#TITLE_ALTERNATIVE#

• Main Author: PARAMA ARYOPUTRO (NIM : 13104030); Pembimbing Utama : Prof. Dr. Ir. Muljowidodo, RENAR
• Format: Final Project
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/16952
• Institution: Institut Teknologi Bandung

Unmanned aircraft technology has been developing rapidly in this last century. One of the model that being developed is an Unmanned Aerial Vehicle (UAV) with capability for Vertical Take-off Landing (VTOL) and hovering in the air. For achieving those capabilities, a UAV must be in a stable condition. The indications that the UAV is in a stable condition are: have a zero moment in roll, pitch and yaw movement. <br /> <br /> <br /> The problem of using a single propeller aircraft is an unwanted yaw movement that caused by an angular momentum of a single propeller. Many ways of controlling an angular momentum, one of it is using a tail rotor like in a helicopter case. In this final project, the angular momentum from single propeller is controlled by using a control surface. Also, a duct has been added outside the propeller in this UAV for optimizing the thrust. This final project consists of designing, manufacturing and testing the UAV. <br /> <br /> <br /> This final project consists of designing duct and control surface, manufacture, and testing. These design projects also include CFD (Computational Fluid Dynamics) analysis for fluid flow. There are also thrust, roll, pitch and yaw movement test in this final project. Load cells in platform were being used to measure force produced by UAV. Finally, testing result and CFD result is compared and analyzed.