Abstract: A device for angularly positioning a solar panel equipping a spacecraft such as a satellite, the panel being connected in hinged manner to the body of the spacecraft. The device comprises a heat-sensitive drive mechanism suitable for causing the panel to be displaced relative to the body of the spacecraft automatically as a function of the direction of incidence of the solar radiation on the spacecraft. The drive mechanism is suitable for taking up two states as a function of its temperature, and is so disposed on the spacecraft that a change in the direction of incidence of the solar radiation on the spacecraft is accompanied by a change in the temperature of the drive mechanism causing a change of a state therein and a change in the angular position of the panel tending to reduce the angle of incidence of the solar radiation on the panel.

Abstract: The invention relates to a braking and heat protection shield (1) for a spacecraft (5), said shield being situated at the front of the spacecraft to oppose a flow of gas striking the spacecraft, and including at least one gap (3a, . . . , 3d) shaped to present a through section to the flow that increases with increasing angle of incidence of the spacecraft, to create an aerodynamic force couple tending to return the spacecraft towards a position of lesser incidence.