A Powered Lift Aerodynamic Analysis for the Design of Ducted Fan UAVs

Guerrero, Ignacio; Londenberg, Kelly; Gelhausen, Paul; Myklebust, A.; Llc, Avid

doi:10.2514/6.2003-6567

Cited by 51 publications

(29 citation statements)

References 2 publications

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“…The force generated by a ducted fan is modeled based on models in references [9], [10] and [11]. The fundamental model of a ducted fan is introduced first, then it is extended to the VTAV case.…”

Section: Dynamical Model a Rigid Body Modelmentioning

confidence: 99%

Hovering control of vectored thrust aerial vehicles

Kumon

Cover

Katupitiya

2010

2010 IEEE International Conference on Robotics and Automation

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In this paper, a vectored thrust aerial vehicle(VTAV) that has three ducted fans is considered. Since ducted fans are powerful and effective in providing lift, they are suitable for thrusters of UAVs, but modeling their aerodynamic effects such as ram drag is very difficult. The VTAV has one ducted fan fixed to its body and two ducted fans that can be tilted in order to make rotational moments, which makes the system dynamics even more complicated. This paper focuses on giving a precise dynamical model that includes aerodynamic effects of ducted fans. Then it presents a hovering controller based on the dynamical model developed. Since the horizontal dynamics are under actuated, a switching control approach is introduced to realize a stabilizing controller. Numerical simulations prove the validity of the approach.

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Section: Dynamical Model a Rigid Body Modelmentioning

confidence: 99%

Hovering control of vectored thrust aerial vehicles

Kumon

Cover

Katupitiya

2010

2010 IEEE International Conference on Robotics and Automation

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“…The superposition of all elements of the model, taking into account any appropriate interaction effects, then yields the summation of all forces and moments acting on the total vehicle airframe. This general approach has been applied to a wide range of problems in modeling and simulation, for example, propellerdominated UAV flight dynamics, 5,6,15 ducted fan configurations, 16 autonomous underwater vehicles, 17 wingonly tumbling analysis, 18 high angle of attack longitudinal aircraft trim analysis, 19 and post-stall flight dynamics and upset modeling [20][21][22][23][24] to name a few.…”

Section: Introductionmentioning

confidence: 99%

Modeling Full-Envelope Aerodynamics of Small UAVs in Realtime

Selig

2010

AIAA Atmospheric Flight Mechanics Conference

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This paper focuses on full six degree-of-freedom (6-DOF) aerodynamic modeling of small UAVs at high angles of attack and high sideslip in maneuvers performed using large control surfaces at large deflections for aircraft with high thrust-to-weight ratios. Configurations such as this include many of the currently available propellerdriven RC-model airplanes that have control surfaces as large as 50% chord, deflections as high as 50 deg, and thrust-to-weight ratios near 2:1. Airplanes with these capabilities are extremely maneuverable and aerobatic, and modeling their aerodynamic behavior requires new thinking because using traditional stability derivative methods is not practical with highly nonlinear aerodynamic behavior and coupling in the presence of high propwash effects. The method described in this paper outlines a component-based approach capable of modeling these extremely maneuverable small UAVs in a full 6-DOF realtime environment over the full envelope that is defined in this paper to be the full ±180 deg range in angle of attack and sideslip. This method is the foundation of the aerodynamics model used in the RC flight simulator FS One. Piloted flight simulation results for four small RC/UAV configurations having wingspans in the range 826 mm (32.5 in) to 2540 mm (100 in) are presented to highlight results of the high-angle aerodynamics modeling approach. Maneuvers simulated include tailslides, knife edge flight, high-angle upright and inverted flight ("harriers"), rolling maneuvers at high angle ("rolling harriers") and an inverted spin of a biplane ("blender"). For each case, the flight trajectory is presented together with time histories of aircraft state data during the maneuvers, which are discussed. Nomenclature,c/4 = moment coefficient about quarter chord D = drag; propeller diameter J = propeller advance ratio based on V N L = lift M = pitching moment about y-axis (positive nose up) n = propeller rotational speed (revs/sec) * Associate Professor, Department of Aerospace Engineering, 104 S. Wright St. Senior Member AIAA.= propeller yawing moment due to angle of attack p, q, r = roll, pitch and yaw rate P N = propeller normal force due to angle of attack Q = propeller axial torque q = dynamic pressure (ρV 2 /2) R = propeller radius S = reference area T = propeller axial thrust u, v, w = components of the local relative flow velocity along x, y, z, respectively V = flow velocity x, y, z = body-axis coordinates, +x out nose, +y out right wing, +z down y c = airfoil camber TED = trailing edge down TEL = trailing edge left TEU = trailing edge up Subscripts N = normal component R = relative component Symbols α = angle of attack (arctan(w/u)) β = sideslip angle (arcsin(v/V )) β ′ = angle of attack for vertical surface (arctan(v/u)) δ a = aileron deflection [(δ a,r − δ a,l )/2], right +TEU, left +TEU δ e = elevator deflection, +TED δ r = rudder deflection, +TEL ǫ = wing induced angle of attack η s = dynamic pressure ratio for flow shadow (shielding) effect φ, θ, ψ = bank angle, pitch angle, heading angl...

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“…Helicopters, however, are uneasy to operate in awkward environments due to the exposed rotor blades. Very little has been done on the development of secure platforms (Hamel et al 2002, Fleming et al 2003, Guerrero et al 2003. Such platforms have considerable potential for surveillance and inspection roles in dangerous or constrained environments.…”

Section: Introductionmentioning

confidence: 99%

Position control of a ducted fan VTOL UAV in crosswind

Pflimlin

Souères

Hamel

2007

International Journal of Control

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This paper describes a control strategy to stabilize the position of a vertical takeoff and landing (VTOL) unmanned aerial vehicle (UAV) in crosswind despite unknown aerodynamic effects. The proposed approach overcomes the problem of gyroscopic coupling by taking advantage of both the structure of the thrust mechanism, which is made of two counter rotating propellers, and the control strategy which involves a decoupling of the yaw rate dynamics from the rest of the system dynamics. The controller is designed by means of backstepping techniques that allow the stabilization of the vehicle's position while online estimating the unknown aerodynamic effects.

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A Powered Lift Aerodynamic Analysis for the Design of Ducted Fan UAVs

Cited by 51 publications

References 2 publications

Hovering control of vectored thrust aerial vehicles

Hovering control of vectored thrust aerial vehicles

Modeling Full-Envelope Aerodynamics of Small UAVs in Realtime

Position control of a ducted fan VTOL UAV in crosswind

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