Research on response of fluctuating pressure on clustered launch vehicle

The fluctuating pressure can probably cause oscillations to structural load and control variables during transonic flight of the binding rockets. The traditional aircraft control system design hardly ever give a vivid description of the influence of fluctuating pressure. Based on the theoretical analysis of the coupling between structure and control system and fluctuating pressure, this thesis focus on the impacts of fluctuating pressure through the frequency response analysis of the closed-loop control system, and the result proves the theoretical analysis and shows that damp ratio increased and flexible generalized displacement has been reduced. The method provided in this thesis could be used for general aircraft design.