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公开(公告)号：US11899451B2
公开(公告)日：2024-02-13
申请号：US18061530
申请日：2022-12-05
Applicant: Textron Innovations Inc.
Inventor： Stephen Yibum Chung , Russell C. Peters , Andrew Vincent Louis
CPC classification number: G05D1/005 , B64C29/0033 , B64C39/024 , G05D1/102 , B64U30/10 , B64U30/20 , B64U50/19 , B64U2201/10 , B64U2201/20
Abstract: In one embodiment, a remote controller for a vehicle includes at least one control element for controlling operation of at least one aspect of the vehicle when the vehicle is in a remote-control mode; an actuator connected the at least one control element for controlling a position of the at least one control element when the vehicle is in an autonomous operations mode; and a processing system for receiving a first control signal from the vehicle indicative of a state of operation of the vehicle. In operation, the processing system generates a second control signal to the actuator to cause the actuator to control a position of the control element such that it corresponds to and indicates the state of operation of the vehicle.
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公开(公告)号：US20230174230A1
公开(公告)日：2023-06-08
申请号：US17540539
申请日：2021-12-02
Applicant: Textron Innovations Inc.
CPC classification number: B64C29/0008 , B64C19/00 , B64D47/00 , G05D1/102 , B64D9/00
Abstract: A tailsitter aircraft includes an airframe, a thrust array attached to the airframe and a flight control system. The thrust array includes propulsion assemblies configured to transition the airframe from a forward flight orientation to a VTOL orientation at a conversion rate for an approach to a target ground location in a forward flight-to-VTOL transition phase. The flight control system implements an adaptive transition system including a transition parameter monitoring module configured to monitor parameters including a ground speed and a distance to the target ground location. The adaptive transition system includes a transition adjustment determination module configured to adjust the conversion rate of the airframe from the forward flight orientation to the VTOL orientation based on the ground speed and the distance to the target ground location such that the airframe is vertically aligned with the target ground location in the VTOL orientation of the forward flight-to-VTOL transition phase.
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公开(公告)号：US20220197308A1
公开(公告)日：2022-06-23
申请号：US17133229
申请日：2020-12-23
Applicant: Textron Innovations Inc.
Inventor： John Robert Wittmaak, JR. , Russell C. Peters , Aaron Hitchcock , William Ben Johns , Levi Charles Hefner , Andrew Vincent Louis
Abstract: An aircraft includes an airframe with a thrust array attached thereto. The thrust array includes a plurality of propulsion assemblies that are independently controlled by a flight control system. A landing gear assembly is coupled to the airframe and includes a plurality of landing feet. An altitude sensor array includes a plurality of altitude sensors each of which is disposed within one of the landing feet such that when the aircraft is in the VTOL orientation, the altitude sensor array is configured to obtain multifocal altitude data relative to a landing surface. The flight control system is configured to generate a three-dimensional terrain map of the surface based upon the multifocal altitude data.
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公开(公告)号：US20240051661A1
公开(公告)日：2024-02-15
申请号：US17885053
申请日：2022-08-10
Applicant: Textron Innovations Inc.
Inventor： Russell C. Peters , John Robert Wittmaak, JR. , Alyssa Berta Armendariz , Christopher John Stroncek
CPC classification number: B64C29/0091 , B64D3/00
Abstract: A tailsitter aircraft for deploying a tow line includes an airframe having wings with pylons extending therebetween and a thrust array attached to the airframe, the thrust array including propulsion assemblies configured to transition the airframe between a forward flight orientation and a VTOL orientation. The tailsitter aircraft includes an attenuation spool coupled to the airframe and an attenuation cable having a first end coupled to the attenuation spool and a second end coupled to the tow line, the attenuation cable partially or fully wound around the attenuation spool. The tailsitter aircraft also includes a spool sensor to detect movement of the attenuation spool and a flight control system implementing a tow line tension monitoring module in communication with the spool sensor to determine a tow line tension parameter and a tow line tension reaction module to initiate an aircraft response based on the tow line tension parameter.
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公开(公告)号：US20230138684A1
公开(公告)日：2023-05-04
申请号：US17518118
申请日：2021-11-03
Applicant: Textron Innovations Inc.
