| 摘要 |
A method and apparatus for controlling an angular parameter between a base member (202) and a control surface (204) of an aircraft is disclosed. An estimate is obtained of an angular rate of the control surface (204) with respect to an inertial frame (215) of the aircraft using a rate sensor (210). A residual angular rate ( ¸ res ) that is a difference between a commanded angular rate and the estimate of the angular rate ( ¸ RVDT ) of the control surface (204) is determined. The residual angular rate ( ¸ res ) is used to control the angular parameter of the control surface (204) or the angular parameter of the base member (202). |
