US-12623772-B2 - Regenerative high lift magnetic clutch and brake generator for electric aircraft

US12623772B2US 12623772 B2US12623772 B2US 12623772B2US-12623772-B2

Abstract

An electric aircraft includes system for operating the aircraft. The electric aircraft includes a wing having a first control surface, a second control surface, a battery and a gearbox mechanically coupled to the first control surface. The first control surface is operated, and a voltage is induced from mechanical energy generated during a deceleration of the first control surface that occurs while operating the first control surface, wherein an airflow across the first control surface causes the deceleration. The induced voltage can be stored at the battery or used to operate the second control surface using the induced voltage.

Inventors

Darrell E. Ankney

Assignees

HAMILTON SUNDSTRAND CORPORATION

Dates

Publication Date: 20260512
Application Date: 20240117

Claims (14)

1 . A method of operating an electric aircraft, comprising: operating a first control surface on a wing of the electric aircraft; generating an induced voltage from mechanical energy generated during a deceleration of the first control surface that occurs while operating the first control surface, wherein an airflow across the first control surface causes the deceleration; operating a second control surface on the wing using the induced voltage; and rotating a rotor shaft in a gearbox from mechanical energy, the rotor shaft including an armature rotatable within a stator coil for generating the induced voltage.
2 . The method of claim 1 , wherein the rotor shaft is mechanically coupled to the first control surface, further comprising activating a clutch at the rotor shaft to mechanically couple the rotor shaft to the second control surface.
3 . The method of claim 2 , further comprising inputting the induced voltage to a boost transformer, wherein a boosted voltage from the boost transformer is used to regenerate a battery.
4 . The method of claim 3 , further comprising electrically isolating the stator coil from the battery via the boost transformer.
5 . The method of claim 3 , further comprising using the battery to control at least one of the first control surface and the second control surface.
6 . The method of claim 1 , wherein the first control surface is one of a slat and a flap and the second control surface is another of the slat and the flap.
7 . The method of claim 6 , further comprising at least one of: (i) controlling an operation of the slat via the mechanical energy generated during a deceleration of the flap during a pre-takeoff operation; (ii) controlling the operation of the flap via the mechanical energy generated during the deceleration of the slat during a post-takeoff operation; (iii) controlling the operation of the slat via the mechanical energy generated during the deceleration of the flap during a pre-landing operation; and (iv) controlling the operation of the flap via the mechanical energy generated during the deceleration of the slat during a post-landing operation.
8 . A system for operating an electric aircraft, comprising: a first control surface on a wing of the electric aircraft; a second control surface on the wing; a battery; and a gearbox mechanically coupled to the first control surface, wherein the gearbox is configured to generate an induced voltage at the battery from mechanical energy generated during a deceleration of the first control surface due to an airflow across the first control surface and operate the second control surface using the induced voltage.
9 . The system of claim 8 , wherein the gearbox further comprises a rotor shaft configured to rotate from the mechanical energy from the first control surface, the rotor shaft including an armature rotatable within a stator coil of the gearbox.
10 . The system of claim 9 , wherein the rotor shaft is mechanically coupled to the first control surface, further comprising a clutch configured to mechanically couple the rotor shaft to the second control surface.
11 . The system of claim 10 , further comprising a boost transformer coupled to the stator coil, wherein the induced voltage generated at the gearbox is supplied to the boost transformer and the boost transformer is configured to supply a boosted voltage to the battery.
12 . The system of claim 11 , wherein the boost transformer is configured to electrically isolate the stator coil from the battery.
13 . The system of claim 11 , wherein the battery is configured to control an operation of at least one of the first control surface and the second control surface.
14 . The system of claim 8 , wherein the first control surface is one of a slat and a flap and the second control surface is another of the slat and the flap.

Description

BACKGROUND Exemplary embodiments pertain to the art of electric aircraft and, in particular, to a system and method for power transfer between control surfaces of the aircraft and regenerating batteries of an electric aircraft using energy harvest from motion of the control surfaces. Electric aircraft are powered by battery supplies located on the aircraft. An important consideration is conserving energy during flight in order not to run out of battery power. Slats and flaps are used during takeoff and landing and require electrical power. The slats and flaps encounter resistance during their motion, which is energetically costly. Accordingly, there is desired to move these surfaces in a manner that reduces energy costs. BRIEF DESCRIPTION Disclosed is a method of operating an electric aircraft. A first control surface on a wing of the electric aircraft is operated. A voltage is induced from mechanical energy generated during a deceleration of the first control surface that occurs while operating the first control surface, wherein an airflow across the first control surface causes the deceleration. A second control surface on the wing is operated using the induced voltage. Additionally or alternatively, in this or other embodiments, the method further includes rotating a rotor shaft in a gearbox from the mechanical energy, the rotor shaft including an armature rotatable within a stator coil for generating the induced voltage. Additionally or alternatively, in this or other embodiments, wherein the rotor shaft is mechanically coupled to the first control surface, the method further includes activating a clutch at the rotor shaft to mechanically couple the rotor shaft to the second control surface. Additionally or alternatively, in this or other embodiments, the method further includes inputting the induced voltage to a boost transformer, wherein a boosted voltage from the boost transformer is used to regenerate a battery. Additionally or alternatively, in this or other embodiments, the method further includes electrically isolating the stator coil from the battery via the boost transformer. Additionally or alternatively, in this or other embodiments, the method further includes using the battery to control at least one of the first control surface and the second control surface. Additionally or alternatively, in this or other embodiments, the first control surface is one of a slat and a flap and the second control surface is another of the slat and the flap. Additionally or alternatively, in this or other embodiments, the method further includes at least one of: (i) controlling an operation of the slat via the mechanical energy generated during a deceleration of the flap during a pre-takeoff operation; (ii) controlling the operation of the flap via the mechanical energy generated during the deceleration of the slat during a post-takeoff operation; (iii) controlling the operation of the slat via the mechanical energy generated during the deceleration of the flap during a pre-landing operation; and (iv) controlling the operation of the flap via the mechanical energy generated during the deceleration of the slat during a post-landing operation. Also disclosed is a system for operating an electric aircraft. The system includes a first control surface on a wing of the electric aircraft, a second control surface on the wing, a battery, and a gearbox mechanically coupled to the first control surface. The gearbox is configured to generate an induced voltage at the battery from mechanical energy generated during a deceleration of the first control surface due to an airflow across the first control surface and operate the second control surface using the induced voltage. Additionally or alternatively, in this or other embodiments, the gearbox further includes a rotor shaft configured to rotate from the mechanical energy from the first control surface, the rotor shaft including an armature rotatable within a stator coil of the gearbox. Additionally or alternatively, in this or other embodiments, the rotor shaft is mechanically coupled to the first control surface and the system further includes a clutch configured to mechanically couple the rotor shaft to the second control surface. Additionally or alternatively, in this or other embodiments, the system further includes a boost transformer coupled to the stator coil, wherein the induced voltage generated at the gearbox is supplied to the boost transformer and the boost transformer is configured to supply a boosted voltage to the battery. Additionally or alternatively, in this or other embodiments, the boost transformer is configured to electrically isolate the stator coil from the battery. Additionally or alternatively, in this or other embodiments, the battery is configured to control an operation of at least one of the first control surface and the second control surface. Additionally or alternatively, in this or other embodiments, the first control surface is one of