BISANCE intends at defining a biphasic system integrated into a full composite nacelle and engine air intake. The biphasic system aims at decreasing significantly the weight, the environmatal footprint as well as the space allocated by the current active systems for the cooling of the engine oil and for the energy supply of th ice protection systems. These both active systems (needing external power) will be replaced by a biphasic passive system (autonomous with no need of external power) which will extract the energy from the engine oil and transfer it to the ice protected surfaces. The objective of the project is thus to decrease the weight by 25kg for the two nacelles of a turboprop A/C, to decrease the CO2 emissions by almost 900 000 kg per AC life and to save 200 000$ of operating costs per AC life. The project will be divided into 5 workpackages along 30 months. The first step intends at defining the specifications and the requirements of the product. Based on the requirements, several concepts of system integration into the structure will be proposed and manufactured for selecting the most promising one. Qualification tests are expected for characterizing the structural resistance and stifness of the concept, for verifying the resistance to heat cycles and to impacts. Finally a fulls scale demonstrator will be manufactured for testing it in icing Wind tunnel. The project will be coordinated by Sonaca, also in charge of the structural developments, in association with Calyos, in charge of the system developments and with RTA in charge of performing the icing wind tunnel testing.

This proposal fits within the framework of aircraft effectiveness constant improvement by reducing fuel and power consumptions. Its ultimate goal is to economically remove ice accreting on aircraft structure critical parts and thus increase reliability and mass saving on the global function. By comparison with the present existing solutions which are based on active pneumatic and electro-thermal means the targeted solutions will enable electrical power consumption, cost and mass reductions and ease the overall integration process. The subject of this proposal is to integrate and test two innovative ice protection systems in aircraft structures. The first system is based on two-phase heat transport and will be tested in a turboprop metallic air intake. The second system is based on electromagnetic induction and will be tested on a wing fixed leading edge and on a flap leading edge.

Current design methodologies used to characterise ice accretion and its effects on air vehicle components and power plant systems are mainly based on empirical methods, comparative analysis, 2D simulation tools and past experience gained on in-service products. Due to the associated uncertainties, cautious design margins are used, leading to conservative and non-optimised solutions. As future air vehicle and propulsive system architectures introduce radical design changes, it will no longer be possible to rely on the existing design methodologies, making future development extremely difficult to accomplish efficiently and within short development cycles that are demanded by customers and desired by industry. These difficulties are increased by the recent changes in certification regulations, in particular for Supercooled Large Droplets (SLD), which require manufacturers to certify their products against more stringent requirements. Snow also remains a challenge, especially for turbine engines and APUs. ICE GE

IMPACT tackles all the challenges of the call JTI-CS2-2019-CfP10-LPA-01-80, “Rear fuselage and empennage shape optimization including anti-icing technologies” by: • unlocking the capability to perform fast and accurate 3D ice accretion simulation suitable for non-straight leading-edge empennages, accounting for effects of passive anti-ice coatings and devices like leading-edge undulations; • characterising, integrating, and exploiting the passive anti-ice coatings and devices for non-straight leading-edge empennage configurations, reaching TRL 5 at the end of the project; • developing and applying innovative aerostructural optimisation methods for advanced rear ends (ARE), including the effects of the passive anti-ice coatings and devices, to minimise drag and include structural and aeroelastic constraints; • validate the accuracy of the 3D icing accretion simulations and the performance of passive anti-ice coating and devices by means of large scale icing wind tunnel (IWT) experimental tests. To realize its ambition, IMPACT builds on a consortium of nine European partners from Austria, Italy and the UK, multiplying the value of EU-funding with a tenth partner from Canada, who joins the project without EU funding. The results delivered by IMPACT are expected to contribute significantly to the objectives of the CS2 IADP LPA ARE by reducing (i) its weight by 7-to-8%, (ii) its recurring costs by 5-to-6%, (iii) the LPA fuel consumption by 1.7-to-2.9%, and (iv) by favourably contributing to reducing lead time. IMPACT will ultimately support Airbus’ progress with the advanced rear end concept, enhancing the competitiveness of the European LPA industry and value chain.