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公开(公告)号：US20200026811A1
公开(公告)日：2020-01-23
申请号：US16293425
申请日：2019-03-05
Applicant: Bell Helicopter Textron Inc.
Inventor： Michael McNair , Brent Chadwick Ross , Christopher Stroncek , Kip Gregory Campbell , Joseph Scott Drennan , Brett Zimmerman , Carey Cannon
Abstract: A method of operating a targeting system simulation tool (TSST) includes providing a TSST configured to receive an obstacle/effect parameterization, a simulation parameterization, a sensor parameterization, an aircraft parameterization, and an autonomy parameterization. The method further includes receiving by the TSST, at least one of each of an obstacle/effect parameterization and a simulation parameterization. The method further includes receiving by the TSST, either (1) a sensor parameterization or (2) an aircraft parameterization. The method further includes operating the TSST to apply the provided ones of the obstacle/effect parameterization, simulation parameterization, sensor parameterization, and aircraft parameterization to generate a value, value range, or value limit for the unprovided aircraft parameterization or unprovided sensor parameterization.
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公开(公告)号：US20200023941A1
公开(公告)日：2020-01-23
申请号：US16416508
申请日：2019-05-20
Applicant: Bell Helicopter Textron Inc.
Inventor： Luke Dafydd Gillett , Sung Kyun Kim , Robert Earl Worsham, II
Abstract: In an embodiment, a rotorcraft includes: a flight control computer configured to: receive a first sensor signal from a first aircraft sensor of the rotorcraft; receive a second sensor signal from a second aircraft sensor of the rotorcraft, the second aircraft sensor being different from the first aircraft sensor; combine the first sensor signal and the second sensor signal with a complementary filter to determine an estimated vertical speed of the rotorcraft; adjust flight control devices of the rotorcraft according to the estimated vertical speed of the rotorcraft, thereby changing flight characteristics of the rotorcraft; and reset the complementary filter in response to detecting the rotorcraft is grounded.
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公开(公告)号：US20200017211A1
公开(公告)日：2020-01-16
申请号：US16031741
申请日：2018-07-10
Applicant: Bell Helicopter Textron Inc.
Inventor： Levi Charles Hefner , Dakota Charles Easley
Abstract: An unmanned aircraft system includes a flying wing airframe having leading and trailing edges with respective sweep angles. A thrust array is coupled to the airframe and includes first and second motor mounts each rotatably coupled to the leading edge. Each motor mount has first and second propulsion assemblies coupled to respective first and second distal ends thereof. A power system is operably associated with the thrust array and is operable to provide power to each propulsion assembly. A flight control system is operably associated with the thrust array and is operable to independently control the speed of each propulsion assembly. In a flight configuration of the system, each motor mount is substantially perpendicular with the leading edge such that the thrust array forms a two-dimensional thrust array. In a compact storage configuration of the system, each motor mount is substantially parallel with the leading edge.
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公开(公告)号：US20200016880A1
公开(公告)日：2020-01-16
申请号：US16036228
申请日：2018-07-16
Applicant: Bell Helicopter Textron Inc.
Inventor： Suvankar Mishra , Jesse J. Wrabel , Vance N. Cribb, III
Abstract: A method is provided in one example embodiment and may include forming a ply stack comprising a plurality of uncured composite plies, wherein one or more uncured composite ply of the plurality of uncured composite plies comprises a plurality of perforations that extend, at least partially, through a thickness of the one or more uncured composite ply; and compacting the ply stack to form a composite structure. The plurality of perforations may provide paths for volatiles to be removed through the thickness of the one or more uncured composite ply of the ply stack during the compacting. Volatiles may also be removed through edges of the ply stack during the compacting. In some instances, all uncured composite plies of the ply stack may include a plurality of perforations that extend, at least partially, through the thickness of each uncured composite ply.
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公开(公告)号：US10532810B2
公开(公告)日：2020-01-14
申请号：US15603119
申请日：2017-05-23
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Richard E. Rauber , Mithat Yuce , Thomas C. Parham, Jr. , Thomas J. Newman , Mark A. Wiinikka
Abstract: An aircraft includes a rotor blade and a rotor hub system. The rotor hub system includes a lead-lag damper having a rod end and being operably associated with the rotor blade; a blade adapter having a first arm and an opposing second arm; a pin carried by the blade adapter and configured to secure in position via the first arm and the second arm; and an actuator secured to the pin and configured to adjust the position of the lead-lag rod end relative to the first arm and the second arm.
