Innovation in Aerospace Technology
PROJEKTE
FFG RESERACH PROJECT FLYSIC
PARTNER:
INFINEON TECHNOLOGIES AG, DLR, FH JOANNEUM, HYCENTA RESERACH GMBH, SILICON AUSTRIA LABS, OIDC
The FlySIC industrial research project addresses one of the key challenges of sustainable aviation: the development of an energy-efficient, hydrogen-based blended wing body short-haul aircraft for up to nine passengers. The technological focus is on integrating a fuel cell system that enables a significant reduction in CO₂ emissions.
Motivation and market relevance
The decarbonization of aviation is essential in order to comply with regulatory requirements and international climate targets. While battery-electric drives are only of limited practical use for short-haul flights due to their low energy density, hydrogen offers a powerful alternative. With an energy density eight to ten times higher than Li-ion batteries and fast refueling, hydrogen as an energy source can significantly increase the operational efficiency and marketability of sustainable aircraft.
Technological innovations
The FlySIC project pursues several innovative approaches:
• Blended wing body design: 30–50% reduction in drag and improved fuel tank integration.
• Hybrid electric drive: Combination of fuel cell and battery storage for optimized range and performance.
• System integration & certification: Development of an economically viable and CS-23-compliant propulsion system for commercial applications.
Through close cooperation with research institutions and industry partners, FlySIC aims to lay the foundations for certifiable, hydrogen-powered short-haul aircraft.
Project objectives
1. Development of the concept for a sustainable, CO₂-neutral short-haul aircraft optimized for operation at regional airports.
2. Design of a hybrid electric hydrogen drive that ensures high power density, scalability for future aircraft, and operational safety.
3. Optimization of the fuel cell system for high-altitude flights and experimental validation of critical components, in particular the compressor system.
4. Development of a competitive aircraft concept, taking into account the increased added value in Austria.
5. Promotion of talent in aviation and sustainable propulsion systems, including consideration of the diversity of this talent.
Sustainability and economic benefits
The project contributes to the achievement of the Sustainable Development Goals (e.g., SDG 7 – Clean Energy, SDG 13 – Climate Action) and supports the Austrian hydrogen strategy. By establishing a regional value chain and developing innovative aircraft architectures, FlySIC will make an important contribution to the competitiveness of the Austrian aviation industry.
FFG RESEARCH PROJECT HyDroneREC
PARTNER: AVT ZT GMBH, FH KUFSTEIN, FH JOANNEUM, JOBY AUSTRIA GMBH, TWINS GMBH,
The use of unmanned, autonomous flight systems for military reconnaissance missions is becoming increasingly important. UAVs reliably cover large, inaccessible areas and can record and evaluate assessments of situations on the ground and make them available to mission commanders. However, the low energy density of battery-powered systems in particular is a hindrance to longer missions and long flight distances. Therefore, the Kufstein University of Applied Sciences in Tyrol and the company TWINS have successfully conducted initial flight tests with a fuel cell-electric rotor drone with a pressurized hydrogen tank in a preliminary project entitled “Hydrogen Drone – funded by the State of Tyrol.”
In addition to the drone's long flight time and range, adapting such systems for military reconnaissance can bring many other advantages. These include increased electrical power supply for more powerful sensors and computer systems, higher achievable payload, stronger communication systems, and lower noise levels compared to combustion engines for covert operations. In the HyDroneREC project presented, the consortium is developing two Class I flight systems: a rotorcraft and a flying wing drone that can be powered by hydrogen and will thus demonstrate a flight time increase of 300 to 400%. To this end, an integrative solution for the tanks is being developed in the supporting structure of the UAVs.
In order to provide optimal support for reconnaissance scenarios, HyDroneRec integrates a multi-sensor reconnaissance platform with optical, thermal, and radar sensors. The platform includes a Phase One optical camera with 150 MPxl resolution and four synchronized thermal cameras.
In addition, a compact, imaging (SAR) FMCW radar system is being integrated into HyDroneRec, and basic functionalities for data, flight, and processing management in various reconnaissance scenarios are being developed, as well as interfaces for integrating the results into a C2 system of the Austrian Federal Ministry of Defense. In the presented project, innovative Austrian manufacturers of UAVs, TWINS and Meder & Partner Aerospace, will work in combination with the expertise in air detection provided by Joanneum Research in cooperation with INRAS and AVT and the Austrian Armed Forces, who require needs-based, innovative systems, in order to be able to successfully guarantee challenging air reconnaissance scenarios in the future with autonomous systems.
Another focus of the project is certification in the Specific category by Austro Control. This enables autonomous flying beyond visual line of sight with a high payload.
