The invention relates to a thermal junction
system (1) comprising first and second structural elements (2, 3) and forming the thermal junction between a first interface (2a) of the first
structural element (2) and a second interface (3a) of the second
structural element (3), the first and second structural elements being intended to be integrated into a
spacecraft, characterised in that the first and second structural elements (2, 3) are in the form of planar extended panels with the first and second interfaces (2a, 3a) having the form of planar surfaces, the thermal junction
system (1) comprising: - a mechanical
guidance system (6) which is configured to bring the first and second movable structural elements (2, 3) closer together from at least one open position, in which the first and second interfaces (2a, 3a) are spaced apart from one another, and a closed position, in which the first and second interfaces (2a, 3a) are clamped against one another so as to be thermally connected; - a thermal seal (5) which extends over one and / or the other of the first and second interfaces (2a, 3a), the thermal seal (5) comprising a dry material or a thermal paste and having a thermal conductance of greater than or equal to 1000 W / m² / K; - a triggering
system (7) which is configured to trigger at least one movement of the first and second structural elements (2, 3) from the open position to the closed position; - a
compression system (8) which is configured at least to press the first and second interfaces (2a, 3a) against one other in the closed position.