-
公开(公告)号：US11505302B2
公开(公告)日：2022-11-22
申请号：US16421371
申请日：2019-05-23
Applicant: Textron Innovations Inc.
Inventor： John Richard McCullough , Paul K. Oldroyd
IPC: B64C27/605 , B64C3/10 , B64C27/54 , B64C29/00
Abstract: A rotor assembly for an aircraft operable to generate a variable thrust output at a constant rotational speed. The rotor assembly includes a mast rotatable at the constant speed about a mast axis. A rotor hub is coupled to and rotatable with the mast. The rotor hub includes a plurality of spindle grips extending generally radially outwardly. Each of the spindle grips is coupled to one of a plurality of rotor blades and is operable to rotate therewith about a pitch change axis. A collective pitch control mechanism is coupled to and rotatable with the rotor hub. The collective pitch control mechanism is operably associated with each spindle grip such that actuation of the collective pitch control mechanism rotates each spindle grip about the respective pitch change axis to collectively control the pitch of the rotor blades, thereby generating the variable thrust output.
-
公开(公告)号：US11479353B2
公开(公告)日：2022-10-25
申请号：US16879074
申请日：2020-05-20
Applicant: Textron Innovations Inc.
Inventor： John Richard McCullough , Andrew Thomas Carter , Sung Kyun Kim , Matthew John Hill
Abstract: An aircraft includes an airframe with first and second wings having a fuselage extending therebetween. A propulsion assembly is coupled to the fuselage and includes a counter-rotating coaxial rotor system that is tiltable relative to the fuselage to generate a thrust vector. Tail assemblies are coupled to wingtips of the first and second wings each having an elevon that collectively form a distributed array of elevons. A flight control system is configured to direct the thrust vector of the coaxial rotor system and to control movements of the elevons such that the elevons collectively provide pitch authority and differentially provide roll authority for the aircraft in the biplane orientation. In addition, when the flight control system detects an elevon fault, the flight control system is configured to perform corrective action responsive thereto at a distributed elevon level or at a coordinated distributed elevon and propulsion assembly level.
-
公开(公告)号：US20220212785A1
公开(公告)日：2022-07-07
申请号：US17706445
申请日：2022-03-28
Applicant: Textron Innovations Inc.
Inventor： John Richard McCullough , Paul K. Oldroyd
Abstract: An aircraft having a high efficiency forward flight mode. The aircraft includes an airframe having at least one wing. A distributed propulsion system is attached to the airframe and includes a first plurality of propulsion assemblies and a second plurality of propulsion assemblies. A flight control system is operably associated with the distributed propulsion system and is operable to independently control each of the propulsion assemblies. The aircraft is configured for thrust-borne lift in a vertical takeoff and landing flight mode and wing-borne lift in the forward flight mode. In the vertical takeoff and landing flight mode, each of the propulsion assemblies is configured to generate vertical thrust. In the forward flight mode, the propulsion assemblies of the first plurality of propulsion assemblies are configured to generate forward thrust and the propulsion assemblies of the second plurality of propulsion assemblies are configured to shut down.
-
公开(公告)号：US20210300580A1
公开(公告)日：2021-09-30
申请号：US17225778
申请日：2021-04-08
Applicant: Textron Innovations Inc.
Inventor： Paul K. Oldroyd , John Richard McCullough
Abstract: An aircraft has multiple independent yaw authority mechanisms. The aircraft includes an airframe having first and second wings with at least first and second pylons extending therebetween and with a plurality of tail members extending therefrom each having an active control surface. A two-dimensional distributed thrust array is coupled to the airframe that includes a plurality of propulsion assemblies each having a rotor assembly and each operable for thrust vectoring. A flight control system is operable to independently control each of the propulsion assemblies. A first yaw authority mechanism includes differential speed control of rotor assemblies rotating clockwise compared to rotor assemblies rotating counterclockwise. A second yaw authority mechanism includes differential longitudinal control surface maneuvers of control surfaces of two symmetrically disposed tail members. A third yaw authority mechanism includes differential thrust vectoring of propulsion assemblies.
-
公开(公告)号：US11104446B2
公开(公告)日：2021-08-31
申请号：US16154326
申请日：2018-10-08
Applicant: Textron Innovations Inc.
Inventor： John Richard McCullough , Paul K. Oldroyd
Abstract: A propulsion assembly for an aircraft includes a nacelle having a rapid connection interface, at least one battery disposed within the nacelle, a speed controller coupled to the battery and a propulsion system coupled to the speed controller and the battery. The propulsion system includes an electric motor having an output drive and a rotor assembly having a plurality of rotor blades that are rotatable with the output drive of the electric motor in a rotational plane to generate thrust. The electric motor is operable to rotate responsive to power from the battery at a speed responsive to the speed controller. The rapid connection interface of the nacelle is couplable to a rapid connection interface of an airframe nacelle station to provide structural and electrical connections therebetween that are operable for rapid in-situ assembly.
