Public Deliverables

3D scanning has established itself as new method to document the final ice accretion on test objects (e.g. components or systems of aircraft, helicopter, and UAV) after icing wind tunnel test runs. The final ice shapes are quite complex and can differ significantly in their size and appearance because the icing process is influenced by many variables. To better understand the icing process and the impact of the final ice accretion on the flight characteristics of the respective aircraft, an accurate 3D scan is of importance. Nevertheless, special software tools are also required to process and evaluate the generated 3D data to investigate the parameters of interest, e.g. ice thickness and ice surface roughness.

This report provides an overview and summarizes the activities performed at the Austrian Institute for Icing Sciences (AIIS) as part of WP4 in the ICE GENESIS project.

Within the European ICE-GENESIS project, the Russian aircraft-laboratory Yak-42D “Roshydromet” and the French ATR42 research aircraft from SAFIRE will perform 2 flight test campaigns out of France and Russia representing a total of 75 flight hours. 

The work performed in order to produce the deliverable D5.1 is entirely related to the choice of most suitable instrumentation for snow microphysics research on above research aircraft, which means we have to take into account payload possibilities, installation constraints, and certification limitations. The work beyond D5.1 to be undertaken subsequently will be to design the flight plans, conduct the two field campaigns and process the observations of basic aircraft, in situ microphysics, and radar observations.

Detailed report presenting an exhaustive literature review on the existing models, numerical techniques and experimental data that are currently available for the development of 3D numerical tools for App C and O. Then requirements will be defined in terms of basic tests to be performed in WP9, model features, model accuracy, numerical techniques to be used, interface with existing industrial tools, and validation procedure.

Detailed report describing the icing conditions and A/C operating envelopes needeed to be investigated to support design validation and certification in App. O conditions and defining  the operating envelope of IWT, the characteristics of instrumentation to be used for measurements and the relevant parameters to be investigated in order to be able to define an experimental envelope being compliant with requirements.