Weight reduction of an unmanned aerial vehicle pylon fitting by topology optimization and additive manufacturing with electron beam melting

2021-12-01
The operating altitudeof unmanned aerial vehiclescan be affected by many parameters. Lightening the structural parts to achieve targetaltitudeis one of the design efforts. Weight reductioncan beachieved by converting primary and secondary structures from metallic to carbon composite material. In addition, some secondary structures, such as fittings, have to be produced metallic and usually made ofaluminum alloys. In addition to the weightdisadvantage,aluminum alloyshave galvanic incompatibility with carbon composite materials. At this point, additive manufacturing methods offer solutions with a combination oftopology optimization. Complex geometries obtained from topology optimization can beeasilymanufactured by additive manufacturing methods duringweight reduction campaignsof unmanned aerial vehiclessuch as fittings. In this study, the pylon fitting of an unmanned aerial vehicleis lightenedby the topology optimization method using commercial software with an engineering approach. The resulting complex geometry isproduced as Ti-6Al-4V by the Electron Beam Melting additive manufacturing method. As a result of the campaign, a fitting design that is both lightweight and galvanic compatible with carbon composite primary structures has emerged. In this way, an engineering approach has been developed forweight reduction campaigns
Journal of Additive Manufacturing Technologies

Suggestions

Hovering Control of a Tilt-Wing UAV
Çakır, Hasan; Kurtuluş, Dilek Funda (2019-09-20)
In this study, the design and analysis of hovering controller of an UAV which is capable of doing vertical take-off and landing using the fixed six rotors placed on the tilt-wing and tilt-tail will be explained. The aircraft will have four rotors on the wing and two rotors on the tail. The main wing and horizontal tail will be capable of 90° tilting. Whole flight is separated into three flight modes, which are VTOL, Transition and Forward Flight, to have a robust control on aircraft. Only hover control of t...
Time and state dependent parameterized model reference adaptive control
Okumuş, Zeynep.; Kutay, Ali Türker; Department of Aerospace Engineering (2019)
Unknown external disturbances or nonlinear dynamics, could affect both the stability and the performance of the of the air vehicles adversely. Unavoidable structure of this reality occurrance in real life applications, led the researches to design adaptive control which could eliminate the deficiencies of the nominal controller. So that, the main aim of the total controller, to satisfy the robustness and performance of the controller could be established. Model following controller, and the model reference ...
Static and dynamic aeroelastic analysis of a very light Aircraft
Demirer, Halime Gül; Kayran, Altan; Department of Aerospace Engineering (2021-9-10)
Aircraft design processes need to ensure that the aircraft is aeroelastically stable within its operational envelope. This thesis presents an overview of the static aeroelastic, flutter and gust response analysis of a very light aircraft. MSC.FlightLoads and MSC.Nastran are used for aeroelastic modeling and analysis. The methods to be used in the aeroelastic analysis of the VLA are tested on the AGARD 445.6 wing, and the results are in good agreement with the literature. Aeroelastic model corrections such a...
Static and Dynamic Aeroelastic Analysis of a Very Light Aircraft
Demirer, Halime Gül; Kayran, Altan (2021-09-08)
Aircraft design processes need to ensure that the aircraft will be aeroelastically stable within its operational envelope. This paper presents an overview of the static aeroelastic analysis results, flutter analysis and gust response analysis results of a very light aircraft. MSC.FlightLoads and MSC.Nastran are used for aeroelastic modeling and analysis. Aerodynamic calculations are based on the Doublet-Lattice Method (DLM), the aerodynamic theory employed by Nastran for subsonic flows. DLM requires all lif...
Aerodynamic parameter estimation of a missile in closed loop control and validation with flight data
Aydın, Güneş; Kutay, Ali Türker; Department of Aerospace Engineering (2012)
Aerodynamic parameter estimation from closed loop data has been developed as another research area since control and stability augmentation systems have been mandatory for aircrafts. This thesis focuses on aerodynamic parameter estimation of an air to ground missile from closed loop data using separate surface excitations. A design procedure is proposed for designing separate surface excitations. The effect of excitations signals to the system is also analyzed by examining autopilot disturbance rejection pe...
Citation Formats
F. Yilmaz, M. Şahin, and E. Gürses, “Weight reduction of an unmanned aerial vehicle pylon fitting by topology optimization and additive manufacturing with electron beam melting,” Journal of Additive Manufacturing Technologies, vol. 1, no. 2, pp. 1–5, 2021, Accessed: 00, 2022. [Online]. Available: https://journals.infinite-science.de/index.php/jamtech/article/view/553/299.