US 12,291,322 B2
Drive system of an aircraft, aircraft and method for operating an aircraft
Mikel Fauri, Ludwigsburg (DE)
Assigned to DR. ING. H.C. F. PORSCHE AKTIENGESELLSCHAFT, Stuttgart (DE)
Filed by Dr. Ing. h.c. F. Porsche Aktiengesellschaft, Stuttgart (DE)
Filed on Apr. 21, 2022, as Appl. No. 17/725,563.
Claims priority of application No. 10 2021 110 378.9 (DE), filed on Apr. 23, 2021.
Prior Publication US 2022/0348311 A1, Nov. 3, 2022
Int. Cl. B64C 13/26 (2006.01); B60L 3/00 (2019.01); B64C 29/00 (2006.01); B64D 27/24 (2006.01); B64D 37/02 (2006.01); B64D 41/00 (2006.01); H01M 8/04082 (2016.01); H01M 8/04089 (2016.01); H01M 8/04746 (2016.01); H01M 8/22 (2006.01)
CPC B64C 13/26 (2013.01) [B60L 3/0053 (2013.01); B64C 29/0008 (2013.01); B64D 27/24 (2013.01); B64D 37/02 (2013.01); B64D 41/00 (2013.01); H01M 8/04089 (2013.01); H01M 8/04201 (2013.01); H01M 8/04753 (2013.01); H01M 8/22 (2013.01); B60L 2200/10 (2013.01); B64D 2041/005 (2013.01); H01M 2250/20 (2013.01)] 12 Claims
OG exemplary drawing
 
1. A drive system for providing drive power to a vertical lift unit or a thrust unit of an aircraft for takeoff, landing and an operational flight after takeoff and before landing, the drive system comprising:
the thrust unit configured to:
generate forward thrust for the operational flight; and
receive a first power for the operational flight,
the vertical lift unit configured to:
generate vertical lift for the takeoff and the landing of the aircraft; and
receive the first power for the operational flight and a second power for the takeoff and the landing,
a power splitter unit configured to:
receive the first power from a fuel cell and the second power from an electrical energy store;
provide the first power to the thrust unit and the vertical lift unit; and
provide the second power to the vertical lift unit, wherein when the power splitter unit does not receive the second power in response to a failure of the electrical energy store, the power splitter unit receives an increased amount of power from the first power based on an additional hydrogen mass flow from an additional hydrogen tank,
the fuel cell configured as a first power source for the drive power, the fuel cell operatively coupled to a hydrogen tank that is configured to supply hydrogen to the fuel cell and operatively coupled to a blower that is configured to supply air to the fuel cell, the fuel cell configured to provide the first power of the drive power for the operational flight after the takeoff and before the landing based on a hydrogen mass flow supplied by the hydrogen tank and based on an air mass flow supplied by the blower;
the electrical energy store configured as a second power source for the drive power and configured to provide at least a portion of the drive power for the takeoff and the landing as the second power; and
the additional hydrogen tank and an air or oxygen tank operatively and controllably coupled to the fuel cell such that, in response to the failure of the electrical energy store, the fuel cell is supplied with the additional hydrogen mass flow from the additional hydrogen tank and with an additional air or oxygen mass flow from the air or oxygen tank.