Feasibility Study on the Flight Demonstration for a reentry vehicle with the Magnetic Flow Control System

In order to investigate the feasibility of the flight test for showing how effective the magnetic flow control system is for reentry vehicles we performed the trajectory analyses. As an initial flight condition, we prepared two different conditions; reentry flight from LEO and suborbital flight using a sounding rocket. For simplicity, a vehicle configuration is assumed to be a sphere with a radius of 20 [cm] and the magnetic dipole is placed at the center of the sphere. The magnetic field strength at the stagnation point was varied up to 2.0 [T]. Numerical results indicate that the flight performance improvement such as reduction in the maximum stagnation point heat flux was clearly observed in both flight conditions and, thus, the flight demonstration for the magnetic flow control system is evaluated to be feasible.