Maneuver load optimal distribution between canard and horizontal tail of three-surface aircraft

A flight load analysis of an aircraft with three-surface wings at two typical maneuver conditions is performed in this article, and a method is proposed for the maneuver load optimal distribution of the three- surface aircraft. The impact on the trim variables, hinge moments, and load distribution is discussed, as a function of the flight dynamic pressure and the coordinated deflection relation between the elevator on the horizontal tail and the control surface on the canard. The coordinated deflection has great effect on the trim angle and the hinge moment of both the elevator on the horizontal tail and the control surface on the canard, and even on the load distribution of the horizontal tail and the canard. The coordinated deflection relation should be selected in the design for the synthetical optimization of load distribution in both the horizontal tail and the canard.