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公开(公告)号：US20190270516A1
公开(公告)日：2019-09-05
申请号：US15909246
申请日：2018-03-01
Applicant: Bell Helicopter Textron Inc.
Inventor： Eric A. Sinusas , Erik John Oltheten , Carlos Alexander Fenny
Abstract: A propulsion system for a rotorcraft includes a first fan assembly including a plurality of first fan blades, a second fan assembly including a plurality of second fan blades and a drive system adapted to provide torque to the first and second fan blades. The first fan blades have a larger rotational inertia than the second fan blades. The second fan blades are adapted to experience a larger angular acceleration than the first fan blades in response to torque from the drive system, thereby providing responsive thrust control for the rotorcraft.
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公开(公告)号：US20190071173A1
公开(公告)日：2019-03-07
申请号：US16183035
申请日：2018-11-07
Applicant: Bell Helicopter Textron Inc.
Inventor： Thomas Dewey Parsons , Carlos Alexander Fenny , Erik John Oltheten
IPC: B64C27/82
Abstract: The present invention includes an anti-torque assembly for a helicopter comprising a plurality of fixed blade pitch motors mounted on one or more pivots on the tail boom of the helicopter, wherein the plurality of fixed blade pitch motors on the one or more pivots are adapted to be oriented substantially in-plane with a tail boom of a helicopter during a first mode of operation that comprises a hover mode and wherein the fixed blade pitch motors are adapted to be oriented substantially off-plane from the tail boom of the helicopter during a second mode of helicopter operation that is different from the first mode.
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公开(公告)号：US10457417B2
公开(公告)日：2019-10-29
申请号：US16171672
申请日：2018-10-26
Applicant: Bell Helicopter Textron Inc.
Inventor： Erik John Oltheten , Thomas Wayne Brooks
Abstract: Embodiments are directed to flight instrument warnings that are configured to automatically adjust a low airspeed warning band on an airspeed indicator based on available torque margin and radar altimeter height. Warnings may be presented on a primary flight display or on flight instruments when a low airspeed band is entered.
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公开(公告)号：US11035877B2
公开(公告)日：2021-06-15
申请号：US16129173
申请日：2018-09-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Erik John Oltheten , Eric Walter Nottorf
Abstract: Various implementation described herein are directed to a method for identifying a blockage in a pitot-static system. A pressure signal is received. Pressure fluctuations in the pressure signal are identified. A determination is made as to whether a blockage has occurred in the pitot-static system based on the identified pressure fluctuations.
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公开(公告)号：US10676212B2
公开(公告)日：2020-06-09
申请号：US15906533
申请日：2018-02-27
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Erik John Oltheten
IPC: H05B33/08 , B64D45/00 , H05B45/00 , H05B45/37 , H05B45/395 , B64D47/02 , G02B5/02 , G09F13/22 , H01G11/00
Abstract: An emergency lighting system (ELS) for an aircraft has a capacitor, at least one of an onboard power system and a ground power unit configured to charge the capacitor, and a light emitting diode (LED) selectively powered by the capacitor.
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Patent Agency Ranking
公开(公告)号：US20200081031A1
公开(公告)日：2020-03-12
申请号：US16129173
申请日：2018-09-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Erik John Oltheten , Eric Walter Nottorf
Abstract: Various implementation described herein are directed to a method for identifying a blockage in a pitot-static system. A pressure signal is received. Pressure fluctuations in the pressure signal are identified. A determination is made as to whether a blockage has occurred in the pitot-static system based on the identified pressure fluctuations.
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公开(公告)号：US20190250606A1
公开(公告)日：2019-08-15
申请号：US15894876
申请日：2018-02-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Erik John Oltheten , Aaron Thomas Halverson , Eric Gordon Emblin
Abstract: An autopilot recoupling system for a rotorcraft having an automatic flight control system with multiple layers of flight augmentation. The autopilot recoupling system includes an autopilot recoupling input operable to generate an autopilot recoupling signal. An autopilot recoupling signal processor is communicably coupled to the autopilot recoupling input. The autopilot recoupling signal processor is configured to receive the autopilot recoupling signal from the autopilot recoupling input and responsive thereto, determine a state of the automatic flight control system, activate a trim systems layer of the automatic flight control system if the trim systems layer is not active, engage an attitude retention systems layer of the automatic flight control system if the attitude retention systems layer is disengage and recouple an autopilot systems layer of the automatic flight control system.
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公开(公告)号：US10377479B2
公开(公告)日：2019-08-13
申请号：US15172811
申请日：2016-06-03
Applicant: Bell Helicopter Textron Inc.
Inventor： Thomas Dewey Parsons , Carlos Alexander Fenny , Erik John Oltheten
Abstract: The present invention includes an anti-torque assembly for a helicopter comprising a plurality of fixed blade pitch motors mounted on one or more pivots on the tail boom of the helicopter, wherein the plurality of fixed blade pitch motors on the one or more pivots are adapted to be oriented substantially in-plane with a tail boom of a helicopter during a first mode of operation that comprises a hover mode and wherein the fixed blade pitch motors are adapted to be oriented substantially off-plane from the tail boom of the helicopter during a second mode of helicopter operation that is different from the first mode.
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公开(公告)号：US10173787B1
公开(公告)日：2019-01-08
申请号：US15894880
申请日：2018-02-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Erik John Oltheten , Aaron Thomas Halverson
Abstract: A rotor speed indication system configured to communicate a rotor speed operating range for a twin engine rotorcraft having a rotor during one engine inoperable conditions. The rotor speed indication system includes a governing reference indicator located on a display and configured to communicate an upper operating range threshold. A droop reference indicator located on the display and configured to communicate a lower operating range threshold. A sensor configured to measure a current rotor speed of the rotor. A dynamic rotor speed indicator located on the display and configured to communicate the current rotor speed of the rotor such that when the dynamic rotor speed indicator is positioned between the governing reference indicator and the droop reference indicator on the display, the current rotor speed of the rotor is within the rotor speed operating range.
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公开(公告)号：US09902502B2
公开(公告)日：2018-02-27
申请号：US14870796
申请日：2015-09-30
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Erik John Oltheten
CPC classification number: B64D45/0015 , B64D45/00 , B64D47/02 , B64D2045/007 , B64D2203/00 , G02B5/0284 , G09F13/22 , G09F2013/222 , H01G11/00 , H05B33/0806 , H05B33/0812 , H05B33/0815 , Y02B20/343
Abstract: An emergency lighting system (ELS) for an aircraft has a capacitor, at least one of an onboard power system and a ground power unit configured to charge the capacitor, and a light emitting diode (LED) selectively powered by the capacitor.
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