Performance degradation of a typical twin engine commuter type aircraft in measured natural icing conditions

Ranaudo, Richard J.; Mikkelsen, Kevin L.; Mcknight, R. C.; Perkins, P. J.

doi:10.2514/6.1984-179

Cited by 20 publications

(7 citation statements)

References 3 publications

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“…In the medium speed range, the TWR req -increase leads to a noticeable reduction of SEP in Fig. 3b, which is in accordance with the expectations from literature [4,21,39,40] and reported occurrences in the past [2,22,23,41].…”

Section: Ice-induced Limitations Of Aircraft Flight Performancesupporting

confidence: 91%

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Comparison of Flight Characteristics of Two Different Airplanes and Ice Configurations

Deiler

2020

Journal of Aircraft

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Section: Ice-induced Limitations Of Aircraft Flight Performancesupporting

confidence: 91%

“…1) Due to the homogeneous and reliable model behavior concerning the flight performance degradation (in accordance with the results of previous studies, e.g., Refs. [4,39,40]), the confidence in a correct model formulation and implementation is strengthened.…”

Section: Ice-induced Limitations Of Aircraft Flight Performancementioning

confidence: 99%

Comparison of Flight Characteristics of Two Different Airplanes and Ice Configurations

Deiler

2020

Journal of Aircraft

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“…The aircraft model used in this paper is a model of the DHC-6 Twin Otter. This aircraft was chosen because it has a rich modeling history, which includes aerodynamic coefficient changes dues to wing icing [31]. The aerodynamic coefficients are from [29].…”

Section: Appendix: Aircraft Modelmentioning

confidence: 99%

Fast Computable Recoverable Sets and Their Use for Aircraft Loss-of-Control Handling

McDonough

Kolmanovsky

2017

Journal of Guidance, Control, and Dynamics

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The paper describes a framework for constrained flight control based on the use of recoverable sets that are chained together to guide constrained admissible transitions between trim points. The recoverable set is the set of all states for which there exists a control sequence such that the subsequent response is guaranteed to satisfy the imposed constraints. The constraints can reflect actuator range/rate limits, safety limits, as well as ranges of validity of the aircraft model. Because in aircraft loss-of-control situations, fast onboard computations are necessary, the approach to computing recoverable sets in this paper exploits linear discrete-time models (which can be generated via onboard system identification and reflect effects of failures and degradations) and recovery sequences generated, either by a stable linear finite-dimensional subsystem or through a reset of the dynamic controller states or of its set points. With this approach, only subsets of the full recoverable set can be computed, however, these recoverable subsets possess certain desirable control invariance properties, and their computations are simple; moreover, the onboard generation of the recovery sequence reduces to a low-dimensional quadratic programming problem. The applications of this approach to longitudinal and lateral linearized and nonlinear aircraft flight models are reported.

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“…Extensive research has been conducted to study the effects of icing through flight tests, wind tunnel tests and simulations [4,5,11,13,19,21,25,28,33]. It was shown that ice accretion increases drag significantly even in short exposure times [4,25,33], affecting especially the lift-independent component [33]. Icing was also found to reduce the maximum lift coefficient, lift curve gradient and stall angle of attack [10].…”

Section: Introductionmentioning

confidence: 99%

“…Aircraft likely to encounter icing conditions in their routine operations are equipped with ice protection systems (IPS), which reduce but do not eliminate the effects of icing [25] and thus can allow for flight in icing conditions up to a certain severity. Currently, however, the activation and operation of the IPS relies largely on the pilot's judgement and view of the airframe.…”

Section: Introductionmentioning

confidence: 99%

Decision-making for unmanned aerial vehicle operation in icing conditions

et al. 2016

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With the increased use of unmanned aerial systems (UAS) for civil and commercial applications, there is a strong demand for new regulations and technology that will eventually permit for the integration of UAS in unsegregated airspace. This requires new technology to ensure sufficient safety and a smooth integration process. The absence of a pilot on board a vehicle introduces new problems that do not arise in manned flight. One challenging and safety-critical issue is flight in known icing conditions. Whereas in manned flight, dealing with icing is left to the pilot and his appraisal of the situation at hand; in unmanned flight, this is no longer an option and new solutions are required. To address this, an icing-related decision-making system (IRDMS) is proposed. The system quantifies in-flight icing based on changes in aircraft performance and measurements of environmental properties, and evaluates what the effects on the aircraft are. Based on this, it determines whether the aircraft can proceed, and whether and which available icing protection systems should be activated. In this way, advice on an appropriate response is given to the operator on the ground, to ensure safe continuation of the flight and avoid possible accidents.

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Performance degradation of a typical twin engine commuter type aircraft in measured natural icing conditions

Cited by 20 publications

References 3 publications

Comparison of Flight Characteristics of Two Different Airplanes and Ice Configurations

Comparison of Flight Characteristics of Two Different Airplanes and Ice Configurations

Fast Computable Recoverable Sets and Their Use for Aircraft Loss-of-Control Handling

Decision-making for unmanned aerial vehicle operation in icing conditions

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