Improved Aerodynamic Model for Efficient Analysis of Flapping-Wing Flight

AIAA Journal ◽  
2011 ◽  
Vol 49 (4) ◽  
pp. 868-872 ◽  
Author(s):  
Dae-Kwan Kim ◽  
Jun-Seong Lee ◽  
Jae-Hung Han
Keyword(s):  
Flapping Wing ◽  
Aerodynamic Model

Aerodynamic Model Updating Using Wind-Tunnel Setup for Hummingbirdlike Flapping Wing Nanorobot

AIAA Journal ◽  
2021 ◽  
pp. 1-11
Author(s):  
Siemen Timmermans ◽  
Maarten Vanierschot ◽  
Dirk Vandepitte
Keyword(s):  
Wind Tunnel ◽  
Model Updating ◽  
Flapping Wing ◽  
Aerodynamic Model

scholarly journals A Sub-100 mg Electromagnetically Driven Insect-inspired Flapping-wing Micro Robot Capable of Liftoff and Control Torques Modulation

2020 ◽  
Vol 17 (6) ◽  
pp. 1085-1095
Author(s):  
Chenyang Wang ◽  
Weiping Zhang ◽  
Yang Zou ◽  
Ran Meng ◽  
Jiaxin Zhao ◽  
...  
Keyword(s):  
Input Voltage ◽  
Flapping Wing ◽  
Total Weight ◽  
Voltage Amplitude ◽  
Torque Measurement ◽  
Electromagnetic Actuators ◽  
Aerodynamic Model ◽  
Micro Robot ◽  
The Mean ◽  
And Control

AbstractInspired by the unique, agile and efficient flapping flight of insects, we present a novel sub-100 mg, electromagnetically driven, tailless, flapping-wing micro robot. This robot utilizes two optimized electromagnetic actuators placed back to back to drive two wings separately, then kinematics of each wing can be independently controlled, which gives the robot the ability to generate all three control torques of pitch, roll and yaw for steering. To quantify the performance of the robot, a simplified aerodynamic model is used to estimate the generated lift and torques, and two customized test platforms for lift and torque measurement are built for this robot. The mean lift generated by the robot is measured to be proportional to the square of the input voltage amplitude. The three control torques are measured to be respectively proportional to three decoupled parameters of the control voltages, therefore the modulation of three control torques for the robot is independent, which is helpful for the further controlled flight. All these measured results fit well with the calculated results of the aerodynamic model. Furthermore, with a total weight of 96 mg and a wingspan of 3.5 cm, this robot can generate sufficient lift to take off.

scholarly journals Unsteady aerodynamic model of flexible flapping wing

2018 ◽  
Vol 80 ◽  
pp. 354-367 ◽  
Author(s):  
Si Chen ◽  
Hao Li ◽  
Shijun Guo ◽  
Mingbo Tong ◽  
Bing Ji
Keyword(s):  
Flapping Wing ◽  
Unsteady Aerodynamic ◽  
Aerodynamic Model

scholarly journals Aerodynamic Analysis of a Flapping Wing Aircraft for Short Landing

2020 ◽  
Vol 10 (10) ◽  
pp. 3404
Author(s):  
Bing Ji ◽  
Zenggang Zhu ◽  
Shijun Guo ◽  
Si Chen ◽  
Qiaolin Zhu ◽  
...  
Keyword(s):  
Aerodynamic Characteristics ◽  
Flapping Wing ◽  
Aerodynamic Analysis ◽  
Drag Forces ◽  
Wing Model ◽  
Aerodynamic Model ◽  
Computational Fluid Dynamics Cfd ◽  
The Difference ◽  
Cfd Method ◽  
Lift And Drag

An investigation into the aerodynamic characteristics has been presented for a bio-inspired flapping wing aircraft. Firstly, a mechanism has been developed to transform the usual rotation powered by a motor to a combined flapping and pitching motion of the flapping wing. Secondly, an experimental model of the flapping wing aircraft has been built and tested to measure the motion and aerodynamic forces produced by the flapping wing. Thirdly, aerodynamic analysis is carried out based on the measured motion of the flapping wing model using an unsteady aerodynamic model (UAM) and validated by a computational fluid dynamics (CFD) method. The difference of the average lift force between the UAM and CFD method is 1.3%, and the difference between the UAM and experimental results is 18%. In addition, a parametric study is carried out by employing the UAM method to analyze the effect of variations of the pitching angle on the aerodynamic lift and drag forces. According to the study, the pitching amplitude for maximum lift is in the range of 60°~70° as the flight velocity decreases from 5 m/s to 1 m/s during landing.

scholarly journals Improving Prediction of Flapping-Wing Motion By Incorporating Actuator Constraints With Models of Aerodynamic Loads Using In-Flight Data

2017 ◽  
Vol 9 (2) ◽  
Author(s):  
John W. Gerdes ◽  
Hugh A. Bruck ◽  
Satyandra K. Gupta
Keyword(s):  
Experimental Data ◽  
Design Space Exploration ◽  
Experimental Testing ◽  
Flapping Wing ◽  
Modeling Framework ◽  
Flight Data ◽  
Flexible Wing ◽  
Wing Motion ◽  
Aerodynamic Model ◽  
Strip Theory

