극초음속 유동에서의 비행체 조종면 거동 특성 연구

초록

In this paper, the behaviors of low aspect ratio wings with control surfaces on generic hypersonic vehicles are studied. The hypersonic flow which induces extremely hot temperature due to viscosity affects the wings and control surfaces. And increasing temperature causes structural deformations with thermal stress and degradation of material properties. Thus, temperature effect as well as aerodynamic forces should be considered to predict the structural deformations of wing structures of hypersonic vehicles more accurately. Therefore, in order to consider the effect of heat flux and aerodynamics forces simultaneously, the Eckert reference temperature method is used to calculate heat flux due to viscosity in boundary layer, and third order piston theory is used to predict a relationship between pressure on surfaces of structures and pressure of steady-state flows. A special purpose element is developed to consider both pressure and heat flux which are dependent on structural deformations and flow conditions. By utilizing this element, the behaviors of hypersonic vehicles which are affected by thermal loading and aerodynamic loading are studied.