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US 2018/0004229 A1Published application
Rotor moment control system for a rotary wing aircraft
AssigneeSikorsky Aircraft Corporation
InventorMatthew A. White
Life of this patent
Estimating the term…
Abstract
A method of controlling rotor moments includes receiving, in a flight control computer (FCC) a rotor moment reference value based on pilot inceptor inputs, sensing rotor moment from one or more sensors, receiving, in the FCC, a rotary wing aircraft condition parameter, and establishing, through the FCC, a rotor blade pitch angle for one or more of a plurality of rotor blades that counteracts external forces acting upon the rotary wing aircraft.
Claims15
A method of controlling rotor moments comprising:
- receiving, in a flight control computer (FCC), a rotor moment reference value based on pilot inceptor inputs;
- sensing rotor moment from one or more sensors;
- receiving, in the FCC, a rotary wing aircraft condition parameter;
- and
- establishing, through the FCC, a rotor blade pitch angle for one or more of a plurality of rotor blades that counteracts external forces acting upon the rotary wing aircraft.
2 more elements
A rotor moment control system for a rotary wing aircraft comprising:
- a flight control computer (FCC);
- a rotor moment control system configured to analyze rotor moments and reduce rotary wing aircraft transients during a transition from a proportional ground control mode and a model following controls mode, the rotor moment control system including computer readable program code embodied therewith, the computer readable program code, when executed by the FCC, causes the FCC to:
- receive a rotor moment reference value based on pilot inceptor inputs;
- sense rotor moment from one or more sensors;
- receive a rotary wing aircraft condition parameter;
- and
- establish a rotor blade pitch angle for one or more of a plurality of rotor blades that counteracts external forces acting upon the rotary wing aircraft.
4 more elements
Dependencies are inferred from the claim text.