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Dynamics and Performance of Tailless Micro Aerial Vehicle with Flexible Articulated Wings

Paranjape, Aditya A. and Chung, Soon-Jo and Hilton, Harry H. and Chakravarthy, Animesh (2012) Dynamics and Performance of Tailless Micro Aerial Vehicle with Flexible Articulated Wings. AIAA Journal, 50 (5). pp. 1177-1188. ISSN 0001-1452. https://resolver.caltech.edu/CaltechAUTHORS:20161130-095641127

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Abstract

The purpose of this paper is to analyze and discuss the performance and stability of a tailless micro aerial vehicle with flexible articulated wings. The dihedral angles can be varied symmetrically on both wings to control the aircraft speed independently of the angle of attack and flight-path angle, while an asymmetric dihedral setting can be used to control yaw in the absence of a vertical tail.Anonlinear aero-elastic model is derived, and it is used to study the steady-state performance and flight stability of the micro aerial vehicle. The concept of the effective dihedral is introduced, which allows for a unified treatment of rigid and flexible wing aircraft. It also identifies the amount of elasticity that is necessary to obtain tangible performance benefits over a rigid wing. The feasibility of using axial tension to stiffen the wing is discussed, and, at least in the context of a linear model, it is shown that adding axial tension is effective but undesirable. The turning performance of an micro aerial vehicle with flexible wings is compared to an otherwise identical micro aerial vehicle with rigid wings. The wing dihedral alone can be varied asymmetrically to perform rapid turns and regulate sideslip. The maximum attainable turn rate for a given elevator setting, however, does not increase unless antisymmetric wing twisting is employed.


Item Type:Article
Related URLs:
URLURL TypeDescription
http://dx.doi.org/10.2514/1.J051447DOIArticle
http://arc.aiaa.org/doi/10.2514/1.J051447PublisherArticle
ORCID:
AuthorORCID
Paranjape, Aditya A.0000-0002-3164-3215
Chung, Soon-Jo0000-0002-6657-3907
Additional Information:© 2012 American Institute of Aeronautics and Astronautics, Inc. Received 21 June 2011; revision received 13 September 2011; accepted for publication 4 November 2011. Presented as Paper 2010-7937 at the AIAA Atmospheric Flight Mechanics Conference, Toronto, Ontario, 2–5 August 2010. This project was supported by the Air Force Office of Scientific Research under the Young Investigator Award Program (grant no. FA95500910089) monitored by Willard Larkin. The original problem was posed by Gregg Abate [Air Force Research Laboratory (AFRL)]. This paper also benefitted from stimulating discussions with Johnny Evers (AFRL).
Group:GALCIT
Funders:
Funding AgencyGrant Number
Air Force Office of Scientific Research (AFOSR)FA95500910089
Issue or Number:5
Record Number:CaltechAUTHORS:20161130-095641127
Persistent URL:https://resolver.caltech.edu/CaltechAUTHORS:20161130-095641127
Official Citation:Aditya A. Paranjape, Soon-Jo Chung, Harry H. Hilton, and Animesh Chakravarthy. "Dynamics and Performance of Tailless Micro Aerial Vehicle with Flexible Articulated Wings", AIAA Journal, Vol. 50, No. 5 (2012), pp. 1177-1188. http://dx.doi.org/10.2514/1.J051447
Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:72434
Collection:CaltechAUTHORS
Deposited By: Ruth Sustaita
Deposited On:30 Nov 2016 19:38
Last Modified:09 Mar 2020 13:19

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