Hall effect thrusters are used for space propulsion. The energy deposition on the inner surfaces of Hall effect thruster is analysed. Using a PIC MC 1D-3V model, the ion and electron exchanges of energy by bombardments are estimated in presence of a potential sheath near the surfaces and an electron secondary emission. Morever, simple expressions are deduced from the classic theory of non collisional potential sheath but without electron secondary emssion. A 3D ray-tracing method to determine the radiation energy deposition on the wall from visible and VUV optical ranges is presented.

The preparation of new Planetary exploration missions needs an adequate planning of the critical Entry, Descent and Landing (EDL) sequences. The planetary entry phase occurs at hypersonic velocities, and the aerodynamic configurations, and the thermal protections of a spacecraft have to be properly tailored. In support of the upcoming European planetary exploration missions, the European Space Agency is funding the development of a new shock-tube facility at the Instituto Superior Tecnico of Lisbonne. The characteristics of this new large facility will be described in this work.