Inventor： Russell C. Peters , Aaron M. Hitchcock , Nathaniel Gordon Lundie
Abstract: A ground state determination system for an aircraft includes sensors configured to detect parameters of the aircraft and a flight control system implementing a ground state module. The ground state module includes a ground state monitoring module configured to monitor the parameters and a ground state determination module configured to compare each of the parameters monitored by the ground state monitoring module to a respective parameter threshold to determine whether the aircraft is on a surface.
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Patent Agency Ranking
公开(公告)号：US11630467B2
公开(公告)日：2023-04-18
申请号：US17133229
申请日：2020-12-23
Applicant: Textron Innovations Inc.
Inventor： John Robert Wittmaak, Jr. , Russell C. Peters , Aaron Hitchcock , William Ben Johns , Levi Charles Hefner , Andrew Vincent Louis
Abstract: An aircraft includes an airframe with a thrust array attached thereto. The thrust array includes a plurality of propulsion assemblies that are independently controlled by a flight control system. A landing gear assembly is coupled to the airframe and includes a plurality of landing feet. An altitude sensor array includes a plurality of altitude sensors each of which is disposed within one of the landing feet such that when the aircraft is in the VTOL orientation, the altitude sensor array is configured to obtain multifocal altitude data relative to a landing surface. The flight control system is configured to generate a three-dimensional terrain map of the surface based upon the multifocal altitude data.
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公开(公告)号：US10967968B2
公开(公告)日：2021-04-06
申请号：US16188553
申请日：2018-11-13
Applicant: Textron Innovations Inc.
Abstract: A method for an aircraft may include determining a transition from an airplane mode to a helicopter mode for a propulsion system of the aircraft, wherein the propulsion system comprises a plurality of rotor blades; determining whether a descent rate condition is satisfied, wherein the descent rate condition is associated with a maximum allowable descent rate for the aircraft; and controlling a collective pitch angle for the plurality of rotor blades based on the descent rate condition.
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公开(公告)号：US20200148346A1
公开(公告)日：2020-05-14
申请号：US16188553
申请日：2018-11-13
Applicant: Textron Innovations Inc.
Abstract: A method for an aircraft is provided in one example embodiment and may include determining a transition from an airplane mode to a helicopter mode for a propulsion system of the aircraft, wherein the propulsion system comprises a plurality of rotor blades; determining whether a descent rate condition is satisfied, wherein the descent rate condition is associated with a maximum allowable descent rate for the aircraft; and controlling a collective pitch angle for the plurality of rotor blades based on the descent rate condition.
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公开(公告)号：US12084200B2
公开(公告)日：2024-09-10
申请号：US17518118
申请日：2021-11-03
Applicant: Textron Innovations Inc.
Inventor： Russell C. Peters , Aaron M. Hitchcock , Nathaniel Gordon Lundie
CPC classification number: B64D45/04 , B64C29/02 , G05D1/0638 , G05D1/0676
Abstract: A ground state determination system for an aircraft includes sensors configured to detect parameters of the aircraft and a flight control system implementing a ground state module. The ground state module includes a ground state monitoring module configured to monitor the parameters and a ground state determination module configured to compare each of the parameters monitored by the ground state monitoring module to a respective parameter threshold to determine whether the aircraft is on a surface.
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公开(公告)号：US11987351B2
公开(公告)日：2024-05-21
申请号：US17885053
申请日：2022-08-10
Applicant: Textron Innovations Inc.
Inventor： Russell C. Peters , John Robert Wittmaak, Jr. , Alyssa Berta Armendariz , Christopher John Stroncek
CPC classification number: B64C29/0091 , B64C29/02 , B64D1/22 , B64D3/00 , B64U10/14 , B64U10/20 , B64U10/60
Abstract: A tailsitter aircraft for deploying a tow line includes an airframe having wings with pylons extending therebetween and a thrust array attached to the airframe, the thrust array including propulsion assemblies configured to transition the airframe between a forward flight orientation and a VTOL orientation. The tailsitter aircraft includes an attenuation spool coupled to the airframe and an attenuation cable having a first end coupled to the attenuation spool and a second end coupled to the tow line, the attenuation cable partially or fully wound around the attenuation spool. The tailsitter aircraft also includes a spool sensor to detect movement of the attenuation spool and a flight control system implementing a tow line tension monitoring module in communication with the spool sensor to determine a tow line tension parameter and a tow line tension reaction module to initiate an aircraft response based on the tow line tension parameter.
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