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A hybrid aerial vehicle (HAV), featured combination of a quadrotor system and a fixed-wing system, is one of the most promising configurations having both a vertical take-off and landing (VTOL) capability and high cruise performance. In this paper, a HAV has been designed and prototyped to analyze the performance of the HAV. The specifications of the HAV are summarized. The aerodynamic coefficients...
This paper presents fuzzy self-tuning PID controller for controlling the altitude of the quadrotor. Although the PID controllers have many advantages, it has a limitation that the main term gains called proportional gain, integration gain, and derivative gain have to be tuned manually. One of a solution to manage its limitation is adding the special feature called self-tuning. So, a fuzzy self-tuning...
Quadrotors are becoming a major platform for both industrial and research activities, increasing the requirements for precise and dynamic control. Best control can be achieved by directly controlling the individual rotor thrust forces, which, during flight, can only be estimated. An identification of the thrust generation mechanism, and subsequent exploitation of this relation in the quadrotor's command...
The goal of Piccolissimo is to create a small, simple, and self-powered flying vehicle. Piccolissimo has just one motor and two rigid bodies, which are propellers that spin in opposite directions. The mass distribution and relative rotor speeds are designed to maintain passive stability in hover. Cartesian velocity control is obtained by introducing an asymmetry in the rotation axis of the two rotating...
Advancements in control theory and the miniaturization of microelectronics has led to significant improvements in the aerial characteristics and performance of single rotor aerial crafts. These single rotor aerial crafts are of particular interest as they can be considered true hybrids between traditional fixed-wing crafts and the maneuverable multi-rotor platforms, allowing both VTOL capabilities...
This paper focuses on a convertible unmanned aerial vehicle (CUAV) whose main characteristics is to perform hover flight for launch or recovery, and horizontal mode during cruise. The dynamic model is obtained using the Newton-Euler approach and it considers the aerodynamic effects. An adaptive backstepping control, based on quaternions, is proposed for the complete operation of the CUAV. The closed-loop...
This paper presents aerodynamic analysis of an unmanned small-scaled gyroplane with a rotor having cyclic pitch system. A comprehensive nonlinear model is derived for it which involves force and moment generation mechanism for the flying vehicle. The nonlinear model is linearized with approximations and deduced on a prescribed flight condition. Our gyroplane dynamic modal response is further reconfigured...
This paper presents a transition-flight mathematical model of a civil tilt-rotor VTOL unmanned aerial vehicle (UAV) TURAC. Forces and moments acting on the UAV body are calculated using Newton's second law. Aerodynamic effects of free airstream and propeller airstream are defined separately. CFD analyses are performed to specify aerodynamic coefficients for transitional flight regime. The trim point...
The calculation for helicopter blades forces according to the designed parameters of a given aerofoil is an important but challenging problem. The more and more calculation approaches based on computer are introduced for tackle with this problem, such as CFD (computational fluid dynamics) and some airflow field analysis. In this paper, we mainly deal with the calculation approach for helicopter blades...
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