An Experimental Investigation to Assess the Effectiveness of Various Anti-Icing Coatings for UAV Propeller Icing Mitigation

Han, Nianhong; Hu, Haiyang; Hu, Hui

doi:10.2514/6.2022-3964

Cited by 7 publications

(9 citation statements)

References 15 publications

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“…τ i and τ j are each panel's tangential vectors. The force contribution of each lattice in the body's three axes was then described by Equation (7), where ∆S is the area of each lattice. The thrust and torque coefficients as well as the Figure of Merit (FoM) were then calculated using Equations ( 8)- (10), respectively.…”

Section: Uvlm Basicsmentioning

confidence: 99%

“…Recent experimental studies have shown that a 2 min exposure to severe icing conditions is enough to cause a 50% reduction in thrust and motor power losses of up to 100% [5]. Icephobic coatings are being tested as a possible means of preventing ice accretion [6,7], yet thermal IPSs have been long considered, and continue to be, the most reliable IPS for rotors [8]. They work by converting electrically supplied energy into heat, which keeps the rotor surfaces warm enough to prevent ice formation [9].…”

Section: Introductionmentioning

confidence: 99%

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A Preliminary Approach towards Rotor Icing Modeling Using the Unsteady Vortex Lattice Method

Samad,

Villeneuve,

Morency

et al. 2024

Drones

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UAV rotors are at a high risk of ice accumulation during their operations in icing conditions. Thermal ice protection systems (IPSs) are being employed as a means of protecting rotor blades from ice, yet designing the appropriate IPS with the required heating density remains a challenge. In this work, a reduced-order modeling technique based on the Unsteady Vortex Lattice Method (UVLM) is proposed as a way to predicting rotor icing and to calculate the required anti-icing heat loads. The UVLM is gaining recent popularity for aircraft and rotor modeling. This method is flexible enough to model difficult aerodynamic problems, computationally efficient compared to higher-order CFD methods and accurate enough for conceptual design problems. A previously developed implementation of the UVLM for 3D rotor aerodynamic modeling is extended to incorporate a simplified steady-state icing thermodynamic model on the stagnation line of the blade. A viscous coupling algorithm based on a modified α-method incorporates viscous data into the originally inviscid calculations of the UVLM. The algorithm also predicts the effective angle of attack at each blade radial station (r/R), which is, in turn, used to calculate the convective heat transfer for each r/R using a CFD-based correlation for airfoils. The droplet collection efficiency at the stagnation line is calculated using a popular correlation from the literature. The icing mass and heat transfer balance includes terms for evaporation, sublimation, radiation, convection, water impingement, kinetic heating, and aerodynamic heating, as well as an anti-icing heat flux. The proposed UVLM-icing coupling technique is tested by replicating the experimental results for ice accretion and anti-icing of the 4-blade rotor of the APT70 drone. Aerodynamic predictions of the UVLM for the Figure of Merit, thrust, and torque coefficients agree within 10% of the experimental measurements. For icing conditions at −5 °C, the proposed approach overestimates the required anti-icing flux by around 50%, although it sufficiently predicts the effect of aerodynamic heating on the lack of ice formation near the blade tips. At −12 °C, visualizations of ice formation at different anti-icing heating powers agree well with UVLM predictions. However, a large discrepancy was found when predicting the required anti-icing heat load. Discrepancies between the numerical and experimental data are largely owed to the unaccounted transient and 3D effects related to the icing process on the rotating blades, which have been planned for in future work.

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Section: Uvlm Basicsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

A Preliminary Approach towards Rotor Icing Modeling Using the Unsteady Vortex Lattice Method

Samad,

Villeneuve,

Morency

et al. 2024

Drones

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“…Recently, multiple solutions to the issue of an IPS on rotors of UAVs have been published, focusing either on surface coatings Han et al, 2022;Villeneuve et al, 2022) or electro-thermal systems (Karpen et al, 2022;Meteomatics, 2017;Hann et al, 2019;Wallisch and Hann, 2022). Most such systems target the rotors of smaller multi-rotor UAVs.…”

Section: Comparison To Other Workmentioning

confidence: 99%

“…The surface coatings developed in other works (Villeneuve et al, 2022;Han et al, 2022) show the potential to reduce the ice adhesion forces and to increase the ice shedding frequency. However, they were not able to keep the propeller ice-free at lower temperatures.…”

Section: Comparison To Other Workmentioning

confidence: 99%

“…This behaviour was observed to be due to a reduction in the accumulated ice mass outside of the impingement zone of the propeller and faster ice shedding. In a follow-up study by Han et al (2022), the effectiveness of different surface coatings was compared in glaze and rime conditions. In this study, it was observed that surface coatings aiming at reducing the adhesion forces of the ice could perform well in glaze and rime conditions.…”

Section: Introductionmentioning

confidence: 99%

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Uav Icing: Development of an Ice Protection System for the Propeller of a Small Uav

Müller

Borup²,

Hann

et al. 2023

Preprint

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Electromechanical ice protection system: de-icing capability prediction considering impedance matching effect

Miao,

Yuan,

Zhu

2024

Aeronaut. j.

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Due to the safety threats caused by icing, the de-icing system is essential in the aviation industry. As an effective method, the electromechanical de-icing system (EDS) is a new ice-protection system based on mechanical vibration principles. For the majority of the current research on system de-icing capability estimation, the effect of impedance-matching is not considered. Impedance matching plays a very important role in improving the performance of the electromechanical system, so we must also consider the impact of impedance matching when designing the EDS. In the present study, a de-icing capability prediction method considering the impact of an impedance-matching device is established based on experimental and numerical methods. The results indicate that the impedance-matching effect has no impact on the mechanical vibration of the structure for the same load power. Meanwhile, impedance-matching devices can significantly improve the power factor and increase the interface shear stress/strain for de-icing. Eight different vibrational modes were tested, and the experimental results showed that the actual interface shear strain after impedance matching is inversely proportional to the de-icing time. The verification experiments were conducted and the accuracy of the proposed prediction method was verified.

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An Experimental Investigation to Assess the Effectiveness of Various Anti-Icing Coatings for UAV Propeller Icing Mitigation

Cited by 7 publications

References 15 publications

A Preliminary Approach towards Rotor Icing Modeling Using the Unsteady Vortex Lattice Method

A Preliminary Approach towards Rotor Icing Modeling Using the Unsteady Vortex Lattice Method

Uav Icing: Development of an Ice Protection System for the Propeller of a Small Uav

Electromechanical ice protection system: de-icing capability prediction considering impedance matching effect

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