Host: The Japan Society of Mechanical Engineers
Name : [in Japanese]
Date : September 11, 2022 - September 14, 2022
Inflatable membrane aeroshell has the potential ability to deliver higher payload in planetary exploration missions. Receiving in-flight aerodynamic force, the membrane surface undergoes large deformation affecting the flow. To investigate the behavior, a coupled aero-structural interactions analysis is required. This paper aims to present a model based on fluid solver SU2, structural solver CalculiX, and coupling library preCICE in a partitioned-coupled manner. The computed results demonstrated that the membrane surface elastically deformed due to the substantial variation in pressure distribution around the aeroshell. Transient behavior has been observed in the aerodynamic coefficients as a result of the small amplitude oscillation of the capsule. This oscillation was induced by the large wake formed behind the vehicle. Wrinkling of the surface caused by the high aerodynamic force shows circumferential movement tendency with time. This study indicated that the analysis model can sufficiently reproduce the coupled aero-structural interaction, which provides insight for developing a flexible structure reentry vehicle.
