| CPC H02J 7/34 (2013.01) [B60L 8/003 (2013.01); B60L 50/60 (2019.02); B60L 50/70 (2019.02); B60L 53/00 (2019.02); B60L 58/12 (2019.02); B64C 39/024 (2013.01); B64D 27/24 (2013.01); B64D 41/00 (2013.01); H02J 3/381 (2013.01); B60L 2200/10 (2013.01); B64D 2041/005 (2013.01); B64D 2211/00 (2013.01); B64U 10/13 (2023.01); B64U 50/19 (2023.01); B64U 50/34 (2023.01); H02J 2300/24 (2020.01); H02J 2310/44 (2020.01)] | 14 Claims |
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1. An assembly for powering an electric aircraft, comprising:
energy storage means for storing electric energy,
electric-power sensing means adapted to detect or measure voltages of said energy storage means and electric currents flowing through said energy storage means,
supplementary-energy supplying means adapted to provide a supplementary energy to said electric aircraft,
energy management means configured for:
estimating a charge level of said energy storage means on the basis of said voltages and said electric currents detected or measured by said electric-power sensing means, and
regulating, on the basis of said charge level and of said electric currents flowing through said energy storage means, a supplementary electric current generated by said supplementary-energy supplying means in order to reduce the amount of electric power supplied by said energy storage means to said electric aircraft when the power consumed by said aircraft exceeds the output power of said supplementary-energy supplying means, and to recharge said energy storage means when the output power of said supplementary-energy supplying means exceeds the power consumed by said aircraft,
navigation and flight-control means for controlling the flight of said electric aircraft, wherein said energy management means are also configured for changing, through said navigation and flight-control means, the capabilities and performance of said electric aircraft by switching between at least two energy profiles on the basis of at least the charge level of said energy storage means, wherein each profile defines at least the maximum speed or acceleration or inclination achievable by said aircraft.
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10. A method for powering an electric aircraft, comprising:
an acquisition phase, wherein voltages of energy storage means for storing electric energy, and electric currents flowing therethrough are detected or measured by means of electric-power sensing means,
a charge estimation phase, wherein a charge level of the energy storage means is estimated, by means of energy management means, on the basis of said voltages and said electric currents detected or measured by said electric-power sensing means,
a regulation phase, wherein a supplementary electric current is generated from a supplementary-energy supplying means adapted to provide a supplementary energy to said electric aircraft, and wherein said supplementary electric current is regulated, through the energy management means, on the basis of said charge level and of said electric currents flowing through said energy storage means, in order to reduce the amount of electric power supplied by said energy storage means to said electric aircraft when the power consumed by said aircraft exceeds the output power of said supplementary-energy supplying means, and to recharge said energy storage means when the output power of said supplementary-energy supplying means exceeds the power consumed by said aircraft, wherein, during the regulation phase, the capabilities and performance of said electric aircraft are switched, by means of navigation and flight-control means, between at least two energy profiles on the basis of at least the charge level of said energy storage means, wherein each profile defines at least the maximum speed or acceleration or inclination achievable by said aircraft.
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