三翼面飞机前翼和平尾机动载荷优化配置

Maneuver Load Optimal Distribution Between Canard and Horizontal Tail of Three-surface Aircraft

对三翼面飞机两种典型机动状态下的飞行载荷进行了分析,提出了一种适合三翼面飞机机动载荷优化配置的方法。讨论平尾升降舵与前翼操纵面之间的协调偏转率变化以及飞行动压变化,对配平参数、铰链力矩和载荷分布的影响。指出协调偏转率变化会引起平尾升降舵和前翼操纵面的配平角度、铰链力矩以及平尾和前翼载荷分布的显著改变,在设计时应该对协调偏转率加以选择,从而对平尾和前翼的载荷进行综合优化配置。

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.