关键词: 级间分离;火箭发动机;侧向喷流+;数值仿真;非定常流

Abstract: Numerical analysis was carried out about the interference to the aerodynamic forces of tail rudders of a missile caused by lateral jets during its booster thrust ceasing process.3D unsteady N-S equations with two species of jet gas and air frozen flow model were considered and solved based on structured multi-block patching meshes using finite difference method.The unsteady interfering characteristics of main external flow and thrust ceasing jets were obtained as well as the variation history of aerodynamic forces of tail rudders involved in such interfering flow field.It is observed from the results that the tail rudders are shrouded in the wake of lateral jets during the early period of the booster combustion chamber decompressing,and,in this period the aerodynamic forces of tail rudders can not provide adequate drag to accomplish booster separation process,the tail rudders deflecting control should be delayed from the beginning of chamber decompressing for nearly 180 ms.

Key words: Stage separation;Rocket engine;Lateral jet+;Numerical simulation;Unsteady flow