Based on computational fluid dynamics and ignition theory

the flow field during the second pulse ignition of a dual-pulse solid rocket motor was numerically analyzed

and the test of the second pulse ignition of a dual-pulse solid rocket motor was conducted. Result showed that

before the diaphragm was opened

the position of the high pressure zone in the second pulse chamber moved from the front of the chamber to the partition

the pressure changed little along the radial direction of the chamber but more obviously along the axial direction

the near wall area of the second chamber head and tail was kept in the low temperature. The diaphragm was opened at 6 ms

and the pressure in the second pulse combustion chamber decreased by 05 MPa

the pressure difference at the front and rear ends of the inner hole of the propellant grain fluctuated violently

the temperature at the front end of the inner hole of the propellant grain decreased by 600 K

while the temperature in other areas changed little. After the diaphragm was opened

the downstream hole formed a zonal high temperature zone along the axis of the first pulse chamber

peak pressure appeared in the first chamber head and tail

the pressure of the first chamber reached a steady state at 18 ms

and the temperature of the first chamber reached a steady state at 25 ms. The pressure-time curves of the first and second chambers measured in test were in good agreement with the simulation result

indicating that the simulation method has certain accuracy.