| 摘要 |
<p>The invention is related to a rotor system of a rotary wing aircraft, e.g. a helicopter with a rotor mast, a rotor hub (1), at least four, angularly essentially even distributed rotor blades (2, 3) and swash plate struts (15) for pitch and subsequently flap control. Said rotor blades (2, 3) are respectively pairwise mounted lag- and flap-stiff to each other with zero offset to said rotor hub (1). The rotor hub (1) is provided with a hollow bearing (20) with at least one further bearing inside (21), a first pair of said rotor blades (2) is mounted on the hollow bearing pivotable in a first flap direction (23) essentially perpendicular to said rotation axis, and at least a second pair of said rotor blades (3) is mounted inside the hollow bearing (20) on the at least one further bearing (21) pivotable in a second flap direction (22) substantially perpendicular to said first flap direction (23) and said rotation axis, and independently of said first pair of connected rotor blades (2).</p> |
