Icing Detection System - Conception, Development, Testing and Applicability to UAVs

Botura, Galdemir; Fahrner, Alan

doi:10.2514/6.2003-6637

Cited by 12 publications

(8 citation statements)

References 1 publication

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“…The potential damage/crash of UAS caused by in-flight icing renders their operation unfeasible in cold climates. As described in Botura and Fahrner [12], 25% of the UAS flights have encountered icing events in military actions that have negatively impacted the success of the missions. Nowadays, the most common icing avoidance strategies for UAS are to keep UAS on the ground [13] or simply modify the path planning [14], which have greatly reduced the operation capability of UAS in cold climates.…”

Section: Introductionmentioning

confidence: 99%

Effects of Ice Accretion on the Aerodynamic Performance and Wake Characteristics of an UAS Propeller Model

Liu

2018

2018 Atmospheric and Space Environments Conference

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A comprehensive experimental study was performed to investigate the effects of ice accretion on the aerodynamic performances and wake characteristics of a UAS propeller model under different icing conditions (i.e., rime vs. glaze). The experimental study was conducted in the unique Icing Research Tunnel available at Iowa State University (ISU-IRT). In addition to acquiring the key features of ice accretion on the rotating propeller blade using a "phase-locked" imaging technique, the wake characteristics of the rotating UAS propeller under the different icing conditions were also resolved by using the Particle Imaging Velocimetry (PIV) technique along with the time-resolved measurements of aerodynamic forces and power consumption of the UAS propeller model. Both "free-run" and "phaselocked" PIV measurements were performed on the propeller model at different stages of the icing experiments (i.e., before, during and after the dynamic icing processes) to provide both the instantaneous flow characteristics and the ensemble-averaged flow statistics (e.g., mean velocity, vorticity, and turbulence kinetic energy) in the wake of the rotating propeller model. It was found that while the rime ice accretion would closely follow the original profiles of the propeller blades, the glaze ice was formed into very irregular structures (e.g., "lobster-taillike" ice structures) that can significantly disturb the wake flow field of the rotating propeller model, generating the much larger and more complex vortices. Such complex large-scale vortices were found to enhance the turbulent mixing in the propeller wake and produce an evident velocity deficit channel around the outer board of the propeller blades, which provided direct evidences in elucidating the dramatic decrease in thrust generation and the significant increase in power consumption of the rotating propeller model in icing conditions. The findings derived from this study revealed the underlying mechanisms of the aerodynamic performance degradation of the iced UAS propeller, which is of significant importance for the development of innovative, effective anti-/de-icing strategies tailored for UAS icing mitigation and protection to ensure the safer and more efficient UAS operations in atmospheric icing conditions.

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Section: Introductionmentioning

confidence: 99%

Effects of Ice Accretion on the Aerodynamic Performance and Wake Characteristics of an UAS Propeller Model

Liu

2018

2018 Atmospheric and Space Environments Conference

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“…The potential damage of inflight icing to UAS renders their operation unfeasible in cold weather. As described in Botura and Fahrner [13], 25% UAS flights encountered ice during a specific military action that has negatively impacted the success of the mission. The common icing avoidance strategies for UAS are keeping UAS on the ground [14] or modifying path planning [15], which would greatly reduce the operation capability of UAS in cold climate.…”

mentioning

confidence: 99%

Experimental Investigation on the Dynamic Icing Process over a Rotating Propeller Model

Liu

Ning

et al. 2018

Journal of Propulsion and Power

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An experimental study was conducted to investigate the dynamic ice accretion process over the blade surfaces of a rotating propeller model for unmanned-aerial-system (UAS) applications. In addition to revealing the transient ice accretion process over the rotating propeller surfaces, the dynamic thrust force generated by the propeller model was also measured simultaneously along with the required power inputs to drive the propeller model. Because of the combined effects of aerodynamics forces and the centrifugal force associated with the rotation motion, the ice accretion process over the rotating propeller surfaces was found to become very complicated. The ice accretion over the rotating propeller surfaces was found to become more preferable along the radial direction with the formation of lobster-tail-like ice structures extruding out from the propeller blade surfaces. The aerodynamic performance of the propeller model was also found to degrade tremendously due to the ice accretion, causing a significant reduction (i.e., up to 70% reduction) in mean thrust generation and a dramatic increase in force fluctuation amplitude (i.e., up to 250% increase). Despite of different types of ice accretion, the propeller model was always found to consume more power operating under icing conditions (i.e., up to 250% more power consumption under glaze icing conditions).

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“…In addition to the ice-induced energy production loss of wind turbines, UAS missions in cold climates are also often influenced by icing. As reported by Botura and Fahrner [12], the success of the mission of 25% military UAS flights encountering icing have been negatively impacted. The unexpected ice accretion over inflight UAS not only increases the gross weight, but also alters the wing configuration resulting in a significant drop in lift.…”

Section: Chapter 1 General Introduction 1aircraft Inflight Icing Phys...mentioning

confidence: 95%

“…The potential damage of inflight icing to UAS renders their operation unfeasible in cold weather. As described in Botura & Fahrner [67], 25% UAS flights encountered icing during a specific military operation that have negatively impacted the success of the mission.…”

Section: Introductionmentioning

confidence: 99%

“…12 shows the AFM scanned images to reveal the significant changes in the surface topology of the SHS coated test plate before and after different duration s of the rain erosion testing experiments (i.e., after 10, 30 and 50 minutes of the rain erosion testing with the nominal droplet impacting speed of U∞ = 65 m/s). Based on the quantitative AFM measurement results as those shown in Fig.2.12, the key parameters to characterize surface topology, i.e., the averaged surface roughness (Ra) and the…”

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confidence: 99%

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Experimental investigations on the interactions between water/deicing fluids and icephobic coatings pertinent to aircraft anti-/de-icing

Zhang

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Icing Detection System - Conception, Development, Testing and Applicability to UAVs

Cited by 12 publications

References 1 publication

Effects of Ice Accretion on the Aerodynamic Performance and Wake Characteristics of an UAS Propeller Model

Effects of Ice Accretion on the Aerodynamic Performance and Wake Characteristics of an UAS Propeller Model

Experimental Investigation on the Dynamic Icing Process over a Rotating Propeller Model

Experimental investigations on the interactions between water/deicing fluids and icephobic coatings pertinent to aircraft anti-/de-icing

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