The present invention relates to a flight control system for a VTOL aircraft (10) defining an aircraft reference frame with a roll axis (Xb), a pitch axis (Yb) and a yaw axis (Zb), the flight control system comprising a first and a second manual control apparatus for inputting control commands by an operator, wherein the first manual control apparatus comprises a first stick member, wherein the first stick member is pivotable around first and second control axes with respect to a first neutral position, wherein the second manual control apparatus comprises a second stick member, wherein the second stick member is pivotable around third and fourth control axes with respect to a second neutral position, a flight control computer, which is connected to the first and second manual control apparatuses and configured to output flight control instructions based on pivot positions of the first and second stick members with respect to the first to fourth control axes, wherein the flight control computer is adapted to derive and output flight control instructions, while at least partially eliminating cross-coupling between the individual directions of motion for longitudinal motion control based on the pivot position of the first stick member with respect to the first control axis, for lateral motion control based on the pivot position of the first stick member with respect to the second control axis, for vertical motion control based on the pivot position of the second stick member with respect to the third control axis, and for directional motion control based on the pivot position of the second stick member with respect to the fourth control axis. The invention further relates to a VTOL aircraft (10) comprising such a flight control system.
FLIGHT CONTROL SYSTEM AND METHOD FOR A VTOL AIRCRAFT
FLUGSTEUERUNGSSYSTEM UND -VERFAHREN FÜR EIN VTOL-FLUGZEUG
SYSTÈME ET PROCÉDÉ DE COMMANDE DE VOL POUR UN AÉRONEF VTOL
2024-10-02
Patent
Electronic Resource
English
Automatic flight control for VTOL aircraft
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