In this study, İSTECOPTER was
modeled, performance evaluations were made and control system was designed .
For the control system, lateral, longitudinal and vertical take-off of the UAV
(Unmanned Aerial Vehicle) and the separate mathematical model of the descent
operations were extracted and expressed as the state space model. The
mathematical model of the wind distortions that will affect the aircraft during
the flight was created and the situation was added to the space model.
Proportional Integral Derivative (PID) control algorithm was used as a control.
The unmanned aircraft was modeled in Solidworks and the simulations in Matlab /
Simulink program. the İSTECOPTER is planned to have 4 brushless DC motors and
has a weight of approximately 1.5 kg without load and 1 kg of payload is
planned. It is planned to enter the TUBITAK rotary wing UAV competition with
istecopter which we intend to design and produce.
Birincil Dil | İngilizce |
---|---|
Konular | Uzay Mühendisliği |
Bölüm | Araştırma Makaleleri |
Yazarlar | |
Yayımlanma Tarihi | 23 Haziran 2019 |
Gönderilme Tarihi | 13 Mayıs 2019 |
Kabul Tarihi | 24 Haziran 2019 |
Yayımlandığı Sayı | Yıl 2019 |
Journal of Aviation - JAV |
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