A control circuitry (130) includes a propulsor trim prediction circuitry (404) configured to generate a predicted propulsor collective blade pitch trim value (444, 562) for a target state of an aircraft (100) based on an aircraft velocity (422) and a pitch attitude deviation from a reference (550, 622). The control circuitry (130) further includes an output circuitry (516, 518) configured to output a propulsor collective blade pitch angle command (452, 564) based on the predicted propulsor collective blade pitch trim value (444, 562). The propulsor collective blade pitch angle command (452, 564) is configured to cause an adjustment in a blade pitch angle of a propulsor (112, 114) of the aircraft (100). Additionally or alternatively, the control circuitry (130) includes a pitch attitude trim prediction circuitry (402) configured to generate a predicted pitch attitude trim value (442). The output circuitry (516, 518) is configured to output an aircraft pitch attitude trim command (550), configured to cause an adjustment in a pitch angle of the aircraft (100), based on the predicted pitch attitude trim value (442).
PITCH AND THRUST CONTROL FOR COMPOUND AIRCRAFT
NEIGUNGS- UND SCHUBREGELUNG FÜR VERBUNDFLUGZEUGE
COMMANDE DE PAS ET DE POUSSÉE POUR AÉRONEF COMPOSÉ
2022-11-23
Patent
Electronic Resource
English