Real-Time Flight Simulation of Highly Maneuverable Unmanned Aerial Vehicles

Selig, Michael S.

doi:10.2514/1.c032370

Cited by 45 publications

(17 citation statements)

References 50 publications

(66 reference statements)

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“…[25][26][27][28][29][30] This method has the ability to account for non-linear effects associated with the stall regime and will be used in this study. To properly simulate an aircraft in stall, both steady and unsteady effects need to be modeled.…”

Section: Introductionmentioning

confidence: 99%

Stall/Post-Stall Modeling of the Longitudinal Characteristics of a General Aviation Aircraft

Ananda

Selig

2016

AIAA Atmospheric Flight Mechanics Conference

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The high rate of accidents in general aviation due to pilot loss of control has necessitated the need to find better methods of training pilots. Pilot control and awareness in the stall/post-stall regime can be improved through the use of higher fidelity flight simulators. To create a high fidelity aerodynamic model in the stall/post-stall regime to be implemented in a flight simulator, both steady and unsteady aircraft characteristics need to be represented. In this paper, the detailed development of a steady-state general aviation aircraft stall/post-stall longitudinal aerodynamic model is described. The steady-state model uses a component buildup approach that uses strip theory to output the aerodynamic forces and moments of an aircraft. An integrated non-linear lifting-line theory approach is used to model the wing and horizontal tail. Longitudinal effects due to elevator deflections are also included. Validation studies are performed against static wind tunnel datasets for a typical single-engine low-wing general aviation aircraft design. Nomenclatureairfoil moment coefficient at quarter chord C M c/4 = surface moment coefficient at quarter chord (= M/ 1 2 ρV 2 ∞ S ref c) C N = surface normal force coefficient (= N/ 1 2 ρV 2 ∞ S ref ) C n = local normal-force coefficient per unit length * Graduate Student (Ph.D. Candidate), 104 S. Wright St., AIAA Student Member. anandak1@illinois.edu † Professor, 104 S. Wright St., AIAA Associate Fellow. m-selig@illinois.edu 1 of 25 American Institute of Aeronautics and Astronautics Downloaded by PURDUE UNIVERSITY on June 22, 2016 | http://arc.aiaa.org | AIAA Aviation d F = fuselage cross-section diameter D = drag D ind = induced drag k = corner radius l ref = reference length l F = fuselage length L = lift M = moment n P = number of lifting surface panels N = normal force r F = fuselage cross-section radius Re = Reynolds number based on mean aerodynamic chord (= V ∞ c/ν) S = lifting surface area S f = flap area S ref = reference area V ∞ = freestream velocity V F = fuselage volume w ind = velocity induced by shed vortices V rel = relative velocity w F = fuselage width x F = axial distance from fuselage nose x ac F = distance from nose to aerodynamic center of fuselage x c F = distance from nose to centroid of fuselage planform area x m F = distance from nose to centroid of fuselage pitching-moment reference center x P S , y P S , z P S = location of spanwise panel station points x LLT , y LLT , z LLT = location of lifting-line points Y = side force α ef f = effective angle of attack α geo = geometric angle of attack α ind = induced angle of attack β = sideslip angle δ f = flap deflection angle η = flap effectiveness correction factor η f use = fuselage crossflow drag proportionality factor Γ = circulation Γ 0 = circulation at center-span Γ LLT = circulation at the lifting-line points Γ SV = shed vortex circulation τ = flap effectiveness factor θ f = factor relating flap to chord ratio to flap effectiveness factor ν = kinematic viscosity ρ = density of air Subscripts c/4 = ...

