Comparative CFD and experimental analysis for power prediction in UAV ice protection systems
Damian Maciorowski, Maciej Osiewicz, Edvin Podlewski, Paulina Woroniecka, Ryszard Chachurski, Jakub Kapuściński
Streszczenie
Unmanned aerial vehicles have become an integral part of a wide range of applications, however, their functionality
in the low ambient temperature regime is significantly limited, particularly for light UAVs powered by electric batteries. As
the ambient temperature decreases, battery capacity also decreases, and a risk of ice accumulation appears. The layer of ice on
the wings that grows over time significantly increases aerodynamic drag, increases weight, and may lead to structural failure.
Unlike commercial aircraft, the UAV sector typically has a very limited Max Takeoff Weight. It is less feasible to integrate
traditional Ice Protection Systems (e.g., pneumatic). UAV designers are forced to look for lighter and more efficient solutions.
In this paper, the energy demands of UAV ice protection are explored through a combination of Computational Fluid Dynamics
simulations and experimental testing.
Experimental icing tests were conducted under controlled conditions to measure ice growth and power requirements for ice
mitigation. The CFD simulations incorporated key icing physics, including droplet impingement, water runback, and phase
transition. By comparing simulation results with experimental measurements, this work aims to provide a methodology for
accurately predicting power requirements for electric IPS for light UAVs based on weather conditions and flight profile.
in the low ambient temperature regime is significantly limited, particularly for light UAVs powered by electric batteries. As
the ambient temperature decreases, battery capacity also decreases, and a risk of ice accumulation appears. The layer of ice on
the wings that grows over time significantly increases aerodynamic drag, increases weight, and may lead to structural failure.
Unlike commercial aircraft, the UAV sector typically has a very limited Max Takeoff Weight. It is less feasible to integrate
traditional Ice Protection Systems (e.g., pneumatic). UAV designers are forced to look for lighter and more efficient solutions.
In this paper, the energy demands of UAV ice protection are explored through a combination of Computational Fluid Dynamics
simulations and experimental testing.
Experimental icing tests were conducted under controlled conditions to measure ice growth and power requirements for ice
mitigation. The CFD simulations incorporated key icing physics, including droplet impingement, water runback, and phase
transition. By comparing simulation results with experimental measurements, this work aims to provide a methodology for
accurately predicting power requirements for electric IPS for light UAVs based on weather conditions and flight profile.