Simulation of convective heat flux and heat penetration for a spacecraft at re-entry

A closed-form simulation model is presented for the convective heat transfer to a space vehicle at re-entry. The analysis is based on given trajectory data, i.e. on vehicle velocity vs. flight altitude. Hence, the uniqueness of the subject engineering method is that it does not solve the equations of motion, but assumes an analytical expression for the flight trajectory together with an isothermal atmosphere. The obtained results for both global and local (e.g. the stagnation point) heat transfers to the vehicle are further used for the prediction of the one-dimensional heat penetration into the vehicle structure. This also includes the accumulated (or integrated) heat load as function of the time of descent. Comparisons of results from the present method with published data for the Space Shuttle and for the European Atmospheric Reentry Demonstrator are presented, both for peak heat loads at stagnation point and integrated reference heat load.