, horizontal velocity, fuel consumption, change of the aircraft's route etc. data such as visualization and interpretation. In the last part, together with the results obtained, the benefits of simulation tools in flight mechanics are mentioned.

With the development of technology from the past to the present, confidence in the aviation sector has increased. This confidence has led to rise in the demands on aviation activities year by year. In such a case, the airports needed for the applying of aviation activities have become much more important. Due to the capacity problem of airports and the significant increase in demand from year to year, the parking demand required by amphibious, training and private jet aircraft at the airport cannot be met during periods of increased tourism activities such as summer months. Although the construction of a new airport is considered as an alternative solution to this problem, this alternative is often not applicable due to the high need for financing and terrain. This study presents a different design that requires less cost and less terrain to solve this problem.