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Patent Agency Ranking
公开(公告)号：US20200003908A1
公开(公告)日：2020-01-02
申请号：US16022455
申请日：2018-06-28
Applicant: Bell Helicopter Textron Inc.
Inventor： Robert Earl Worsham, II , Charles Eric Covington , Thomas Wayne Brooks
Abstract: A rotorcraft includes a flight control computer (FCC), a GPS receiver configured to calculate a groundspeed based on a first carrier signal, and an attitude and heading reference system (AHRS) configured to determine an acceleration of the rotorcraft. The AHRS is operable to receive an indication of the groundspeed from the GPS receiver and to calculate a velocity of the rotorcraft based on the indication of the groundspeed and the acceleration. The FCC is operable to receive an indication of the velocity from the AHRS, to generate the flight control device control signal according to the indication of velocity, and to send a flight control device control signal to one or more flight control devices.
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公开(公告)号：US20200001987A1
公开(公告)日：2020-01-02
申请号：US16084970
申请日：2017-03-14
Applicant: BELL HELICOPTER TEXTRON, INC.
Inventor： Jouyoung Jason CHOI , David HEVERLY , Michael SEIFERT , Michael SMITH , Frank Brad STAMPS , Thomas PARHAM, JR. , Amarjit Olenchery KIZHAKKEPAT
Abstract: A vibration attenuation system for attenuating vibrations in a mast of an aircraft includes a weight attached to the mast but free to orbit about the mast. The weight can be comprised of one or more weight assemblies. Embodiments can include a single weight, or plural weight assemblies wherein each weight assembly can include a mechanical interconnecting mechanism so that each weight assembly receives feedback regarding the position and movement of one or more other weight assemblies. Each weight can be associated with a spring that urges the weight towards a neutral position. Rotation of the mast can cause the weight to orbit about the mast and self-excite such that the weight acts against the urging of the spring towards an attenuating position.
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公开(公告)号：US10518906B2
公开(公告)日：2019-12-31
申请号：US15634903
申请日：2017-06-27
Applicant: Bell Helicopter Textron Inc.
Inventor： Alan Soo Love
Abstract: A system has a flight measurement sensor configured to provide a flight measurement of an aircraft, a regime engine configured to identify a plurality of flight regimes that the aircraft operated in during a period of time, a component engine configured to assign a first flight regime of the plurality of flight regimes to a first component of the aircraft for the period of time, and a health assessment system configured to determine an amount of damage inflicted on the component as a result of the first component spending time in the first flight regime assigned by the component engine.
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公开(公告)号：US20190389571A1
公开(公告)日：2019-12-26
申请号：US16014441
申请日：2018-06-21
Applicant: Bell Helicopter Textron Inc.
Inventor： Colton Gilliland , Jeffrey Williams , Michael E. Rinehart , James Kooiman , Mark Przybyla , Clegg Smith , Eric Stephen Olson , George Ryan Decker , David Russell Bockmiller
Abstract: A tiltrotor aircraft includes a propulsion system with a fixed engine and a rotatable proprotor. The engine is located below the wing of the tiltrotor aircraft, and the rotatable proprotor assembly is mounted on the top surface of the wing. The engine and proprotor assembly are connected via a series of one or more gearboxes that route the engine output from the engine to the proprotor.
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公开(公告)号：US20190389568A1
公开(公告)日：2019-12-26
申请号：US16013201
申请日：2018-06-20
Applicant: Bell Helicopter Textron Inc.
Inventor： Carlos Alexander Fenny , Jouyoung Jason Choi
Abstract: An aircraft comprises a fuselage, one or more support structures connected to the fuselage, one or more engines or motors disposed within or attached to the one or more support structures or the fuselage, and a distributed propulsion system. The distributed propulsion system comprising two or more propellers symmetrically distributed in an array along the one or more support structures with respect to a center of gravity of the aircraft and operably connected to the one or more engines or motors, wherein each propeller has a rotation direction within a tilted plane of rotation, and a summation of horizontal force vectors created by the tilted plane of rotation of all the propellers is substantially zero when all the propellers are creating a substantially equal thrust magnitude. Movement of the aircraft is controlled by selectively increasing or decreasing a thrust of at least one of the two or more propellers.
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