When a hypersonic vehicle undergoes direct force control in the atmosphere， the interaction between the control jet and the incoming flow creates disturbance flow fields. Traditional Reynolds-averaged Navier-Stokes （RANS） models struggle to accurately predict these disturbances， leading to uncertainties. In order to deepen the understanding of the influence of supersonic side-jet inflow interference on the control system and its mechanism， a highly analytical numerical calculation method for the turbulent flow field based on the cone-pillar-skirt model is established. Comparing delayed detached eddy simulation （DDES） and RANS models under varying grid densities reveals significant discrepancies in the downstream jet wake disturbance region. DDES improves the reliability of lateral jet control results， especially under well-resolved turbulent grid conditions. Supported by simulations， the study enhances understanding of turbulent characteristics in supersonic lateral jet-induced disturbances. Dynamic DDES methods show improved pressure prediction compared to traditional RANS simulations， offering insights for enhancing the prediction accuracy of direct force control systems.

Fairing separation simulation is an important part of aerospace research and development， and its key lies in the analysis of separation safety. In this paper， we review the previous simulation studies on the safety of throw hood separation and find that the existing analysis methods and simulation methods are based on the generated simulation separation trajectory. With the development of times and needs， the environment of fairing separation and the material structure of fairing itself have changed. On the basis of the original rigid body separation trajectory， the analysis of flexible fairing has become the main research direction of simulation fairing separation. After the summary of the existing research， the author believes that the main difficulties and key technologies of the existing fairing separation simulation focus on the simplification of the coupling model， the dynamic grid and the CSD model. This paper makes a concrete analysis and prospect of these three technologies. Finally， some conclusions and suggestions are given for the development of simulation of throw hood separation.