A DUAL TYPE FLIGHT CONTROL SYSTEM

摘要

The present invention relates to a dual type flight control system for a helicopter. The dual type flight control system comprises: a control input unit; a first drive member mechanically connected to the control input unit and driven by an operation of the control input unit; a second drive member electrically controlled based on an input signal corresponding to the operation of the control input unit; and a link member unit connected to the first drive member and the second drive member, and operated to change displacement generated during the operation of the first drive member or the second drive member toward an actuator. According to the present invention, an electronic flight system can be used in combination with a mechanical flight control system of which the safety is confirmed. Accordingly, the dangerousness when developing a new helicopter flight control system can be reduced, and the application and the degree of normality of the new helicopter flight control system can be sufficiently verified.