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公开(公告)号：US20230205229A1
公开(公告)日：2023-06-29
申请号：US18085275
申请日：2022-12-20
Applicant: Electra Aero, Inc.
Inventor： Oliver MASEFIELD , Christopher B. COURTIN , Robert John HANSMAN, Jr.
CPC classification number: G05D1/0808 , B64D45/00 , B64C13/0421 , B64D27/24 , B64D31/06
Abstract: In accordance with some embodiments, a system for controlling an aircraft is provided. The system can include a computing device, wherein the computing device includes at least one processor configured to control a flight path angle of the aircraft, and wherein the aircraft is a blown lift aircraft. The system can also include a control operator communicatively coupled to the computing device, wherein the control operator is configured to have at least two selectable settings. The system can also include at least two thrust-producing devices operatively coupled to a pair of wings on the aircraft and communicatively coupled to the computing device. The computing device may control the flight path angle of the aircraft by selectively operating the at least two thrust-producing devices based on a plurality of conditions provided by a plurality of sensors on the aircraft and a selected setting of the control operator.
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公开(公告)号：US20230063801A1
公开(公告)日：2023-03-02
申请号：US17560383
申请日：2021-12-23
Applicant: ELECTRA AERO, INC.
Inventor： Christopher B. COURTIN , Mark DRELA , Robert John HANSMAN, JR. , John S. LANGFORD, III , Oliver MASEFIELD
Abstract: A system and method for lift augmentation of an aircraft having a wing with a leading edge and a trailing edge extending along a wingspan, a plurality of thrust-producing devices connected to the bottom of said wing, at least one flap connected to an inboard portion of said wing proximate the trailing edge, and an aircraft roll control device connected to said wing, wherein the improvement comprises a plurality of slipstreams associated with a plurality of thrust producing devices and a flap adaptable to deflect from a chord of the inboard portion of the wing.
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公开(公告)号：US20240051655A1
公开(公告)日：2024-02-15
申请号：US18465375
申请日：2023-09-12
Applicant: ELECTRA AERO, INC.
Inventor： Christopher B. COURTIN , Mark DRELA , Robert John HANSMAN, JR. , John S. LANGFORD, III , Oliver MASEFIELD
CPC classification number: B64C9/28 , B64C11/00 , B64C9/18 , B64D27/24 , B64C3/58 , B64C9/24 , B64C2009/005
Abstract: A system and method for lift augmentation of an aircraft having a wing with a leading edge and a trailing edge extending along a wingspan, a plurality of thrust-producing devices connected to the bottom of said wing, at least one flap connected to an inboard portion of said wing proximate the trailing edge, and an aircraft roll control device connected to said wing, wherein the improvement comprises a plurality of slipstreams associated with a plurality of thrust producing devices and a flap adaptable to deflect from a chord of the inboard portion of the wing.
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公开(公告)号：US20240045447A1
公开(公告)日：2024-02-08
申请号：US18489228
申请日：2023-10-18
Applicant: Electra Aero, Inc.
Inventor： Oliver MASEFIELD , Christopher B. COURTIN , Robert John HANSMAN, JR.
CPC classification number: G05D1/0808 , B64D45/00 , B64D31/06 , B64D27/24 , B64C13/0421
Abstract: In accordance with some embodiments, a system for controlling an aircraft is provided. The system can include a computing device, wherein the computing device includes at least one processor configured to control a flight path angle of the aircraft, and wherein the aircraft is a blown lift aircraft. The system can also include a control operator communicatively coupled to the computing device, wherein the control operator is configured to have at least two selectable settings. The system can also include at least two thrust-producing devices operatively coupled to a pair of wings on the aircraft and communicatively coupled to the computing device. The computing device may control the flight path angle of the aircraft by selectively operating the at least two thrust-producing devices based on a plurality of conditions provided by a plurality of sensors on the aircraft and a selected setting of the control operator.
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公开(公告)号：US20240409206A1
公开(公告)日：2024-12-12
申请号：US18774466
申请日：2024-07-16
Applicant: Electra Aero, Inc.
Inventor： Oliver MASEFIELD , Mark DRELA
Abstract: Systems and methods for minimizing an aircraft turn radius are disclosed. For example, a method to minimize an aircraft turn radius may include receiving an activation signal from an activation switch. The activation switch may be configured allow a selected turn. The method may also include receiving a turn command in a direction of the selected turn. The method may also include transmitting a turn signal to an actuator operatively coupled to a nosewheel assembly. The actuator may rotate a shaft in the direction of the selected turn to move at least one nosewheel from a first angle to a second angle with reference to a longitudinal axis of the aircraft. The method may also include transmitting a thrust signal to at least one of a plurality of thrust-producing devices operatively coupled to a first wing and a second wing operatively coupled to the aircraft.
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Patent Agency Ranking
公开(公告)号：US20240085926A1
公开(公告)日：2024-03-14
申请号：US18494416
申请日：2023-10-25
Applicant: Electra Aero, Inc.
Inventor： Robert John HANSMAN, JR. , Christopher B. COURTIN , Oliver MASEFIELD
CPC classification number: G05D1/0825 , B64C13/16 , B64D31/10
Abstract: An aircraft may include a tail having a rudder and a pair of wings. The pair of wings may include at least one flap and at least one roll control device. The aircraft may also include at least two thrust-producing devices. The aircraft may also include a differential thrust control system including a computing device having at least one processor. The at least one processer may be configured to control an attitude of the aircraft by selectively operating the at least two thrust-producing devices, the rudder, and the at least one roll control device based at least in part on a plurality of conditions provided by a plurality of sensors on the aircraft and a selected mode setting of a mode control panel. The computing device may be communicatively coupled to the at least two thrust-producing devices, the rudder, and the at least one roll control device.
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公开(公告)号：US20230280764A1
公开(公告)日：2023-09-07
申请号：US18114828
申请日：2023-02-27
Applicant: Electra Aero, Inc.
Inventor： Robert John HANSMAN, JR. , Christopher B. COURTIN , Oliver MASEFIELD
CPC classification number: G05D1/0825 , B64C13/16 , B64D31/10
Abstract: An aircraft may include a tail having a rudder and a pair of wings. The pair of wings may include at least one flap and at least one roll control device. The aircraft may also include at least two thrust-producing devices. The aircraft may also include a differential thrust control system including a computing device having at least one processor. The at least one processer may be configured to control an attitude of the aircraft by selectively operating the at least two thrust-producing devices, the rudder, and the at least one roll control device based at least in part on a plurality of conditions provided by a plurality of sensors on the aircraft and a selected mode setting of a mode control panel. The computing device may be communicatively coupled to the at least two thrust-producing devices, the rudder, and the at least one roll control device.
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公开(公告)号：US20240059403A1
公开(公告)日：2024-02-22
申请号：US18500352
申请日：2023-11-02
Applicant: Electra Aero, Inc.
Inventor： Oliver MASEFIELD , Mark DRELA
Abstract: Systems and methods for minimizing an aircraft turn radius are disclosed. For example, a method to minimize an aircraft turn radius may include receiving an activation signal from an activation switch. The activation switch may be configured allow a selected turn. The method may also include receiving a turn command in a direction of the selected turn. The method may also include transmitting a turn signal to an actuator operatively coupled to a nosewheel assembly. The actuator may rotate a shaft in the direction of the selected turn to move at least one nosewheel from a first angle to a second angle with reference to a longitudinal axis of the aircraft. The method may also include transmitting a thrust signal to at least one of a plurality of thrust-producing devices operatively coupled to a first wing and a second wing operatively coupled to the aircraft.
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公开(公告)号：US20230294824A1
公开(公告)日：2023-09-21
申请号：US18122532
申请日：2023-03-16
Applicant: Electra Aero, Inc.
Inventor： Oliver MASEFIELD , Mark DRELA
Abstract: Systems and methods for minimizing an aircraft turn radius are disclosed. For example, a method to minimize an aircraft turn radius may include receiving an activation signal from an activation switch. The activation switch may be configured allow a selected turn. The method may also include receiving a turn command in a direction of the selected turn. The method may also include transmitting a turn signal to an actuator operatively coupled to a nosewheel assembly. The actuator may rotate a shaft in the direction of the selected turn to move at least one nosewheel from a first angle to a second angle with reference to a longitudinal axis of the aircraft. The method may also include transmitting a thrust signal to at least one of a plurality of thrust-producing devices operatively coupled to a first wing and a second wing operatively coupled to the aircraft.
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公开(公告)号：US20230234718A1
公开(公告)日：2023-07-27
申请号：US18100935
申请日：2023-01-24
Applicant: Electra Aero, Inc.
Inventor： Oliver MASEFIELD , Mark DRELA , Christopher B. COURTIN
CPC classification number: B64D31/00 , B64C5/02 , B64D27/24 , B64C9/00 , G05D1/0808
Abstract: In some embodiments, a lift augmentation system for a blown lift aircraft includes a blown lift tailplane operatively coupled to the blown lift aircraft. The blown lift tailplane may include a leading edge and a trailing edge, an upper surface and a lower surface, and a first side and a second side. The lift augmentation system may include one or more tailplane thrust-producing devices on the first side and the second side of the blown lift tailplane operatively coupled to the leading edge of the blown lift tailplane. The one or more tailplane thrust-producing devices on the first side and the second side of the blown lift tailplane may produce a plurality of slipstreams corresponding to each of the tailplane thrust-producing devices. The plurality of slipstreams corresponding to each of the tailplane thrust-producing devices may blow over the upper surface and the lower surface of the blown lift tailplane.
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