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

Lampton, Amanda; Valasek, John

doi:10.2514/1.31165

Cited by 16 publications

(9 citation statements)

References 24 publications

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“…( ) is the original dynamical parameter that connects with icing. As noted in [23], the icing parameter ranges from 0 to max . If =0, it represents the aircraft has not encountered icing conditions and is considered clean.…”

Section: Iced Aircraft Modelmentioning

confidence: 99%

Safety Analysis for Icing Aircraft during Landing Phase Based on Reachability Analysis

Zhou

Zheng

et al. 2018

Mathematical Problems in Engineering

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Icing is one of the leading causes of fatal aircraft accidents worldwide. Encountering icing conditions, dynamic characteristics of the aircraft will be damaged, thereby greatly affecting flight safety. Research on real-time estimations of the safety envelope under icing conditions is critical to improve flight safety. In order to determine the safety envelope, the reachability analysis based on the level set method is presented. The reachable set is obtained via computing the Hamilton-Jacobi partial differential equation (HJPDE), which is based on optimal control and is used in the landing phase of an aircraft. The results show that icing will shrink the safety envelope. Particularly under severe icing conditions, the stall speed of the aircraft will increase, and dynamic behavior will be more sensitive. A slight change of command by the pilot may contribute to the flight state moving outside the safety envelope. Furthermore, the effect of flap deflection was considered, which positively impacts the expanding safety envelope during the landing phase. Finally, a maneuvering coping strategy based on safety envelope is proposed. Examples are provided using the NASA’s generic transport model (GTM), and the results can be applied to flight safety risk assessment, providing theoretical guidance for the design of envelope protection systems.

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Section: Iced Aircraft Modelmentioning

confidence: 99%

Safety Analysis for Icing Aircraft during Landing Phase Based on Reachability Analysis

Zhou

Zheng

et al. 2018

Mathematical Problems in Engineering

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“…Tail stalls are dangerous and a pilot should be ready for them since ice can build up faster on the tail section than on the wing. Also, roll upsets may occur as a result of ice creating forces that cause the ailerons to deflect [28].…”

Section: Chapter 2-literature Review 21 the Icing Phenomenonmentioning

confidence: 99%

“…The problem can be approached in a couple different ways. One such way is to use data from a known aircraft to create a state-space representation at nominal conditions [28]. Icing effects for such a model can be implemented by modifying the existing stability and control derivatives (or the system matrices), which are typically provided in the form of lookup tables.…”

Section: Computational Icing Researchmentioning

confidence: 99%

“…In order to use this aircraft model for this application, icing data would have to be found that could be applied to the aircraft. The next step taken was to determine the aircraft's airfoil shape and it was found to be a NACA 23014 at the wing's root and a NACA 23012 shape at the wing's tip [28]. Ultimately icing data for a NACA 23012 was found and determined to be useable because ice accretions tend to build up at the wing tips first.…”

Section: Aircraft Selectionmentioning

confidence: 99%

“…Therefore, it was necessary to use two methods of modifying aircraft aerodynamic parameters. Additional information from the literature on predicted icing effects on light aircraft [28] revealed that the stability derivatives of the aircraft were modified by a percentage based on exposure to icing conditions. Other research with the Dehavilland Twin Otter has used similar processes of modifying an aircraft stability or control derivative by a percentage based on icing conditions [4].…”

Section: Icing Model Equationsmentioning

confidence: 99%

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A Simplified Icing Model for Simulation and Analysis of Dynamic Effects

Cunningham¹

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A Simplified Icing Model for Simulation and Analysis of Dynamic Effects Matthew A. Cunningham Ice accretions on aerodynamic surfaces are a major concern during flight. In this research effort, glaze ice is being modeled and its effects on aircraft dynamics analyzed. This type of ice builds up as a clear layer on aerodynamic surfaces and other components such as antennas and intakes. Glaze icing is dangerous because as the amount of ice increases, it alters the shape and properties of the aerodynamic surface. Wind tunnel tests of this type of icing and data analysis have shown that the main effects of icing consist of decrease of lift coefficient, reduction of stall angle of attack, increase in drag coefficient, reduction of control surface effectiveness, and degradation of stability characteristics. In some instances, icing can produce significant gravimetric alterations and aerodynamic control surface lockage. Based on these conclusions, a simplified icing model has been developed as part of a simulation package for aircraft health management instruction. The objective of this simulation package is to offer an interactive educational environment for experimentation, demonstration, and analysis of flight at both nominal and abnormal conditions. This icing model is expected to provide computationally effective tools primarily for the study of dynamic effects of ice accretions on aircraft performance, handling qualities, and pilot workload. Experimental wind tunnel data under icing conditions were used to develop regression models for the lift and drag coefficients. Linear variation with time in icing was considered for the degradation of stability and control derivatives. The simplified icing model has been integrated with a business jet real-time simulation model since this type of aircraft is frequently subjugated to icing conditions. The impact of icing on aircraft is analyzed via simulation and observation of modal parameters. During steady state flight, linearization is performed to obtain stability matrices and their eigenvalues are used to determine and study the modal parameters on both the longitudinal and lateral-directional channels. In addition, the performance analysis studies the aircraft capabilities to maintain steady level symmetric and asymmetric flight. Also, an examination of the aircraft longitudinal and lateral-directional handling qualities compared to specifications for Class II aircraft in phase B flight conditions was considered. Numerical simulations have revealed that the icing model behaves qualitatively as expected. While the time under icing conditions increases, the aircraft becomes much more difficult to control and a steady level flight condition can no longer be maintained after approximately three minutes when the throttle command saturates. Continued exposure to icing conditions results in approaching stall conditions and/or loss of altitude. The modal parameter analysis shows a degradation of handling qualities for both longitudinal and lateral-directional channels. The larges...

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Unmanned Aerial Vehicle Flight Control Evaluations Under Sensor and Actuator Faults

Ashokkumar

York

2017

J Intell Robot Syst

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

Cited by 16 publications

References 24 publications

Safety Analysis for Icing Aircraft during Landing Phase Based on Reachability Analysis

Safety Analysis for Icing Aircraft during Landing Phase Based on Reachability Analysis

A Simplified Icing Model for Simulation and Analysis of Dynamic Effects

Unmanned Aerial Vehicle Flight Control Evaluations Under Sensor and Actuator Faults

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