The newly developed Inflatable Thermal Shield(ITS) technology offers a simple, reliable and economical way to recover various vehicles from orbits and is therefore possible to be a substitute for parachute systems in the future. The selection of the aeroshell shape for the ITS recovery system is discussed. CFD methods are used to predict the subsonic, transonic and supersonic aerodynamics of the selected shape and compared with the Newtonian hypersonic estimation. The single-stage and two-stage inflation schemes are examined with the calculation of a 90kg cargo's re-entry trajectory, the latter is shown to possess better combination of deceleration and thermal protection and is therefore the ideal ITS re-entry scheme.