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

Development of key technologies to address a new wing design for a HER aircraft maturing up to TRL5: manufacturing, assembly, structural concepts and processes, concept studies, configuration and architecture trade offs for a full wing component are part of the activity. As a physical demonstration concept, the detail design and manufacturing of the relevant components of a centre wing section of a HER Aircraft will be addressed. Conceptual wing studies: configuration and architecture (structural arrangement, Systems allocation and disposition, flight control system) trade offs for a full wing. Full wing structural arrangement mock up for innovative wing concepts, Structural and Multidisciplinary Optimization studies for definition of the optimal structural configuration of wing. Demonstration platform: wingbox, high lift devices, control surfaces, load alleviation devices focusing on the centre section as a demonstration platform: - Integrated Centre section wing box structure with the inner Propulsion stage: Full span (pylon to pylon) torsion box concept representative of more ambitious tip 2 tip concept. Multispar concept, Access manholes and panels, Sustainable aviation fuel and Integrated Fuel vent systems. - Inner section Leading Edges, Integrated Inductive ice protection system integration, Multifunctionality: erosion, impact, Lightning, ice protection, Morphing concepts, Functional tests, Bird strike tests (virtual or real) - Inner section Flap and high lift solutions: Integrated flap solutions. Multifunctionality application to flap. Key processing technologies: Low cost-high integrated out of autoclave technologies. Dry fiber placement and liquid resin infusion for integrated multispar torsion box. Thermoplastic composites processing: In situ consolidation for integrated flap skin and Leading edge applications. Thermoplastic welding and co-consolidation for Integration. Bonding technologies exploration towards certifiable solutions.

TRIcEPS aims at fulfilling all the requirements of the JTI-CS2-2018-CfP08-FRC-01-21, “Development of integrated engine air intake and protection systems for Tilt Rotor” by designing, manufacturing, testing and qualifying the left-hand and the right-hand side air intakes and their integrated engine protection system for the NextGenCTR technology demonstrator, contributing to meet the goals of the CS2JU FRC WP1. The proposed engine protection system is geared on two key enabling technologies: • a removable thermoelectric ice protection system based on the heater layer technology. This is already under development on the blade of the NextGenCTR and on the wing of the regional aircraft; • a vortex tubes filter for protecting the engine from ingestion of particles in harsh environment. The air intake will be equipped with a bypass for operation in clean flow and a compressor washing system. The choice of a vortex tubes instead of a barrier filter is key in TRIcEPS. This solution, despite providing 1-to-2% lower particle separation efficiency, allows for: • full self-cleaning capabilities, thus not requiring maintenance (i.e. fit and forget approach); • stable pressure drop in brownout operation, resulting in no need of emergency bypass actuation which would expose the engine to the harsh environment; • significantly reduced icing issues; • easier flight certification path, according to FAA; resulting in the best technical compromise for the NextGenCTR considering its mission profile. Moreover, this choice does not to infringe IPRs on tilt rotor air intake (as per patenting activities by Bell Helicopters on barrier filter), thus securing the position of Leonardo with respect to the future market. TRIcEPS will deliver the air intake, its engine protection system and all the relevant sub-systems at TRL 7, supplying Leonardo with the reference technical solution for engine protection of the NextGenCTR, strengthening the competitiveness of the European rotorcraft industry.