A reconstructing technique for the forebody shock system of hypersonic vehicles was proposed. The flow mechanism and the control law of the technique were investigated numerically. The application of the technique in the variable hypersonic inlet with fixed geometry was also explored. The results showed that the first ramp shock was deflected outward effectively and the second ramp shock was weakened and even eliminated when the controlling activity was employed

indicating the forebody shock system was reconstructed entirely. The required secondary mass flow to drive the first ramp shock to the shock-on-lip condition decreased with the increase of the injection angle. The shock-on-lip condition can be maintained within the operating Mach number range of 5 to 6 at a maximum secondary flow ratio of 2.04%. Furthermore

as compared with the variable inlet using previous fluidic shock control technique

the required secondary mass flow ratio of the newly developed variable hypersonic inlet is less and the total pressure recovery at the exit of the inlet is higher.