公开(公告)号：US10696391B2

公开(公告)日：2020-06-30

申请号：US15815411

申请日：2017-11-16

Applicant: Textron Innovations Inc.

Inventor： Alan Carl Ewing ,  Eric Ricardo Gonzalez ,  Mark Loring Isaac ,  Frank Bradley Stamps

IPC: B64C29/00 ,  G05D1/08 ,  B64C27/28 ,  B64C27/26 ,  B64C27/08 ,  B64C27/30 ,  B64C39/08 ,  G05D1/00 ,  B64C11/28

Abstract: A quad tiltrotor aircraft has a longitudinally extending fuselage with forward and aft stations. A forward wing having first and second outboard ends extends laterally from the forward station. An aft wing having first and second outboard ends extends laterally from the aft station. First and second forward rotors are respectively coupled proximate the first and second outboard ends of the forward wing and are tiltable relative to the forward wing between vertical lift and forward thrust orientations. First and second aft rotors are respectively coupled proximate the first and second outboard ends of the aft wing and are tiltable relative to the aft wing between vertical lift and forward thrust orientations. The forward rotors are higher disk-loading rotors than the aft rotors. The aft rotors are foldable in the forward flight mode to provide extended range for the quad tiltrotor aircraft.

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.

Inventor： Stephen Yibum Chung ,  Eric Ricardo Gonzalez ,  Russell C. Peters ,  Matthew Edward Louis

IPC: B64C29/00 ,  B64C27/08 ,  G05D1/06 ,  G05D1/08

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.

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.

Inventor： Stephen Yibum Chung ,  Eric Ricardo Gonzalez ,  Russell C. Peters ,  Matthew Edward Louis

IPC: B64C29/00 ,  G05D1/08 ,  G05D1/06 ,  B64C27/08

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.