公开(公告)号：US12110102B2

公开(公告)日：2024-10-08

申请号：US18022384

申请日：2021-08-23

申请人： HILL GROUP TECHNOLOGIES LIMITED

发明人： Jason Hill

IPC分类号： B64C27/06 ,  B64C17/00 ,  B64D41/00 ,  H01M8/04082 ,  H01M8/04746

CPC分类号： B64C27/06 ,  B64C17/00 ,  B64D41/00 ,  H01M8/04201 ,  H01M8/04753 ,  B64D2041/005 ,  H01M2250/20

摘要： Disclosed is a helicopter having a longitudinal axis, a lateral axis and a vertical axis, a helicopter centre of mass and a maximum gross mass of less than 5000 kg, the helicopter comprising a fuselage elongate along the longitudinal axis, the fuselage comprising an aerodynamically shaped shell defining a front, a rear, a top and a bottom of the fuselage and a passenger cabin therein having two forward-facing front seating positions for the pilot and a co-pilot or a passenger, and forward-facing rear seating positions for at least 2 passengers, optionally 3 passengers; a primary fuel cell mounted substantially behind the passenger cabin; the front seating position for the pilot having a centre of mass at a first location substantially in front of the rotor hub location, and the primary fuel cell having a centre of mass at a second location substantially behind the rotor hub location; a landing gear arrangement; a power plant mounted substantially above and behind the passenger cabin, wherein the primary fuel cell is arranged to provide fuel to the power plant; and a secondary fuel cell having a centre of mass at a nose location in front of the rotor hub location by at least 1500 mm.

公开(公告)号：US11866145B2

公开(公告)日：2024-01-09

申请号：US16565919

申请日：2019-09-10

申请人： Infineon Technologies AG

发明人： Saumitra Sanjeev Chafekar ,  Ankit Kalbande

IPC分类号： B64C17/00 ,  B64C39/02 ,  B64D45/00

CPC分类号： B64C17/00 ,  B64C39/02 ,  B64D45/00 ,  B64U2201/10

摘要： A device for sensing a physical parameter includes a sensor element configured for measuring the physical parameter and for outputting a corresponding measured signal, wherein the measured signal is influenceable by a sensor drift of the sensor element. The device includes a corrector for correcting the measured signal output by the sensor element to obtain a corrected signal, wherein the corrector is configured for evaluating the measured signal to determine a drift effect of the sensor drift on the measured signal and for correcting the measured signal so as to at least partially compensate for the drift effect. The device includes a signal output configured for outputting the corrected signal.

公开(公告)号：US11767112B2

公开(公告)日：2023-09-26

申请号：US18112832

申请日：2023-02-22

申请人： Textron Innovations Inc.

发明人： John Richard McCullough ,  Paul K. Oldroyd

IPC分类号： B64C39/08 ,  B64C29/00 ,  B64C3/56 ,  B64C11/46 ,  B64C17/00 ,  B64C29/02 ,  B64C39/02 ,  B64D27/24 ,  B64D27/26 ,  B64C27/30 ,  B64C1/06 ,  G05D1/00 ,  G05D1/10 ,  B64U30/10 ,  B64U30/20 ,  B64U101/60

CPC分类号： B64C39/08 ,  B64C1/063 ,  B64C3/56 ,  B64C11/46 ,  B64C17/00 ,  B64C27/30 ,  B64C29/0033 ,  B64C29/02 ,  B64C39/024 ,  B64D27/24 ,  B64D27/26 ,  G05D1/0094 ,  G05D1/101 ,  G05D1/102 ,  G05D1/106 ,  B64C2211/00 ,  B64D2027/262 ,  B64U30/10 ,  B64U30/20 ,  B64U2101/60

摘要： An aircraft is configured for thrust-borne lift in a vertical takeoff and landing flight mode and wing-borne lift in a forward flight mode. The aircraft includes an airframe having a first wing and a first payload station. A distributed propulsion system that is coupled to the airframe includes a plurality of propulsion assemblies configured to provide vertical thrust in the vertical takeoff and landing flight mode and forward thrust in the forward flight mode. A control system is operably associated with the distributed propulsion system and is operable to independently control each of the propulsion assemblies. A payload module is configured to be transported by the airframe from a pickup location to a delivery location. The payload module is magnetically coupled to the first payload station during transportation and, responsive to a command from the control system, is magnetically decoupled from the first payload station at the delivery location.

