Patent ID: 9726248
Date: 2017-08-08
CPC Classifications: B64G,F16F

Claim:
1. An isolation module between a satellite launcher, which is a vibration-generating device, and a satellite structure to be isolated, the isolation module comprising: at least two fastening parts intended to be fastened respectively on the vibration-generating device and the structure to be isolated, an elastomeric connecting means interposed between the two fastening parts, allowing at least one degree of freedom in translation along a longitudinal axis between the two fastening parts, wherein a first fastening part, comprises a frame that includes; wherein a second fastening part, comprises a support, the support includes; wherein each of the support median branches extend between two branches of the frame, the frame and the support each have a longitudinal plane of symmetry perpendicular to the radial axis, and in which, the elastomeric connecting means comprise at least one pair of identical elastomer pads, in which each pad extends along the longitudinal axis between a first end and a second end, a first pad having the first end supported on a lower branch of the frame and the second end supported on the median branch of the support and the second pad having the first end supported on the upper branch of the frame and the second end supported on the median branch of the support, the two pads of the pair being thus mounted in parallel between the frame and the support and being active along the longitudinal axis in opposite directions, so that when one pad works under tension, the other pad of the pair works under compression, and vice-versa, a stiffness of the module being symmetrical, whether a force applied thereto along the longitudinal axis is oriented in one direction or the opposite direction, and each pad is dimensioned so that a contact surface S 1 of one end in contact with a radial branch and a free contact surface S 2 satisfy the relationship: