ROTOR SYSTEM OF A ROTARY WING AIRCRAFT

摘要

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).

主权项

1. A rotor system of a rotary wing aircraft with a rotor mast with a longitudinal axis as rotation axis, a rotor hub coaxially arranged at said rotor mast, at least four, angularly essentially even distributed rotor blades and swash plate struts mounted to each of said rotor blades for pitch and subsequently flap control,
said rotor blades being respectively pairwise mounted lag-stiff and flap-stiff to each other with zero offset to said rotor hub for rotation about said rotation axis in a substantially common rotor plane, and connected opposed to each other and substantially symmetrical with regard to the rotor hub, wherein: the rotor hub is provided with a hollow bearing having at least one further bearing inside, respectively arranged in line with said rotation axis, a first pair of said rotor blades is mounted by means of a first yoke on the hollow bearing pivotable about a first flap direction essentially perpendicular to said rotation axis, and at least a second pair of said rotor blades is mounted by means of a second yoke inside the hollow bearing on the at least one further bearing pivotable about a second flap direction substantially perpendicular to said first flap direction and said rotation axis, and independently of said first pair of rotor blades.