公开(公告)号：US20230060888A1

公开(公告)日：2023-03-02

申请号：US17948500

申请日：2022-09-20

申请人： Gaofei YAN ,  James DEES

发明人： Gaofei YAN ,  James DEES

IPC分类号： B64C1/06 ,  A63H33/00 ,  A63H27/00 ,  A63H15/06 ,  B64C17/00 ,  B64C1/08 ,  A63H30/04 ,  B64C27/10 ,  B64C1/00 ,  B64C17/02 ,  B64C39/02 ,  B64D47/08 ,  G05D1/08 ,  B64C27/20 ,  G05D1/00

摘要： An aeronautical vehicle that rights itself from an inverted state to an upright state has a self-righting frame assembly has a protrusion extending upwardly from a central vertical axis. The protrusion provides an initial instability to begin a self-righting process when the aeronautical vehicle is inverted on a surface. A propulsion system, such as rotor driven by a motor can be mounted in a central void of the self-righting frame assembly and oriented to provide a lifting force. A power supply is mounted in the central void of the self-righting frame assembly and operationally connected to the at least one rotor for rotatably powering the rotor. An electronics assembly is also mounted in the central void of the self-righting frame for receiving remote control commands and is communicatively interconnected to the power supply for remotely controlling the aeronautical vehicle to take off, to fly, and to land on a surface.

公开(公告)号：US20210316843A1

公开(公告)日：2021-10-14

申请号：US17308309

申请日：2021-05-05

申请人： Bell Textron Inc.

发明人： Derek William HEARD ,  Richard Theodore PERRYMAN ,  Nathan Craig CLARK ,  Joshua Andrew EMRICH ,  Yann LAVALLEE ,  Ralph Michael GANNARELLI

IPC分类号： B64C17/00

摘要： A movable ballast system for an aircraft includes first and second ballast docks secured to the aircraft. The first ballast dock includes a first housing and a first ballast tray secured within the first housing. The first ballast tray includes a plurality of channels. The second ballast dock is positioned aft of a CG of the aircraft and includes a second housing and a second ballast tray secured within the second housing. The second ballast tray includes a plurality of channels. The movable ballast system includes a plurality of movable ballasts, each movable ballast of the plurality of movable ballasts being configured to fit within at least one channel of each of the plurality of channels of the first and second ballast trays.

公开(公告)号：US20200247522A1

公开(公告)日：2020-08-06

申请号：US16799799

申请日：2020-02-24

申请人： Gaofei YAN ,  James Dees

发明人： Gaofei YAN ,  James Dees

IPC分类号： B64C1/06 ,  G05D1/00 ,  B64C27/20 ,  G05D1/08 ,  B64D47/08 ,  B64C39/02 ,  B64C17/02 ,  B64C1/00 ,  B64C27/10 ,  A63H30/04 ,  B64C1/08 ,  B64C17/00 ,  A63H15/06 ,  A63H27/00 ,  A63H33/00

摘要： An aeronautical vehicle that rights itself from an inverted state to an upright state has a self-righting frame assembly has a protrusion extending upwardly from a central vertical axis. The protrusion provides an initial instability to begin a self-righting process when the aeronautical vehicle is inverted on a surface. A propulsion system, such as rotor driven by a motor can be mounted in a central void of the self-righting frame assembly and oriented to provide a lifting force. A power supply is mounted in the central void of the self-righting frame assembly and operationally connected to the at least one rotor for rotatably powering the rotor. An electronics assembly is also mounted in the central void of the self-righting frame for receiving remote control commands and is communicatively interconnected to the power supply for remotely controlling the aeronautical vehicle to take off, to fly, and to land on a surface.

