Aerodynamics of flapping-wing micro air vehicles

Sergey V Shkarayev, Dmitro Silin

Research output: Chapter in Book/Report/Conference proceedingConference contribution

13 Citations (Scopus)

Abstract

The research study outlined in the paper addresses the aerodynamic features of flexible flapping wings used in micro air vehicles called ornithopters. Aerodynamic force measurements were conducted for the 25-cm and 74-cm-wing-span models at different airflow velocities and flapping frequencies. A series of experiments were conducted on the 25-cm flapping-wing model without free stream airflow. In order to study the effect of a dihedral on generated thrust and normal force, the model was modified to accommodate three values of dihedral angle. It appeared that the thrust force is higher for higher dihedral angle. Effects of a wing's bending stiffness and of the wing root constraint on the generated thrust force and required power were investigated. The aerodynamic forces on flapping wings were studied with the stroke plane angle varied from horizontal to vertical. An important result was found that flapping wings do not exhibit a typical, abrupt stall seen with the fixed wings. Experimental results were analyzed in the framework of the momentum theory. The results of this study were realized in micro ornithopter designs that was successfully flight tested.

Original languageEnglish (US)
Title of host publication47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition
StatePublished - 2009
Event47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition - Orlando, FL, United States
Duration: Jan 5 2009Jan 8 2009

Other

Other47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition
CountryUnited States
CityOrlando, FL
Period1/5/091/8/09

Fingerprint

Micro air vehicle (MAV)
flapping
aerodynamics
wings
Aerodynamics
vehicles
thrust
air
aerodynamic forces
Dihedral angle
dihedral angle
wing roots
wing span
fixed wings
momentum theory
Flexible wings
airflow
free flow
Fixed wings
strokes

Keywords

  • Dynamics
  • Experiments
  • Flapping
  • Flight
  • Lift
  • Ornithopter
  • Thrust
  • Wind tunnel

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Shkarayev, S. V., & Silin, D. (2009). Aerodynamics of flapping-wing micro air vehicles. In 47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition [2009-0878]

Aerodynamics of flapping-wing micro air vehicles. / Shkarayev, Sergey V; Silin, Dmitro.

47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. 2009. 2009-0878.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Shkarayev, SV & Silin, D 2009, Aerodynamics of flapping-wing micro air vehicles. in 47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition., 2009-0878, 47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Orlando, FL, United States, 1/5/09.
Shkarayev SV, Silin D. Aerodynamics of flapping-wing micro air vehicles. In 47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. 2009. 2009-0878
Shkarayev, Sergey V ; Silin, Dmitro. / Aerodynamics of flapping-wing micro air vehicles. 47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. 2009.
@inproceedings{ef6bbbdd13df4c25806866839b41d993,
title = "Aerodynamics of flapping-wing micro air vehicles",
abstract = "The research study outlined in the paper addresses the aerodynamic features of flexible flapping wings used in micro air vehicles called ornithopters. Aerodynamic force measurements were conducted for the 25-cm and 74-cm-wing-span models at different airflow velocities and flapping frequencies. A series of experiments were conducted on the 25-cm flapping-wing model without free stream airflow. In order to study the effect of a dihedral on generated thrust and normal force, the model was modified to accommodate three values of dihedral angle. It appeared that the thrust force is higher for higher dihedral angle. Effects of a wing's bending stiffness and of the wing root constraint on the generated thrust force and required power were investigated. The aerodynamic forces on flapping wings were studied with the stroke plane angle varied from horizontal to vertical. An important result was found that flapping wings do not exhibit a typical, abrupt stall seen with the fixed wings. Experimental results were analyzed in the framework of the momentum theory. The results of this study were realized in micro ornithopter designs that was successfully flight tested.",
keywords = "Dynamics, Experiments, Flapping, Flight, Lift, Ornithopter, Thrust, Wind tunnel",
author = "Shkarayev, {Sergey V} and Dmitro Silin",
year = "2009",
language = "English (US)",
isbn = "9781563479694",
booktitle = "47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition",

}

TY - GEN

T1 - Aerodynamics of flapping-wing micro air vehicles

AU - Shkarayev, Sergey V

AU - Silin, Dmitro

PY - 2009

Y1 - 2009

N2 - The research study outlined in the paper addresses the aerodynamic features of flexible flapping wings used in micro air vehicles called ornithopters. Aerodynamic force measurements were conducted for the 25-cm and 74-cm-wing-span models at different airflow velocities and flapping frequencies. A series of experiments were conducted on the 25-cm flapping-wing model without free stream airflow. In order to study the effect of a dihedral on generated thrust and normal force, the model was modified to accommodate three values of dihedral angle. It appeared that the thrust force is higher for higher dihedral angle. Effects of a wing's bending stiffness and of the wing root constraint on the generated thrust force and required power were investigated. The aerodynamic forces on flapping wings were studied with the stroke plane angle varied from horizontal to vertical. An important result was found that flapping wings do not exhibit a typical, abrupt stall seen with the fixed wings. Experimental results were analyzed in the framework of the momentum theory. The results of this study were realized in micro ornithopter designs that was successfully flight tested.

AB - The research study outlined in the paper addresses the aerodynamic features of flexible flapping wings used in micro air vehicles called ornithopters. Aerodynamic force measurements were conducted for the 25-cm and 74-cm-wing-span models at different airflow velocities and flapping frequencies. A series of experiments were conducted on the 25-cm flapping-wing model without free stream airflow. In order to study the effect of a dihedral on generated thrust and normal force, the model was modified to accommodate three values of dihedral angle. It appeared that the thrust force is higher for higher dihedral angle. Effects of a wing's bending stiffness and of the wing root constraint on the generated thrust force and required power were investigated. The aerodynamic forces on flapping wings were studied with the stroke plane angle varied from horizontal to vertical. An important result was found that flapping wings do not exhibit a typical, abrupt stall seen with the fixed wings. Experimental results were analyzed in the framework of the momentum theory. The results of this study were realized in micro ornithopter designs that was successfully flight tested.

KW - Dynamics

KW - Experiments

KW - Flapping

KW - Flight

KW - Lift

KW - Ornithopter

KW - Thrust

KW - Wind tunnel

UR - http://www.scopus.com/inward/record.url?scp=78549239600&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=78549239600&partnerID=8YFLogxK

M3 - Conference contribution

AN - SCOPUS:78549239600

SN - 9781563479694

BT - 47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition

ER -