scholarly journals Numerical Simulation of a Flapping Micro Aerial Vehicle Through Wing Deformation Capture

AIAA Journal ◽  
2018 ◽  
Vol 56 (8) ◽  
pp. 3257-3270 ◽  
Author(s):  
W. B. Tay ◽  
J. H. S. de Baar ◽  
M. Percin ◽  
S. Deng ◽  
B. W. van Oudheusden
Keyword(s):  
Numerical Simulation ◽  
Micro Aerial Vehicle ◽  
Aerial Vehicle ◽  
Wing Deformation

scholarly journals Numerical simulation of the aerodynamic performance of a novel micro-aerial vehicle mimicking a locust

2021 ◽  
Author(s):  
Mohamed A. Mohamed ◽  
Talal Maksoud ◽  
Rodney J. Santos ◽  
Mohamed Hefny Salim ◽  
Mohamed F.C. Esmail
Keyword(s):  
Numerical Simulation ◽  
Aerodynamic Performance ◽  
Micro Aerial Vehicle ◽  
Aerial Vehicle

scholarly journals Beneficial wake-capture effect for forward propulsion with a restrained wing-pitch motion of a butterfly

2021 ◽  
Vol 8 (8) ◽  
pp. 202172
Author(s):  
You-Jun Lin ◽  
Sheng-Kai Chang ◽  
Yu-Hsiang Lai ◽  
Jing-Tang Yang
Keyword(s):  
Experimental Data ◽  
Numerical Simulation ◽  
Small Amplitude ◽  
Capture Effect ◽  
Wake Region ◽  
Micro Aerial Vehicle ◽  
Pitch Motion ◽  
Thrust Generation ◽  
Aerial Vehicle ◽  
Induced Flow

Unlike other insects, a butterfly uses a small amplitude of the wing-pitch motion for flight. From an analysis of the dynamics of real flying butterflies, we show that the restrained amplitude of the wing-pitch motion enhances the wake-capture effect so as to enhance forward propulsion. A numerical simulation refined with experimental data shows that, for a small amplitude of the wing-pitch motion, the shed vortex generated in the downstroke induces air in the wake region to flow towards the wings. This condition enables a butterfly to capture an induced flow and to acquire an additional forward propulsion, which accounts for more than 47% of the thrust generation. When the amplitude of the wing-pitch motion exceeds 45°, the flow induced by the shed vortex drifts away from the wings; it attenuates the wake-capture effect and causes the butterfly to lose a part of its forward propulsion. Our results provide one essential aerodynamic feature for a butterfly to adopt a small amplitude of the wing-pitch motion to enhance the wake-capture effect and forward propulsion. This work clarifies the variation of the flow field correlated with the wing-pitch motion, which is useful in the design of wing kinematics of a micro-aerial vehicle.

Energy-Based Design of Reconfigurable Micro Aerial Vehicle (MAV) Flight Structures

2012 ◽  
Author(s):  
James Joo ◽  
Gregory Reich ◽  
James Elgersma ◽  
Kristopher Aber
Keyword(s):  
Micro Aerial Vehicle ◽  
Aerial Vehicle ◽  
Energy Based Design

scholarly journals Run Your Visual-Inertial Odometry on NVIDIA Jetson: Benchmark Tests on a Micro Aerial Vehicle

2021 ◽  
pp. 1-1
Author(s):  
Jinwoo Jeon ◽  
Sungwook Jung ◽  
Eungchang Lee ◽  
Duckyu Choi ◽  
Hyun Myung
Keyword(s):  
Micro Aerial Vehicle ◽  
Benchmark Tests ◽  
Aerial Vehicle

scholarly journals Towards the Development of an Automatic UAV-Based Indoor Environmental Monitoring System: Distributed Off-Board Control System for a Micro Aerial Vehicle

2021 ◽  
Vol 11 (5) ◽  
pp. 2347 ◽  
Author(s):  
Jorge Solis ◽  
Christoffer Karlsson ◽  
Simon Johansson ◽  
Kristoffer Richardsson
Keyword(s):  
Control System ◽  
Environmental Monitoring ◽  
Monitoring System ◽  
Target Location ◽  
Flight Time ◽  
Distributed Control System ◽  
Micro Aerial Vehicle ◽  
Environmental Monitoring System ◽  
Rapid Changes ◽  
Aerial Vehicle

This research aims to develop an automatic unmanned aerial vehicle (UAV)-based indoor environmental monitoring system for the acquisition of data at a very fine scale to detect rapid changes in environmental features of plants growing in greenhouses. Due to the complexity of the proposed research, in this paper we proposed an off-board distributed control system based on visual input for a micro aerial vehicle (MAV) able to hover, navigate, and fly to a desired target location without considerably affecting the effective flight time. Based on the experimental results, the MAV was able to land on the desired location within a radius of about 10 cm from the center point of the landing pad, with a reduction in the effective flight time of about 28%.

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