Damped machined primary structure for a spacecraft, satellite incorporating this primary structure and method for manufacturing such a satellite

A method for manufacturing a spacecraft comprising a predetermined number of panels defining a box connected to an interface ring and arranged to close an interior volume of the spacecraft, wherein the method comprises

• forming each panel of the predetermined number of panels by machining a single solid metal block from which metal material is removed to form a network of intersecting ribs, a thinned plate from which protrudes the network of ribs and open recesses,
• assembling the panels by connecting the panels y to one another to form the box,
• assembling damping inserts with the interface ring to form a primary structure of the spacecraft, the damping inserts being arranged in the open recesses in the panels, wherein the damping inserts are parallel to a geometric axis (A) of the interface ring;
• and
• assembling component elements of the spacecraft with the panels,
• wherein the network of intersecting ribs in each of the panels provides a determined stiffness and a transfer of forces between a proximal edge of the panel and a distal edge of the panel relative to the interface ring,
• wherein the machining includes forming the open recesses in each of the panels, and the open recesses are configured to receive the damping inserts, are on the panel proximate to the interface ring and are parallel to the geometric axis (A) of the interface ring such that an opening of each of the open recesses faces the interface ring,
• wherein a periphery of each of the open recesses is defined by a respective first rib of the network of ribs, and
• wherein at least one rib of the network of ribs extends respectively from each of the respective first ribs in a longitudinal direction which does not intersect the geometric axis (A) of the interface ring.