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US 2026/0200598 A1Published application
Design principles for electric aircraft
AssigneeCoöperatie Elysian Aircraft Company U.A.
InventorsRobert Eduard WOLLESWINKEL, Reynard DE VRIES, Roelof VOS
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Abstract
The present disclosure relates to an aircraft comprising: a fuselage and at least one wing arranged in a tube-and-wing design; a plurality of propulsors; and a primary energy source configured to power the propulsors, the primary energy source comprising rechargeable batteries. The aircraft has a maximum take-off mass ‘MTOM’ of at least 8,618 kg; and an electric range factor ‘ERF’ of at least 6.
Claims19
An aircraft comprising:
- a fuselage and at least one wing arranged in a tube-and-wing design;
- a plurality of propulsors;
- and
- a primary energy source configured to power the propulsors, the primary energy source comprising rechargeable batteries,
- wherein the aircraft has:
- a maximum take-off mass ‘MTOM’ of at least 8,618 kg;
- and
- an electric range factor ‘ERF’ of at least 6.
5 more elements
A wing assembly for a tube-and-wing design aircraft, the wing assembly comprising:
- a wing structure;
- and
- a primary energy source configured to power a plurality of propulsors, the primary energy source comprising rechargeable batteries,
- wherein the wing structure has a mass of at least 600 kg, and the ratio of the mass of the rechargeable batteries to the mass of the wing structure is at least 4.
1 more element
(canceled)
(canceled)
An aircraft comprising:
- a fuselage and at least one wing assembly arranged in a tube-and-wing design, the wing assembly comprising:
- a wing structure;
- and
- a primary energy source configured to power a plurality of propulsors, the primary energy source comprising rechargeable batteries,
- wherein the wing structure has a mass of at least 600 kg, and the ratio of the mass of the rechargeable batteries to the mass of the wing structure is at least 4;
- a plurality of propulsors;
- and
- a primary energy source configured to power the propulsors, the primary energy source comprising rechargeable batteries,
- wherein the aircraft has:
- a maximum take-off mass ‘MTOM’ of at least 8,618 kg;
- and
- an electric range factor ‘ERF’ of at least 6.
9 more elements
Dependencies are inferred from the claim text.