Design and Implementation of a Compact Rotational Speed and Air Flow Sensor for Unmanned Aerial Vehicles

2019 ◽  
Vol 19 (22) ◽  
pp. 10298-10307 ◽  
Author(s):  
Federico Fries ◽  
Shane Kyi Hla Win ◽  
Emmanuel Tang ◽  
Jun En Low ◽  
Luke Soe Thura Win ◽  
...  
Keyword(s):  
Unmanned Aerial Vehicles ◽  
Rotational Speed ◽  
Air Flow ◽  
Flow Sensor ◽  
Design And Implementation ◽  
Aerial Vehicles

MULTIDIMENSIONAL SIMULATIONS AND TEST FIRES OF A HYDROGEN-FUELED RAMJET WITH AN ANNULAR DETONATIVE COMBUSTOR AT APPROACHING AIR FLOW OF MACH 2 AND 1.5

2020 ◽  
Author(s):  
V. S. IVANOV ◽  
◽  
V. S. AKSENOV ◽  
S. M. FROLOV ◽  
P. A. GUSEV ◽  
...  
Keyword(s):  
Unmanned Aerial Vehicles ◽  
High Speed ◽  
Constant Pressure ◽  
Air Flow ◽  
Thermodynamic Cycle ◽  
Aerial Vehicles ◽  
Mach Numbers

Modern high-speed unmanned aerial vehicles are powered with small-size turbojets or ramjets. Existing ramjets operating on the thermodynamic cycle with de§agrative combustion of fuel at constant pressure are efficient at flight Mach numbers M ranging from about 2 to 6.

scholarly journals Performance analysis of nonlinear observers applied to the fixed-wing unmanned aerial vehicles flight under decoupled-reduced model

2017 ◽  
Vol 9 (2) ◽  
pp. 111-123 ◽  
Author(s):  
Ricardo P Parada ◽  
A Tadeo Espinoza ◽  
Alejandro E Dzul ◽  
Francisco G Salas
Keyword(s):  
Unmanned Aerial Vehicles ◽  
Flight Control ◽  
Sliding Mode ◽  
Reduced Model ◽  
Control Law ◽  
Extended State ◽  
Nonlinear Observers ◽  
Design And Implementation ◽  
Aerial Vehicles ◽  
Nonlinear Extended State Observer

In this paper, we present the design and implementation of two nonlinear observers: nonlinear extended state observer and sliding mode observer for estimating the pitch, yaw and roll angles and angular rates of a fixed-wing unmanned aerial vehicles system under a decoupled-reduced model in real flight experiments. A backstepping control law is designed for control in a decentralized way for altitude, yaw and roll of the airplane. This scheme allows us to test experimentally the feasibility of using the online estimated data from the observers in flight control, which is useful for increasing the robustness of the control and the safety of flight. Furthermore, a comparative analysis of the performance of both nonlinear observers is conducted.

scholarly journals Review of Microscale Flow-Sensor-Enabled Mechanosensing in Small Unmanned Aerial Vehicles

2019 ◽  
Vol 56 (3) ◽  
pp. 962-973 ◽  
Author(s):  
August Mark ◽  
Yunjun Xu ◽  
Benjamin T. Dickinson
Keyword(s):  
Unmanned Aerial Vehicles ◽  
Flow Sensor ◽  
Aerial Vehicles ◽  
Microscale Flow

scholarly journals Angle of Attack Sensor for Small Fixed-Wing Unmanned Aerial Vehicles

Proceedings ◽  
2020 ◽  
Vol 39 (1) ◽  
pp. 19
Author(s):  
Wanngoen ◽  
Saetunand ◽  
Saengphet ◽  
Tantrairatn
Keyword(s):  
Unmanned Aerial Vehicles ◽  
Flow Direction ◽  
Air Flow ◽  
Angle Of Attack ◽  
Flight Test ◽  
Unmanned Aircraft ◽  
Aerodynamic Parameter ◽  
Aerial Vehicles ◽  
Flow Changes ◽  
Good Agreement

The angle of attack (AOA) is an important parameter for estimating aerodynamic parameter the performance and stability of aircraft. Currently, AOA sensors are used in general aircraft. However, there is no a reasonable-price AOA sensor that is compatible to a small fixed-wing unmanned aerial vehicles (UAVs). This research aims to designs and constructs angle of attract (AOA) sensor for small fixed-wing unmanned aircraft. Mechanism Design, which is similar to aerodynamic wheatear vane, can operate in airspeed 10–30 m/s. The direction of airfoil aligns with the air flow direction. When the AOA of the UAV changes, the air flow changes the direction, resulting in the change of airfoil direction. The high-resolution rotary encoder, that was used to measure the angle of the airfoil, was installed with the fin airfoil. For experiment, the accuracy of the AOA sensor was validated by comparing the angles obtained from the encoder with the standard rotary table in static and wind tunnel. Finally, the AOA sensor, which was attached on aircraft, was verified and recorded in flight test. As the results of the measurement, the airfoil angles detected by the encoder were in good agreement with the standard angles.

scholarly journals Motion Equations and Attitude Control in the Vertical Flight of a VTOL Bi-Rotor UAV

Electronics ◽  
2019 ◽  
Vol 8 (2) ◽  
pp. 208 ◽  
Author(s):  
Sergio Garcia-Nieto ◽  
Jesus Velasco-Carrau ◽  
Federico Paredes-Valles ◽  
Jose Salcedo ◽  
Raul Simarro
Keyword(s):  
Unmanned Aerial Vehicles ◽  
Attitude Control ◽  
Controller Design ◽  
Experimental Studies ◽  
Hardware In The Loop ◽  
Motion Equations ◽  
Design And Implementation ◽  
Aerial Vehicles ◽  
Attitude Tracking ◽  
Tracking Controller

This paper gathers the design and implementation of the control system that allows an unmanned Flying-wing to perform a Vertical Take-Off and Landing (VTOL) maneuver using two tilting rotors (Bi-Rotor). Unmanned Aerial Vehicles (UAVs) operating in this configuration are also categorized as Hybrid UAVs due to their ability of having a dual flight envelope: hovering like a multi-rotor and cruising like a traditional fixed-wing, providing the opportunity of facing complex missions in which these two different dynamics are required. This work exhibits the Bi-Rotor nonlinear dynamics, the attitude tracking controller design and also, the results obtained through Hardware-In-the-Loop (HIL) simulation and experimental studies that ensure the controller’s efficiency in hovering operation.

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