为研究基于合成双射流的阵风减缓策略，针对NACA0012翼型在其上表面阵列式布置合成双射流激励器，通过反向射流方式主动诱导流动分离，并详细研究分离涡的演化及动态涡脱落过程，为开展基于零质量射流的载荷控制提供了新的理念。结果表明，随着动量系数C_μ 的增大，合成双射流对于阵风载荷控制能力逐渐提高且没有造成升力系数C_L 较大的脉动，当C_μ =0.033时，后缘分离区发展到翼型中部位置，C_L，max响应幅值降低了47.9%。由于后缘处分离区较大，关闭射流激励器后分离涡在上翼面的卸载过程会对C_L 造成较大影响，在气流冲击分离涡的过程中，上下翼面压差迅速增大进而造成C_L 迅速减小；针对这一过程研究C_μ 阶梯递减控制，设置C_μ 区间式变化，相较于持续施加恒定C_μ 的情况，这一控制方法在达到相同减缓幅值的情况下能耗更低，且翼型处于高载荷冲击的时间也更短。

To study the gust alleviation strategy based on Dual Synthetic Jets （DSJ）， we arrange the actuators in an array on the upper surface of the NACA0012 airfoil， actively induce the flow separation through reverse jets， and study the evolution of the separated vortex and the dynamic vortex shedding， providing a new insight for load control based on the zero-mass jet. The results show that with the increase of the momentum coefficient C_μ， the control ability of DSJ over the gust load is gradually improved without causing large fluctuation of the lift coefficient C_L . At C_μ = 0.033， the trailing edge separation zone develops to the middle position of the airfoil， and the response amplitudes of C_L，max decrease by 47.9%. Because of the large separation zone at the trailing edge， the unloading process of the separated vortex on the upper wing surface after closing the jet actuator will have a significant impact on C_L . In the process of airflow impacting the separated vortex， the pressure difference between the upper and lower wings rapidly increases， leading to rapid decrease of C_L . Then， aiming at this process， we study the C_μ step-decreasing control， and set the C_μ interval change. Compared with the case of continuously applying constant C_μ， this control method requires less energy consumption in achieving the same slowing amplitude， and the airfoil also spends less time under high load impact.