DIFFERENTIAL VARIABLE PITCH BLADE AND HELICOPTER ROTOR SYSTEM

WIPO Patent Application WO/2019/109791

A1

A differential variable pitch blade, comprising: at least two airfoil sections (301), the adjacent airfoil sections (301) being rotatably connected, each airfoil section (301) being provided with a first through hole and a second through hole; a torsion bar (302), penetratingly and rotatably arranged within the first through holes of all the airfoil sections (301); a variable pitch control cable (305), penetratingly arranged within the second through holes of all the airfoil sections (301), two ends of the variable pitch control cable (305) being respectively fixed on the airfoil sections at the blade root and the blade tip, wherein a first airfoil section located at the blade root is connected to a first twist mechanism used for driving the first airfoil section to twist by a first angle, and a second airfoil section located at the blade tip is connected to a second twist mechanism used for driving the second airfoil section to twist by a second angle. The variable pitch control cable (305) and the torsion bar (302) transfer torsion forces located at a blade root portion and a blade tip portion to a blade central portion, so that the airfoil sections located at the blade central portion twist in a synchronous manner, thereby reducing power transfer links, and improving energy transfer efficiency.

LIU YANTAO (CN)

PCT/CN2018/115810

June 13, 2019

November 16, 2018

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CHINA HELICOPTER RES & DEVELOPMENT INST (CN)

B64C11/30; B64C11/20

CN104973236A	2015-10-14
CN207450223U	2018-06-05
CA2864980A1	2015-04-11
CN102167156A	2011-08-31
FR2957329A1	2011-09-16

HANG XIN GAO KE ZHI SHI CHAN QUAN DAI LI SHI WU SUO (CN)

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