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Section: Introductionmentioning

confidence: 99%

Stall/Post-Stall Modeling of the Longitudinal Characteristics of a General Aviation Aircraft

Ananda

Selig

2016

AIAA Atmospheric Flight Mechanics Conference

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“…The shortcoming lies in the fact that a horizontal stabilizer and its elevator require sufficient air-flow in order to effectively actuate flight controls. For that reason, most aerobatic fixed-wing aircrafts are de-signed such that the control surfaces are immersed in propeller wash so that they are able to perform many of the signature post-stall aerobatic maneuvers such as prop-hang (vertical hover), flatspin, blender, harrier, tailslide, waterfall and their derivatives [2] [3] [4] [5]. The aerobatic maneuvers most relevant to this work are harrier and waterfall.…”

Section: Introductionmentioning

confidence: 99%

“…The aerobatic maneuvers most relevant to this work are harrier and waterfall. The harrier maneuver is one in which the aircraft flies in its post-stall regime in trim at high angles of attack near 45˚ with nose-up elevator input [5]. This maneuver relies on lift from the wing and the vertical component of propeller thrust in order to sustain level trimmed flight [5].…”

Section: Introductionmentioning

confidence: 99%

“…The harrier maneuver is one in which the aircraft flies in its post-stall regime in trim at high angles of attack near 45˚ with nose-up elevator input [5]. This maneuver relies on lift from the wing and the vertical component of propeller thrust in order to sustain level trimmed flight [5]. A distinctive characteristic of these aircraft is the thrust-to-weight ratio that exceeds unity [2] and therefore can potentially be used to create VTOL airplanes with ultra-agility.…”

Section: Introductionmentioning

confidence: 99%

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Roto-Stabilizer for Superb Pitch-Related Post-Stall Maneuvers and STOL

Poh¹,

Poh²

2018

AAST

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Stabilizers and their control surfaces are vital components in maneuvering an airplane during flight. However, a shortcoming of stabilizers is that they require airstream or propeller wash for them to work properly. In this work, we propose the concept of roto-stabilizer as viable substitution for conventional horizontal stabilizer. A key benefit of the proposed technique is its ability to exert powerful moment in the absence of forward airspeed or propeller wash. Proof of principle is demonstrated via computer simulations. Results reveal that new aerobatic maneuvers are made possible. Furthermore, when implemented in canard configuration, it is possible to achieve ultra-STOL and VTOL.

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“…There have been lots of studies and modeling done related to high angle of attack aerodynamics. [1][2][3][4][5][6] However, due to the complexity and risk involved, there have only been a few testbeds that have actually taken flight and recorded experimental data. [7][8][9][10][11] This paper describes high angle of attack flight testing performed by a subscale aerobatic aircraft, the UIUC Subscale Sukhoi, which is a 35% scale, 2.6 m (102 in) wingspan Sukhoi 29S electric aircraft, shown in Fig.…”

Section: Introductionmentioning

confidence: 99%

High Angle of Attack Flight of a Subscale Aerobatic Aircraft

Dantsker

Selig

2015

33rd AIAA Applied Aerodynamics Conference

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This paper describes initial high angle of attack flight testing performed by a subscale aerobatic aircraft. A 35% scale, 2.6 m (102 in) wingspan Sukhoi 29 S electric aircraft, the UIUC Subscale Sukhoi, was developed and used for this research. The aircraft was instrumented with a custom 100 Hz sensor data acquisition system, which had been previously developed and tested. The aircraft was flown through several stalls and descending harrier maneuvers during which flight data was recorded by the sensor data acquisition system. The flight data recorded during the maneuvers was used to produce time histories of aircraft state and aerodynamic coefficients. A brief literature review of similar aerobatic unmanned aircraft used for high angle of attack research is first presented. Then a background and a description of the development of the aircraft are given along with specifications. Next, information about data analysis methods used to analyze flight test data is given. After that, initial test flight results are presented, including flight path trajectory plots, time histories and aircraft aerodynamic coefficient data. Finally a list of proposed future work is given.

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Real-Time Flight Simulation of Highly Maneuverable Unmanned Aerial Vehicles

Cited by 45 publications

References 50 publications

Stall/Post-Stall Modeling of the Longitudinal Characteristics of a General Aviation Aircraft

Stall/Post-Stall Modeling of the Longitudinal Characteristics of a General Aviation Aircraft

Roto-Stabilizer for Superb Pitch-Related Post-Stall Maneuvers and STOL

High Angle of Attack Flight of a Subscale Aerobatic Aircraft

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