Propeller-integrated airfoil heater system for small multirotor drones in icing environments: Anti-icing feasibility study

Karpen, Norbert; Diebald, Stefan; Dezitter, Fabien; Bonaccurso, Elmar

doi:10.1016/j.coldregions.2022.103616

Cited by 19 publications

(13 citation statements)

References 22 publications

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“…For the glaze ice test case at 7800 RPM, the predictions match from hub to tip, and the effects of aerodynamic heating are captured by both numerical tools. Keeping in mind that the results of [49] were also validated using their experimental data, it can be concluded that the UVLM-RHT method predicts acceptable estimates of the . Q wall for lower LWC and MVD icing conditions.…”

Section: Discussionmentioning

confidence: 93%

“…The UVLM-RHT method was used to analyze another rotor test case with a heat-leading edge from the literature [49]. The test case consisted of a 0.33 m diameter 2-blade rotor with an operation at either 4000 or 7800 RPM.…”

Section: Discussionmentioning

confidence: 99%

“…The results are focused on simulating a previous experimental setup of a 4-blade rotor fitted with heated blades via electro-thermal heating elements. The aerodynamic per- Q wall by the UVLM-RHT method and numerical data from the literature [49].…”

Section: Discussionmentioning

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: Discussionmentioning

confidence: 93%

Section: Discussionmentioning

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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show abstract

“…IPS have been successfully developed for the wings of UAVs (Hann et al, 2019;Wallisch and Hann, 2022). A rotor with an IPS has been developed by Karpen et al (2022). In this design, a rotor of a multi-rotor UAV was covered with an electrical heater that consisted of three different heater zones over the propeller.…”

Section: Introductionmentioning

confidence: 99%

“…Another issue is the power delivery to the rotating propeller. One solution is to provide the rotor with an independent power source in the hub of the rotor (Karpen et al, 2022) or supply it with energy from the UAV through the motor, as done by Meteomatics (2017) in their developed electro-thermal IPS for a rotor of a small multirotor UAV.…”

Section: Introductionmentioning

confidence: 99%

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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Challenges in Detecting Clouds in Polar Regions Using a Drone with Onboard Low-Cost Particle Counter

Inoue,

Sato

2023

Atmospheric Environment

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Propeller-integrated airfoil heater system for small multirotor drones in icing environments: Anti-icing feasibility study

Cited by 19 publications

References 22 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

Challenges in Detecting Clouds in Polar Regions Using a Drone with Onboard Low-Cost Particle Counter

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