Patent ID: 7461812
Filing Date: 2008-12-09
Classification: B64C

Abstract:
1. A control system for a rotorcraft comprising: a cyclic for receiving pilot input commands; a torque tube pivotally coupled to the cyclic; a forward-aft output link pivotally coupled to the torque tube for transmitting forward-aft pilot input commands to a main rotor; a stepped mixing linkage pivotally coupled to the torque tube; a ground link pivotally coupled between the stepped mixing linkage and a grounded structure; a lateral output link pivotally coupled to the stepped mixing linkage; and a left-right output link pivotally coupled to the lateral output link for transmitting left-right pilot input commands to the main rotor; wherein the stepped mixing linkage, the ground link, and the lateral output link are configured to generate a selected lateral sinusoidal output, a selected rotation of the sinusoidal output, and a selected ramped output in response to each forward-aft cyclic input command.