Flapping-wing flight is a challenging system integration problem for designers due to tight coupling between propulsion and flexible wing subsystems with variable kinematics. High fidelity models that capture all the subsystem interactions are computationally expensive and too complex for design space exploration and optimization studies. A combination of simplified modeling and validation with experimental data offers a more tractable approach to system design and integration, which maintains acceptable accuracy. However, experimental data on flapping-wing aerial vehicles which are collected in a static laboratory test or a wind tunnel test are limited because of the rigid mounting of the vehicle, which alters the natural body response to flapping forces generated. In this study, a flapping-wing aerial vehicle is instrumented to provide in-flight data collection that is unhindered by rigid mounting strategies. The sensor suite includes measurements of attitude, heading, altitude, airspeed, position, wing angle, and voltage and current supplied to the drive motors. This in-flight data are used to setup a modified strip theory aerodynamic model with physically realistic flight conditions. A coupled model that predicts wing motions is then constructed by combining the aerodynamic model with a model of flexible wing twist dynamics and enforcing motor torque and speed bandwidth constraints. Finally, the results of experimental testing are compared to the coupled modeling framework to establish the effectiveness of the proposed approach for improving predictive accuracy by reducing errors in wing motion specification.

Generic Modeling and Parametric Study of Flapping Wing Micro-Air-Vehicle

2012 ◽  
Vol 225 ◽  
pp. 18-25 ◽  
Author(s):  
Harijono Djojodihardjo ◽  
Alif Syamim Syazwan Ramli ◽  
Surjatin Wiriadidjaja
Keyword(s):  
Parametric Study ◽  
Three Dimensional ◽  
Unsteady Aerodynamics ◽  
Flapping Wing ◽  
Phase Lag ◽  
Aerodynamic Model ◽  
Strip Theory ◽  
Thrust Characteristics ◽  
Generic Modeling ◽  
Wing Geometry

The present work is focused on the unsteady aerodynamics of bio-inspired flapping wing to produce lift and thrust for hovering and forward flight. A generic approach is followed to understand and mimic the mechanism and kinematics of ornithopter by considering the motion of a three-dimensional rigid thin wing in flapping and pitching motion, using strip theory and two-dimensional unsteady aerodynamics for idealized wing in pitching and flapping oscillations with phase lag. Parametric study is carried out to obtain the lift, drag, and thrust characteristics within a cycle for assessing the plausibility of the aerodynamic model, and for the synthesis of a Flapping Wing MAV model with simplified mechanism. Other important parameters such as flapping frequency and wing geometry are considered. Results are assessed in comparison with the existing theoretical results.

Experimental evaluation of a flapping-wing aerodynamic model for MAV applications

2008 ◽  
Author(s):  
Jun-Seong Lee ◽  
Dae-Kwan Kim ◽  
Jin-Young Lee ◽  
Jae-Hung Han
Keyword(s):  
Experimental Evaluation ◽  
Flapping Wing ◽  
Aerodynamic Model

scholarly journals Further Development of the Kinematic and Aerodynamic Modeling and Analysis of Flapping Wing Ornithopter from Basic Principles

2014 ◽  
Vol 629 ◽  
pp. 9-17
Author(s):  
Harijono Djojodihardjo ◽  
Muhammad Anas Abd Bari ◽  
Azmin Shakrine Mohd Rafie ◽  
Surjatin Wiriadidjaja
Keyword(s):  
Three Dimensional ◽  
Unsteady Aerodynamics ◽  
Flapping Wing ◽  
Phase Lag ◽  
Basic Principles ◽  
Modeling And Analysis ◽  
Aerodynamic Modeling ◽  
Aerodynamic Model ◽  
Strip Theory ◽  
Further Development

<p>The basis of this work was to understand the generation of lift and thrust of a flapping bi-wing ornithopter, which is influenced by its geometrical, dynamic, kinematic and aerodynamic features by following a generic approach in order to identify and mimic the mechanisms. As further development of earlier work, three-dimensional rigid thin wing is considered in flapping and pitching motion using strip theory and two-dimensional unsteady aerodynamics for idealized wing in pitching and flapping oscillations with phase lag. Later, parametric study is carried out to attain a complete cycle’s lift and thrust physical characteristics for evaluating the plausibility of the aerodynamic model and for the synthesis of an ornithopter model with simplified mechanism. Further investigation is conducted to identify individual contribution of generic motion towards the flight forces. Results are assessed in comparison with existing theoretical and experimental results as appropriate.</p>

scholarly journals Linear Aerodynamic Model Identification of a Flapping Wing MAV Based on Flight Test Data

2013 ◽  
Vol 5 (4) ◽  
pp. 273-286 ◽  
Author(s):  
J.V. Caetano ◽  
C.C. de Visser ◽  
G.C.H.E. de Croon ◽  
B. Remes ◽  
C. de Wagter ◽  
...  
Keyword(s):  
Test Data ◽  
Model Identification ◽  
Flight Test ◽  
Flapping Wing ◽  
Aerodynamic Model
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