Unsteady processes in aerospace power units with stage separation (Q1370039)

The process of the ejection of the body of the booster from the duct of a ramjet which is used as a sustainer is simulated. The booster body is ejected by the gas dynamic free stream after the propulsion burnout. A mathematical description is proposed of the motion of the booster body and the accompanying gas dynamic flow in the freed part of the duct with the subsequent establishment of a flow before the starting of the combustion chamber of the sustainer. The problem reduces to the simultaneous integration of the equations of unsteady gas dynamics in a duct, the form of which changes with time, and the equations of motion of a rigid body under the action of forces which depend on time and are obtained during the solution of the gas dynamic problem.