Numerical investigation on flow field interference characteristics and dynamics of interstage thermal separation
By using numerical simulation methods and combining dynamic grid technology,the unsteady flow field and rigid body motion during the interstage thermal separation were coupled calculated.The changes in the flow field structure both inside and outside the interstage were analyzed,and the dynamic analysis of the first stage missile body was conducted.The research results indicate that the nozzle of the two-stage projectile engine is in an overexpansion state,and as the separation process progresses,the normal shock wave inside the nozzle continuously moves downstream,and the shock wave intensity continuously weakens.The lateral jet at the interstage gap forms a complex flow interference phenomenon with the external supersonic free flow,and the separation shock wave and plume shock wave intensity in the interference flow field gradually weaken and move downstream.The area of the flow separation area in the interference flow field continuously expands with the increase of flight altitudeduring the separation process,and the interstage segment exhibits a state of initial pressure suppression and later pressure relief.The axial load of the first stage projectile shows a pattern of rapid increase in the initial stage and rapid decreases after peak value,and slow decreases after small fluctuations.As the flight altitude increases,the lateral displacement of the first stage projectile changes in the negative direction of the corresponding coordinate axis.
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