发动机喘振产生的瞬时高压引起的进气道内锤激波载荷是飞机进气道结构强度设计的关键因素之一。通过对飞行器进行内外流一体化非定常三维数值计算，分析双S弯进气道内锤激波三维流场非定常特性的演化过程，研究了不同马赫数，不同超压比对双S弯进气道锤激波载荷的影响。研究表明：锤激波经过进气道弯道时，弯道外侧流场压力远大于内侧；锤激波离开进气道入口后，进气道内流场经过数个周期逐渐恢复至初始状态；相同进气道反压时，来流马赫数越小，锤激波在进气道内部传播速度越快，且进气道内部压力系数峰值越大；相同来流马赫数下，随着超压比的增大，锤激波在进气道内部传播速度加快，进气道内部压力系数峰值增大。

The hammer shock load caused by the transient high pressure induced by engine surge is one of the key factors in the aircraft inlet structural strength design. Through the unsteady numerical calculation of the integrated internal and external flow of the aircraft, the evolution process of the unsteady three-dimensional flow field of the internal hammershock wave in the double S-bend inlet was analyzed, and the influence of different Mach number and overpressure ratio on the inlet hammer shock wave load of the inlet hammer was studied. The results show that when the hammer shock wave passes through the inlet curve, the pressure of the flow field on the outside of the curve is much greater than that on the inside. After the hammer shock wave leaves the inlet, the flow field in the inlet gradually returns to the initial state after several cycles. When the inlet pressure is the same, the smaller the incoming Mach number is, the faster hammer shock wave propagates in the inlet, and the larger the peak value of the inlet pressure coefficient is. Under the same inlet Mach number, with the increase of the overpressure ratio, the faster the hammer shock wave propagates in the inlet, the larger the peak value of the pressure coefficient in the inlet.