Unmanned aerial vehicle with fly wing configuration can suffer critical loading when flying through at-mospheric turbulence. Restricted to the aerodynamic configuration and control surfaces distribution, traditional strat-egies for gust load alleviation cannot be applied to the fly wing configuration vehicle. Aerodynamic characteristics of control surfaces are contrasted and analyzed. According to the visible differences in force coefficient and moment co-efficient of the control surfaces, an alleviation strategy is proposed for the unmanned aerial vehicle with fly wing configuration. In this strategy, all control surfaces cooperate in generating longitudinal direct force while keeping ad-dition moment trimmed. A nonlinear controller is designed based on active disturbance rejection control techniques to compensate for system error and turbulence disturbance by online estimation. Simulation results and their analysis show preliminarily that the g-load response to atmospheric turbulence is improved after applying the longitudinal di-rect force control strategy and that the nonlinear controller, and the flight attitude and track can maintain stability besides.%飞翼布局无人机在大气紊流中飞行会受到较大的紊流载荷，而受限于自身构型和舵面配置，无法采用传统控制方案进行紊流载荷减缓。分析了飞翼布局无人机的舵面气动特性，提出一种多组舵面配合产生纵向直接控制力的垂直紊流减缓方案，并采用自抗扰控制技术设计了非线性控制器，在线估计系统误差和紊流扰动，并进行补偿控制。仿真结果表明：飞翼布局无人机采用直接力控制方案，并加入该非线性控制器后，能显著减缓在大气紊流中飞行中的法向过载，同时保证姿态和航迹稳定。
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