Wind Tunnel Data Base Development and Nonlinear Modeling Applied to Powered Micro Air Vehicles with Flexible Wing

2006 ◽  
Author(s):  
Roberto Albertani ◽  
Richard DeLoach ◽  
Bret Stanford ◽  
James Hubner ◽  
Peter Ifju
Keyword(s):  
Wind Tunnel ◽  
Data Base ◽  
Nonlinear Modeling ◽  
Micro Air Vehicles ◽  
Flexible Wing ◽  
Wind Tunnel Data ◽  
Air Vehicles

Numerical Simulation of Micro Air Vehicles With Membrane Wings

2007 ◽  
Author(s):  
Xiaoqin Zhang ◽  
Ling Tian
Keyword(s):  
Numerical Simulation ◽  
Pressure Distribution ◽  
Micro Air Vehicles ◽  
Flexible Wings ◽  
Design Modification ◽  
Structure Deformation ◽  
Flexible Wing ◽  
Fluid Field ◽  
Distributed Pressure ◽  
Air Vehicles

Micro Air Vehicles (MAVs) have advantages of small size, low cost, flexibility and controllability etc., so they will be applied widely in military and civilian fields. They have obviously low Reynolds number aerodynamics, which is different from traditional aircrafts. In this paper, numerical simulation based on fluid-structure interaction for flexible wing MAVs is presented. Flexible wings are composed of carbon frames and covered with membrane skins. Because flexible wing MAVs easily deform in airflow, both structure model and fluid model should be built. The two models are connected by interfaces of membrane wings, which transmit distributed pressure and deformations of membrane wings. When membrane wings are located in airflow, they will deform with actions of surrounding airflow. Deformation of membrane wings also affects airflow and pressure distributed on the wings’ surfaces will also be changed relatively, which will compel the shape of membrane wings to be changed once more. Therefore, numerical simulation of flexible wing MAVs is not only the analysis of fluid field, but also the structure deformation effects. Navier-Stokes Equations are nonlinear and complicated, so direct interaction of fluid and structure equations is rather difficult and costs too much time. Indirect interaction method is more feasible and it is adopted in this paper. Structure deformation and distributed pressure on membrane wings surfaces are calculated separately, and then pressure distribution from fluid solver is transmitted to structure solver. After structure deformation is calculated in structure solver, it will be transmitted to fluid field again. Iteration goes on in this way and finally converges. Simulation results show the deformation, stress and pressure distribution of flexible wings. All these results are good reference for MAVs design, modification and wind tunnel experiments generally.

scholarly journals Flexible-wing-based micro air vehicles

2002 ◽  
Author(s):  
P. Ifju ◽  
D. Jenkins ◽  
S. Ettinger ◽  
Y. Lian ◽  
W. Shyy ◽  
...  
Keyword(s):  
Micro Air Vehicles ◽  
Flexible Wing ◽  
Air Vehicles

scholarly journals WIND TUNNEL CALIBRATION, CORRECTIONS AND EXPERIMENTAL VALIDATION FOR FIXED-WING MICRO AIR VEHICLES MEASUREMENTS

Aviation ◽  
2020 ◽  
Vol 23 (4) ◽  
pp. 104-113
Author(s):  
Ahmed Aboelezz ◽  
Yunes Elqudsi ◽  
Mostafa Hassanalian ◽  
Ahmed Desoki
Keyword(s):  
Reynolds Number ◽  
Wind Tunnel ◽  
Aspect Ratio ◽  
Low Reynolds Number ◽  
Micro Air Vehicles ◽  
Measured Data ◽  
Published Data ◽  
Low Aspect Ratio ◽  
Low Reynolds ◽  
Air Vehicles

The increase in the number of Unmanned Aerial Vehicles (UAVs) and Micro Air Vehicles (MAVs), which are used in a variety of applications has led to a surge in low Reynolds number aerodynamics research. Flow around fixedwing MAVs has an unusual behavior due to its low aspect ratio and operates at low Reynolds number, which demanded to upgrade the used wind tunnel for this study. This upgrade enables measuring the small aerodynamics forces and moment of fixed-wing MAVs. The wind tunnel used in this work is upgraded with a state of art data acquisition system to deal with the different sensors signals in the wind tunnel. For accurate measurements, the sting balance, angle sensor, and airspeed sensor are calibrated. For validation purposes, an experiment is made on a low aspect ratio flat plate wing at low Reynolds number, and the measured data are corrected and compared with published results. The procedure presented in this paper for the first time gave a detailed and complete guide for upgrading and calibrating old wind tunnel, all the required corrections to correct the measured data was presented, the turbulence level correction new technique presented in this paper could be used to estimate the flow turbulence effect on the measured data and correct the measured data against published data.

1D16 Flexible wing design in flapping micro air vehicles

2013 ◽  
Vol 2013.25 (0) ◽  
pp. 141-142
Author(s):  
Haruka SUZUKI ◽  
Toshiyuki NAKATA ◽  
Hiroto TANAKA ◽  
Hao LIU
Keyword(s):  
Micro Air Vehicles ◽  
Wing Design ◽  
Flexible Wing ◽  
Air Vehicles

Design of Flexible Wing with Embedded Piezoelectric Actuator

2013 ◽  
Vol 325-326 ◽  
pp. 951-955
Author(s):  
Yu Hua Zhou ◽  
Yu Tao Ju ◽  
Chang Sheng Zhou
Keyword(s):  
Mathematical Model ◽  
Dynamic Characteristic ◽  
Piezoelectric Actuator ◽  
Micro Air Vehicles ◽  
Previous Model ◽  
Ansys Software ◽  
Flexible Wing ◽  
The Mathematical Model ◽  
Air Vehicles

This paper introduces a new kind of flexible wing with embedded piezoelectric actuator as framework for Micro Air Vehicles (MAV), which was fixed spar in the previous flexible wing. This made it a controllable flexible wing because the new flexible wing can not only works as previous model without control, but also can change its wing profiles in our purpose by using the embedded piezoelectric actuator when its necessary. The mathematical model of the deformation of piezoelectric actuator under control has developed. with which the structure of the flexible wing was designed. The simulation of dynamic characteristic of the flexible wing with embedded piezoelectric actuator has been done with ANSYS software.

Design of Gust Wind Tunnel With Unsteady and Shear Main-Flows

2021 ◽  
Author(s):  
Yu Nishio ◽  
Ryotaro Miyazaki ◽  
Takanobu Ogawa
Keyword(s):  
Wind Tunnel ◽  
Shear Layer ◽  
Velocity Gradient ◽  
Test Section ◽  
Micro Air Vehicles ◽  
Strong Impact ◽  
Velocity Change ◽  
Linear Shear ◽  
Shutter Mechanism ◽  
Air Vehicles

Abstract Micro air vehicles (MAVs) have been developed for many fields. The MAVs usually receive strong impact from a velocity change in time or space, and facilities for aerodynamic experiments of MAVs under a gusty environment have been required. The present study has developed a gust wind tunnel to generate unsteady and non-uniform flows. We developed a small wind tunnel with eight multi-fans and a shutter mechanism at the upstream of the test section. We controlled the outputs of the fans independently and obtained a linear shear layer with an error of 5 percent. The velocity gradient of the shear layer was from 5 to 8 s−1. The shutter mechanisms provided a longitudinal gust with the velocity change from 2 m/s to 10 m/s within 0.3 seconds.

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