-
Patent Agency Ranking
公开(公告)号：US11084579B2
公开(公告)日：2021-08-10
申请号：US16743203
申请日：2020-01-15
Applicant: Textron Innovations Inc.
Inventor： Steven Ray Ivans , Jason Paul Hurst , Brent Chadwick Ross , John Richard McCullough , Paul K. Oldroyd
Abstract: An aircraft for capturing drones includes an airframe having a drone channel with first and second wings extending outboard thereof. A two-dimensional distributed thrust array includes a plurality of propulsion assemblies coupled to each of the first and second wings such that the rotor disc of each propulsion assembly is outboard of the drone channel. A flight control system is coupled to the airframe and is operable to independently control each of the propulsion assemblies. A mesh bag is coupled to the drone channel forming a drone capture net. The aircraft is configured to convert between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft is also configured to overtake a drone during flight in the biplane orientation such that the drone passes through the drone channel into the mesh bag, thereby capturing the drone in the drone capture net.
-
公开(公告)号：US11027834B2
公开(公告)日：2021-06-08
申请号：US15902402
申请日：2018-02-22
Applicant: Textron Innovations Inc.
Inventor： Andrew Maresh , Troy Cyril Schank , Chyausong Tzeng , John Richard McCullough , Robert Wardlaw
IPC: B64C27/48 , B64C3/32 , F16F1/38 , B64C27/473
Abstract: An inboard bearing attachment for carrying centrifugal force (“CF”) loads in a rotor blade assembly of a rotorcraft includes a CF fitting having a curved surface and a shear bearing retainer aligned with the curved surface. A mounting flange connected to either the CF fitting or the shear bearing retainer is used to mount the inboard bearing attachment to a yoke.
-
公开(公告)号：US10994835B2
公开(公告)日：2021-05-04
申请号：US15718592
申请日：2017-09-28
Applicant: Textron Innovations Inc.
Inventor： John Richard McCullough , Paul K. Oldroyd , Brett Rodney Zimmerman
IPC: B64C27/00 , B64C27/06 , B64C27/473
Abstract: An inertia weight assembly positionable within a receiving portion of a rotor blade for use on a rotorcraft. The inertia weight assembly includes a weighted core and a casing having a closed outboard end and forming a cavity. The weighted core is disposed in the cavity such that the casing at least partially encloses the weighted core. The weighted core is formed from a first material and the casing is formed from a second material that is dissimilar to the first material. The casing provides an interface between the weighted core and the receiving portion of the rotor blade. The second material is more bondable to the receiving portion of the rotor blade than the first material.
-
公开(公告)号：US10913541B2
公开(公告)日：2021-02-09
申请号：US16790676
申请日：2020-02-13
Applicant: Textron Innovations Inc.
Inventor： Paul K. Oldroyd , John Richard McCullough
IPC: B64D31/10 , B64D27/24 , B64C29/02 , B64C39/02 , B64C27/52 , G05D1/00 , B64D27/26 , G05D3/00 , G05D1/10
Abstract: An aircraft has an airframe with a two-dimensional distributed thrust array attached thereto having a plurality of propulsion assemblies that are independently controlled by a flight control system. Each propulsion assembly includes a housing with a gimbal coupled thereto that is operable to tilt about first and second axes responsive to first and second actuators. A propulsion system is coupled to and operable to tilt with the gimbal. The propulsion system includes an electric motor having an output drive and a rotor assembly having a plurality of rotor blades that rotate in a rotational plane to generate thrust having a thrust vector. Responsive to a thrust vector error of a first propulsion assembly, the flight control system commands at least a second propulsion assembly, that is symmetrically disposed relative to the first propulsion assembly, to counteract the thrust vector error, thereby providing redundant directional control for the aircraft.
-
公开(公告)号：US10737765B2
公开(公告)日：2020-08-11
申请号：US15972461
申请日：2018-05-07
Applicant: Textron Innovations Inc.
Inventor： Paul K. Oldroyd , John Richard McCullough
Abstract: An aircraft has an airframe with a distributed thrust array attached thereto that includes a plurality of propulsion assemblies each of which is independently controlled by a flight control system. Each propulsion assembly includes a housing with a gimbal coupled thereto and operable to tilt about a single axis. A propulsion system is coupled to and operable to tilt with the gimbal. The propulsion system includes an electric motor having an output drive and a rotor assembly having a plurality of rotor blades that rotate in a rotational plane to generate thrust having a thrust vector with a magnitude in the longitudinal direction. Actuation of each gimbal is operable to tilt the respective propulsion system relative to the airframe in the longitudinal direction to change the rotational plane of the respective rotor assembly relative to the airframe, thereby controlling the magnitude of the respective thrust vector in the longitudinal direction.
-
-
-
-
-
-
-
-
-
Search Results
55
records
(took 0.028 seconds)
