Aircraft Climbing Flight Dynamics with Simulated Ice Accretion

Sibilski, Krzysztof; Lasek, Maciej; Maryniak, Jerzy

doi:10.2514/6.2004-4948

Cited by 13 publications

(9 citation statements)

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“…The research described in [9] concerns the dangerous reduction in stall angle of attack and how climbing at high angles of attack could approach this reduced stall angle causing an unexpected wing stall. The nonlinear simulation incorporating the effects of ice accretion was set up specifically for a jet trainer in an attempt to project the trajectory of a crash caused by ice accretion [9].…”

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confidence: 99%

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Prediction of Icing Effects on the Dynamic Response of Light Airplanes

Lampton

Valasek

2007

Journal of Guidance, Control, and Dynamics

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The accumulation of ice on an airplane in flight is one of the leading contributing factors to general aviation accidents. To date, only relatively sophisticated methods based on detailed empirical data and flight data exist for its analysis. This paper develops a methodology and simulation tool for preliminary safety and performance evaluations of airplane dynamic response and climb performance in icing conditions. The important aspect of dynamic response sensitivity to pilot control input with the autopilot disengaged is also highlighted. Using only basic mass properties, configuration, propulsion data, and known icing data from a similar configuration, icing effects are applied to the dynamics of a non-real-time, six degree-of-freedom simulation model of a different, but similar, light airplane. Besides evaluating various levels of icing severity, the paper addresses distributed icing which consists of wing alone, horizontal tail alone, and unequal distributions of combined wing and horizontal tail icing. Results presented in the paper for a series of simulated climb maneuvers with various levels and distributions of ice accretion show that the methodology captures the basic effects of ice accretion on pitch response and climb performance, and the sensitivity of the dynamic response to pilot control inputs. Nomenclature= arbitrary stability and control derivative C A iced = arbitrary stability and control derivative with icing effectshe has been with Texas A&M University, where he is Associate Professor of aerospace engineering, and Director of the Flight Simulation Laboratory. He teaches courses on digital control, nonlinear systems, flight mechanics, aircraft design, and coteaches a short course on digital flight control for the University of Kansas Division of Continuing Education. Current research interests include control of morphing air and space vehicles, multi-agent systems, intelligent autonomous control, vision-based navigation systems, and fault-tolerant adaptive control. He is an Associate Fellow of AIAA, past Chairman and current member of the Atmospheric Flight c = mean geometric chord D = carry through matrix f ice = icing factor g = gravitational acceleration h = integration step size I yy = airplane moment of inertia about y axis i = index, imaginary component j = imaginary component k 0 C A = coefficient icing factor constant L = roll angular acceleration M = pitch angular acceleration; modal matrix N = yaw angular acceleration nframes = number of time steps P = airplane body-axis roll rate p = perturbed airplane body-axis roll rate Q = airplane body-axis pitch rate q = perturbed airplane body-axis pitch rate _ q = airplane body-axis pitch acceleration q = dynamic pressure R = airplane body-axis yaw rate r = perturbed airplane body-axis yaw rate S = wing area t = time U = airplane velocity in the body-axis x direction U = control input vector u = stability axis airplane velocity in the x direction _ u = incremental change in the stability axis airplane velocity in the x direction V = airplane...

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confidence: 99%

“…The area of forensic engineering is also concerned with the effect ice has on climb performance and aerodynamic degradation [9]. The research described in [9] concerns the dangerous reduction in stall angle of attack and how climbing at high angles of attack could approach this reduced stall angle causing an unexpected wing stall.…”

mentioning

confidence: 99%

Prediction of Icing Effects on the Dynamic Response of Light Airplanes

Lampton

Valasek

2007

Journal of Guidance, Control, and Dynamics

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“…The research described in Sibilski et al [8] concerns the dangerous reduction in the stall angle of attack and how climbing at high angles of attack could approach this reduced stall angle, causing an unexpected wing stall. The nonlinear simulation incorporating the effects of ice accretion was set up specifically for a jet trainer in an attempt to project the trajectory of a crash caused by ice accretion [8]. Reehorst et al [9] employ Navier-Stokes analysis to test the flowfield and resulting lift and drag produced by a wing section with various ice shapes.…”

