Experimental Studies on a Propelled Micro Air Vehicle

Durai, Arivoli; Dodamani, Ravi; Antony, Roshan; Chitlur, Suraj; Gopalan, Ramesh; Ahmed, Saeed

doi:10.2514/6.2011-3656

Cited by 9 publications

(3 citation statements)

References 3 publications

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“…Sungjin Choi found, that aerodynamic efficiency metered by lift to drag ratio decreased by 2% in the case of pusher propeller on MAV [16]. Arivoli Durai found significant effect of propeller slipstream during experimental studies of MAV on lift, drag and stall angle once the propeller was installed in tractor configuration [33]. Deng found, that at lower AoA, micro aerial vehicle was submerged with propeller vortex ring whereas, at higher AoA, wing tip vortex structure had a major contribution to flow physics [34].…”

Section: Effects Of Propeller Helical System On Aircraft Aerodynmentioning

confidence: 98%

Experimental Investigation of Propeller Induced Flow on Flying Wing Micro Aerial Vehicle for Improved 6DOF Modeling

et al. 2020

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In this research effect of propeller induced flow on aerodynamic characteristics of low aspect ratio flying wing micro aerial vehicle has been investigated experimentally in subsonic wind tunnel. Left turning tendencies of right-handed propellers have been discussed in literature, but not much work has been done to quantify them. In this research, we have quantified these tendencies as a change in aerodynamic coefficient with a change in advance ratio at a longitudinal trim angle of attack using subsonic wind tunnel. For experimental testing, three fixed pitch propeller diameters (5 inch, 6 inch and 7 inch), three propeller rotational speeds (7800, 10800 and 12300 RPMs) and three wind tunnel speeds (10, 15 and 20 m/s) have been considered to form up 27 advance ratios. Additionally, wind tunnel tests of 9 wind mill cases were conducted and considered as baseline. Experimental uncertainty assessment for measurement of forces and moments was carried out before conduct of wind tunnel tests. Large variation in lift, drag, yawing moment and rolling moment was captured at low advance ratios, which indicated their significance at high propeller rotational speeds and large propeller diameters. Side force and pitching moment did not reflect any significant change. L D at trim point was found a nonlinear function of propeller diameter to wingspan ratio D b , and propeller rotational speed. Rate and control derivatives were obtained using unsteady vortex lattice method with propeller induced flow effect modeled by Helical Vortex Modeling approach. In this research, we have proposed improved 6-DOF equations of motion, with a contribution of advance ratio J. It is concluded, that propeller induced flow effects have a significant contribution in flight dynamic modeling for vehicles with large propeller diameter to wingspan ratio, D b of 22% or more. INDEX TERMS Advance ratio, aerodynamic characteristics, flying wing micro aerial vehicle, Propeller induced flow, , wind tunnel testing, 6DOF Modeling

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Section: Effects Of Propeller Helical System On Aircraft Aerodynmentioning

confidence: 98%

Experimental Investigation of Propeller Induced Flow on Flying Wing Micro Aerial Vehicle for Improved 6DOF Modeling

et al. 2020

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“…The coefficients K 2 , K 1 and K 0 are second order polynomials of β and determined based on experimental data of a micro air vehicle [18]. Only the units of side slip angle and angle of attack are degree in Eq.…”

Section: Iic Applied Forces and Momentsmentioning

confidence: 99%

Controllability Analysis of a Mass-Actuated Airplane

Erturk

Dogan

2015

AIAA Atmospheric Flight Mechanics Conference

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This paper is to follow up on prior work on a mass-actuated airplane that is controlled by internally moving masses instead of conventional control surfaces. The mass-actuated aircraft effectively has two control variables: the internal positions of two control masses, one of which is moved longitudinal along the body x-axis and the other is moved laterally along the wings. Prior works showed feasible trim results of mass actuated airplane during straight level flight and steady state turn with and without side slip angle at constant altitude. This work investigates the controllability of the aircraft with mass actuation. Furthermore, to determine quality or level of controllability by mass-actuation as compared to that by aerodynamic control surfaces, two different methods are used: (i) a measure of controllability based on controllability Gramian and (ii) values of pertaining entries in control/input matrix.

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“…where the last three terms of C D expression are added to model the contribution of side slip angle on drag. The coefficients K 2 , K 1 and K 0 are second order polynomials of β and determined based on experimental data of a micro air vehicle [22]. Table . 3.1 consists of the aerodynamic coefficients for the aircraft.…”

Section: Applied Forces and Momentsmentioning

confidence: 99%

Development and Flight Test of Moving-mass Actuated Unmanned Aerial Vehicle

Vengate

2016

AIAA Atmospheric Flight Mechanics Conference

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Conventional airplane control is achieved by aerodynamic control surfaces by generating moments around all the three axes of the aircraft. Deflections of the control surfaces have some disadvantages such as induced drag, increase in radar signature, and exposure to high temperature in high speed applications. As an alternative moment generation mechanism, prior research proposed internal mass-actuation, which is to generate gravitational moment by changing the center of gravity of the aircraft through motion of internal masses within the aircraft. Prior research investigated the feasibility and benefit of internal mass-actuation in airplane control based on simulation analysis. The main focus of this research is to design, build and flight test a UAV (Unmanned Aerial Vehicle) with internal mass-actuation, as a proof-of-concept.Specifically, this effort has built and flight tested a small electric powered UAV with an internal mass within each wing to generate rolling moment instead of aerodynamic rolling moment by ailerons. The internal structure of each wing is specifically designed to place a linear electric actuator that moves the internal mass. The aircraft is also equipped with all three conventional control surfaces. Most parts of the airplane were laser cut based on 3D CAD designs. The airplane is also equipped with a data acv quisition system to record flight data during the flight test. The RC (radio control) transmitter is programmed to switch between aileron-actuation and mass-actuation. During test flights, an RC operator flew the airplane to a steady level flight at a safe altitude, and then switch to mass-actuation and put the airplane in steady-turn. The flight tests has successfully demonstrated the feasibility of flying the airplane with mass-actuation instead of ailerons. viTABLE OF CONTENTS

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Experimental Studies on a Propelled Micro Air Vehicle

Cited by 9 publications

References 3 publications

Experimental Investigation of Propeller Induced Flow on Flying Wing Micro Aerial Vehicle for Improved 6DOF Modeling

Experimental Investigation of Propeller Induced Flow on Flying Wing Micro Aerial Vehicle for Improved 6DOF Modeling

Controllability Analysis of a Mass-Actuated Airplane

Development and Flight Test of Moving-mass Actuated Unmanned Aerial Vehicle

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