US 12,187,461 B2
Damped machined primary structure for a spacecraft, satellite incorporating this primary structure and method for manufacturing such a satellite
Florian Gacoin, Toulouse (FR); Jean-Marc Pierinet, Toulouse (FR); Mireya Joya, Toulouse (FR); Julien Pradal, Toulouse (FR); Sara Lopez-Sanchez, Toulouse (FR); and Nicolas Fabre, Toulouse (FR)
Assigned to Airbus Defence and Space SAS, Toulouse (FR)
Appl. No. 18/014,870
Filed by AIRBUS DEFENCE AND SPACE SAS, Toulouse (FR)
PCT Filed Jul. 2, 2021, PCT No. PCT/EP2021/068392
§ 371(c)(1), (2) Date Jan. 6, 2023,
PCT Pub. No. WO2022/008386, PCT Pub. Date Jan. 13, 2022.
Claims priority of application No. 2007212 (FR), filed on Jul. 8, 2020.
Prior Publication US 2023/0348112 A1, Nov. 2, 2023
Int. Cl. B64G 1/22 (2006.01)
CPC B64G 1/228 (2023.08) [B64G 1/22 (2013.01)] 12 Claims
OG exemplary drawing
 
1. A primary structure for a spacecraft comprising:
an interface ring, and
a predetermined number of panels defining a box arranged to close an interior volume of the spacecraft,
the box is connected to the interface ring,
panels of the predetermined number of panels that define sides of the box and the panels are parallel to a geometric axis (A) of the interface ring,
the interface ring is configured to be temporarily fastened to a system supporting the spacecraft in a launcher,
wherein each of the panels is a one-piece machined metal panel,
wherein each of the panels at a base of the box is connected to the interface ring via damping inserts,
wherein each of the panels includes a network of intersecting ribs connected by a thinned plate, wherein the network of intersecting ribs and thinned plate are machined from a metal block,
wherein the network of the intersecting ribs in each of the panels is arranged to induce at least a determined stiffness and to transfer forces between a proximal edge of the panel and a distal edge of the panel relative to the interface ring,
wherein the panels at the base of the box each comprise open recesses configured to receive within the open recess the damping inserts,
wherein each of the open recesses is adjacent the proximal edge of the panel and is aligned with the geometric axis such that an opening to the open recess faces towards the interface ring;
wherein each of the open recesses has a corresponding first rib of the intersecting ribs which defines a periphery of the open recesses, and
wherein a second rib of the intersecting ribs extends from the first rib across the thinned plate in a direction which does not intersect the geometric axis (A) of the interface ring.