High lift control system design for a transport aircraft

Abstract

A high lift control system is designed based on the control requirements of the leading edge flap and the trailing edge slat in the process of an aircraft take-off, landing and airdropping. The system provides fly-by-wire control, system protection and built in test function. A differential speed reducer is designed based on converse thinking, and thus solve the synthesis problem of double motor torque output. Using the reverse drive double non-return device, effectively avoid the flap/slat torque back propagation effects on the system may cause. The controller interface requirement to flap skew detection is greatly reduced based on the using of coupling between two sine and cosine sensors. A simple backup control circuit is design by only using switch interlock, to achieve flap and slat after the failure of flap/slat controller. The methods used in this paper, simplified the system design and thus improved the system reliability.