单喷管可回收火箭逆向喷流干扰气动特性研究

Vertical recovery of launch vehicle stands as a viable and practical recovery approach in the current landscape of aerospace engineering. However，during the power deceleration process of vertical recovery trajectory，a complex flow field configuration is generated by the reverse jet from the engine，significantly influencing the aerodynamic characteristics of the rocket stage. This study numerically simulates the 3D flow field around a rocket equipped with a single jet during the power deceleration process of vertical recovery，employing the finite volume method to solve the Reynolds-averaged N-S equations coupled with the SST k-ω turbulence model. The flow field characteristics are analyzed，and the dependence of the aerodynamic properties on Mach number and altitude is investigated. The research findings reveal that，during the power deceleration process，a concavity is formed at the edge of the reverse jet’s termination shock wave，giving rise to subsonic recirculation zones both within the concavity and in proximity to the base of the rocket stage. The aerodynamic axial force coefficient，normal force coefficient，and pitching moment coefficient of the rocket are markedly decreased by the reverse jet from the engine. When a reverse jet is present during the power deceleration process，the aerodynamic axial force coefficient of the rocket undergoes more pronounced variations with changes in flight Mach number，altitude，and angle of attack. The normal force coefficient experiences more significant changes with variations in altitude. Notably，the thrust of the reverse jet during power deceleration process of the engine in the same altitude conditions is not affected by the Mach number，but slightly increases with the flight altitude. In the angle of attack range from 0° to 8°，the ratio of aerodynamic axial force to engine thrust of the rocket increases with the attack angle，so the deceleration effect of the rocket stage can be enhanced by increasing the attack angle appropriately.