为研究基于合成双射流的阵风减缓策略，针对NACA 0012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以及动态涡脱落过程，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Cμ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CL较大的脉动，当Cμ=0.033时，后缘分离区发展到翼型中部位置， CL,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CL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CL迅速降低，之后针对这一过程研究Cμ?阶梯递减控制，设置Cμ区间式变化，相较于持续施加恒定Cμ的情况，这一控制方法达到相同减缓的幅值的情况下付出的能耗更少，且翼型处于高载荷冲击的时间也更短。

In order to study the gust alleviation strategy based on Dual Synthetic Jets(DSJ), the actuators are arranged in an array on the upper surface of NACA 0012 airfoil, and the flow separation is actively induced by reverse jets. The evo-lution of separated vortex and the dynamic vortex shedding are studied in detail, which provides a new idea for load control based on zero-mass jet. The results show that with the increase of momentum coefficient Cμ, the control ability of DSJ to gust load is gradually improved without causing large fluctuation of lift coefficient CL. When Cμ = 0.033, the trailing edge separation zone develops to the middle position of airfoil, and the response amplitudes of CL,max de-crease 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 great impact on CL. In the process of airflow impacting the separated vortex, the pressure difference between the upper and lower wings increases rapidly, which leads to the rapid decrease of CL. Then, aiming at this process, the Cμ step-decreasing control is studied, and the Cμ interval change is set. Compared with the case of continuously applying constant Cμ, this control method pays less energy consumption when achieving the same slowing amplitude, and the airfoil also spends less time under high load impact.