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confidence: 97%

“…The resulting increase in drag, decrease in lift, and change in pitching moment is tabulated [11]. In general, the consensus appears to be that the aerodynamics of an airfoil is degraded by ice accretion such that lift decreases, drag increases, stall angle of attack is reduced, and pitching moment is degraded [8,10,[12][13][14][15][16][17].…”

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confidence: 98%

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Prediction of Icing Effects on the Coupled Dynamic Response of Light Airplanes

Lampton

Valasek

2008

Journal of Guidance, Control, and Dynamics

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Most methods for the preliminary safety and performance evaluation of airplane dynamical response, stability characteristics, and climb performance in icing conditions require relatively sophisticated methods, based on detailed empirical data and existing flight data. This paper extends a pitch axis 3-degree-of-freedom methodology to the fully coupled, 6-degree-of-freedom case. It evaluates various levels of icing severity and addresses distributed icing with unequal ice distribution between wing halves on the coupled pitch, roll, and yaw responses. The important aspect of dynamic response sensitivity to pilot control input with the autopilot disabled is also highlighted. Using only basic mass properties, configuration, propulsion data, and known icing data from a similar configuration, icing effects are applied to the 6-degree-of-freedom dynamics of a nonreal-time simulation model of a different, but similar, light airplane. Results presented in the paper for a series of simulated climb maneuvers and cruise disturbances with equal or unequal ice levels between wing halves show that the methodology captures the basic effects of ice accretion on the coupled pitch, roll, and yaw responses and the sensitivity of the dynamic response to pilot control inputs. NOMENCLATURE= arbitrary stability and control derivative C A A iced = arbitrary stability and control derivative with icing effectsicing factor constant with respect to a stability and control derivative L = roll angular acceleration M = pitch angular acceleration N = yaw angular acceleration P = aircraft body-axis roll rate p = perturbed aircraft body-axis roll rate _ p = aircraft body-axis roll acceleration Q = aircraft body-axis pitch rate q = perturbed aircraft body-axis pitch rate _ q = aircraft body-axis pitch acceleration q = dynamic pressure R = aircraft body-axis yaw rate r = perturbed aircraft body-axis yaw rate _ r = aircraft body-axis yaw acceleration S = wing area t = time U = aircraft velocity in the body-axis x direction U = control input vector u = perturbed aircraft stability axis velocity in the x direction _ u = aircraft stability axis acceleration in the x direction V = aircraft velocity in the body-axis y direction W = aircraft velocity in the body-axis z direction _ w = aircraft body-axis acceleration in the z direction X = linear acceleration in the body-axis x direction X = state vector _ X = derivative of state vector Y = linear acceleration in the body-axis y direction Y = output vector Z = linear acceleration in the body-axis z direction = angle of attack _ = rate of change of angle of attack = sideslip angle _ = rate of change of sideslip angle = discrete control distribution matrix = control deflection angle ice = icing severity factor 1 = aircraft steady-state pitch attitude angle = pitch attitude angle _ = rate of change of pitch attitude angle = modal vector = time constant = eigenvector = discrete plant matrix 1 = aircraft steady-state roll attitude angle = roll attitude angle _ = rate of change of roll attitude angle 1 = aircraft...

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Effect of and Protection from Ice Accretion on Aircraft

Wang

2020

Ice Adhesion

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Aircraft Climbing Flight Dynamics with Simulated Ice Accretion

Cited by 13 publications

References 4 publications

Prediction of Icing Effects on the Dynamic Response of Light Airplanes

Prediction of Icing Effects on the Dynamic Response of Light Airplanes

Prediction of Icing Effects on the Coupled Dynamic Response of Light Airplanes

Effect of and Protection from Ice Accretion on Aircraft

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