Patent ID: 6793173
Filing Date: 2004-09-21
Classification: G05D

Abstract:
A device for the automatic control of a helicopter comprising a main forward motion and lift rotor capable of being controlled at least along a collective axis and along a pitching axis, said device comprising:at least one objective law in respect of the pitching axis, the aim of such an objective law being to bring at least one state parameter of the helicopter to an objective which represents a preset value of a state parameter, said objective law in respect of the pitching axis automatically determining for this purpose a control command for operating the tilting of the disk of said main rotor of the helicopter; and at least two objective laws in respect of the collective axis, each of these laws automatically determining a control command for operating the collective pitch of the blades of said main rotor, which device comprises:at least two objective laws in respect of the pitching axis, which function simultaneously; first selection means for automatically selecting the objective law, whose control command is used for the collective axis; and second selection means for automatically selecting, as a function of the selection made by said first selection means, the objective law whose control command is used for the pitching axis.