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Unmanned Aerial Vehicles (UAVs) with different configurations exist to supply requirements for diverse applications. One of them is the tailsitter that gathers complementary advantages from Vertical Takeoff and Landing (VTOL) and fixed-wing UAVs. In this paper, we present a new design of a tailsitter UAV, named AVALON (Autonomous VerticAL takeOff and laNding). This UAV is composed of typical actuators...
This paper addresses the modeling and attitude control of a novel shrouded floating wind turbine with hinged structure in harsh environmental conditions. Firstly, SimMechanics™ is applied to model the mechanical components of the wind turbine system. Secondly, the wave- and wind-loads acting on the system are respectively calculated based on Morison's equation and blade element momentum theory. Controllers...
In this paper, a completely numerical simulation model of a tilt rotor helicopter is established. Based on the hierarchical and modular modeling principles, the whole simulation model is finally realized on the Simulink platform. Then a sliding mode variable structure controller based on expansion state observer (ESO) is designed in order to realize the attitude control of this nonlinear and strong...
The flight of unmanned aerial vehicle (UAV) is vulnerable to various disturbances and faults. In this paper, the small damage of the wing of an unmanned aerial vehicle is taken into consideration. The UAV control framework consists of force loop and torque loop, where the nonlinear disturbance observer (NDO) based dynamic inverse (DI) control and the extended state observer (ESO) based dynamic inverse...
In the paper, a nonlinear modeling approach for a class of unmanned-aerial-vehicle (UAV) helicopters is presented. The applied approach adopts a component buildup method to calculate the component forces and moments. In order to improve the modeling accuracy and applicability, the rotor dynamics are detailedly analyzed by taking into account the influences of airspeed in hub center and the coupling...
We establish the dynamics relative to flapping angle of the flapping wing vehicle based on the quasi-steady aerodynamics model and Newton-Euler motion equations, and describe the stability analysis method of linearized perturbation equation under active control by varying flapping frequency based on the Routh-Hurwitz stability criterion. To give a demonstration, we design a flapping wing mechanism...
This article is concerned with parameters identification problems and computer modeling of thrust generation subsystem for small unmanned aerial vehicles (UAV) quadrotor type. In this paper approach for computer model generation of dynamic process of thrust generation subsystem that consists of fixed pitch propeller, EC motor and power amplifier, is considered. Due to the fact that obtainment of aerodynamic...
Considering the Insect-like flapping-wing micro aerial vehicle, this paper has analyzed the composite of quasi-steady aerodynamics. That process has associated with the affection due to addition quality produced by wake capture. With introducing rotate circulation. This paper has calculated the lift, drag force, and pitch torque which take part on the wings' surfaces. Ignoring the wings' quality,...
This paper faces the technical and economic challenges related to the design of a green recharge area for electric vehicles at the Campus of Palermo, Italy, with the aim of reduce both costs and pollution connected to the charging process. Based on the behaviour of the student population, the electrical load is identified and two possible solutions are evaluated to manage the peak load: an orientation...
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...
In practice, the lift that a propeller produces is composed of theoretical value and fluctuation, which results in vibration in aircraft. This paper will analyze the effect of the fluctuation on the quadcopter. In order to reduce the vibration caused by the fluctuation, an improved Additive-State-Decomposition-Based (ASDB) dynamic inversion stabilized controller is proposed. To show its effectiveness,...
To research the effect on the canard rudder aerodynamic layout for the projectile correction, the steering gear model under different aerodynamic layout was established. Various kinds of aerodynamic parameters were obtained through simulation. Through the establishment of the ballistic model of suitable for less spin correction projectiles, the capability of correcting has been received under the...
This article shows development of a fixed wing Unmanned Aerial Vechicle (UAV) prototype with multi rotor control system. This model pretends increase flight time of multi rotor system using aerodynamic characteristics. The lift force generated by a wing reduce the required power of the motors to raise up the structure during horizontal forward flight. For airfoil selection and sizing of the wing,...
An original multi-rotor flying robot (MFR) with six non-planar coaxial rotor pairs is introduced in this paper, compared with the other small rotorcrafts, the corresponding two adjacent face-to-face (F-F) and the back-to-back (B-B) rotor units are proposed as the research component to study the overall performance of the rotorcraft. The main characteristic of this novel configuration is that the attitude...
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...
This paper presents a computational framework to identify the effects of wind on the dynamics of a quadrotor unmanned aerial vehicle. Then, using the identified model, the strength and the direction of the wind are estimated with the inertial measurements. The proposed approach is based on a geometric numerical integrator on the special Euclidean group, referred to as a Lie group variational integrator...
Reducing the inter-vehicle separation in a platoon results in the most benefits in terms of aerodynamic savings and vehicles throughput. However, this makes braking maneuvers dangerous and leads to long stopping distances, in particular, when considering heterogeneous vehicles with different braking capacities. Even though control theoretic approaches exist for the platoon cruise operation, the scenario...
With the advent of autonomous driving, road trains or platoons are regaining importance as a meaningful way of improving traffic efficiency and economizing on fuel/energy. It has been shown that reducing inter-vehicle separations to less than one car length results in the most benefits for the whole platoon; however, this poses a number of challenges. In particular, it becomes difficult to guarantee...
Active debris removal and defunct satellites mitigation is one of current hot spots in space research. Based on the deployment process, a new mixed space web is proposed in present paper. Firstly, the Vector Form Intrinsic Finite Element Method and “Kelvin-Voigt” viscoelastic constitution relation are adopted to establish the dynamic model of space web. Then the reliability of the simulation model...
In this paper, we present the application of radial basis function (RBF) neural network for aerodynamic parameter estimation. The Two-Stage RBF neural network (NN) architecture is proposed for complete aerodynamic modelling. The RBF NN is trained by hybrid learning using K-means clustering and recursive least squares (RLS) methods. The proposed architecture yields the significant improvements for...
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