Result indicates that, for discrete gust ,the largest acceleration of the wing tip and the largest bending moment of the wing root increase by gust velocity ; the ply angle has little effect on the largest acceleration of the wing tip but great on the largest bending moment of the wing root.
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Because the response calculations are all based on the flight kinetic equations, the solutions for discrete and continuous gust models can be obtained using the similar method.
由于计算是从基本飞行运动方程出发，故对紊流的离散型和连续型有统一的求解方法。
Approaches to calculate the response to continuous and discrete gust for hacw were presented.
为此建立了大展弦比机翼突风响应的分析方法。
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