公开(公告)号：US10539201B2

公开(公告)日：2020-01-21

申请号：US15810793

申请日：2017-11-13

申请人： The Boeing Company

发明人： Steven F. Griffin ,  Stefan P. Hovik

IPC分类号： F16F7/04 ,  B64C17/00 ,  G01M9/04 ,  F16F7/10 ,  F16F15/02 ,  F16F7/104

摘要： Methods of damping vibrations in a host structure are described. In one embodiment, the vibrations can be damped using a tuned mass damper. The tuned mass damper can include a suspended mass with magnets which is configured to move in response to current being applied to a voice coil. The tuned mass damper can damp vibrations resulting from an external load applied to the host structure, such as an external aerodynamic load. In one embodiment, the tuned mass damper can be mounted within a wind tunnel model undergoing transonic testing. The tuned mass damper can be operated to limit potentially destructive vibrations which can occur during testing.

公开(公告)号：US10526066B2

公开(公告)日：2020-01-07

申请号：US16398344

申请日：2019-04-30

申请人： Hideo Suzuki

发明人： Hideo Suzuki ,  Sachihiro Suzuki ,  Kotaro Matsushita ,  Masaki Hanada ,  Toru Shinohara ,  Noriko Niijima ,  Tadao Nakamura

IPC分类号： B64C9/06 ,  B64D27/02 ,  B64C19/02 ,  B64C17/00 ,  B64C29/00

摘要： An aircraft encompasses a main-body, a frame-structure to support the main-body, main and auxiliary rotors provided to the frame-structure and a controller for controlling rotations of the main and auxiliary rotors. In a first mode, the controller delivers a same control signal for rotating the set of the main and auxiliary rotors, and when one of the main and auxiliary rotors becomes abnormal, the controller delivers the same control signal for compensating a decrease of the lift. In a second mode, the controller delivers a control signal only to the normal rotor for increasing the rotation of the normal rotor. Sets of the main and auxiliary rotors in divided regions adjacent to a subject divided region are rotated in a direction counter to the subject divided region. By the first and second modes, the lifts are equalized for balancing the aircraft.

公开(公告)号：US10479503B2

公开(公告)日：2019-11-19

申请号：US16247791

申请日：2019-01-15

申请人： Vita Inclinata Technologies, Inc.

发明人： Derek Sikora ,  Caleb B. Carr ,  Logan Goodrich

IPC分类号： B64D9/00 ,  B64D1/08 ,  H04W4/02 ,  G05D1/10 ,  B64C17/00

摘要： Load stability systems and methods for stabilizing swinging motions of suspended loads. The load stability systems include a fully automated, self-powered device that employs thrust to counteract and control lateral and rotational motion of an external load. The device is a temporary installment on the load, cable, or boom, and is agnostic to the platform from which it is suspended.

公开(公告)号：US20190256191A1

公开(公告)日：2019-08-22

申请号：US16398344

申请日：2019-04-30

申请人： Hideo SUZUKI

发明人： Hideo SUZUKI ,  Sachihiro SUZUKI ,  Kotaro MATSUSHITA ,  Masaki HANADA ,  Toru SHINOHARA ,  Noriko NIIJIMA ,  Tadao NAKAMURA

IPC分类号： B64C9/06 ,  B64D27/02 ,  B64C29/00 ,  B64C19/02 ,  B64C17/00

摘要： An aircraft encompasses a main-body, a frame-structure to support the main-body, main and auxiliary rotors provided to the frame-structure and a controller for controlling rotations of the main and auxiliary rotors. In a first mode, the controller delivers a same control signal for rotating the set of the main and auxiliary rotors, and when one of the main and auxiliary rotors becomes abnormal, the controller delivers the same control signal for compensating a decrease of the lift. In a second mode, the controller delivers a control signal only to the normal rotor for increasing the rotation of the normal rotor. Sets of the main and auxiliary rotors in divided regions adjacent to a subject divided region are rotated in a direction counter to the subject divided region. By the first and second modes, the lifts are equalized for balancing the aircraft.