Challenges

Specific challenges

Hybrid-electric propulsion and pure electric propulsion are widely seen as having the potential to bring strong and disruptive gains in overall aircraft energy efficiency and emissions reductions, in particular when combined with the potential for relaxing design constraints related to current aircraft designs and making use of e.g. distributed propulsion, energy carriers such as advanced batteries and fuel-cells; and advanced airframe/propulsion integration.

The proposal takes full advantage of the latest advances in aerospace, electrification and autonomous technologies in a hybrid-electric propulsion strategy and couples the most efficient turbines with generators and recharging batteries, to provide electric power in hybrid-electric aircraft configurations that are under its scope. The technologies investigated in view of this proposal are also complementary to engine core technologies currently under investigation in other EU projects.

The limitation in specific energy storage capacity of today’s battery technology probably leads to favour hybrid-electric propulsion concepts instead of full-electric configurations.

The proposed concepts are based on hybrid-electric propulsion concepts, utilizing batteries for several segments of the flight mission. Moreover, great innovation potential is foreseen in all-solid-state and flow batteries which will be investigated and assessed in the optimization loop.

This thematic topic focuses on the aircraft design of a 19 passenger commuter aircraft based on alternative propulsion concepts (electric, hybrid/electric, fuel cells, etc.) targeting near zero CO2 emission.

The project will focus on setting technical targets for a future 19-passenger commuter aircraft employing hybrid-electric, battery based motive power systems. The adopted morphological solution and the aircraft top level requirements will be compliant with the new level 4 FAR23/CS23 regulation.

Architectures may include (but are not limited to) concepts based on a jet-fuel powered (piston or turbine) generator providing electric power, recharging batteries and driving propellers or fans (distributed or not) through electrical engines, full electric aircraft, or propulsion using alternative energy systems and energy carriers like fuel cells, hydrogen, LNG etc.

Various architectures will be studied and proposed based on turbine engines, energy storage, motors and generators and the overall controlling systems. During the technology-down-selection process which will be performed at the first period of the project, the potential and feasibility of all available technologies (e.g. distributed propulsion – boundary layer ingestion) will be assessed.

A full design loop is required, evaluating a range of design options, resulting in a mature conceptual design for the selected design. The design should be compliant with the new level 4 FAR23 / CS23 regulation, range and payload and operating parameters may be optimized.

With a focus on the key propulsion sub-systems, aircraft structure and performance that interfaces with existing conceptual design frameworks (e.g. in-house developed EVA framework), this project will aim at full design space exploration of the various hybrid-electric concepts at low TRL level to provide the mature conceptual design for the selected architectures.

The expected project outcome would include a gap analysis and roadmap for performance critical technologies, the sizing and layout of system components, including fault tolerance scenarios, and quantified environmental performance gains, including a full LCA analysis of the proposed concepts.

A recap of the main project innovations is reported in the ‘Innovation Potential’ section where a preliminary gap analysis has been included. The thorough analysis will be prepared and delivered as part of the project’s implementation actions. Moreover, a techno-economic and a full LCA analysis will be performed and a specific deliverable will be prepared within HECARRUS project.