ANALISIS KEGAGALAN UJI TERBANG CRUISE KE HOVER PADA
UAV FLYING WING KIT GLIDER 525
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
Christine Wenno, Ardelia
Subject
T Technology (General)
Datestamp
2024-02-27 02:59:33
Abstract :
In this modern era, the Vertical Take-Off and Landing (VTOL) system is one of the exciting innovations. It is in demand to improve the performance of Unmanned Aerial Vehicle (UAV) to be more optimal even if they have to carry out flying missions on minimal runways. In the implementation process, the UAV often encountered problems during test flights. In this study, the authors wanted to diagnose a problem with the Glider 525 flying wing kit with a VTOL tailsitter system which experienced a stall during the flight test. To have the capacity to diagnose the problem, read the data flash logs contained in the flight control memory. The data flash logs obtained are flight data when the UAV conducts a test flight in open space for approximately 1 minute and 8 seconds. In the process of testing the VTOL system, the vehicle has 4 flight modes. The take-off test flight begins when the UAV is in hover mode, then transitions from hover to cruise and fly level. After flying level in cruise mode, the rides return to the cruise to hover transition. The occurrence of a stall during the VTOL flight test took place due to the detection of mechanical failure due to failure to deactivate one of the parameters, so that the throttle was reduced during nose-up and made the UAV fly even further. This is also influenced by the shape of the control surface on the fuselage. On a VTOL tailsitter, the control surface scales directly with the throttle. A high throttle will result in less movement of the control surfaces, while a low throttle will result in more action.
In this modern era, the Vertical Take-Off and Landing (VTOL) system is one of the exciting innovations. It is in demand to improve the performance of Unmanned Aerial Vehicle (UAV) to be more optimal even if they have to carry out flying missions on minimal runways. In the implementation process, the UAV often encountered problems during test flights. In this study, the authors wanted to diagnose a problem with the Glider 525 flying wing kit with a VTOL tailsitter system which experienced a stall during the flight test. To have the capacity to diagnose the problem, read the data flash logs contained in the flight control memory. The data flash logs obtained are flight data when the UAV conducts a test flight in open space for approximately 1 minute and 8 seconds. In the process of testing the VTOL system, the vehicle has 4 flight modes. The take-off test flight begins when the UAV is in hover mode, then transitions from hover to cruise and fly level. After flying level in cruise mode, the rides return to the cruise to hover transition. The occurrence of a stall during the VTOL flight test took place due to the detection of mechanical failure due to failure to deactivate one of the parameters, so that the throttle was reduced during nose-up and made the UAV fly even further. This is also influenced by the shape of the control surface on the fuselage. On a VTOL tailsitter, the control surface scales directly with the throttle. A high throttle will result in less movement of the control surfaces, while a low throttle will result in more action.
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