公开(公告)号：EP3552960A1

公开(公告)日：2019-10-16

申请号：EP18181177.9

申请日：2018-07-02

Applicant: Bell Helicopter Textron Inc.

Inventor： HAMPTON, Dalton T ,  HALDEMAN, Andrew Paul ,  ACEE, Aaron Alexander ,  HILL, Matthew John

IPC: B64C27/82

Abstract: Systems and methods include providing an aircraft (100) with a tail rotor system having a tail rotor housing (112, 200, 300, 400) that forms a cambered airfoil between an upper cambered surface and an lower cambered surface of the tail rotor housing (112, 200, 300, 400). The cambered airfoil design of the tail rotor housing (112, 200, 300, 400) is capable of providing sufficient lifting force of an aircraft (100) to offload the tail rotor (108) during forward flight, thereby eliminating the need for a traditional vertical stabilizer or fin. The tail rotor blades (110) of the tail rotor system are disposed within an aperture (139) in the tail rotor housing (112, 200, 300, 400), which minimizes or preferably eliminates exposure of the tail rotor blades (110) to edgewise airflow typically encountered during forward flight, thereby allowing rigid rotor hubs, both in-plane and out-of-plane, to be used in the tail rotor system while also reducing noise output of the tail rotor system.

公开(公告)号：EP3708499A1

公开(公告)日：2020-09-16

申请号：EP20152387.5

申请日：2020-01-17

Applicant: Bell Helicopter Textron Inc.

Inventor： ACEE, Aaron Alexander ,  HALDEMAN, Andrew Paul ,  SINUSAS, Eric Albert ,  LAVALLEE, Yann ,  BRAND, Albert G.

IPC: B64D31/06 ,  B64C27/82

Abstract: An exemplary electric distributed propulsion system (600) includes two or more rotors (612a-d) that are individually controlled by the rotational speed of associated motors (611a-d), an input control (626) connected to the associated motors to provide rotational speed control to the two or more rotors to produce a desired net thrust, and a logic (624) connected to the input control (626) and the associated motors (611a-d), the logic (624) for controlling speed and direction of the two or more rotors (612a-d) to achieve the desired net thrust and to avoid a motor speed condition.

公开(公告)号：EP3552960B1

公开(公告)日：2020-05-13

申请号：EP18181177.9

申请日：2018-07-02

Applicant: Bell Helicopter Textron Inc.

Inventor： HAMPTON, Dalton T ,  HALDEMAN, Andrew Paul ,  ACEE, Aaron Alexander ,  HILL, Matthew John

IPC: B64C27/82

公开(公告)号：EP3514912A1

公开(公告)日：2019-07-24

申请号：EP18157736.2

申请日：2018-02-20

Applicant: Bell Helicopter Textron Inc.

Inventor： SINUSAS, Eric A. ,  REGNIER, Bradley Paul ,  ACEE, Aaron Alexander ,  SPELLER, Charles Hubert ,  QUELLET, Marc

IPC: H02J4/00

Abstract: A power system (30) for an aircraft (10) includes a plurality of power consumers (32, 34, 36) each operable to consume power in a range from zero to maximum power demand and collectively capable of consuming a combined maximum power demand, a power source (40) operable to output power to the power consumers (32, 34, 36) and a power allocation system (44) operable to allocate power from the power source (40) to the power consumers (32, 34, 36) based on an operational parameter of the aircraft (10). The power allocated by the power allocation system (44) is less than the combined maximum power demand of the power consumers (32, 34, 36), thereby allowing the power source (40) to have a maximum power output less than the combined maximum power demand of the power consumers (32, 34, 36).

公开(公告)号：EP3878739A1

公开(公告)日：2021-09-15

申请号：EP21167220.9

申请日：2018-12-13

Applicant: Bell Helicopter Textron Inc.

Inventor： ACEE, Aaron Alexander ,  HALDEMAN, Andrew Paul

IPC: B64C27/82 ,  B63H1/14 ,  B64C27/46 ,  B64C27/467

Abstract: A bidirectional aircraft rotor for a rotorcraft tail rotor. The rotorcraft tail rotor uses a hub and a first tail rotor blade affixed to the hub. A pitch of the first tail rotor blade is fixed, and a profile of a leading edge of the first tail rotor blade is identical to a profile of a trailing edge of the first tail rotor blade. The tail rotor is driven by a torque source, such as an electric motor or an engine. The tail rotor uses variable RPM and reversible rotational direction to provide rotorcraft with yaw control.

公开(公告)号：EP3647191A1

公开(公告)日：2020-05-06

申请号：EP18212490.9

申请日：2018-12-13

Applicant: Bell Helicopter Textron Inc.

Inventor： ACEE, Aaron Alexander ,  HALDEMAN, Andrew Paul

IPC: B64C27/82 ,  B63H1/14 ,  B64C27/46 ,  B64C27/467

Abstract: A bidirectional aircraft rotor for a rotorcraft tail rotor (301). The rotorcraft tail rotor uses a hub (121) and a first tail rotor blade (423) affixed to the hub (121). A pitch of the first tail rotor blade (423) is fixed, and a profile of a leading edge (203, 303) of the first tail rotor blade (423) is identical to a profile of a trailing edge (205, 305) of the first tail rotor blade (423). The tail rotor is driven by a torque source, such as an electric motor or an engine. The tail rotor uses variable RPM and reversible rotational direction to provide rotorcraft with yaw control.

公开(公告)号：EP3604128A1

公开(公告)日：2020-02-05

申请号：EP19188383.4

申请日：2019-07-25

Applicant: Bell Helicopter Textron Inc.

Inventor： SINUSAS, Eric Albert ,  LAMBERT, Edward ,  LAVALLEE, Yann ,  ACEE, Aaron Alexander ,  BRAND, Albert G

IPC: B64C27/00 ,  B64D45/00 ,  B64D43/00

Abstract: The disclosure relates to an aircraft (110) having an electric motor (156) coupled to a rotor (152) and an instrument (160) electronically connected to the electric motor (156) and configured to communicate a time available value before a motor condition reaches a motor condition limit.