Effect of ice accretion on aircraft flight dynamics

Bragg, Michael B.; Hutchison, Tim; Merret, Jason M.

doi:10.2514/6.2000-360

Cited by 112 publications

(91 citation statements)

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“…Finally, the icing effect is modeled as an additive timedependent disturbance E(u,w,q)η, where η is the icing severity factor [25], and E(u,w,q) is given by [16]:…”

Section: Quasi-lpv Model Of the Uav Subject To Icing/faultsmentioning

confidence: 99%

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Detection of icing and actuators faults in the longitudinal dynamics of small UAVs using an LPV proportional integral unknown input observer

Rotondo

Cristofaro

Johansen

et al. 2016

2016 3rd Conference on Control and Fault-Tolerant Systems (SysTol)

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Abstract-This paper proposes a linear parameter varying proportional integral unknown input observer (PI-UIO) for the diagnosis of actuator faults and icing in unmanned aerial vehicles. It is shown that in presence of sensor noise, the proposed PI-UIO has the advantage of being affected by the noise, but not by its derivative. Another contribution of the paper is the introduction of an icing to wind/noise ratio, which allows performing an optimal tuning of some PI-UIO design parameters. Results obtained with a Zagi Flying Wing simulator are used to validate the effectiveness of the proposed approach.

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“…Finally, the icing effect is modeled as an additive timedependent disturbance E(u,w,q)η, where η is the icing severity factor [25], and E(u,w,q) is given by [16]:…”

Section: Quasi-lpv Model Of the Uav Subject To Icing/faultsmentioning

confidence: 99%

“…where the coefficients K i depend on aircraft design and operating conditions [25]. The undesired effects are added as additive terms (unknown inputs) in the LPV state equation (1), modifying it as follows:…”

Section: Quasi-lpv Model Of the Uav Subject To Icing/faultsmentioning

confidence: 99%

Detection of icing and actuators faults in the longitudinal dynamics of small UAVs using an LPV proportional integral unknown input observer

Rotondo

Cristofaro

Johansen

et al. 2016

2016 3rd Conference on Control and Fault-Tolerant Systems (SysTol)

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“…Table 2 lists the coefficients used in this work, for different icing configurations: wing icing, tail icing and full icing. It is worth remarking that these coefficients have been computed by mimicking the proportional variation of the stability and control derivatives for a Twin Otter aircraft (Bragg et al, 2002), and they are expected to differ in the case of other UAVs. These values are used in the simulator in order to provide realistic icing effects.…”

Section: Icing Effectsmentioning

confidence: 99%

“…The accretion of ice on the UAV surfaces modifies the stability and control derivatives according to the following linear model (Bragg et al, 2002):…”

Section: Icing Effectsmentioning

confidence: 99%

Icing diagnosis in unmanned aerial vehicles using an LPV multiple model estimator * *D. Rotondo acknowledges that this work was carried out during the tenure of an ERCIM Alain Bensoussan Fellowship Programme. This work was also supported by the Research Council of Norway through the Centers of Excellence funding scheme, Project number 223254 - Centre for Autonomous Marine Operations and Systems (NTNU-AMOS)

et al. 2017

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The phenomenon of icing, i.e. ice accretion on aircraft surfaces, affects the flight performance of unmanned aerial vehicles (UAVs). Autonomous icing detection schemes are needed in order to assure high efficiency and limit energy consumption of de-icing and anti-icing schemes. The novel contribution of this paper is to apply a linear parameter varying multiple model adaptive estimator to the model of the longitudinal nonlinear dynamics of a UAV, in order to achieve an icing diagnosis that provides information about the icing location. An advantage of applying a linear parameter varying approach is that the icing diagnosis scheme is consistent with the UAV dynamics for a wide range of operating conditions, and it uses only existing standard sensors. Simulation results are used to illustrate the application of the proposed method.

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“…A six degree-offreedom simulation has been developed for this purpose. 3,4 This paper presents continued development of this capability and uses it to explore the effect of atmospheric disturbances on characterization and initial research on envelope protection.…”

Section: Introductionmentioning

confidence: 99%

Envelope protection and atmospheric disturbances in icing encounters

Merret

Hossain²,

Bragg³

2002

40th AIAA Aerospace Sciences Meeting &Amp; Exhibit

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Research is reported on aircraft performance and control in icing, related to the development of Smart Icing Systems for improved flight safety. Microburst and gravity wave atmospheric disturbances were modeled, and their effects on the aircraft performance and control were compared to that of an icing encounter. Simulations were run using a six degreeof-freedom computational flight dynamics model. The study showed that microbursts could easily be differentiated from icing encounters. On the other hand gravity waves are more difficult to differentiate. A plan was formulated for developing an envelope protection system effective in icing conditions. Two dimensional airfoil data were analyzed and showed promising results for prediction of envelope limit exceedence. Changes in unsteady hinge moments were especially effective in predicting stall.

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Effect of ice accretion on aircraft flight dynamics

Cited by 112 publications

References 0 publications

Detection of icing and actuators faults in the longitudinal dynamics of small UAVs using an LPV proportional integral unknown input observer

Detection of icing and actuators faults in the longitudinal dynamics of small UAVs using an LPV proportional integral unknown input observer

Envelope protection and atmospheric disturbances in icing encounters

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