One aspect is a flight control system for a rotary wing aircraft including a main rotor system and an elevator control system. A flight control computer of the flight control system includes processing circuitry configured to execute control logic. The control logic includes an inverse plant model that produces a main rotor feed forward command based on a pitch rate command, and a load alleviation control filter configured to reduce loads on a main rotor system and produce an elevator command for an elevator control system. A transformed elevator command filter produces a main rotor pitch adjustment command based on the elevator command, and a main rotor command generator generates an augmented main rotor feed forward command for the main rotor system based on the main rotor feed forward command and the main rotor pitch adjustment command.
ELEVATOR LOAD ALLEVIATING CONTROL FOR A ROTARY WING AIRCRAFT
2017-02-02
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
Elevator load alleviating control for a rotary wing aircraft
Europäisches Patentamt | 2018
|ELEVATOR LOAD ALLEVIATING CONTROL FOR A ROTARY WING AIRCRAFT
Europäisches Patentamt | 2015
|ELEVATOR LOAD ALLEVIATING CONTROL FOR A ROTARY WING AIRCRAFT
Europäisches Patentamt | 2019
|GUST ALLEVIATING CONTROL FOR A COAXIAL ROTARY WING AIRCRAFT
Europäisches Patentamt | 2016
|GUST ALLEVIATING CONTROL FOR A COAXIAL ROTARY WING AIRCRAFT
Europäisches Patentamt | 2018
|