公开(公告)号：CA2369837C

公开(公告)日：2009-12-08

申请号：CA2369837

申请日：2002-01-30

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： STAMPS FRANK B ,  BRASWELL JAMES L JR ,  POPELKA DAVID A ,  COVINGTON CECIL E ,  BENNETT RICHARD L ,  COVINGTON CHARLES E ,  SETTLE THOMAS B JR

IPC: B64C27/28 ,  B64C27/08 ,  B64C27/37 ,  B64C27/39 ,  B64C27/605 ,  B64C29/00

Abstract: An aircraft with a tilt rotor assembly comprising a craft body, a plurality of rotor blades which are subject to three modes of flight operation, a tilting mast coupling the plurality of rotor blades to the craft body and for selectively moving the plurality of rotor blades between the three modes of flight operation, a hub coupling the plurality of rotor blades to the tilting mast in a manner which transfers torque and thrust whi le allowing tilting of a rotor thrust vector, a main swashplate for tilting in response to operator input to control the direction of the rotor thrust vector, a plurality of pitch horns , each mechanically coupled to a particular one of the plurality of rotor blades and to the main swashplate, for communicating swashplate input to each of the plurality of rotor blades, a plurality of links coupling the main swashplate to the plurality of pitch horns, wherein each o f the plurality of pitch horns is mechanically coupled to a particular one of the plurality of rotor blades by one of the plurality of links in a particular position which yields a delta- 3 value which is not optimum, and a feedback swashplate and cooperating feedback links for receiving disk tilting input from the plurality of rotor blades during flight, and for supplying a mechanical input tothe main swashplate to compensate for the less than optimum delta-3 coupling between the plurality of pitch horns and the plurality of links. The three modes of flight include: (1) an airplane mode of flight with the plurality of rotor blades i n a rotor disk position which is substantially transverse to the craft body; (2) a helicopt er mode of flight with the plurality of rotor blades in a rotor disk position substantially parallel to the craft body with direction of flight being controlled by a rotor thrust vector; and (3) a transition mode of flight with the plurality of rotor blades moving between the rotor disk positions associated with the airplane mode of flight and the helicopter mode of fligh t.

公开(公告)号：CA2369837A1

公开(公告)日：2002-08-16

申请号：CA2369837

申请日：2002-01-30

Applicant: BELL HELICOPTER TEXTRON INC

Inventor： BRASWELL JAMES L JR ,  STAMPS FRANK B ,  COVINGTON CECIL E ,  POPELKA DAVID A ,  COVINGTON CHARLES E ,  BENNETT RICHARD L ,  SETTLE THOMAS B JR

IPC: B64C27/08 ,  B64C27/37 ,  B64C27/605 ,  B64C29/00 ,  B64C27/28 ,  B64C27/39

Abstract: An aircraft with a tilt rotor assembly comprising a craft body, a plurality of rotor blades which are subject to three modes of flight operation, a tilting mast coupling the plurality of rotor blades to the craft body and for selectively moving the plurality of rotor blades between the three modes of flight operation, a hub coupling the plurality of rotor blades to the tilting mast in a manner which transfers torque and thrust whi le allowing tilting of a rotor thrust vector, a main swashplate for tilting in response to operator input to control the direction of the rotor thrust vector, a plurality of pitch horns , each mechanically coupled to a particular one of the plurality of rotor blades and to the main swashplate, for communicating swashplate input to each of the plurality of rotor blades, a plurality of links coupling the main swashplate to the plurality of pitch horns, wherein each o f the plurality of pitch horns is mechanically coupled to a particular one of the plurality of rotor blades by one of the plurality of links in a particular position which yields a delta- 3 value which is not optimum, and a feedback swashplate and cooperating feedback links for receiving disk tilting input from the plurality of rotor blades during flight, and for supplying a mechanical input to the main swashplate to compensate for the less than optimum delta-3 coupling between the plurality of pitch horns and the plurality of links. The three modes of flight include: (1) an airplane mode of flight with the plurality of rotor blades i n a rotor disk position which is substantially transverse to the craft body; (2) a helicopt er mode of flight with the plurality of rotor blades in a rotor disk position substantially parallel to the craft body with direction of flight being controlled by a rotor thrust vector; and (3) a transition mode of flight with the plurality of rotor blades moving between the rotor disk positions associated with the airplane mode of flight and the helicopter mode of fligh t.