公开(公告)号：US10384776B2

公开(公告)日：2019-08-20

申请号：US15438972

申请日：2017-02-22

Applicant: Bell Helicopter Textron Inc.

Inventor： Jouyoung Jason Choi ,  Daniel Bryan Robertson ,  Kirk Landon Groninga ,  Frank Bradley Stamps ,  Matthew Edward Louis

IPC: B64C39/00 ,  B64C3/32 ,  B64C3/14 ,  B64D27/12 ,  B64D27/26 ,  B64C29/00 ,  B64C27/26 ,  B64C27/28 ,  B64C27/52 ,  B64C23/02

Abstract: A tiltrotor aircraft has a fuselage and a wing having upper and lower surfaces with a plurality of channels extending therebetween, each with a cycloidal rotor mounted therein. At least two pylon assemblies are rotatably coupled to the wing to selectively operate the tiltrotor aircraft between helicopter and airplane flight modes. Each pylon assembly includes a mast and a proprotor assembly operable to rotate with the mast to generate thrust. At least one engine provides torque and rotational energy to the proprotor assemblies and the propulsion assemblies. Each of the cycloidal rotors has a plurality of blades that travels in a generally circular path and has a plurality of pitch angle configurations such that each cycloidal rotor is operable to generate a variable thrust and a variable thrust vector, thereby providing vertical lift augmentation, roll control, yaw control and/or pitch control in the helicopter flight mode.

公开(公告)号：US20180237136A1

公开(公告)日：2018-08-23

申请号：US15438972

申请日：2017-02-22

Applicant: Bell Helicopter Textron Inc.

Inventor： Jouyoung Jason Choi ,  Daniel Bryan Robertson ,  Kirk Landon Groninga ,  Frank Bradley Stamps ,  Matthew Edward Louis

IPC: B64C39/00 ,  B64C3/32 ,  B64C3/14 ,  B64D27/12 ,  B64D27/26 ,  B64C29/00 ,  B64C27/26 ,  B64C27/28 ,  B64C27/52

CPC classification number: B64C39/005 ,  B64C3/14 ,  B64C3/32 ,  B64C23/02 ,  B64C27/26 ,  B64C27/28 ,  B64C27/52 ,  B64C29/0033 ,  B64C39/003 ,  B64C2003/143 ,  B64D27/12 ,  B64D27/26 ,  B64D2027/262 ,  Y02T50/12

Abstract: A tiltrotor aircraft has a fuselage and a wing having upper and lower surfaces with a plurality of channels extending therebetween, each with a cycloidal rotor mounted therein. At least two pylon assemblies are rotatably coupled to the wing to selectively operate the tiltrotor aircraft between helicopter and airplane flight modes. Each pylon assembly includes a mast and a proprotor assembly operable to rotate with the mast to generate thrust. At least one engine provides torque and rotational energy to the proprotor assemblies and the propulsion assemblies. Each of the cycloidal rotors has a plurality of blades that travels in a generally circular path and has a plurality of pitch angle configurations such that each cycloidal rotor is operable to generate a variable thrust and a variable thrust vector, thereby providing vertical lift augmentation, roll control, yaw control and/or pitch control in the helicopter flight mode.

公开(公告)号：US20180044009A1

公开(公告)日：2018-02-15

申请号：US15233897

申请日：2016-08-10

Applicant: Bell Helicopter Textron Inc.

Inventor： Daniel Bryan Robertson ,  Dudley Smith ,  Mark Dreier ,  Steve Ray Ivans ,  Kirk Landon Groninga

IPC: B64C27/82 ,  B64C27/06

CPC classification number: B64C27/82 ,  B64C11/006 ,  B64C27/06 ,  B64C39/008 ,  B64C2027/8245 ,  B64C2027/8254 ,  F04D17/04 ,  F04D29/362 ,  F05D2220/90

Abstract: In some embodiments, a rotorcraft includes a fuselage, a tailboom, a drive system and a variable thrust cross-flow fan system. The cross-flow fan system includes a cross-flow fan assembly that is mechanically coupled to a drive shaft and operable to rotate with the drive shaft about a longitudinal axis. The cross-flow fan assembly includes first and second driver plates having a plurality of blades rotatably mounted therebetween. The blades are disposed radially outwardly from the longitudinal axis and have a generally circular path of travel when the cross-flow fan assembly rotates about the longitudinal axis. The blades are moveable between a plurality of pitch angle configurations. A control assembly is coupled to the blades. The control assembly is operable to change the pitch angle configuration of the blades to generate variable thrust at a substantially constant rotational speed of the cross-flow fan assembly.