-
公开(公告)号：EP3366583A1
公开(公告)日：2018-08-29
申请号：EP17208612.6
申请日：2017-12-19
Applicant: Bell Helicopter Textron Inc.
Inventor： CHOI, Jouyoung Jason , ROBERTSON, Daniel Bryan , GRONINGA, Kirk Landon , STAMPS, Frank Bradley , LOUIS, Matthew Edward
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 (10) has a fuselage (12) and a wing (18) having upper and lower surfaces (18a-b) with a plurality of channels (56a-d) extending therebetween, each with a cycloidal rotor (28a-h) mounted therein. At least two pylon assemblies (22a-b) are rotatably coupled to the wing (18) to selectively operate the tiltrotor aircraft (10) between helicopter and airplane flight modes. Each pylon assembly (22a-b) includes a mast (54) and a proprotor assembly (24a-b) operable to rotate with the mast (54) to generate thrust. At least one engine (40) provides torque and rotational energy to the proprotor assemblies (24a-b) and the propulsion assemblies. Each of the cycloidal rotors (28a-h) has a plurality of blades (108) that travels in a generally circular path and has a plurality of pitch angle configurations such that each cycloidal rotor (28a-h) 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：EP3636542A1
公开(公告)日：2020-04-15
申请号：EP19156604.1
申请日：2019-02-12
Applicant: Bell Helicopter Textron Inc.
Inventor： GRONINGA, Kirk L. , ROBERTSON, Daniel B. , LOUIS, Matthew Edward , VAUGHN, Robert Glenn , RYAN, Michael J. , ACHTTIEN, Brent Randal
Abstract: A rotor system (280) is provided in one example embodiment and may include a rotor duct (220); at least one rotor blade (200), wherein the at least one rotor blade (200) comprises a tip end (204); and a tip extension (230) affixed at the tip end (204) of the at least one rotor blade (200), wherein the tip extension (230) is comprised, at least in part, of a flexible material and the rotor blade (200) has a fixed extended length (212b) based on the tip extension (230). The tip extension (230) may provide a clearance distance (216) between the tip extension (230) and the rotor duct (220).
-
公开(公告)号：EP3366583B1
公开(公告)日：2019-07-17
申请号：EP17208612.6
申请日：2017-12-19
Applicant: Bell Helicopter Textron Inc.
-
-
Search Results
3
records
(took 0.033 seconds)