Approval was granted in June 2025.
FFG RESERACH PROJECT FLYLONG
PARTNER: AVL LIST GMBH, INFINEON TECHNOLOGIES AG
The aim of the project was to develop a feasible propulsion concept for a general aviation aircraft with a blended wing body design. The basic concept for the aircraft was the MX 22 Silhouette flying wing from Deep Blue Aviation. The power requirements were determined using aerodynamic simulations and available reference documents on blended wing construction. Commercially available subsystems were selected and mathematically modeled to estimate overall performance and energy consumption. Two separate variants were investigated with regard to the use of liquid hydrogen or 700 bar compressed hydrogen. ALV contributed all the necessary expertise and specific specification data for a possible fuel cell system. Infineon contributed several improvement options through the use of the latest wide bandgap power semiconductors for the fuel cell DC/DC converter and the motor control inverter.
A proposal for battery management using Infineon semiconductors was also developed. The highlight is that performance estimates and simulations show that both variants have been successfully analyzed and are feasible. They even offer twice the flight time that was originally required. In addition, a cooling concept was developed in which air is fed through special cooling channels into the fuselage of the aircraft, where two water cooling subsystems can be used in addition to the general air cooling of all components. One cooling system contains chemically purified water for cooling the fuel cell, while a second cooling system was intended for power electronics such as inverters and DC/DC converters. In addition to computer simulations, a 1:2 demonstrator was used to conduct extensive test flights.
RESERACH PROJECT MX 18 EVTOL
PARTNER: HTL EISENSTADT, M&S WÖRGL
The MX 18 Silhouette is an electrically powered, vertical take-off and landing aircraft for transporting people and goods. In addition to the rotors, this concept uses wings to generate lift during horizontal flight in order to save energy and improve flight characteristics.
During vertical take-off, lift is generated by the horizontal alignment of all three engines, causing the aircraft to lift off. Propulsion is achieved by gradually tilting the two front rotors, as in a twin-engine aircraft. During vertical take-off, lift is generated by the horizontal alignment of all three motors, causing the aircraft to lift off. Propulsion is generated by gradually tilting the two front rotors, similar to a twin-engine aircraft. The flying wing design maximizes lift characteristics and strengthens the structure of the aircraft. The internal rotors minimize the risk of accidents during take off and landing.
The MX 18 Silhouette was developed in three different versions: unmanned, two-seater, and five-seater.
Innovation
Vertical take off and landing with electric drive
• No traffic infrastructure required (e.g., runways, airfields)
• Low space requirements
• Electric motors generate less noise than helicopters, for example
• No emissions (“fuel” electricity = renewable energy)
Lift generated by motors and wings
Unlike EVTOL concepts, which generate lift during flight solely via propellers, this concept also uses wings for lift in order to save energy during flight, which is extremely important for electric drives.
In the event of engine failure, the gliding characteristics can be used for an emergency landing, as with an airplane.
Tiltable rotors for flexible flight behaviour
During vertical take off, lift is generated by the horizontal alignment of all three engines and the aircraft takes off. The gradual tilting of the two front rotors generates propulsion similar to that of a twin-engine aircraft. This allows higher flight speeds to be achieved than with conventional concepts (multicopters, “air taxis”) and reduces energy consumption.
Flying wing concept for optimal lift
• Maximized lift characteristics, entire aircraft body provides lift (up to 90% lift, conventional aircraft with fuselage, wings, and tail up to 50% lift).
• Engine power is used more economically (energy savings of 15–25%).
• Lower structural forces, aircraft can be built lighter (weight savings).
Foldable wings during take off and landing
The outer section of the wings can be swung upward during take off and landing. This reduces the wingspan by two-thirds. The aircraft can thus land in minimal space.
Rotors inside the wing
• Reduction of the risk of accidents caused by rotating propellers
• Less space required for landing as there is no danger zone caused by the propellers.
FFG RESERACH PROJECT COOLING SYSTEM FOR THE SILHOUETTE
The goal was to develop an innovative air cooling system that offers outstanding aerodynamic and thermodynamic efficiency, thus providing both ecological and economic advantages. A comprehensive CAE (computer-aided engineering) simulation environment was used to maximize aerodynamic performance, flight stability, and air cooling efficiency through targeted design optimization. To this end, the HPC laboratory at FH Joanneum (Institute of Aviation) was used to apply modern CAE methods that allow for extensive scenarios and enable the visualization and analysis of flow conditions, aerodynamic forces and moments, and cooling efficiency. The result was an optimized design study that will serve as the basis for further planning and development of the MX 24 silhouette.