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US 7,210,651 B2Granted
Compact co-axial rotor system for a rotary wing aircraft and a control system therefor
AssigneeSikorsky Aircraft Corporation
InventorMark Winfield Scott
Life of this patent
Estimating the term…
Abstract
A dual, counter rotating, coaxial rotor system provides an upper and lower rotor system, with a reduced axial rotor separation distance along a common axis by way of rotor tip position sensing and rotor position controls to avoid tip contact.
Claims23
A coaxial rotor system comprising:
- a first rotor system having a multiple of first rotor blades which rotates about an axis;
- a second rotor system having a multiple of second rotor blades which rotates about said axis, said second rotor system spaced an axial distance from said first rotor system;
- and
- a rotor control system which independently controls said first rotor system and said second rotor system with regard to pitch to maintain a minimum rotor blade tip separation between said multiple of first rotor blades and said multiple of second rotor blades.
1 more element
A coaxial rotor system comprising:
- a first rotor system having at least one servo flap;
- a second rotor system having at least one servo flap;
- said second rotor system being spaced an axial distance from said first rotor system;
- and
- a rotor control system which independently controls the at least one servo flap associated with the first rotor system and the at least one servo flap associated with the second rotor system with regard to pitch to maintain a minimum rotor blade tip separation between said first rotor system and said second rotor system.
2 more elements
A rotary-wing aircraft comprising:
- a first rotor system having a multiple of first rotor blades which rotate about said axis, each of said multiple of first rotor blades having at least one servo flap;
- a second rotor system having a multiple of second rotor blades which rotate about said axis, said second rotor system spaced an axial distance from said first rotor system, each of said multiple of second rotor blades having at least one servo flap;
- a sensor suite which measures a relative position of each of said multiple of first rotor blades and said multiple of second rotor blades;
- a flight control system in communication with said sensor suite;
- and
- a rotor control system which determines a relative separation distance between each of said multiple of first rotor blades and each of said multiple of second rotor blades, said rotor control system in communication with said flight control system to independently control said servo flap on each of said multiple of first rotor blades and said multiple of second rotor blades with regard to pitch to maintain a minimum rotor blade tip separation between each of said multiple of first rotor blades and each of said multiple of second rotor blades.
3 more elements
Dependencies are inferred from the claim text.